767-300 - Aviation For All - Aviação sem mistérios! · PDF fileNon-Normal Checklists - Index QA.Index.2 June 17, 2008 REVIEWED BY: _____ Michael Bihuniak 757/767-300 - Technical

Quick Action Index

767-300Quick Reference Handbook

QA.Index Non-Normal Checklists-IndexABORTED ENGINE START . . . . . . . . . . . . . . . 7.1AIRSPEED UNRELIABLE . . . . . . . . . . . . . . . . 10.2APU FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.2CABIN ALTITUDE OR RAPID DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . 2.6

DUAL ENGINE FAILURE . . . . . . . . . . . . . . . . . 7.4ENGINE FIRE OR SEVERE DAMAGE OR SEPARATION . . . . . . . . . . . . . . . . . . . . . . . . . 8.8

ENGINE LIMIT OR SURGE OR STALL . . . . . 7.34ENGINE TAILPIPE FIRE . . . . . . . . . . . . . . . . . 7.44EVACUATION . . . . . . . . . . . . . . . . . . Back Cover.2SMOKE OR FIRE OR FUMES . . . . . . . . . . . . 8.18

Revision Number: 8© 2008 Delta Air Lines, Inc.

QA.Index.1June 17, 2008

Non-Normal Checklists -Index

REVIEWED BY: _______________________________Michael Bihuniak

757/767-300 - Technical Manager

APPROVED BY: ______________________________Jim Stava

757/767-300 - Chief Line Check Pilot - Domestic

APPROVED BY:______________________________Hank Sardelli

757/767-300 - Chief Line Check Pilot - International

APPROVED BY:______________________________Dean Bloom

757/767-300 - Fleet Captain

QA.Index.2 June 17, 2008

767-300 Operations Manual

Annunciated Index Chapter ANNEICAS Messages Section Index

Copyright © Delta Air Lines, Inc. See QA.Index.1 for details.

ANN.Index Annunciated Index-EICAS MessagesAACCESS DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1AFT CABIN TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8AFT CARGO DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3, 1.4AFT CARGO FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4AFT CARGO OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9AFT FUEL X-FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.8AILERON LOCKOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1AIR/GND SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1ALT CALLOUTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1ALT DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.4ALTITUDE ALERT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1ANTISKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1ANTISKID OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1APU BLEED VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1, 7.1APU BTL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1, 8.1APU BTL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1, 8.1APU FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2APU FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2, 8.2APU FUEL VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.3APU GEN OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14, 7.3ATC FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.1ATT DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5AUTO SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3AUTOBRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2AUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1AUTOPILOT DISC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1AUTOTHROT DISC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1BBATTERY OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14

ANN.Index.1June 16, 2008


Annunciated Index -EICAS Messages


BODY DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5BRAKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2BULK CARGO DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3,4BULK CARGO OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9CC BLD ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4C DEM HYD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1C HYD DEM PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1C HYD 1 OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2C HYD 2 OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2C HYD QTY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.3C HYD PRIM 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2C HYD PRIM 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2C HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.4C IRS DC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8C IRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.3, 11.8C IRS ON DC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8C TAIL HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.16C WING HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.21CABIN ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.5, 2.6CABIN AUTO INOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7CAPT PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2CARGO BTL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3CARGO BTL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3CARGO DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3, 1.4CTR L FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12CTR R FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12DDATALINK LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7DATALINK SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7EE/E ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1

ANN.Index.2 June 16, 2008




EICAS CONT PNL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EICAS DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EMER DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8, 1.5EMER LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.9ENG BTL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13, 8.6ENG BTL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13, 8.6ENGINE CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14FF/O PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6FIRE/OVHT SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.16FLAP LD RELIEF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLAPS (warning) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4, 15.1FLT CONT VALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLT DECK TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.21FMC MESSAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7FUEL CONFIG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.6FUEL CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.8FUEL JET NOZ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.10FWD ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1FWD CABIN TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8FWD CARGO DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3, 1.4FWD CARGO FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4FWD CARGO OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9FWD EQPT COOLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.17FWD EQPT OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.18FWD EQPT SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.19, 8.15FWD EQPT VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20FWD FUEL X-FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.8GGEAR DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.4GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6GEAR NOT DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6, 15.2





GND PROX SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2GPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7IIAS DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5ICE DET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DET OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DET ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICING ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8ICING WING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8IDLE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45INSTR SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6LL AC BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.1, 6.8L AFT EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8L AFT ENTRY DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10L AFT FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12L and C HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.10L and R HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.13L AOA PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1L AUX PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1L BLD DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2, 2.3L BLD ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4L BUS ISOLATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14L CTR ENT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10L DEM HYD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1L DRAG BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.3L EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8L EEC OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6L ENG ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3, 3.4, 7.7, 7.8L ENG BLD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.12, 7.12L ENG BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . 2.10, 2.11, 7.10, 7.11L ENG BLEED VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.13, 7.13





L ENG CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14L ENG EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14L ENG EEC MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.15L ENG FUEL FILT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21L ENG FUEL VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.26L ENG HI STAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.14, 7.27L ENG HPSOV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.15, 7.28L ENG LIM PROT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36L ENG LOW IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36L ENG OIL PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.37L ENG OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.40, 8.12L ENG PRV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.16, 7.42L ENG RPM LIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43L ENG SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43L ENG STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43L ENGINE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18L ENTRY DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10L FMC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.2 ,11.3, 11.4, 11.6L FUEL JET PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11L FUEL SPAR VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45, 12.13L FUEL SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.14L FWD EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8L FWD ENT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10L FWD FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12L FWD WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10L GEN DRIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.15L GEN OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.16L GPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7L HYD DEM PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1L HYD PRIM PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2L HYD QTY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.3L HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.7





L IRS DC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8L IRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.3, 11.8L IRS ON DC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8L JET XFER VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11L OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.46, 7.46L PACK OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.22L PACK TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.24L PRIM HYD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.17L RECIR FAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25L REV ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.47L SIDE BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.9L SIDE WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10L STARTER CUTOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.51L STRUT DCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.28L TAIL HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.16L UTIL BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.18L WING ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.11, 3.12L WING HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.21L WING SLIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.15L YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.22LE SLAT ASYM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.6LE SLAT DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.8LOW FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.15MMAIN BAT DISCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17MID CABIN TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8NNOSE A/G SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7OOVERSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2PPARKING BRAKE (advisory) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7





PARKING BRAKE (warning) . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7, 15.2PASS OXYGEN ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.12PROBE HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8RR AC BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.1, 6.8R AFT EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8R AFT ENTRY DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10R AFT FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12R and C HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.14R AOA PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1R AUX PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1R BLD DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2, 2.3R BLD ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4R BUS ISOLATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14R CTR ENT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10R DEM HYD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1R DRAG BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.3R EEC OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6R EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8R ENG ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3, 3.4, 7.7, 7.8R ENG BLD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.12, 7.12R ENG BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . 2.10, 2.11, 7.10, 7.11R ENG BLEED VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.13, 7.13R ENG CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14R ENG EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14R ENG EEC MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.15R ENG FUEL FILT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21R ENG FUEL VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.26R ENG HI STAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.14, 7.27R ENG HPSOV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.15, 7.28R ENG LIM PROT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36R ENG LOW IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36





R ENG OIL PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.37R ENG OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.40, 8.12R ENG PRV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.16, 7.42R ENG RPM LIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43R ENG SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43R ENG STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43R ENGINE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18R ENTRY DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10R FMC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.2, 11.3, 11.4, 11.6R FUEL JET PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11R FUEL SPAR VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45, 12.13R FUEL SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.14R FWD EMER DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8R FWD ENT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10R FWD FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12R FWD WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10R GEN DRIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.15R GEN OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.16R GPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7R HYD DEM PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1R HYD PRIM PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2R HYD QTY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.3R HYD SYS PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.8R IRS DC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8R IRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.3, 11.8R IRS ON DC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8R JET XFER VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11R OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.46, 7.46R PACK OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.22R PACK TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.24R PRIM HYD OVHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.17R RECIR FAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25





R REV ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.47R SIDE BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.9R SIDE WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10R STARTER CUTOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.51R STRUT DCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.28R TAIL HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.16R UTIL BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.18R WING ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.11, 3.12R WING HYD VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.21R WING SLIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.15R YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.22RAT UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.18REV ISLN VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.47RSV BRAKE VAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.8RUDDER RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.10SSATVOICE LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11, 5.12SPEEDBRAKES EXT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.11SPOILERS (advisory) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.13SPOILERS (warning) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.12, 15.3STAB TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.15STABILIZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.14, 15.3STANDBY BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17TTAIL SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.10TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.9TCAS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TCAS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TE FLAP ASYM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.17TE FLAP DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.18TERR OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4TERR POS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4





TRIM AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.26UUNABLE RNP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.10UNSCHD STAB TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.20WWHEEL WELL FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.22, 14.10WINDOW HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10

WINDSHEAR SYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4



Preface Chapter PQTable of Contents Section 0


PQ.0 Preface-Table of ContentsQuick Reference Handbook (QRH)

Quick Action Index.............................................................................QAAnnunciated Index ...........................................................................ANNPreface................................................................................................. PQChecklist Introduction...........................................................................CINon–Normal Checklists................................................................... NNCManeuvers....................................................................................... MANIndex................................................................................................ IndexEvacuation Checklist..............................................................Back Cover

PQ.TOC.0.1June 12, 2006


Preface -Table of Contents


IntentionallyBlank

PQ.TOC.0.2 June 12, 2006


Preface Chapter PQModel Identification Section 1


PQ.1 Preface-Model IdentificationGeneralThe airplanes listed in the table below are covered in the Operations Manual. The numbers are used to distinguish data peculiar to one or more, but not all of the airplanes. Where data applies to all airplanes listed, no reference is made to individual airplane numbers. Use of the table below permits flight crew correlation of configuration differences by number within an operator’s fleet for airplanes covered in this manual. Configuration data reflects the airplane as delivered configuration and is updated for service bulletin incorporations in conformance with the policy stated in the Introduction section of this chapter.Airplane number is supplied by the operator. Registry number is supplied by the national regulatory agency. Serial and tabulation numbers are supplied by Boeing.The procedures and information contained in this manual also apply to aircraft acquired by Delta Air Lines subsequent to the current revision; however, this document may not address all pertinent information for these airplanes. In such instances, specific operating procedures and systems information can be found in appropriate Differences Chapter(s) and/or Flight Crew Bulletin(s) prior to their incorporation in the next scheduled revision.

Airplane Number Registry Number Serial Number Tabulation Number

121 N121DE 23435 VK036

124 N124DN 23438 VK039

125 N125DL 24075 VK040

126 N126DL 24076 VK041

127 N127DL 24077 VK042

128 N128DL 24078 VK043

129 N129DL 24079 VK044

130 N130DL 24080 VK045

131 N131DN 24852 VK046

132 N132DN 24981 VK047

133 N133DN 24982 VK048

134 N134DL 25123 VK049

PQ.1.1June 17, 2008


Preface -Model Identification


135 N135DL 25145 VK050

136 N136DL 25146 VK051

137 N137DL 25306 VK052

138 N138DL 25409 VK053

139 N139DN 25984 VK054

171 N171DN 24759 VN251

172 N172DN 24775 VN252

173 N173DN 24800 VN253

174 N174DN 24802 VN254

175 N175DN 24803 VN255

176 N176DN 25061 VN256

177 N177DN 25122 VN257

178 N178DN 25143 VN258

179 N179DN 25144 VN259

180 N180DN 25985 VN260

181 N181DN 25986 VN261

182 N182DN 25987 VN262

183 N183DN 27110 VN263

184 N184DN 27111 VN264

185 N185DN 27961 VN265

186 N186DN 27962 VN266

187 N187DN 27582 VN267

188 N188DN 27583 VN268

189 N189DN 25990 VN269

190 N190DN 28447 VN270

191 N191DN 28448 VN271

192 N192DN 28449 VN272

193 N193DN 28450 VN273

194 N194DN 28451 VN274


PQ.1.2 June 17, 2008




195 N195DN 28452 VN275

196 N196DN 28453 VN276

197 N197DN 28454 VS066

198 N198DN 28455 VS067

199 N199DN 28456 VS068

1401 N140LL 25988 VK055

1402 N1402A 25989 VK056

1403 N143DA 25991 VR4711

1404 N144DA 27584 VR472

1501 N1501P 24983 VN301

1502 N152DL 24984 VN302

1503 N153DL 24985 VN303

1504 N154DL 25241 VN304

1505 N155DL 25269 VN305

1506 N156DL 25354 VN306

1521 N394DL 27394 VL753

1601 N169DZ 29689 VS073

1602 N1602 29694 VS074

1603 N1603 29695 VS075

1604 N1604R 30180 VS076

1605 N1605 30198 VS077

1606 N16065 30199 VS078

1607 N1607B 30388 VS466

1608 N1608 30573 VS467

1609 N1609 30574 VS468

1610 N1610D 30594 VS469

1611 N1611B 30595 VS470

1612 N1612T 30575 VS471

1613 N1613B 32776 VS472


PQ.1.3June 17, 2008




1701 N171DZ 29690 VS266

1702 N172DZ 29691 VS267

1703 N173DZ 29692 VS268

1704 N174DZ 29693 VS269

1705 N175DZ 29696 VS270

1706 N176DZ 29697 VS271

1707 N177DZ 29698 VS272

1708 N178DZ 30596 VS273

And Subsequent


PQ.1.4 June 17, 2008


Preface Chapter PQIntroduction Section 2


PQ.2 Preface-IntroductionGeneralThe Boeing Company developed normal and non-normal procedures for the 767-300 aircraft. Delta Air Lines, Inc. has modified some of the procedures for simplification and standardization, when appropriate, with other Delta Air Lines, Inc. aircraft. Finally, the FAA has approved the procedures presented in the Operations Manual, with the exception of flight crew bulletins.These procedures are company policy for pilots to follow during ground operations and in flight. Deviations from these policies and procedures should be made only with good cause and based on the safest course of action. If an abnormality occurs that is not covered by these procedures, the Captain must use his best judgement.

Manual RightsThis 767-300 Operations Manual has been prepared for the exclusive use of Delta Air Lines, Inc. Flight Operations personnel under the direction and authority of Delta and shall, at all times, remain the property of Delta Air Lines, Inc. The holder hereof acknowledges and agrees that this manual contains or may contain trade secrets, copyrighted material and commercial and proprietary information, privileged and confidential, to the interest of Delta Air Lines, Inc. and the holder hereof further agrees that this manual may not be reproduced, distributed or copied, in whole or in part, without the express prior written consent of Delta Air Lines, Inc.• In the event this 767-300 Operations Manual is sold or distributed to any

other party, no warranty or guarantee, expressed or implied, is made as to the accuracy, sufficiency or suitability of the materials contained herein or of any revision, supplement or bulletin hereto. It is understood and agreed to by such other party that it shall release indemnify and hold Delta Air Lines, Inc., its officers, employees and agents harmless against any and all claims or actions of whatever nature which may arise or claim to arise from the use hereof.

PQ.2.1June 12, 2006


Preface -Introduction


Corrections to the ManualTo correct any errors or discrepancies discovered in this manual, or to submit a suggested change to any Aircraft Operating Manual (Volume 1, Volume 2, QRH, Flight Crew Training Manual), Normal Checklist, Airway Manual, Flight Operations Manual (FOM), OE/TOE Guide, Flight Crew Bulletin (FCB), or Flight Operations Bulletin (FOB):Log on to the Delta Flight Operations Portal - http://dlnet.delta.com/portal - and submit a Publications Change Request (PCR).There are links to the PCR form on each fleet page and also on the Flight Ops Manuals/Library Services page.Once submitted, the PCR is automatically routed to the applicable Fleet Technical Manager, Technical Writer, and Specialist for that manual.

OrganizationThe operations manual is organized in the following manner.Volume 1• Preface – contains general information regarding the manual’s purpose,

structure, and content. It also contains lists of abbreviations, a record of revisions, a list of effective pages, and bulletins.

• Limitations and Normal Procedures chapters cover operational limitations and normal procedures. All operating procedures are based on a thorough analysis of crew activity required to operate the airplane, and reflect the latest knowledge and experience available.

• Supplementary Procedures chapter covers those procedures accomplished as required rather than routinely on each flight.

• Aircraft Differences chapter notes differences between aircraft types.Volume 2 - Chapters 1 through 15 contain general airplane and systems information. These chapters are generally subdivided into sections covering controls and indicators and systems descriptions.Quick Reference Handbook (QRH) - The QRH covers normal checklists, non-normal checklists, and non-normal maneuvers.Flight Crew Training Manual (FCTM) - The Flight Crew Training Manual provides information and recommendations on maneuvers and techniques.

PQ.2.2 June 17, 2008




Page NumberingThe Quick Reference Handbook manual uses a decimal page numbering system. The page numbers for the Non-Normal Checklists are divided into two fields; section and page, and are found at the top and the bottom of each page in larger sized font. An example of a page number for the Non-Normal Checklist chapter follows:

Example Page Number

Warnings, Cautions, and NotesThe following levels of written advisories are used throughout the manual and are not to be confused with EICAS messages, which are separately identified in the text.

WARNING: An operating procedure, technique, etc., that may result inpersonal injury or loss of life if not carefully followed.

CAUTION: An operating procedure, technique, etc., that may result indamage to equipment if not carefully followed.

Note: An operating procedure, technique, etc., considered essential to emphasize. Information contained in notes may also be safety related.

8.9

Page Number

Section (Fire Protection)

PQ.2.3June 12, 2006




IntentionallyBlank

PQ.2.4 June 12, 2006


Preface Chapter PQ
Abbreviations Section 3
PQ.3 Preface-Abbreviations

The following abbreviations may be found throughout the manual. Some abbreviations may also appear in lowercase letters. Abbreviations having very limited use are explained in the chapter where they are used. Since this list is compiled across several fleets, there may be some abbreviations that do not apply to this specific fleet.

AAFE Above Field Elevation

AFM Airplane Flight Manual


ABV Above

AC Alternating Current or Aircraft

ACARS Aircraft Communications Addressing and Reporting System

ACE Actuator Control Electronics

ACP Audio Control Panel

ACT Active

ADC Air Data Computer

ADF Automatic Direction Finder

ADI Attitude Director Indicator

ADIRS Air Data Inertial Reference System

ADIRU Air Data Inertial Reference Unit

ADM Air Data Module

AED Automatic External Defribulator

AFDC Autopilot Flight Director Computer

AFDS Autopilot Flight Director System

(FAA approved)

AFM - DPI Airplane Flight Manual - Digital Performance Information

AFS Automatic Flight System (Autopilot or Autothrottle)

A/G Air/Ground

AGL Above Ground Level

AH Alert Height

AHRS Attitude Heading Reference System

AI Anti-Ice

AIL Aileron

ALFA Safe Stall Margin Speed

ALT Altitude

ALT ACQ Altitude Acquire

ALT HOLD Altitude Hold

ALTN Alternate

AM Amplitude Modulation

AIMS Airplane Information Management System

AMI Airline Modifiable Information

PQ.3.1June 12, 2006


Preface - Abbreviations

ANP Actual Navigational Performance

ANT Antenna

ANU Aircraft Nose Up

AOA Angle of Attack

AOC Airline Operational Communication Data Link

A/P Autopilot

APL Airplane

APP Approach

APU Auxiliary Power Unit

ARINC Aeronautical Radio, Incorporated

ARM Aircraft Restrictions Manual

ARPT Airport

ARR Arrival

ART Automatic Reserve Thrust

ASA Autoland Status Annunciator

ASI Airspeed Indicator

ASR Airport Surveillance Radar

ASYM Asymmetry

A/T Autothrottle

ATA Actual Time of Arrival

ATC Air Traffic Control

ATIS Automated Terminal Information Service

ATM Assumed Temperature Method

Copyright © Delta Air Lines, I

PQ.3.2

ATT Attitude

AUTO Automatic

AUTO–THROT

Autothrottle

AUX Auxiliary

AVAIL Available

AWABS Automated Weight and Balance System

B

BARO Barometric

BAT Battery

B/C orB/CRS orBAC orBCS

Back Course

BFO Beat Frequency Oscillator

BITE Built-In Test Equipment

BKR Breaker

BLD Bleed

BLW Below

BRG Bearing

BRT Bright

BTL Bottle

BTL DISCH Bottle Discharge (fire extinguisher)

BTMS Brake Temperature Monitoring System

C

C Captain or

Celsius or

Center or

Cool

nc. See QA.Index.1 for details.

June 16, 2008



CAA Civil Aviation Authority

CADC Central Air Data Computer

CALSEL Call Select

CANC/RCL Cancel/Recall

CANPA Constant Angle Non-Precision Approach

CAP Capture

CAPT Captain

CAWS Central Aural Warning System

CB Circuit Breaker

CCD Cursor Control Device

CDS Common Display System

CDU Control Display Unit

CFIT Controlled Flight Into Terrain

CG Center of Gravity

CHKL Checklist

CHR Chronograph

CKD Checked

CKT Circuit

CL Close

CLB Climb

CLMP Computer Lockout Manual Power

CLR Clear

CMD Command

CO Company

COMM Communication

COMP Comparator

COMPT Compartment


June 16, 2008

CON Continuous

CONFIG Configuration

CONT Control

COOL Cooling

CRS Course

CRT Cathode Ray Tube

CRZ Cruise

CTL Control

CTR Center

CWS Control Wheel Steering

D

DA Decision Altitude

DA(H) Decision Altitude (Height)

DC Direct Current

DCU Display Concentrator Unit

D/D Direct Descent

DDA Derived Decision Altitude (MDA +50 feet)

DDG Dispatch Deviations Guide

DEL Delete

DEP Departure

DEP ARR Departure Arrival

DEPR Depressurize

DES Descent

DEU Display Electronic Unit

DFCS Digital Flight Control System

DFGC Digital Flight Guidance Computer


PQ.3.3



DFGS Digital Flight Guidance System

DH Decision Height

DIFF Differential

DIR Direct

DISC Disconnect

DISCH Discharge

DK Deck

DME Distance Measuring Equipment

DN Down

DSP Display Select Panel

DSPL Display

DTG Distance to Go

DTW Distance to Waypoint

E

EADI Electronic Attitude Director Indicator

ECON Economy

E/D End of Descent

E/E Electrical/Electronic

EEC Electronic Engine Control

EFI Electronic Flight Instruments

EFIS Electronic Flight Instrument System

EGPWS Enhanced Ground Proximity Warning System

EGT Exhaust Gas Temperature

EHSI Electronic Horizontal Situation Indicator


PQ.3.4

EICAS Engine Indication and Crew Alerting System

EIS Electronic Instrument System

ELEC Electrical

ELEV Elevator

EMER Emergency

ENG Engine

ENG OUT Engine Out

ENT Entry

EO or E/O Engine Out

EOAP Electronic Overhead Annunciation Panel

EPR Engine Pressure Ratio

EQPT or EQUIP

Equipment

ETOPS Extended Range Operation with Twin Engine Airplanes

EVAC Evacuation

EXEC Execute

EXT Extend or External

F

F Fahrenheit

FAC Final Approach Course

FAA Federal Aviation Administration

FADEC Full Authority Digital Engine Control

FAF Final Approach Fix

FAR Federal Aviation Regulation

FCB Flight Crew Bulletin


June 16, 2008



FCC Flight Control Computer

FCTL Flight Control

FCTM Flight Crew Training Manual

FD, F/D orFLT DIR

Flight Director

FF Fuel Flow

FFM Force Fight Monitor

FGCP Flight Guidance Control Panel

FGS Flight Guidance System

FILT Filter

FIR Flight Information Region

FL CH or FLCH

Flight Level Change

FLT Flight

FLT CTRL Flight Control

FLPRN Flaperon

FMA Flight Mode Annunciator

FMC Flight Management Computer

FMS Flight Management System

F/O or F O First Officer

FOM Flight Operations Manual

FPA Flight Path Angle

FPM Feet Per Minute

FPV Flight Path Vector

FREQ Frequency

F/S Fast/Slow

FT Feet


June 16, 2008

FWD Forward

FWSOV Fire Wall Shut Off Valve

FX Fix

G

GA Go–Around

GEN Generator

GLS GPS Landing System

GMT Greenwich Mean Time

GND Ground

GP orG/P

Glide Path

GPS Global Positioning System

GPWS Ground Proximity Warning System

GS Ground Speed

G/S Glide Slope

GW Gross Weight

H

HAA Height Above Airport

HAT Height Above Touchdown

HDG Heading or

Hydraulic Driven Generator

HDG REF Heading Reference

HDG SEL Heading Select

HF High Frequency

HGS Head-Up Guidance System (HGS® is a registered trademark of Flight Dynamics)

HI High


PQ.3.5



HLD Hold

HPA Hectopascals

HPSOV High Pressure Shut Off Valve

HSI Horizontal Situation Indicator

HUD Head-Up Display

HYD Hydraulic

I

IAF Initial Approach Fix

IAN Instrument Approach Navigation

IAS Indicated Airspeed

IDENT Identification

IFE In-Flight Entertainment System

IFR Instrument Flight Rules

IGN Ignition

IGS Instrument Guidance System

ILS Instrument Landing System

IM Inner Marker

IMC Instrument Meteorological Conditions

IN Inches

INBD Inboard

IND Indicator

IND LTS Indicator Lights

INOP Inoperative

INIT Initialization

INSTR Instrument


PQ.3.6

INT or INTPH

Interphone

INTC Intercept

INTC CRS Intercept Course

IP Instructor Pilot

IRS Inertial Reference System

IRU Inertial Reference Unit

ISA International Standard Atmosphere

ISDU Inertial System Display Unit

ISFD Intergrated Standby Flight Display

ISLN Isolation

J

JAA Joint Aviation Authority

K

K or KTS Knots

KCAS Knots Calibrated Airspeed

KGS Kilograms

KIAS Knots Indicated Airspeed

L

L Left

LAT Latitude

LBS Pounds

LD Load

LDA Localizer-type Directional Aid

LDG Landing

LDG ALT Landing Altitude


June 16, 2008



LE Leading Edge

LIM Limit

LIM SPD Limit Speed

LKD Locked

L NAV or LNAV

Lateral Navigation

LOC Localizer

LOC-BC Localizer Back Course

LOM Locator Outer Marker

LON Longitude

LRC Long Range Cruise

LRU Line Replaceable Unit

LSK Line Select Key

LT Light

LWR CTR Lower Center

LWR DSPLY orLWR DSPL

Lower Display

M

M Mach

MAG Magnetic

MAHP Missed Approach Holding Point

MAN Manual

MAP Missed Approach Point

MASI Mach/Airspeed Indicator

MAX Maximum

MCC Maintenance Control Center

MCDU Multi-purpose Control and Display Unit

MCO Maintenance Carry Over


June 16, 2008

MCP Mode Control Panel

MCT Maximum Continuous Thrust

MDA Minimum Descent Altitude

MDA(H) Minimum Descent Altitude (Height)

MDM Mechanical Dispatch Manual

MEA Minimum Enroute Altitude

MEL Minimum Equipment List

MFD Multifunction Display

MHZ Megahertz

MIC Microphone

MIN Minimum

MKR Marker

MLS Microwave Landing System

MM Middle Marker

MMO Maximum Mach Operating Speed

MNPS Minimum Navigation Performance Specification

MOCA Minimum Obstruction Clearance Altitude

MOD Modify

MORA Minimum Off Route Altitude

MSA Minimum Safe Altitude

MSG Message


PQ.3.7



MSGS RCVD

Messages Received

MSL Mean Sea Level

MTRS Meters

MUH Minimum Use Height

N

N Normal

NADP Noise Abatement Departure Procedures

NAR North American Route

NAV Navigation

NAV RAD Navigation Radio

ND Navigation Display

NLT No Later Than

NM Nautical Mile(s)

NNC Non-Normal Checklists

NNM Non-Normal Maneuvers

NPS Navigation Performance Scales

NORM Normal

N1 Low Pressure Rotor Speed

N2 High Pressure Rotor Speed (Pratt & Whitney and GE engines) or

Intermediate Pressure Rotor Speed (Rolls Royce Engines)

N3 High Pressure Rotor Speed (Rolls Royce Engines)

O

OAP Overhead Annunciator Panel (a.k.a. EOAP)


PQ.3.8

OAT Outside Air Temperature

OCC Operations Control Center

ODM Operational Data Manual

OFST Offset

OHU Overhead Unit

OM Outer Marker

OP Open

OUTBD DSPL

Outboard Display

OVHD Overhead

OVHT Overheat

OVRD Override

OVSPD Overspeed

OXY orO2

Oxygen

P

PA Passenger Address

PAPI Precision Approach Path Indicator

PAR Precision Approach Radar

PASS Passenger

PBE Protective Breathing Equipment

PCP Pilot Call Panel

PDC Pitch Data Computeror

Performance Data Computeror

Pre-Departure Clearance

PERF Performance


June 16, 2008



PERF INIT Performance Initialization

PES Pitch Enhancement System

PF Pilot Flying

PFC Primary Flight Computer

PFD Primary Flight Display

PI Performance Inflight

PIP Product Improvement Package

PM Pilot Monitoring

PMC Power Management Control

PNL Panel

POS Position

POS INIT Position Initialization

POS REF Position Reference

PPI Planned Position Indicator

PPOS Present Position

PRES or PRESS

Pressure

PREV Previous

PRI Primary

PROG Progress

PROX Proximity

P/RST Push To Reset

PRV Pressure Regulating Valve

PSI Pounds Per Square Inch

PTH Path

PTT Push To Talk


June 16, 2008

PTU Power Transfer Unit

PWR Power

PWS Predictive Windshear System

Q

Q Quantity

QFE Local Station Pressure

QNH Altimeter Setting

QRH Quick Reference Handbook

QTY Quantity

R

R Right

RA Radio Altitude or

Resolution Advisory

RAD Radio

RAT Ram Air Temperature orRam Air Turbine

RCL Request for Clearance

RDMI Radio Distance Magnetic Indicator

REC Recorder

RECIR or RECIRC

Recirculation

REF Reference

RET Retract

REV Reverse

RF Radius-to-Fix (RF) Legsor

Refill

RMI Radio Magnetic Indicator

RNAV orRNV

Area Navigation


PQ.3.9



RNP Required Navigational Performance

RPL Rudder Pressure Limiter

RPM Revolutions Per Minute

RPR Rudder Pressure Reducer

RSEP Rudder System Enhancement Program

RST Reset

RSVR Reservoir

R/T Radio Transmit

RTE Route

RTO Rejected Takeoff

RTP Radio Tuning Panel

RUD Rudder

RVR Runway Visual Range

RVSM Reduced Vertical Separation Minimum

S

SAARU Secondary Attitude Air Data Reference Unit

SAT Static Air Temperature

orSatellite

SB Service Bulletin

S/B Speedbrake

S/C Step Climb

SDF Simplified Directional Facility

SEI Standby Engine Indicator

SEL Select

SELCAL Selective Calling

SENS Sensitivity


PQ.3.10

SERV Service

SG Symbol Generator

SPD Speed

SPDBRK Speedbrake

STA Station

STAB Stabilizer

STAT Status

STBY Standby

STD Standard

SYS System

T

T or TRU True

T or TK or TRK

Track (to a Navaid)

TA Traffic Advisory

TAA Terminal Arrival Area

TACAN Tactical Air Navigation

TAC Thrust Asymmetry Compensation

TAI Thermal Anti–Ice

TAS True Airspeed

TAT Total Air Temperature

T/C Top of Climb

TCA Terminal Control Area

TCAS Traffic Alert and Collision Avoidance System

T/D Top of Descent

TDZ Touch Down Zone

TDZE Touch Down Zone Elevation

TE Trailing Edge


June 16, 2008



TEMP Temperature

TERR Terrain

TFC Traffic

TFR Transfer

THR Throttle or

Thrust

THR HOLD Throttle Hold

TMC Thrust Management Computer

TMI Track Message Identifier

TMSP Thrust Mode Select Panel

TO or T/O Takeoff

TOC Top of Climb

TOD Top of Descent

TO/GA Takeoff/Go–Around

TR Traffic Resolution

TRP Thrust Rating Panel

TRU Transformer Rectifier Unit

TURB Turbine or

Turbulence

U

UNLKD Unlocked

UNSCHD or UNSCHED

Unscheduled

UPR DSPL Upper Display

U.S. United States

USB Upper Side Band

UTC Universal Time Coordinated

UTIL Utility


June 16, 2008

V

VA Design maneuvering speed

VAL Valve

VANP Vertical Actual Navigational Performance

VASI Visual Approach Slope Indicator

VDP Visual Descent Point

VEF Speed at Engine Failure

VERT Vertical

VFR Visual Flight Rules

VG Vertical Gyro

VHF Very High Frequency

VIB Vibration

VLV Valve

VMC Visual Meteorological Conditions

VMCA Minimum Control Speed Air or

Single Engine Minumum Control Airspeed

VMCG Minimum Control Speed Ground

VMO Maximum Operating Speed

V NAV or VNAV

Vertical Navigation

VOR VHF Omnidirectional Range

VR Rotation Speed

VREF Reference Speed


PQ.3.11


Preface -Abbreviations


VRNP Vertical Required Navigation Performance

V/S Vertical Speed

VSCF Variable Speed Constant Frequency

VSD Vertical Situation Display

VSI Vertical Speed Indicator

VTK Vertical Track

V1 Takeoff Decision Speed

V1 (MCG) Minimum V1 for Control on the Ground

V2 Scheduled Takeoff Target Speed

W

W Warm

WATRS Western Atlantic Route System

WDR Weight Data Record

WGS-84 World Geodetic System of 1984

WHL Wheel

WPT Waypoint

WT Weight

WXR Weather Radar

X

X–FEED Crossfeed

XPDR or XPNDR

Transponder

XTK Cross Track

PQ.3.12 June 16, 2008


Preface Chapter PQRevision Record Section 4


PQ.4 Preface-Revision RecordRevision Transmittal LetterTo: All holders of Delta Air Lines, Inc., 767-300 Operations Manual, QRH.Subject: Operations Manual Revision.This revision reflects the most current information available to Delta Air Lines, Inc. through the subject revision date. The following revision highlights explain changes in this revision. General information below explains the use of revision bars to identify new or revised information.

Revision RecordNo. Revision Date Date

FiledNo. Revision Date Date

Filed

0 April 08, 2002 1 September 23, 2002

2 July 28, 2003 3 March 22, 2004

4 January 31, 2005 5 June 12, 2006

6 April 30, 2007 7 June 16, 2008

8 June 17, 2008

PQ.4.1June 17, 2008


Preface -Revision Record


GeneralDelta Air Lines, Inc. issues operations manual revisions to provide new or revised procedures and information. Formal revisions also incorporate appropriate information from previously issued operations manual bulletins.The revision date is the approximate date the revision material is distributed and considered current. The revision should be incorporated on the revision date, but may be incorporated as much as 21 days after the revision date.Formal revisions include a Transmittal Letter, a new Revision Record, Revision Highlights, and a current List of Effective Pages. Use the information on the new Revision Record and List of Effective Pages to verify the operations manual content.The Revision Record should be completed by the person incorporating the revision into the manual.

Filing InstructionsConsult the List of Effective Pages (PQ.5). Pages identified with an asterisk (*) are either replacement pages, new (original) issue pages, or deleted pages. Remove corresponding old pages and replace or add new pages. Remove pages marked DELETED; there are no replacement pages for deleted pages.Be careful when inserting changes not to throw away pages from the manual that are not replaced. The List of Effective Pages determines the correct content of the manual.

PQ.4.2 June 17, 2008




Revision HighlightsThis section (PQ.4) replaces the existing section PQ.4 in your manual.Pages containing revised technical and non-technical material have revision bars associated with the changed text or illustration. Repaginated material not containing technical revisions are identified only by a new page date.

Chapter PQ - Preface

Quick Action Index PageUpdated for current revision.

Annunciated IndexUpdated for current revision.

Section 1 - Model IntroductionPQ.1.1 - Added information for aircraft manual coverage.

Section 2 - IntroductionPQ.2.2 - Updated URL in Corrections to the Manual.

Section 4 - Revision RecordPQ.4.1-4 - Updated for current revision.

Section 5 - List of Effective PagesPQ.5.1-4 - Updated for current revision.

PQ.4.3June 17, 2008




Chapter NNC - Non-Normal Checklists

Section 0 - Unannunciated ChecklistsSMOKE OR FIRE OR FUMES

0.38 - Deleted LEFT RECIRCULATION FAN switch step.0.39 - Modified EQUIPMENT COOLING selector step name and responseto match panel.

SMOKE OR FUMES REMOVAL0.41 - Corrected name of referring checklist to SMOKE OR FIRE ORFUMES.0.41 - Added EQUIPMENT COOLING selector step.0.41 - Added conditional statement and EQUIPMENT COOLING selectorstep.0.42 - Corrected name of referring checklist to SMOKE OR FIRE ORFUMES.

Section 1 - Airplane General, Emergency Equipment, Doors, WindowsEMERGENCY DOOR(S)

1.8 - Added EICAS messages to provide coverage for all aircraft.1.8 - Modified Condition statement to provide coverage for all aircraft.

WING SLIDE1.16 - Deleted effectivities; this checklist is applicable to all aircraft.

Section 8 - Fire ProtectionSMOKE OR FIRE OR FUMES

8.18 - Deleted LEFT RECIRCULATION FAN switch step.8.19 - Modified EQUIPMENT COOLING switch step name and response tomatch panel.

SMOKE OR FUMES REMOVAL8.21 - Corrected name of referring checklist to SMOKE OR FIRE ORFUMES.8.21 - Added EQUIPMENT COOLING selector step.8.21 - Added conditional statement and EQUIPMENT COOLING selectorstep.8.22 - Corrected name of referring checklist to SMOKE OR FIRE ORFUMES.

PQ.4.4 June 17, 2008


PrefaceList of Effective Pages - FAA Approved

Chapter PQ

Section 5
June 12, 2006PQ.5 Preface-List of Effective Pag-es - FAA Approved
Page Date

Quick Reference Handbook

Quick Action Index

* QA.Index.1-2 June 17, 2008

Annunciated Index (tab)

ANN.Index.1-3 June 16, 2008

* ANN.Index.4-10 June 17, 2008

Preface (tab)

PQ.TOC.0.1-2 June 12, 2006

* PQ.1.1-4 June 17, 2008

PQ.2.1 June 12, 2006

* PQ.2.2 June 17, 2008

PQ.2.3-4 June 12, 2006

PQ.3.1 June 12, 2006

PQ.3.2-12 June 16, 2008

* PQ.4.1-4 June 17, 2008

* PQ.5.1-4 June 17, 2008

Checklist Introduction (tab)

CI.TOC.0.1-2 June 16, 2008

CI.1.1-3 June 12, 2006

CI.1.4 June 16, 2008

CI.2.1 June 12, 2006

CI.2.2-16 June 16, 2008

Non-Normal Checklists (tab)

0 Unannunciated Checklists (tab)

TOC.0.1-2 June 16, 2008

0.1-10 June 12, 2006

0.11 June 16, 2008

0.12-19 June 12, 2006

0.20-21 June 16, 2008

0.22-23 June 12, 2006

0.24-26 June 16, 2008

0.27-37 June 12, 2006

* 0.38-42 June 17, 2008

0.43-48 June 16, 2008

1 Airplane General, Emergency Equipment, Doors, Windows (tab)

TOC.1.1-2 June 16, 2008

1.1-2 June 12, 2006

1.3 June 16, 2008

1.4-7 June 12, 2006

* 1.8 June 17, 2008

1.9-14 June 12, 2006

1.15 June 16, 2008

* 1.16 June 17, 2008

Page Date

* = Revised, Added, or DeletedCopyright © Delta Air Lines, Inc. See QA.Index.1 for details.

PQ.5.1June 17, 2008


Preface -List of Effective Pages - FAA Approved

2 Air Systems (tab)

TOC.2.1-2 June 16, 2008

2.1 June 12, 2006

2.2 June 16, 2008

2.3-9 June 12, 2006

2.10 June 16, 2008

2.11-12 June 12, 2006

2.13-14 June 16, 2008

2.15-22 June 12, 2006

2.23 June 16, 2008

2.24 June 12, 2006

2.25-26 June 16, 2008

3 Anti-Ice, Rain (tab)

TOC.3.1-2 June 12, 2006

3.1-2 June 12, 2006

3.3 June 16, 2008

3.4-6 June 12, 2006

3.7 June 16, 2008

3.8-10 June 12, 2006

3.11 June 16, 2008

3.12 June 12, 2006

4 Automatic Flight (tab)

TOC.4.1-2 June 12, 2006

4.1-2 June 12, 2006

Page Date

5 Communications, Datalink (tab)

TOC.5.1-2 June 12, 2006

5.1-3 June 12, 2006

5.4-5 June 16, 2008

5.6-7 June 12, 2006

5.8 June 16, 2008

5.9-10 June 12, 2006

5.11 June 16, 2008

5.12-14 June 12, 2006

6 Electrical (tab)

TOC.6.1-2 June 16, 2008

6.1-18 June 16, 2008

7 Engines, APU (tab)

TOC.7.1-2 June 16, 2008

7.1-54 June 16, 2008

8 Fire Protection (tab)

TOC.8.1-2 June 16, 2008

8.1-17 June 12, 2006

* 8.18-22 June 17, 2008

9 Flight Controls (tab)

TOC.9.1-2 June 12, 2006

9.1-16 June 12, 2006

9.17-19 June 16, 2008

9.20-22 June 12, 2006

10 Flight Instruments, Displays (tab)

TOC.10.1-2 June 12, 2006

10.1-6 June 12, 2006

11 Flight Management, Navigation (tab)

TOC.11.1-2 June 16, 2008

11.1-10 June 16, 2008

Page Date


PQ.5.2 June 17, 2008


Preface -List of Effective Pages -

FAA Approved

12 Fuel (tab)

TOC.12.1-2 June 16, 2008

12.1-7 June 12, 2006

12.8 June 16, 2008

12.9-11 June 12, 2006

12.12-16 June 16, 2008

13 Hydraulics (tab)

TOC.13.1-2 June 12, 2006

13.1-3 June 12, 2006

13.4 June 16, 2008

13.5-6 June 12, 2006

13.7-8 June 16, 2008

13.9 June 12, 2006

13.10 June 16, 2008

13.11-12 June 12, 2006

13.13-14 June 16, 2008

13.15-18 June 12, 2006

14 Landing Gear (tab)

TOC.14.1-2 June 16, 2008

14.1-3 June 12, 2006

14.4-10 June 16, 2008

15 Warning Systems (tab)

TOC.15.1-2 June 16, 2008

15.1-4 June 16, 2008

Page Date

Maneuvers (tab)

MAN.TOC.0.1-2 June 12, 2006

MAN.1.1-8 June 12, 2006

MAN.1.9 June 16, 2008

MAN.1.10-11 June 12, 2006

MAN.1.12 June 16, 2008

MAN.1.13-14 June 12, 2006

MAN.1.15-18 June 16, 2008

MAN.2.1-8 June 12, 2006

Index (tab)

NNC.Index.1-8 June 16, 2008

Evacuation Checklist (tab)

Back Cover.1-2 June 12, 2006

Page Date


PQ.5.3June 17, 2008


Preface -List of Effective Pages - FAA Approved

IntentionallyBlank


PQ.5.4 June 17, 2008


Checklist Introduction Chapter CITable of Contents Section 0


CI.0 Checklist Introduction-Table of Contents

Normal Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.1Normal Checklist Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.1

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.1Reading the Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.1

Checklist Content . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.2Checklist Construction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.3

Designators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.3Other Conventions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.3Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.1.4

Non-Normal Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.1Non-Normal Checklist Operation . . . . . . . . . . . . . . . . . . . . . . . . CI.2.2

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.2Landing at the Nearest Suitable Airport . . . . . . . . . . . . . . . . . CI.2.2Land Immediately . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.2Checklists Prescribing Engine Shutdown . . . . . . . . . . . . . . . . CI.2.3Non-Normal Checklist Assumptions . . . . . . . . . . . . . . . . . . . CI.2.4

Non–Normal Checklist Use . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.5General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.5Calling for the Checklist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.5Reading the Checklist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.6Dual Verification of Critical Controls . . . . . . . . . . . . . . . . . . . CI.2.6Conditional Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.7Deferred Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.7Consequential EICAS Alert Messages . . . . . . . . . . . . . . . . . . CI.2.7Notes and Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.8Checklist Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.8Checklist Completion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.8

CI.TOC.0.1June 16, 2008


Checklist Introduction -Table of Contents


Ditching & Evacuation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.9Coast Guard Ditching Recommendations . . . . . . . . . . . . . . . . CI.2.8Flight Crew Duties Summary For Emergency Landing/Ditching Evacuation . . . . . . . . . . . . . . . . . . . . . . . CI.2.10

Evacuation Flow/Philosophy . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.13Smoke/Fumes Principles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.14

Known Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.14Unknown Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.14

Smoke/Fumes Priorities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.15Priorities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CI.2.15

CI.TOC.0.2 June 16, 2008


Checklist Introduction Chapter CINormal Checklists Section 1


CI.1 Checklist Introduction-Normal ChecklistsIntroductionNormal Checklists contain, in abbreviated form, information required by thetrained flight crew to operate the airplane in normal situations.This introduction gives guidelines for use of the Normal Checklist (NC).The NC is organized by phase of flight. The NC is used to verify that critical items have been done.

Normal Checklist Operation

GeneralNormal checklists are used by the flight crew after accomplishing all applicableprocedural items found in the Amplified Procedures section of Volume 1.

Note: Normal checklists will be used as verification lists, not as do lists.

Reading the ChecklistsOn the ground, the Captain calls for the checklists and the First Officer reads thechecklists after the procedures are accomplished. The Captain may elect to readthe Before Start checklist, in which case, the First Officer will respond. In flight, the Pilot Flying (PF) calls for the checklists and the Pilot Monitoring(PM) reads the checklists after the procedures are accomplished.If the airplane configuration does not agree with the needed configuration:• stop the checklist• complete the respective procedure steps• continue the checklist

If it becomes apparent that an entire procedure was not done:• stop the checklist• complete the entire procedure• Accomplish the checklist from the start

Try to accomplish checklists before or after high work load times. The crew mayneed to stop a checklist for a short time to do other tasks. If the interruption isshort, continue the checklist with the next step. If a pilot is not sure where thechecklist was stopped, accomplish the checklist from the start. If the checklist isstopped for a long time, also accomplish the checklist from the start.

CI.1.1June 12, 2006


Checklist Introduction -Normal Checklists


On the ground, if any checklist item has not been completed when challenged, ora disagreement between the response and checklist answer occurs, it is mandatorythat the checklist be discontinued until the item is accomplished or resolved.However, the PUSHBACK/START checklist may be started while awaiting the“CABIN IS READY FOR PUSHBACK” report from the OBL. The first flight ofthe day items are only required to be accomplished on the first flight aftermidnight local time.If the flight deck is vacated by all pilots during or after accomplishing theBEFORE START checklist, the checklist must be re-accomplished.The AFTER LANDING checklist will be accomplished only after the aircraft hascleared the active runway, unless a back-taxi is required. In this case, perform thechecklist after the 180° turn and at normal taxi speed.In flight, if any item has not been accomplished, continue with the remainingitems. In this case, the pilot reading the checklist will state, “(THOSE ITEMS) TOGO.” When the missing items are accomplished, the checklist may be calledcomplete.Following the completion of each normal checklist, including those accomplishedsilently, the crewmember reading the checklist states, “________ CHECKLISTCOMPLETE.”

Checklist ContentThe checklist has the minimum items needed to operate the airplane safely.Normal checklists have items that meet any of the following criteria:• items essential to safety of flight that are not monitored by an alerting

system, or• items essential to safety of flight that are monitored by an alerting system

but if not done, would likely result in a catastrophic event if the alertingsystem fails, or

• needed to meet regulatory requirements, or• items needed to maintain fleet commonality between the MD88/90, 737,

757, 767, and 777, or• items that enhance safety of flight and are not monitored by an alerting

system (for example autobrakes), or• during shutdown and secure, items that could result in injury to personnel

or damage to equipment if not done.

CI.1.2 June 12, 2006




Checklist ConstructionWhen a checklist challenge does not end with “switch or lever”, then the challengerefers to system status. For example, “Landing Gear...Down”, refers to the statusof the landing gear, not just the position of the lever.When a checklist challenge ends with “switch or lever”, then the challenge refersto the position of the switch or lever. For example, “FUEL CONTROLswitches...CUT OFF” refers to the position of the switches.

DesignatorsLocated on the right side of certain challenge-response items are designatorswhich indicate that verbalization is required. The pilot(s) designated will visuallyverify switch position or status and then make the response to the pilotchallenging. Items that do not have designators are to be accomplished silently.

Note: Items that are critical to flight safety are indicated by the designators“C&F” or “All” and require a response from both crewmembers or allflight deck occupants.

The following designators are used:

Other ConventionsWhen alternatives are available in a checklist item, a forward slash “/”will be used(e.g., APU/ external power).When the printed response to any checklist item is “as reqd”, the proper verbalresponse is the actual position of that switch or system.A blank line “____” requires a numerical response and is used when the responseis a variable value, such as altimeters, bugs, flaps, slats, or stabilizer trim settings.When the challenge requires verification of proper system operation, “ckd” is usedas the response.

C - CaptainF - First OfficerAll - All flight deck positions, including jump seat(s)PM - Pilot MonitoringC&F - Captain and First Officer

CI.1.3June 12, 2006




SymbolsA indicates items that should be considered for re-accomplishment in the event of a runway/intersection change. The Captain should call for “Runway Change Items” if not previously briefed.The First Officer will then verbalize each runway change item by stating the challenge to the item and then the designated crewmember(s) will respond with either:• “No Change” for an item , or • The appropriate checklist response for the item that changed.

CI.1.4 June 16, 2008


Checklist Introduction Chapter CINon-Normal Checklists Section 2


CI.2 Checklist Introduction-Non-Normal ChecklistsIntroductionThe Non-Normal Checklists chapter contains checklists used by the flight crew to cope with non–normal situations. The checklists are grouped in logical sections which match the system description chapters in Volume 2. The checklists are in alphabetical order in each section.Most checklists correspond to an EICAS alert message. An EICAS alert message annunciates a failure condition and is the cue to select and do the checklist.Checklists without an EICAS alert message (such as DITCHING PREPARATION) are called unannunciated checklists. All unannunciated checklists are found in the first section of the Non–Normal Checklists chapter. Some unannunciated checklists also appear in the respective systems section (such as ENGINE FUEL LEAK in the Fuel section).A condition statement is given for all alert messages. The condition statement briefly describes the condition which caused the message to show. Unannunciated checklists also have condition statements to help in understanding the reason for the checklist.Checklists can have both recall and reference items. Recall items are critical steps that must be done from memory and are placed within a box. Each crewmember is required to know all recall items. Bullets, notes and bracketed items within the recall box support action steps and are not considered recall items. Reference items are actions to be done while reading the checklist. In the Table of Contents for each non-normal checklist section, the titles of checklists containing memory items are printed in bold type.Some amplified information is included in brackets [ ] in the printed non-normal checklist when the reason for an item is not obvious.

CI.2.1June 12, 2006


Checklist Introduction -Non-Normal Checklists


Non-Normal Checklist Operation

GeneralNon–normal checklists start with steps to correct the situation or condition. Information for planning the rest of the flight is included. When special items are needed to configure the airplane for landing, the items are deferred to the Approach or Landing checklist. Flight patterns for some non-normal situations are located in the Maneuvers chapter of this manual and the Flight Crew Training Manual (FCTM) and show the sequence of configuration changes.

While every attempt is made to provide needed non–normal checklists, it is not possible to develop checklists for all conceivable situations, especially those involving multiple failures. In some unrelated multiple failure situations, the flight crew may combine elements of more than one checklist or exercise judgment to determine the safest course of action. The Captain must assess the situation and use good judgment to determine the safest course of action.

Landing at the Nearest Suitable AirportThere are some situations where the crew must always land at the nearest suitable airport. These situations include, but are not limited to, conditions where:• the non–normal checklist has the words “Plan to land at the nearest

suitable airport”• cabin smoke or fire persists• normal aircraft pitch, roll, or yaw cannot be maintained using aircraft trim

systems• there is only one AC power source (such as an engine or APU generator)• one hydraulic system remains, or• any other situation determined by the crew to have a significant adverse

effect on safety if the flight is continuedIt must be stressed that for persistent smoke or a fire that cannot be positively confirmed to be completely extinguished, the earliest possible descent, landing, and evacuation must be done.

Land ImmediatelyIf a smoke, fire or fumes condition becomes uncontrollable, the SMOKE, FIRE OR FUMES checklist directs the flight crew to consider an immediate landing. “Immediate landing” implies immediate diversion to a runway. However, the smoke, fire or fumes situation may be severe enough that the Captain should consider an overweight landing, a tailwind landing, an off-airport landing, or a ditching.

CI.2.2 June 16, 2008




Checklists Prescribing Engine ShutdownChecklists prescribing an engine shutdown must be evaluated by the Captain to determine whether an actual shutdown, or operation at reduced thrust, is the safest course of action. Consideration must be given to probable effects if the engine is operated at the minimum needed thrust.There are no non–normal checklists associated with the loss of an engine indication, or with an automatic display of the secondary engine indications. Operate the engine normally unless an EICAS message shows or a limit is exceeded.

CI.2.3June 16, 2008




Non-Normal Checklist AssumptionsNon-normal checklists assume:• Continuing to fly the airplane is the single most important consideration

in every situation.• Hurried action may be inappropriate and could result in a more serious

situation.Non–normal checklists also assume:• During engine start and before takeoff, the respective non–normal

checklist is done if an EICAS alert message is shown. Upon completion of the checklist, the Mechanical Dispatch Manual is consulted to determine if Minimum Equipment List relief is available

• System controls are in the normal configuration for the phase of flight before the start of the non–normal checklists

• Aural alerts are silenced and the system reset by the flight crew as soon as the cause of the alert is recognized

• The EMERGENCY position of the oxygen regulator is used when needed to supply positive pressure in the masks to evacuate contaminants. The 100% position of the oxygen regulator is used when positive pressure is not needed, but contamination of flight deck air exists. The NORMAL position of the oxygen regulator is used if prolonged use is needed and the situation allows. Normal boom mic operation is restored when oxygen use is no longer needed

• Indicator lights are tested to verify suspected faults

CAUTION: Flight crew reset of a tripped circuit breaker in flight is notrecommended unless specifically directed to do so in anon-normal checklist. However, a tripped circuit breaker maybe reset once, after a short cooling period (approximately 3minutes), if in the judgment of the Captain, the situationresulting from the circuit breaker trip has a significant adverseeffect on safety. A ground reset of a tripped circuit breaker bythe flight crew should only be accomplished after maintenancehas determined it is safe to reset the circuit breaker. Flightcrew cycling (pulling and resetting) of circuit breakers to clearnon-normal conditions is not recommended unless directed bya non-normal checklist. If it is determined that the circuitbreaker must be reset, turn off the affected component (ifpossible), and wait 3 minutes to let the circuit breaker coolproperly prior to reset. Attempt only one reset.

WARNING: Do not reset a tripped fuel boost pump CB.

CI.2.4 June 16, 2008




Non–Normal Checklist Use

GeneralNon–normal checklist use starts when the airplane flight path and configuration are correctly established. Only a few situations need an immediate response (such as a stall warning, ground proximity PULL UP and WINDSHEAR warnings, or a rejected takeoff). Usually, time is available to assess the situation before corrective action is started. All actions must then be coordinated under the Captain's supervision and done in a deliberate, systematic manner. Flight path control must never be compromised.Airplane effectivity is shown above a line item when:• the procedures in a non-normal checklist are different because of an

airplane configuration difference• that difference applies to only a single line item

For example:

This example shows that 0601 through 0682 have a single fuel crossfeed switch. 0683 through 6717 have dual fuel crossfeed switches.If the effectivity applies to all the procedure, the effectivity is shown centered below the title.

Calling for the ChecklistWhen a non-normal situation occurs, at the direction of the pilot flying, bothcrewmembers systematically and without delay do all recall items in their areas ofresponsibility.The pilot flying may also direct reference procedures to be done by recall if nohazard is created by such action, or if the situation does not allow reference to achecklist.Call for the checklist when:• the flight path is under control• the airplane is not in a critical stage of flight (such as takeoff or landing)• all recall items are complete.

FUEL CROSSFEED switch. . . . . . . . . . . . . . . . . . . . . . .OFF

FUEL CROSSFEED switches (Both). . . . . . . . . . . . . . .OFF

0601 through 0682:

0683 through 6717:

CI.2.5June 16, 2008




Reading the ChecklistFor those checklists with only recall items or a combination of recall and reference items, the pilot monitoring first verifies each recall item has been done. The checklist is normally read aloud during this verification. The pilot flying does not need to respond except for items not in agreement with the checklist.The checklist title, condition statement, message (where applicable) and reference items, including the response or action and any amplifying information, are read aloud by the pilot monitoring. Information appearing in brackets does not need to be read aloud. The pilot flying need not repeat these items, but must acknowledge that the items were heard and understood. Action is taken by the crewmember if the control is in the crewmember’s area of responsibility. After moving the control, the crewmember taking the action also states the checklist response.

Dual Verification of Critical ControlsPrior to actuation of any critical controls when accomplishing a non-normalchecklist in flight, a dual response is required. The following are consideredcritical controls: • Thrust lever reduction of a failed engine• fuel control switches/engine start levers• any fire switch• any IDG/CSD disconnect switch.

After determination that a critical control must be actuated in flight, the followingsteps must be taken:• Both pilots must verbally and visually identify the affected control.• The pilot performing the action will place their hand on the affected

control. • The pilot monitoring the action will verbally and visually confirm the

proper control has been selected.• The pilot performing the action then actuates the affected control.

CI.2.6 June 16, 2008




Conditional ItemsConditional items are used at a decision point. Conditional items usually beginwith “If.” When a conditional item is encountered in a procedure, apply thefollowing logic:• If the conditional item applies, accomplish the action step(s) immediately

following it.• If the conditional Item does not apply, skip the associated action step(s)

and proceed to the next procedural step.

Deferred ItemsThe pilot flying is to be made aware when there are deferred items. These items may be delayed until the usual point during descent, approach or landing.Following completion of the applicable non–normal checklist items, normal checklists are used to verify that the configuration is correct for each phase of flight.

Consequential EICAS Alert MessagesConsequential EICAS alert messages can show as the result of a primary failure condition (such as HYDRAULIC ENGINE PUMP from HYDRAULIC SYSTEM PRESSURE (L ONLY)) or the result of a non–normal checklist crew action (such as PACK OFF from SMOKE OR FUMES AIR CONDITIONING). Consequential messages fall into two categories:• If the crew does not need to do the consequential checklists, then the

following statement shows in the checklist: “Do not accomplish the following checklists.”

• If the crew does need to do the consequential checklists, then no reference is made to the consequential message.

CI.2.7June 16, 2008




Notes and InformationNotes and information items, except for condition statements, are read aloud. Thepilot flying need not repeat these items, but should acknowledge that the itemswere heard and understood.Checklists show lists of inoperative equipment only when knowledge of thecondition of such equipment is essential for planning the rest of the flight.

Checklist LimitationsPilots must be aware that checklists cannot be created for all conceivablesituations and are not intended to replace good judgment. In some conditions,deviation from checklists may, at the Captain’s discretion, be needed.

Checklist CompletionThe following symbol shows that the checklist is complete.

Each checklist has a checklist complete symbol at the end. The checklist complete symbol can also be in the body of the checklist. This occurs only when a checklist divides into two or more paths. Each path can have a checklist complete symbol. The checklist complete symbol shows the end of the applicable path. The crew need not continue the checklist after that point.Following completion of each non-normal checklist, the pilot monitoring states: “_______ CHECKLIST COMPLETE.” When a non-normal checklist is complete except for the deferred items, the pilot monitoring states: “______ CHECKLIST COMPLETE EXCEPT FOR DEFERRED ITEMS.”

CI.2.8 June 16, 2008




Ditching & Evacuation

Coast Guard Ditching RecommendationsIn a ditching situation, the Captain should consider requesting a US Coast Guard Search and Rescue (SAR) aircraft to launch for intercept. Initial contact with SAR may be made on primary HF frequency or 121.5 mhz. To assist SAR aircraft, squawk 7700 unless assigned another code.The SAR aircraft may intercept 1000 feet below your aircraft in VFR or 1000 feet above in IFR. Therefore, the altimeters of each aircraft must be compared prior to intercept to ensure safe vertical separation.If ditching is unavoidable, the Coast Guard may be able to recommend a ditching heading either through the SAR aircraft or from a surface ship. If possible, ditch in the lee of an island, in a lagoon, or near a ship.On primary HF, try to obtain information on ship location through USCG, Navy, AMVER, or RCC. If a merchant ship is nearby, attempt to communicate on 4125 or 2182 kHz. USCG and Navy vessels may be able to communicate on 121.5.Coast Guard, Navy, and some merchant ships may have the capability of supplying homing signals, radar for intercept, flares for night ditching, and other aids. Standard low frequency homing signal is 410 hz, giving the call sign, followed by 2 (two) 10 (ten) second dashes.

Continued on next page

CI.2.9June 16, 2008




Continued from previous page

Flight Crew Duties Summary For Emergency Landing/Ditching EvacuationThe following flight crew duties summary is designed to assist the crew members in preparing the aircraft’s occupants for emergency landing and evacuation. Time is essential in preparing passengers for the evacuation (especially non-ambulatory). Flight attendants should be advised of the problem(s) as soon as flight safety is in doubt. Specific flight attendant duties are outlined in the In-Flight Service On-Board Manual. Additionally, the flight attendants should be informed of any conditions such as high winds, irregular ground condition, sea state, structural damage and/or fire that affect or alter status of the escape slides/raft deployment.


Pre Landing/DitchingCaptain First Officer

• Advise crew to prepare for emergency landing (or ditching) and order distress message sent.

• Set course for most logical point of landing under existing circumstances.

• Order flight deck emergency preparation as conditions dictate.

• Fasten seat belt and shoulder harness and lock.

• Signal cabin crew/passengers when touchdown is imminent, using PA system if operative.

• If ditching: don life vest.

• Send distress message (MAY DAY), giving aircraft identification, type, position, heading, airspeed, altitude, fuel remaining in hours and minutes, nature of distress, intentions, and assistance desired.

• Assist in flight deck emergency preparations as directed by the Captain and as conditions dictate.

• Fasten seat belt and shoulder harness and lock.

• If ditching: don life vest.

Relief Pilot (When Aboard)• Assist in flight deck emergency preparations as directed by the Captain

and as conditions dictate.• Open flight deck door. Stow loose articles.• Fasten seat belt and shoulder harness and lock.• If ditching: don life vest.

CI.2.10 June 16, 2008






Post LandingCaptain First Officer

• Order evacuation.• Proceed to forward cabin area.• Assist in evacuating passengers

as conditions dictate.• After ensuring that all

passengers are off the aircraft or all possible assistance has been given, exit from the rear of the aircraft if able.

• Assume command outside the aircraft.

• Proceed to forward entry/exit door area.

• Ensure forward exits are open.• Exit aircraft from forward exit

and assist in the evacuation from outside the aircraft.

Relief Pilot (When Aboard)• Proceed to forward entry/exit door area.• Ensure forward exits are open.• Exit aircraft from forward exit and assist in the evacuation from outside

the aircraft.

CI.2.11June 16, 2008





DitchingCaptain First Officer

• Order evacuation.• Proceed to forward cabin area.• Assist in evacuating passengers

as conditions dictate.• After ensuring that all

passengers are off the aircraft or all possible assistance has been given, exit from the rear of the aircraft if able. Board raft.

• Assume command outside the aircraft.

• After exiting, assemble passengers/rafts away from the aircraft.

• Take radio beacon.• Ensure forward exits are open.• (121, 124-139, 1401-1404)

Assist in securing 46-man raft located on the floor in a storage compartment on the right side of the center aisle lavatory in the mid cabin and launch left from 1R door.

• Exit aircraft from forward exit and board raft.

• Assist in assembling passengers/rafts away from the aircraft.

Relief Pilot (When Aboard)• (1501-1506, 1521) Direct passengers, and exit aircraft, through 2R door;

board slide raft.• Exit aircraft from forward entry/exit door area and board raft.• Assist in assembling passengers/rafts away from aircraft.

CI.2.12 June 16, 2008




Evacuation Flow/PhilosophyEvacuation flow items listed below are not included within the EVACUATION checklist. They are meant to refresh the logical pattern of procedures that must occur for a successful evacuation. In the unlikely event that the checklist cannot be read due to smoke/fire, darkness, injury or incapacitation, the simple flow or philosophy should lead the pilot to completion of all critical tasks contributing to the safest possible evacuation.The checklist follows the flow pattern of:

STOPCONFIGURESHUT DOWNEVACUATE

CI.2.13June 16, 2008




Smoke/Fumes PrinciplesAll smoke/fire/fumes events are different, and every contingency cannot be addressed in a single checklist. At the beginning of any smoke/fire/fumes event, crews should always consider the following:• Protecting themselves (e.g., oxygen masks)• Communicating (Crew and ATC)• Diverting• Assessing the smoke/fire/fumes situation and available resources.

If smoke/fire/fumes are associated with an annunciated checklist (e.g., cargo fire), accomplish that checklist prior to the "SMOKE, FIRE OR FUMES" or "SMOKE OR FUMES REMOVAL" checklists.

Known SourceMany smoke/fire/fumes events involve aircraft equipment or materials readily accessible. Rapid, positive extinguishing of the source is the key to preventing escalation of the event. Confirmation that the situation has been resolved is critical. Do not consider flight continuation unless the source is positively identified, confirmed to be extinguished and smoke/fumes are decreasing.

Unknown SourceIt may not always be possible to accurately identify the smoke/fire/fumes source due to ambiguous cues, such as multiple sources. It may not be possible to determine the difference between electrical smoke/fumes and air conditioning smoke/fumes by sense of smell. The source identification/elimination steps in the "SMOKE, FIRE OR FUMES" Checklist will systematically remove the most probable smoke/fire/fumes sources.Inordinate depowering of airplane systems is not likely to benefit an unknown smoke/fire/fumes situation. Such action significantly reduces airplane capabilities without commensurate likelihood of depowering the unknown smoke/fire/fumes source.

CI.2.14 June 16, 2008




Smoke/Fumes Priorities

GeneralThe following information is critical to survival in a smoke/fumes situation. Though all applicable non-normal checklists can be found in other sections of this manual, Section 8 (Fire Protection) contains all of these checklists.

Note: Pilots should remain at their stations to fly the aircraft, coordinate with ATC and accomplish the checklists. The incapacitation of a pilot fighting a fire would seriously complicate the situation.

PrioritiesDiversionAfter making a preliminary assessment of the smoke/fire/fumes source, the flight crew is reminded a diversion may be necessary.

Oxygen Masks (if required)The flight crew should don the oxygen mask anytime smoke/fire/fumes are detected on the flight deck. If smoke/fire/fumes are detected in another part of the aircraft, flight crew judgment will determine if/when the Oxygen Masks are donned.

Crew and Cabin CommunicationsFor a cabin smoke/fire/fumes situation, continuous communications between the flight crew and a designated flight attendant is essential. Flight attendants should be directed to inspect the entire cabin in an attempt to locate the smoke/fire/fumes source. Passengers should be moved away from the source.

Identification/EliminationThe flight crew should, without delay or analysis, perform the initial "SMOKE, FIRE OR FUMES" checklist steps that remove the most probable smoke/fire/fumes sources. The flight crew should attempt to identify and eliminate the source, and visually confirm it is extinguished and the smoke/fumes are decreasing.


CI.2.15June 16, 2008





AssessmentOnce a fire or concentration of smoke/fumes is detected, continuing the flight to the planned destination is not recommended unless the source of the smoke/fire/fumes is positively identified and visually confirmed to be extinguished and the smoke/fumes are decreasing. If initial identification / elimination steps do not positively identify and remove the smoke/fire/fumes, a diversion will be necessary."Visually confirmed to be extinguished" means that a crew member can physically see the source of smoke and that it has been extinguished. An example would be if a cabin crewmember visually identified smoke coming from an oven, and after power was removed from the oven, visually can see that the smoke has stopped. On the other hand, if the smoke stops after depowering a particular system (e.g., Recirculation Fan), the smoke/fire is not "positively identified and visually confirmed to be extinguished", therefore a diversion will be necessary. The flight crew must continually evaluate the situation to determine if further actions (e.g. oxygen mask, diversion, immediate landing, immediate smoke removal) are necessary.

RemovalThe "SMOKE OR FUMES REMOVAL" checklist should be accomplished only when the smoke/fumes are the greatest threat, or when the source is confirmed to be extinguished. Smoke/fumes removal may change the airflow and make the situation worse by fanning or masking the ignition source

WARNING: Do not activate the emergency passenger oxygen system. Itprovides no smoke protection for passengers as it mixes oxygenwith cabin air. It is also an extreme fire hazard.

CI.2.16 June 16, 2008


Non-Normal Checklists Chapter NNCUnannunciated Checklists Section 0


Table of ContentsNNC.0 Non-Normal Checklists-Unannunciated ChecklistsABORTED ENGINE START . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.1

AIRSPEED UNRELIABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.2ALL FLAPS AND SLATS UP LANDING . . . . . . . . . . . . . . . . . . . 0.4AUTOMATIC UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.4CABIN ALTITUDE OR RAPID DEPRESSURIZATION . . . . . 0.5DITCHING PREPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.6DUAL ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.8ENGINE FAILURE OR SHUTDOWN . . . . . . . . . . . . . . . . . . . . . 0.10ENGINE FIRE OR SEVERE DAMAGE OR

SEPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.12ENGINE FUEL LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.15ENGINE IN–FLIGHT START . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.20ENGINE LIMIT OR SURGE OR STALL . . . . . . . . . . . . . . . . . 0.24ENGINE OIL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . 0.26ENGINE TAILPIPE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.27FUEL JETTISON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.28GEAR LEVER WILL NOT MOVE UP . . . . . . . . . . . . . . . . . . . . 0.29JAMMED OR RESTRICTED FLIGHT CONTROLS . . . . . . . . . 0.30LOCK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.31LOW FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.32RADIO TRANSMIT CONTINUOUS

(STUCK MICROPHONE SWITCH) . . . . . . . . . . . . . . . . . . . . . 0.33REVERSER UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.34SMOKE OR FIRE OR FUMES . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.38SMOKE OR FUMES REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . 0.41TAIL STRIKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.43VOLCANIC ASH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.44WINDOW DAMAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.46

TOC.0.1June 16, 2008


Non-Normal Checklists -Unannunciated Checklists


WINDOW OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.47

TOC.0.2 June 16, 2008

767-300 Operations Manual 0.1


Condition: During a ground start, an abort engine start condition occurs.

If the ENGINE START selector is in GND:

Motor the engine for 30 seconds.

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . AUTO

If the ENGINE START selector is in AUTO:

After N2 decreases below 20%:

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . GND


ENGINE START selector . . . . . . . . . . . . . . . . . . . . AUTO

ABORTED ENGINE START

FUEL CONTROL switch . . . . . . . . . . . . . . . . . . . . . . . CUT OFF

0.1June 12, 2006



Condition: Airspeed/Mach indication is suspected to be unreliable.

One or more of the following may be evidence of unreliable airspeed/Mach indication:• Speed/altitude information not consistent with pitch

attitude and thrust setting• Speed/Airspeed/Mach failure flags• Blank or fluctuating airspeed displays• Variation between Captain and First Officer airspeed

displays• Amber line through one or more ADI flight mode

annunciations• Overspeed indications• Radome damage or loss• Simultaneous overspeed and stall warnings• Display of one or more of the following EICAS messages:

Pitch attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . Check

If pitch attitude or thrust is not normal for phase of flight:

AUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISENGAGE

AUTOTHROTTLE . . . . . . . . . . . . . . . . . . . . . . . . .Disconnect

FLIGHT DIRECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . AdjustEstablish normal pitch attitude and thrust setting for phase of flight.

Note: Normal pitch attitude and thrust settings are available in the ODM, ABNORMAL section, OPERATION WITHOUT AIRSPEED INDICATION.


AIRSPEED UNRELIABLE

AILERON LOCKOUTALT DISAGREECAPT PITOTF/O PITOTIAS DISAGREE

L AUX PITOTOVERSPEEDPROBE HEATR AUX PITOTRUDDER RATIO

0.2 June 12, 2006




Altitude information, vertical speed information, limit N1/EPR, Reference N1/EPR, and N1/EPR bug may be unreliable.Note: Flight may not be permitted in RVSM airspace.

Contact ATC. Refer to the Airway Manual, Navigation section, for RVSM requirements.

Speed indications . . . . . . . . . . . . . . . . . . . . . . . . .Cross checkCross check Captain and First Officer airspeed indications and standby airspeed indicator. An airspeed display differing by more than 15 knots from the standby indicator should be considered unreliable.

If the reliable airspeed data source can be determined:

AIR DATA SOURCE SELECTswitch (Unreliable side) . . . . . . . . . . . . . . . . . . . . . . . .ALTN

Invalid overspeed warning and invalid input to AFDS and autothrottle may occur or continue.

If the reliable airspeed data source cannot be determined:

Attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . . .AdjustMaintain normal pitch attitude and thrust setting for phase of flight. Refer to the ODM, ABNORMAL section, OPERATION WITHOUT AIRSPEED INDICATION.

------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Maintain visual conditions if possible.

Establish landing configuration early.

Use electronic and visual glideslope indicators, where available, for approach and landing.

Refer to IRS ground speed on the CDU POS REF page and reported wind on approach.

0.3June 12, 2006



Condition: Leading edge slats and trailing edge flaps cannot be extended.

CAUTION: Accomplish this checklist only when directed by the LEADING EDGE SLAT ASYMMETRY checklist.

Note: Do not slow below VREF 30 + 80 until established on final approach.

Note: Limit bank angle to 15 degrees below VREF 30 + 80.

Note: Reduced tail clearance on landing.

ENGINE START selectors (Both) . . . . . . . . . . . . . . . . . . CONT

GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD

Use VREF 30 + 50 for landing.Refer to Non-Normal Maneuvers section in QRH for All Flaps and Slats Up Landing.

Condition: The flight deck door AUTO UNLK light illuminated indicates the correct emergency access code has been entered and the flight deck door is programmed to automatically unlock after a time delay.

FLIGHT DECK DOOR LOCK selector . . . . . . . . . . . . . . . DENYRotate and hold for 1 second.[Prohibits unauthorized access to the flight deck.]

ALL FLAPS AND SLATS UP LANDING

AUTOMATIC UNLOCK

0.4 June 12, 2006



Condition: The CABIN ALT or CABIN ALTITUDE light illuminated indicates cabin altitude is excessive.

Cabin altitude and rate . . . . . . . . . . . . . . . . . . . . . . . . . . Check[Confirms pressurization problem.]

If cabin altitude uncontrollable:

PASSENGER OXYGEN switch . . . . . . . . . . . . . . . . . . . . .ON

Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AccomplishWithout delay, close thrust levers, extend speedbrakes, and descend at Vmo/Mmo. Level off at lowest safe altitude or 10,000 feet, whichever is higher. If structural integrity is in doubt, limit airspeed and avoid high maneuvering loads.

CABIN ALTITUDE OR RAPID DEPRESSURIZATION

Message: CABIN ALTITUDE

Oxygen masks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On, 100%

Crew communications . . . . . . . . . . . . . . . . . . . . . . . . Establish

0.5June 12, 2006



Condition: Airplane ditching and evacuation are required.

Note: Refer to Checklist Introduction for the Flight Crew Duties Summary for Emergency Landing/Ditching Evacuation.

Distress signal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transmit

Crew and passengers . . . . . . . . . . . . . . . . . . . . . . . . . . .Advise----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

When below 5,000 feet:

GROUND PROXIMITY/CONFIGURATIONGEAR OVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . OVRD

GROUND PROXIMITY TERRAINOVERRIDE switch (As installed) . . . . . . . . . . . . . . . . OVRD

PACK control selector (Both) . . . . . . . . . . . . . . . . . . . . . OFF[Ensures airplane is depressurized for opening passenger entry doors.]

CABIN ALTITUDE MODE selector . . . . . . . . . . . . . . . . MAN

CABIN ALTITUDE MANUAL control . . . . . . . . . . .DESCENDPosition outflow valve fully closed.[Prevents water from entering airplane through the valve.]

PASSENGER SIGN selectors . . . . . . . . . . . . . . . . . . . . . .ON

Do not accomplish the following checklists:PACK OFFCABIN AUTOMATIC INOPERATIVE


DITCHING PREPARATION

0.6 June 12, 2006




When on final approach (omit LANDING checklist):

Passenger cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

Advise cabin crew of imminent touchdown.

Maintain airspeed at VREF 30 to touchdown. Flare airplane to achieve minimum rate of descent at touchdown.

0.7June 12, 2006



Condition: Thrust or thrust lever response is lost from both engines.

If engine appears stalled or EGT approaches the Standby Engine Indicator (SEI) placard limit:

Repeat the above step as necessary.[Reduces EGT and improves airflow.]

Note: SEI maximum EGT limit is in–flight start EGT limit.

RAM AIR TURBINE switch . . . . . . . . . . . . . . . . . . . . . . UNLKD[Backs up automatic deployment of the RAT.]

Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ______ knots0120 through 0139:• Above 30,000 feet use 240 knots.• 30,000 feet or below use 260 knots minimum.

0171 through 0199, 1200 through 1201, 1401 through 1404:• Above 35,000 feet use 240 knots.• Above 20, 000 to 35,000 feet use 250 knots minimum.• 20,000 feet and below use 200 knots minimum.

1501 through 1506, 1521, 1601 through 1708:• Above 30,000 feet use 240 knots.• 30,000 feet or below use 220 knots minimum.

Note: OVSPD light and associated aural warning will indicate Vmo/Mmo exceedances.


DUAL ENGINE FAILURE

ENGINE START selectors (Both) . . . . . . . . . . . . . . . . . . . . FLT

Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Close

FUEL CONTROL switches (Both) . . . . . . .CUT OFF, then RUN

0.8 June 12, 2006




APU selector(If APU available) . . . . . . . . . . . . . . . . . . . . . . .START, then ON

Do not wait for successful engine start(s) prior to starting the APU.

If both engines remain failed:

Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE

FUEL CONTROL switches(Both) . . . . . . . . . . . . . . . . . . . . . . . . . . .CUT OFF, then RUN

Remain approximately 30 second in each position during start attempts.Repeat until engine start is achieved.Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.

Note: Cabin altitude warning may occur during descent.

After restarting one or both engines:

Plan to land at the nearest suitable airport.

FMC route. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Activate

FMC Performance data . . . . . . . . . . . . . . . . . . . . . . . . . Enter

If an IRS ALIGN light is illuminated:

IRS MODE selector(Affected IRS(s) only) . . . . . . . . . . . . . . . . . . . . . . . . . ATT

Heading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EnterEnter heading on IRS control panel or FMC POS INIT page.


If one engine remains failed:

Accomplish ENGINE FAILURE OR SHUTDOWN checklist.

0.9June 12, 2006



Condition: Engine has failed, engine has flamed out, or when prescribed by another non–normal procedure.

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . . OFF[Autothrottle use not recommended under engine inoperative conditions.]

Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE[Assists in recognition of affected engine.]

Engine conditions permitting, operate at idle for two minutes to allow engine to cool and stabilize.FUEL CONTROL switch. . . . . . . . . . . . . . . . . . . . . . . .CUT OFF


[Provides an additional source of electrical power.]Note: Monitor fuel balance.


TRANSPONDER mode selector . . . . . . . . . . . . . . . . . . . . . . TA[Prevents climb commands which can exceed single engine performance capability.]

WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Prevents asymmetrical wing anti-icing.]

Plan to land at the nearest suitable airport.Continued on next page

ENGINE FAILURE OR SHUTDOWN

0.10 June 12, 2006




If wing anti–ice required:

PACK control selector (Affected side). . . . . . . . . . . . . . OFF[Reduces bleed air demand.]

ISOLATION switch (Affected side) . . . . . . . . . . . . . . . . . .ON

WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / ON

When wing anti–ice no longer required:

WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

LEFT and RIGHT ISOLATION switches. . . . . . . . . . . OFFNote: Use flaps 20 and VREF 20 for landing and flaps 5 for

go–around.

Do not accomplish the following checklists:ENGINE SHUTDOWNPACK OFF

0.11June 16, 2008



Condition: Fire is detected in the affected engine, or airframe vibrations detected with abnormal engine indications, or the engine has separated.

FUEL CONTROL switch. . . . . . . . . . . . . . . . . . . . . . . .CUT OFF

Engine fire switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pull

If engine fire warning light remains illuminated:

Engine fire switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . RotateRotate to the stop and hold for 1 second.

If, after 30 seconds, engine fire warning light remains illuminated:

Engine fire switch . . . . . . . . . . Rotate to the other bottleRotate to the stop and hold for 1 second.

If high airframe vibration occurs and continues after engine shutdown:

Without delay, reduce airspeed and descend to a safe altitude which results in an acceptable vibration level. If high vibration returns and further airspeed reduction and descent is not practical, increasing the airspeed may reduce the vibration.


ENGINE FIRE OR SEVERE DAMAGE OR SEPARATION

Message: L ENGINE FIRE R ENGINE FIRE

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . .OFF[Autothrottle use not recommended under engine inoperative conditions.]

Thrust lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Close[Assists in recognition of affected engine.]

0.12 June 12, 2006








WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF


Plan to land at the nearest suitable airport.Consider an evacuation.








go–around.


0.13June 12, 2006




Do not accomplish the following checklists:ENGINE BOTTLEENGINE SHUTDOWNPACK OFF

0.14 June 12, 2006



Condition: An inflight engine fuel leak suspected or confirmed.

One or more of the following may be evidence of a fuel leak:• Visual observation of fuel spray from strut/engine• Excessive engine fuel flow• Total fuel quantity decreasing at an abnormal rate• FUEL CONFIG message on EICAS• LOW FUEL message on EICAS• FUEL DISAGREE–PROG 2 or FUEL QTY ERROR–PROG 2

message on the CDU scratchpad• INSUFFICIENT FUEL message on the CDU scratchpad

CENTER FUEL PUMP switches (Both) . . . . . . . . . . . . . . . . OFFFUEL CONFIG message is displayed with fuel in the center tank.

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . . . OFF

Identify an engine fuel leak by observing a left or right main tank fuel quantity decreasing faster than the other.An increase in fuel imbalance of approximately 1000 lbs or more in 30 minutes should be considered an engine fuel leak.Conditions permitting, visually check for engine fuel leak.


ENGINE FUEL LEAK

0.15June 12, 2006




If left and right main tank quantities decrease at the same rate:

Resume normal fuel management procedures.

If FUEL DISAGREE–PROG 2 or FUEL QTY ERROR–PROG 2 is displayed on the CDU scratchpad:

PROGRESS PAGE 2 . . . . . . . . . . . . . . . . . . . . . . . . Select

TOTALIZER or CALCULATED . . . . . . . . . . . . Select USESelect most accurate indication.Compare TOTALIZER and CALCULATED fuel values with flight plan for indication of fuel leak. If CALCULATED fuel remaining is greater than TOTALIZER fuel, a fuel leak upstream of the fuel flow transmitter may exist. TOTALIZER should be used to determine fuel remaining.A 3,000 pound difference between TOTALIZER and CALCULATED fuel causes the USE prompts to appear.


0.16 June 12, 2006




If engine fuel leak confirmed:

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . OFF[Autothrottle use not recommended under engine inoperative conditions.]

Thrust lever (Affected engine) . . . . . . . . . . . . . . . . . . Close

FUEL CONTROL switch (Affected engine) . . . . . .CUT OFF

APU selector(If APU available) . . . . . . . . . . . . . . . . . . . . .START, then ON

[Provides an additional source of electrical power.]

GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD

TRANSPONDER mode selector . . . . . . . . . . . . . . . . . . . . TA[Prevents climb commands which can exceed single engine performance capability.]

WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF




PACK control selector (Affected side) . . . . . . . . . . . OFF[Reduces bleed air demand.]

ISOLATION switch (Affected side) . . . . . . . . . . . . . . .ON

WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . AUTO / ON


WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

LEFT and RIGHT ISOLATION switches . . . . . . . . OFF


0.17June 12, 2006




If engine fuel leak confirmed: (continued)

If FUEL DISAGREE–PROG 2 or FUEL QTY ERROR–PROG 2 displayed on CDU scratchpad:


TOTALIZER . . . . . . . . . . . . . . . . . . . . . . . . . . . Select USEUse TOTALIZER to determine fuel remaining.

After engine shutdown, all remaining fuel can be used for the operating engine. Resume normal fuel management procedures.Note: Use flaps 20 and VREF 20 for landing and flaps 5

for go–around.


If LOW FUEL message is displayed:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . .ON[Ensures fuel is available to both engines if the low tank empties.]

FUEL PUMP switches (All) . . . . . . . . . . . . . . . . . . . . . . . .ON[Ensures all fuel is available for use.]


Avoid high nose up attitude and excessive acceleration and deceleration.

Do not accomplish the following checklist:LOW FUEL

0.18 June 12, 2006



IntentionallyBlank

0.19June 12, 2006



Condition: Engine start is needed after a shutdown with no fire or apparent damage.

Note: Do not attempt restart unless greater emergency exists.

Altitude and airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . CheckStarts not assured outside EICAS envelope.

If X–BLD is not shown:

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . . FLT

0121, 0124 through 0139, 1501 through 1506, 1521,1601 through 1708:

FUEL CONTROL switch . . . . . . . . . . . . . . . . . . . . . . .RUN

If EGT does not increase in 45 seconds or another abort start condition as listed in normal procedures occurs:

FUEL CONTROL switch . . . . . . . . . . . . . . . .CUT OFF

0171 through 0199, 1200 through 1201, 1401 through 1404:





ENGINE IN–FLIGHT START

0.20 June 16, 2008




If X–BLD is shown:

PACK control selector (Affected side). . . . . . . . . . . . . . OFF[Reduces pneumatic demand.]


IGNITION selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . BOTH

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . GND


FUEL CONTROL switch . . . . . . . . . . . . . . . . . . . . . . RUNSelect when N2 exceeds minimum rotation.


FUEL CONTROL switch. . . . . . . . . . . . . . . . .CUT OFF

ENGINE START selector . . . . . . . . . . . . . . . . . . AUTO







0.21June 16, 2008




If X–BLD is shown: (continued)

Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.

After engine started:


PACK control selectors (Both) . . . . . . . . . . . . . . . . . . AUTO

LEFT and RIGHT ISOLATION switches . . . . . . . . . . . . . OFF

GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

0.22 June 12, 2006



IntentionallyBlank

0.23June 12, 2006



Condition: Engine EGT or RPM are abnormal or are approaching or exceeding limits, abnormal engine noises are heard, or there is no response to thrust lever movement.

Note: If an engine compressor surge/stall occurs during ground operations, or takeoff is rejected due to an engine compressor surge/stall, a maintenance inspection is required prior to flight.

Note: Do not initiate an over-water crossing when a surge or stall has occurred.

Note: EGT may take up to two minutes to recover to normal range.

If indications abnormal or EGT continues to increase:


If indications stabilized and EGT stabilized or decreasing:

Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AdvanceAdvance slowly. Check that RPM and EGT follow thrust lever movement.[Attempts to restore normal control of engine operation.]


ENGINE LIMIT OR SURGE OR STALL

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . .OFF[Allows thrust lever to remain where manually positioned.]

Thrust lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RetardRetard until indications remain within normal limits or the thrust lever is closed.

0.24 June 16, 2008




If indications stabilized and EGT stabilized or decreasing: (continued)

If RPM and EGT follow thrust lever movement and some or all thrust is restored:

Operate engine normally or at a reduced thrust level which is surge and stall free.

If RPM does not follow thrust lever movement and EGT is normal:

[Engine is hung due to improper position of the bleed valve.]

ENGINE BLEED AIR switch . . . . . . . . . . . . . . . . . . . . OFF[Improves engine acceleration.]

If engine responds:

ENGINE BLEED AIR switch. . . . . . . . . . . . . . . . . . .ON


If engine does not respond:

Operate engine at idle.


If operating engine at idle or at a reduced thrust level which is surge and stall free:

Note: Monitor fuel balance.



Note: Use flaps 20 and VREF 20 for landing and flaps 5 for go-around.

0.25June 16, 2008



Condition: The oil temperature in the amber band or the oil temperature above the red line limit indicates engine oil temperature is high.

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . . OFF[Allows thrust lever to remain where manually positioned.]

Thrust lever (Affected engine) . . . . . . . . . . . . . . . . . . . . Decrease gradually

Retard thrust lever slowly until temperature decreases.


If temperature is in the amber band for 15 minutes or reaches red line limit:





ENGINE OIL TEMPERATURE

0.26 June 16, 2008



Condition: An engine tailpipe fire is reported on the ground with no engine fire warning.

Advise the cabin.If bleed air is available:

PACK control selectors (Both) . . . . . . . . . . . . . . . . . . . . OFF[Allows maximum bleed air for engine motoring.]

ISOLATION switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON[Ensures bleed air is available to either engine’s starter.]

If the affected ENGINE START selector is not in GND

Allow N2 to decrease to 30%.

ENGINE START selector (Affected engine) . . . . . . GND

Advise the tower.If the engine is being motored:

Continue to motor until the tailpipe fire is extinguished.

ENGINE START selector (Affected engine) . . . . . . . . AUTO

ENGINE TAILPIPE FIRE

FUEL CONTROL switch (Affected engine). . . . . . . . CUT OFF

0.27June 12, 2006



0171 through 0199, 1200 through 1201, 1501 through 1506, 1521, 1601 through 1708

Condition: Fuel jettison must be accomplished.

FUEL JETTISON selector . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

FUEL JETTISON NOZZLE switches (Both) . . . . . . . . . . . . .ONFuel jettison is from center tank only.Time required to empty full center tank is approximately 30 minutes.

When jettison is complete:

FUEL JETTISON NOZZLE switches (Both) . . . . . . . . . . OFF

FUEL JETTISON selector . . . . . . . . . . . . . . . . . . . . . . . . OFF----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Verify VREF speed for new gross weight.Do not accomplish the following checklist:

WINDOW (HEAT)

FUEL JETTISON

0.28 June 12, 2006



Condition: Landing gear lever cannot be positioned to UP.

LEVER LOCK OVERRIDE switch . . . . . . . . . . . Push and hold

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . UP, then OFF

GEAR LEVER WILL NOT MOVE UP

0.29June 12, 2006



Condition: Jammed or restricted flight controls is experienced in roll, pitch, or yaw.

Jammed or restricted system . . . . . . . . . . . . . . . . . OverpowerUse maximum force, including a combined effort of both pilots, if required.

Do not turn off any flight control hydraulic power switch.If freezing water is the suspected cause:

Consider descent to warmer air if conditions permit and reattempt to override the jammed or restricted controls.

If the faulty system cannot be overpowered:

Use operative flight controls, trim, and thrust as required for airplane control.

Plan to land at the nearest suitable airport

JAMMED OR RESTRICTED FLIGHT CONTROLS

0.30 June 12, 2006



Condition: The flight deck door LOCK FAIL light illuminated indicates the flight deck door lock has failed.

If the flight deck door lock has failed:

Mechanical latch pin . . . . . . . . . . . . . . . . . . . . . . . . . . Insert

Note: A second crewmember is required to secure the flight deck door when a crewmember leaves the flight deck. Reference the FOM for flight deck entry/exit procedures.

LOCK FAIL

0.31June 12, 2006



Condition: Fuel temperature is approaching minimum.

When fuel temperature is approaching fuel temperature limit (3°C above the fuel freeze point):

Increase speed, change altitude, and or deviate to a warmer air mass to achieve a TAT equal to or higher than the fuel temperature limit.

TAT will increase approximately 0.5 to 0.7 °C for each.01 Mach increase in speed. In extreme conditions it may be necessary to descend as low as FL250.

LOW FUEL TEMPERATURE

0.32 June 12, 2006



Condition: A radio is continuously transmitting without crew input.

Microphone selector switches (All audio control panels) . . . . . . . . . . . . . . .Flight Interphone

[Deselects radios and stops radio transmissions.]

The microphone/interphone with the stuck switch continuously transmits on flight interphone.The associated audio control panel should remain on flight interphone. All other audio control panels may be used normally.

RADIO TRANSMIT CONTINUOUS (STUCK MICROPHONE SWITCH)

0.33June 12, 2006



Condition: REV annunciation displayed and reverse thrust not intentionally selected.

Reverse thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DownVerify reverse thrust lever is in the full down position.

With no yaw, loss of airspeed, or buffet:

Operate engine normally.

With yaw, loss of airspeed, or buffet:

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Retract[Prevents slat damage from turbulence created by the open cowl.]


Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Close





TRANSPONDER mode selector . . . . . . . . . . . . . . . . . . . . TA [Prevents climb commands which can exceed single engine performance capability.]

WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Prevents asymmetrical wing anti–icing.]



REVERSER UNLOCKED

0.34 June 12, 2006




With yaw, loss of airspeed, or buffet: (continued)




WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . AUTO / ON


WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


Use trailing edge flaps 20 and VREF 30 + 30 for landing.


0.35June 12, 2006




With yaw, loss of airspeed, or buffet: (continued)------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Use ALTERNATE FLAP OPERATION to extend trailing edge flaps.

Do not extend leading edge slats.

ENGINE START selectors (Both) . . . . . . . . . . . . . . . . CONT[Provides ignition for landing with leading edge slats retracted.]

ALTERNATE FLAP OPERATION:

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . SETPosition to agree with FLAP lever.

TRAILING EDGE (TE) ALTERNATEFLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . SETExtend or retract trailing edge flaps as required.

Note: Flap indicator may not move until flaps 5 or greater is selected.

0.36 June 12, 2006



IntentionallyBlank

0.37June 12, 2006



Condition: Smoke, fire, or fumes are identified

Diversion may be needed.Oxygen masks (As required) . . . . . . . . . . . . . . . . . . On, 100%

Crew communications . . . . . . . . . . . . . . . . . . . . . . . Establish

Advise the cabin crew to turn off main IFE and PC power switches (As installed).Advise cabin crew that main cabin lighting will be turned off.UTILITY BUS switches (Both) . . . . . . . . . . . . . . . . . . . . . . . OFF

APU BLEED AIR switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Any time the smoke or fumes become the greatest threat, do the SMOKE OR FUMES REMOVAL checklist. If the source of the smoke, fire, or fumes is both obvious and can be extinguished quickly:

Source . . . . . . . . . . . . . . . . . . . . . . . Isolate and extinguish

If possible, remove power from the affected equipment by switch or circuit breaker in the flight deck or cabin.

If both of the following are true:• The source is visually confirmed to be

extinguished, and• The smoke or fumes are decreasingContinue the flight at the Captain’s discretion.Restore unpowered items at the Captain’s discretion.Do the SMOKE OR FUMES REMOVAL checklist if needed.


SMOKE OR FIRE OR FUMES

0.38 June 17, 2008




EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . .STBY[Selects standby fan operating mode to remove normal fan operations as a possible source of fumes.]

Initiate a diversion to the nearest suitable airport while continuing the checklist.Consider an immediate landing if the smoke, fire, or fumes situation becomes uncontrollable.Do not delay landing in an attempt to complete all of the following steps.LEFT AND RIGHT ISOLATION switches. . . . . . . . . . . . . . . OFF

[Isolates left and right sides of the bleed air system.]

RIGHT PACK CONTROL selector . . . . . . . . . . . . . . . . . . . . OFF[Removes right side of the air conditioning system as a possible source of smoke or fumes.]

Wait 2 minutes unless the smoke or fumes are increasing.[Allows time for the smoke or fumes to clear.]

If smoke or fumes continue or are increasing:

RIGHT PACK CONTROL selector . . . . . . . . . . . . . . . . AUTO[Restores right side of the air conditioning system]

LEFT PACK CONTROL selector . . . . . . . . . . . . . . . . . . . OFF[Removes left side of the air conditioning system as a possible source of smoke or fumes]

Wait 2 minutes unless the smoke or fumes are increasing.

[Allows time for the smoke or fumes to clear.]


LEFT PACK CONTROL selector . . . . . . . . . . . . . . AUTO[Restores left side of the air conditioning system.]

Consider an immediate landing.


0.39June 17, 2008




Do the SMOKE OR FUMES REMOVAL checklist if needed.Do not accomplish the following checklists:

UTILITY BUS OFFPACK OFFRECIRCULATION FAN

0.40 June 17, 2008



Condition: Smoke or fumes removal is needed

Do this checklist only when directed by the SMOKE OR FIRE OR FUMES checklist.Do not delay landing in an attempt to complete the following steps.

WARNING:Do not turn an operating pack OFF. Selecting packs OFF will result in increased smoke concentrations. Do not activate passenger oxygen system.

Flight deck door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Close[Prevents smoke or fumes from penetrating onto flight deck.]

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . OVRD

LANDING ALTITUDE selector . . . . . . . . . . . . . . . . . . 9,500 feet

CABIN ALTITUDE AUTO RATE control . . . . . . . . . . . . . . MAX[Increases the ventilation rate.]

If smoke or fumes is persistent:

Descend to 9,500 feet or below as soon as conditions permit.

At 9,500 feet:

CABIN ALTITUDE MODE selector . . . . . . . . . . . . . . MAN

CABIN ALTITUDE MANUAL control . . . . . . . . . . .CLIMBPosition outflow valve fully open[Depressurizes the airplane and provides maximum ventilation rate.]

Do not accomplish the following checklist:CABIN AUTOMATIC INOPERATIVE

When smoke has dissipated:

EQUIPMENT COOLING selector . . . . . . . . . . . . . . .STBY


SMOKE OR FUMES REMOVAL

0.41June 17, 2008




Return to the SMOKE OR FIRE OR FUMES checklist and complete the remaining steps.

0.42 June 17, 2008



Condition: Tailskid/fuselage contact with runway on takeoff.

CAUTION: Do not pressurize the airplane due to possible structural damage

CABIN ALTITUDE MODE selector . . . . . . . . . . . . . . . . . . . MAN

CABIN ALTITUDE MANUAL control . . . . . . . . . . . . . . . .CLIMBPosition outflow valve fully open to depressurize airplane.

Level off at lowest safe altitude.Plan to land at the nearest suitable airportIf climb above 11,000 feet is required:

PACK control selectors (Both) . . . . . . . . . . . . . . . . . . . . OFF[Ensures cabin will remain depressurized when the outflow valve closes automatically at 11,000 feet.]


TAIL STRIKE

0.43June 16, 2008



Condition: Static discharge around the windshield, bright glow in the engine inlets, smoke or dust on the flight deck, or acrid odor indicates the airplane is in volcanic ash.

CAUTION: Exit volcanic ash as quickly as possible. Consider a 180 degree turn.

Oxygen masks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On, 100%

Crew Communications . . . . . . . . . . . . . . . . . . . . . . . Establish

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . . OFF[Allows thrust levers to remain where manually positioned.]

Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CloseConditions permitting, operate engines at idle.[Reduces possible engine damage and/or flameout by decreasing EGT.]


RECIRCULATION FANswitches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Increases bleed air extraction to improve engine stall margin by putting packs into high flow.]

ENGINE ANTI–ICEselectors / switches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . .ON

[Increases bleed air extraction to improve engine stall margin.]

WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON



[Provides an electrical power source in the event one or both engines flame out.]


VOLCANIC ASH

0.44 June 16, 2008



Continued from previous pageNote: Volcanic ash can cause non–normal system reactions

such as:• engine malfunctions, increasing EGT, engine stall or

flameout• decrease or loss of airspeed indications• equipment overheat or smoke indications• cargo fire indications.

Note: Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.

If engines flamed out or stalled, or EGT rapidly approaching or exceeding limit:

Accomplish the DUAL ENGINE FAILURE checklist.

Plan to land at the nearest suitable airport.Do not accomplish the following checklist:

RECIRCULATION FAN

0.45June 16, 2008



Condition: Arcing, delamination, shattered, or cracked condition of any flight deck window is observed.

If window arcing, shattered, or cracked:

WINDOW HEAT switch (Affected window) . . . . . . . . . . OFF[Removes electrical power to prevent arcing.]

If the damaged window deforms, or an air leak is observed:


If airplane altitude above 10,000 feet:

Descend to lowest safe altitude or 10,000 feet, whichever is higher.

[Minimizes forces on the window. Outward cabin pressure counters inward air load on the window.]

Sustained flight below 10,000 feet is not recommended due to greater risk of bird strike.

Do not accomplish the following checklist:WINDOW (HEAT)

WINDOW DAMAGE

0.46 June 16, 2008



Condition: A side window opens during takeoff or in flight.

Maintain the maneuvering speed for existing flap setting until the window is closed.

[Minimizes noise.]

The force required to close the window increases with airspeed. It may not be possible to close the window at speeds above 250 knots.Close and lock the window.

Note: It may be necessary to completely open the window prior to closing in order to reset the locking mechanism.

If the window does not lock or pressurization is not normal:

Level off at the lowest safe altitude.The airplane can fly unpressurized and land safely with the window open.

If the window locks and pressurization is normal:

Continue normal operation.

WINDOW OPEN

0.47June 16, 2008



IntentionallyBlank

0.48 June 16, 2008


Non-Normal Checklists Chapter NNCAirplane General, Emergency Equipment, Doors, Windows


Table of ContentsNNC.1 Non-Normal Checklists-Airplane General, Emergency Equipment, Doors, WindowsACCESS DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1

AUTOMATIC UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2CARGO DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3CARGO DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.4DITCHING PREPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.6EMERGENCY DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.9ENTRY DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10LOCK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.11PASSENGER OXYGEN ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.12WINDOW DAMAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.13WINDOW (HEAT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14WINDOW OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.15WING SLIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.16

TOC.1.1June 16, 2008


Non-Normal Checklists -Airplane General, Emergency Equipment, Doors, Windows


IntentionallyBlank

TOC.1.2 June 16, 2008



Condition: The ACCESS DOORS light illuminated indicates the forward equipment bay or the electrical equipment compartment door is not closed and latched and locked.

Note: The door is in a safe configuration as long as cabin pressurization is normal.

[Positive cabin differential pressure ensures door remains in place.]

If pressurization not normal:


LANDING ALTITUDE selector . . . . . . . . . . . . . . . . 9,500 feet

If occurrence is on takeoff or initial climb:

Do not exceed 10,000 feet.

If occurrence is in climb, cruise, or descent:


ACCESS DOOR(S)Message: ACCESS DOORS

E/E ACCESS DOOR FWD ACCESS DOOR

1.1June 12, 2006



Condition: The flight deck door AUTO UNLK light illuminated indicates the correct emergency access code has been entered and the flight deck door is programmed to automatically unlock after a time delay.

FLIGHT DECK DOOR LOCK selector . . . . . . . . . . . . . . . DENYRotate and hold for 1 second.[Prohibits unauthorized access to the flight deck.]

AUTOMATIC UNLOCK

1.2 June 12, 2006



0121, 0124 through 0139, 1401 through 1404

Condition: The CARGO DOORS light illuminated indicates the forward, aft or bulk cargo door is not closed and latched and locked.










CARGO DOOR(S)

Message: CARGO DOORSAFT CARGO DOOR

BULK CARGO DOORFWD CARGO DOOR

1.3June 16, 2008




Condition: The CARGO DOORS light illuminated indicates the forward, aft or bulk cargo door is not closed and latched and locked.

Note: The aft and bulk doors are in a safe configuration as long as cabin pressurization is normal.


If pressurization not normal or FWD CARGO DOOR message displayed:







CARGO DOOR(S)

Message: CARGO DOORSAFT CARGO DOOR

BULK CARGO DOORFWD CARGO DOOR

1.4 June 12, 2006



IntentionallyBlank

1.5June 12, 2006



Condition: Airplane ditching and evacuation are required.

Note: Refer to Checklist Introduction for the Flight Crew Duties Summary for Emergency Landing/Ditching Evacuation.

Distress signal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transmit

Crew and passengers . . . . . . . . . . . . . . . . . . . . . . . . . . .Advise----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

When below 5,000 feet:


GROUND PROXIMITY TERRAINOVERRIDE switch (As installed) . . . . . . . . . . . . . . . . OVRD

PACK control selectors (Both) . . . . . . . . . . . . . . . . . . . . OFF[Ensures airplane is depressurized for opening passenger entry doors.]

CABIN ALTITUDE MODE selector . . . . . . . . . . . . . . . . MAN

CABIN ALTITUDE MANUAL control . . . . . . . . . . .DESCENDPosition outflow valve fully closed.[Prevents water from entering airplane through the valve.]


Do not accomplish the following checklists:PACK OFFCABIN AUTOMATIC INOPERATIVE


DITCHING PREPARATION

1.6 June 12, 2006




When on final approach (omit LANDING checklist):

Passenger cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure


Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

Advise cabin crew of imminent touchdown.

Maintain airspeed at VREF 30 to touchdown. Flare airplane to achieve minimum rate of descent at touchdown.

1.7June 12, 2006



Condition: The EMER DOORS light illuminated indicates that one or more emergency overwing exit doors are not closed and latched and locked.










If a wing slide deployment is suspected:

Accomplish WING SLIDE checklist.

EMERGENCY DOOR(S)Message: EMER DOORS

L EMER DOORL AFT EMER DOORL FWD EMER DOOR

R EMER DOORR AFT EMER DOORR FWD EMER DOOR

1.8 June 17, 2008



Condition: The emergency lights switch is not in the ARMED position.

EMERGENCY LIGHTSMessage: EMER LIGHTS

1.9June 12, 2006



Condition: The ENTRY DOORS light illuminated indicates one or more entry door is not closed and latched and locked.










ENTRY DOOR(S)Message: L ENTRY DOORS

L AFT ENTRY DOORL CTR ENT DOORL FWD ENT DOOR

R ENTRY DOORSR AFT ENTRY DOORR CTR ENT DOORR FWD ENT DOOR

1.10 June 12, 2006



Condition: The flight deck door LOCK FAIL light illuminated indicates the flight deck door lock has failed.

If the flight deck door lock has failed:

Mechanical latch pin . . . . . . . . . . . . . . . . . . . . . . . . . . Insert

Note: A second crewmember is required to secure the flight deck door when a crewmember leaves the flight deck. Reference the FOM for flight deck entry/exit procedures.

LOCK FAIL

1.11June 12, 2006



Condition: The passenger oxygen ON light illuminated indicates the passenger oxygen system is activated.

PASSENGER OXYGEN ONMessage: PASS OXYGEN ON

1.12 June 12, 2006



Condition: Arcing, delamination, shattered, or cracked condition of any flight deck window is observed.

If window arcing, shattered, or cracked:

WINDOW HEAT switch (Affected window) . . . . . . . . . . OFF[Removes electrical power to prevent arcing.]

If the damaged window deforms, or an air leak is observed:




[Minimizes forces on the window. Outward cabin pressure counters inward air load on the window.]

Sustained flight below 10,000 feet is not recommended due to greater risk of bird strike.

Do not accomplish the following checklist:WINDOW (HEAT)

WINDOW DAMAGE

1.13June 12, 2006



Condition: A window heat INOP light illuminated indicates the affected window is not being heated.

WINDOW HEAT switch. . . . . . . . . . OFF 10 Seconds, then ON[Allows cooling period and resets controller.]

If INOP light remains illuminated:

WINDOW HEAT switch . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

WINDOW (HEAT)Message: L FWD WINDOW

L SIDE WINDOWWINDOW HEAT

R FWD WINDOWR SIDE WINDOW

1.14 June 12, 2006



Condition: A side window opens during takeoff or in flight.

Maintain the maneuvering speed for existing flap setting until the window is closed.

[Minimizes noise.]

The force required to close the window increases with airspeed. It may not be possible to close the window at speeds above 250 knots.Close and lock the window.

Note: It may be necessary to completely open the window prior to closing in order to reset the locking mechanism.

If the window does not lock or pressurization is not normal:

Level off at the lowest safe altitude.The airplane can fly unpressurized and land safely with the window open.

If the window locks and pressurization is normal:


WINDOW OPEN

1.15June 16, 2008



Condition: The EMER DOORS light illuminated indicates that a wing slide door is not closed and latched and locked.

If visual or aural observation confirms the overwing ramp slide deployed and remains attached to the airplane:

Minor damage to the trailing edge flap, aft fuselage, and empennage may occur.

Airspeed (As required) . . . . . . . . . . . . . . . . . . . . . . . ReduceIf necessary operate at a reduced airspeed to minimize slide oscillations and subsequent airplane damage.

GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRDNote: Conditions permitting, use flaps 20 and VREF 20

for landing.[May reduce slide oscillations and preclude slide separation on final approach.

WING SLIDE

Message: EMER DOORSL WING SLIDE R WING SLIDE

1.16 June 17, 2008


Non-Normal Checklists Chapter NNCAir Systems Section 2


Table of ContentsNNC.2 Non-Normal Checklists-Air SystemsAPU BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1

BLEED DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2BLEED DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3BLEED ISOLATION VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4BODY DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5CABIN ALTITUDE OR RAPID DEPRESSURIZATION . . . . . 2.6CABIN AUTOMATIC INOPERATIVE . . . . . . . . . . . . . . . . . . . . . 2.7CABIN TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8CARGO OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9ENGINE BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10ENGINE BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.11ENGINE BLEED OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.12ENGINE BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.13ENGINE HIGH STAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.14ENGINE HPSOV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.15ENGINE PRV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.16EQUIPMENT COOLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.17EQUIPMENT OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.18EQUIPMENT SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.19EQUIPMENT VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20FLIGHT DECK TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . 2.21PACK OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.22PACK TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.24RECIRCULATION FAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25STRUT DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25TRIM AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.26

TOC.2.1June 16, 2008


Non-Normal Checklists -Air Systems


IntentionallyBlank

TOC.2.2 June 16, 2008



Condition: The APU bleed air VALVE light illuminated indicates the valve position disagrees with the commanded position.

APU BLEED VALVEMessage: APU BLEED VAL

2.1June 12, 2006



0121, 0124 through 0139

Condition: A DUCT LEAK light illuminated indicates a high temperature bleed air leak is detected.

ENGINE BLEED AIR switch (Affected side) . . . . . . . . . . . . OFF

ISOLATION switch (Affected side) . . . . . . . . . . . . . . . . . . . OFF

If DUCT LEAK light remains illuminated:

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . OFF[Allows thrust lever to remain where manually positioned.]

Thrust lever (Affected side) . . . . . . . . . . . . . . . . . . . . RetardRetard slowly until light extinguishes. Thrust may be restored if light remains illuminated at idle.

WING ANTI–ICE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents possible asymmetrical ice buildup on the wings.]

Avoid icing conditions

CAUTION: Flight beyond six hours with a DUCT LEAK light illuminated may result in structural damage.

Do not accomplish the following checklists:ENGINE BLEED OFFPACK OFF

BLEED DUCT LEAK

Message: L BLD DUCT LEAK R BLD DUCT LEAK

2.2 June 16, 2008



0171 through 0199, 1200 through 1201, 1401 through 1404, 1501 through 1506, 1521, 1601 through 1708



ISOLATION switch (Affected side) . . . . . . . . . . . . . . . . . . . OFF

WING ANTI–ICE selector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

[Prevents possible asymmetrical ice buildup on the wings.]


CAUTION: Flight beyond six hours with a DUCT LEAK light illuminated may result in structural damage.


BLEED DUCT LEAK

Message: L BLD DUCT LEAK R BLD DUCT LEAK

2.3June 12, 2006



Condition: The bleed isolation VALVE light illuminated indicates the valve position disagrees with the commanded position.

BLEED ISOLATION VALVEMessage: C BLD ISLN VAL

R BLD ISLN VALL BLD ISLN VAL

2.4 June 12, 2006




CENTER ISOLATION switch . . . . . . . . . . . . . . . . . . . . . . . . OFF

APU BLEED AIR switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFNote: ADP is inoperative.

If DUCT LEAK light remains illuminated or duct pressure on either side is below 10 psi:

ENGINE BLEED AIR switch (Either) . . . . . . . . . . . . . . . OFF




CAUTION: Flight beyond six hours may result in structural damage.


BODY DUCT LEAKMessage: BODY DUCT LEAK

2.5June 12, 2006



Condition: The CABIN ALT or CABIN ALTITUDE light illuminated indicates cabin altitude is excessive.

Cabin altitude and rate . . . . . . . . . . . . . . . . . . . . . . . . . . Check[Confirms pressurization problem.]

If cabin altitude uncontrollable:

PASSENGER OXYGEN switch . . . . . . . . . . . . . . . . . . . . .ON

Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AccomplishWithout delay, close thrust levers, extend speedbrakes, and descend at Vmo/Mmo. Level off at lowest safe altitude or 10,000 feet, whichever is higher. If structural integrity is in doubt, limit airspeed and avoid high maneuvering loads.

CABIN ALTITUDE OR RAPID DEPRESSURIZATION

Message: CABIN ALTITUDE

Oxygen masks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On, 100%

Crew communications . . . . . . . . . . . . . . . . . . . . . . . . Establish

2.6 June 12, 2006



Condition: The cabin AUTO INOP light illuminated indicates automatic pressurization control has failed or the CABIN ALTITUDE MODE selector is in manual.

CABIN ALTITUDE MODE selector . . . . . . . . . . . . . . . . . . . MAN

CABIN ALTITUDE MANUAL control . . . . . CLIMB / DESCENDPosition as required to control desired cabin rate and altitude.

Note: Recommended cabin rate is approximately 500 fpm for climbs and descents.

Note: Recommended cabin altitude in cruise is:FLIGHT LEVEL CABIN ALTITUDEUp to 230 . . . . . . . Landing Field Elevation

260 . . . . . . . . . . . . . . . . . . . . . . . .2,000300 . . . . . . . . . . . . . . . . . . . . . . . .4,000350 . . . . . . . . . . . . . . . . . . . . . . . .6,000400 and above . . . . . . . . . . . . . .8,000

----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

When at pattern altitude:

CABIN ALTITUDE MANUAL control . . . . . . . . . . . . . .CLIMBPosition to CLIMB until outflow valve fully open.

CABIN AUTOMATIC INOPERATIVEMessage: CABIN AUTO INOP

2.7June 12, 2006



Condition: A cabin temperature INOP light illuminated indicates a fault in the zone temperature controller, the compartment temperature control is in the OFF position, or a trim air switch is OFF.

Affected COMPARTMENTTEMPERATURE control . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Allows temperature to be controlled by the coolest compartment.]

If affected compartment temperature continues too warm or too cold:

TRIM AIR switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Shuts off trim air and schedules operating pack(s) to provide a preselected mean temperature.]

Do not accomplish the following checklist:TRIM AIR

CABIN TEMPERATUREMessage: AFT CABIN TEMP

MID CABIN TEMPFWD CABIN TEMP

2.8 June 12, 2006



Condition: A cargo heat OVHT light illuminated indicates a cargo compartment temperature above the standard control range.

If cargo heat not required:

CARGO HEAT switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

CARGO OVERHEATMessage: AFT CARGO OVHT

FWD CARGO OVHTBULK CARGO OVHT

2.9June 12, 2006



0121, 0124 through 0139, 1401 through 1404, 1501 through 1506, 1521

Condition: The engine bleed air OFF light illuminated indicates the engine bleed air valve is closed for a system fault.


PACK control selector (Affected side) . . . . . . . . . . . . . OFF[Reduces bleed air demand.]



ISOLATION switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ENGINE BLEED OFF

Message: L ENG BLEED OFF R ENG BLEED OFF

2.10 June 16, 2008



0171 through 0199, 1200 through 1201, 1601 through 1708


WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents asymmetrical wing anti–icing.]




WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . AUTO


WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . OFF

LEFT and RIGHT ISOLATION switches. . . . . . . . . . . OFF

1601 through 1708:

Thrust reverser on the affected side may be inoperative.

ENGINE BLEED OFF


2.11June 12, 2006



0171 through 0199, 1200 through 1201, 1401 through 1404,1501 through 1506, 1521, 1601 through 1708

Condition: The engine bleed air OVHT light illuminated indicates engine bleed air temperature is excessive.

ENGINE BLEED AIRswitch (Affected side) . . . . . . . . . . . . . . . . . . . . . OFF, then ON

Select to ON after thrust is reduced for cruise.

If OVHT light remains illuminated or re–illuminates:

ENGINE BLEED AIRswitch (Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF






WING ANTI–ICEselector / switch. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


1501 through 1506, 1521, 1601 through 1708:

Thrust reverser on the affected side is inoperative.

Do not accomplish the following checklist:ENGINE BLEED OFF

ENGINE BLEED OVERHEAT

Message: L ENG BLD OVHT R ENG BLD OVHT

2.12 June 12, 2006



0121, 0124 through 0139

Condition: The engine BLEED light illuminated indicates the engine high pressure bleed valve is open when commanded closed.








ENGINE BLEED VALVE

Message: L ENG BLEED VAL R ENG BLEED VAL

2.13June 16, 2008



0121, 0124 through 0139

Condition: The engine HI STAGE light illuminated indicates engine bleed air temperature is excessive.



If HI STAGE light remains illuminated or re-illuminates:








ENGINE HIGH STAGE

Message: L ENG HI STAGE R ENG HI STAGE

2.14 June 16, 2008




Condition: The engine BLEED light illuminated indicates the high pressure bleed air valve is open when commanded closed.


WING ANTI–ICE selector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF





WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / ON


WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF



ENGINE HPSOV

Message: L ENG HPSOV R ENG HPSOV

2.15June 12, 2006




Condition: The engine BLEED light illuminated indicates the pressure regulating valve is open when commanded closed.


WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF







WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

LEFT and RIGHT ISOLATION switches . . . . . . . . . . OFF


ENGINE PRV

Message: L ENG PRV R ENG PRV

2.16 June 12, 2006



Condition: The equipment cooling NO COOLING light illuminated indicates OVRD selected and no reverse air flow through the E/E compartment avionics.

Avionics and electronic equipment and displays, not powered by standby buses, are subject to imminent failure.Avionics and electrical equipment on standby buses are reliable for 90 minutes. Continued flight beyond 90 minutes can result in loss of essential avionics and electrical equipment.

EQUIPMENT COOLINGMessage: FWD EQPT COOLING

2.17June 12, 2006



Condition: The equipment cooling OVHT light illuminated indicates high temperature or low airflow in the equipment cooling system.

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . .STBY

If the OVHT light re–illuminates after a five minute delay:

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . OVRD

EQUIPMENT OVERHEATMessage: FWD EQPT OVHT

2.18 June 12, 2006



Condition: The equipment cooling SMOKE light illuminated indicates smoke is detected in the forward equipment cooling ducts.

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . OVRDThe SMOKE light will extinguish when smoke clears.

If NO COOLING light illuminates after a one minute delay:

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . .STBY

EQUIPMENT SMOKEMessage: FWD EQPT SMOKE

2.19June 12, 2006



Condition: The equipment cooling VALVE light illuminated indicates an equipment cooling valve is not in the commanded position.

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . .STBYIf the VALVE light remains illuminated after 30 seconds, pressurization cannot be ensured.

EQUIPMENT VALVEMessage: FWD EQPT VAL

2.20 June 12, 2006



Condition: The flight deck temperature INOP light illuminated indicates a fault in the flight deck zone temperature controller, or the trim air switch is OFF.

FLIGHT DECK TEMPERATURE control . . . . . . . . . . . . . . MANPosition trim air valve as required

If compartment temperature continues too warm or too cold:

TRIM AIR switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Shuts off trim air and schedules operating pack(s) to provide a preselected mean temperature.]

Do not accomplish the following checklist:TRIM AIR

FLIGHT DECK TEMPERATUREMessage: FLT DECK TEMP

2.21June 12, 2006



Condition: The PACK OFF light illuminated indicates the associated pack valve is closed.

If a single PACK OFF light illuminated:


If both PACK OFF lights illuminated:

Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AccomplishLevel off at lowest safe altitude or 10,000 feet, whichever is higher. If flight conditions require, accomplish descent with speedbrakes extended at Vmo/Mmo to prevent excessive cabin altitude.

Consider an alternate engine bleed air source, or if below 17,000 feet the APU bleed air source, if dual PACK OFF condition is a result of engine bleed air loss not caused by a duct leak or engine start valve failure.


PACK OFFMessage: L PACK OFF R PACK OFF

2.22 June 12, 2006




If both PACK OFF lights illuminated: (continued)

If both PACK OFF lights remain illuminated and level at or below 10,000 feet:

Airspeed . . . . . . . . . . . . . . . . . . . . . 290 knots maximum[Minimizes cabin heating due to skin heat friction.]


CABIN ALTITUDE MANUAL control . . . . . . . . . . .CLIMBPosition outflow valve full open for ventilation.

SHOULDER AND FOOT HEATERSswitches (All) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Flight deck lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . .SetMinimize flight deck lighting intensity to reduce heat.

Flight deck door . . . . . . . . . . . . . . . . . . . . . . As required[If necessary, open to improve flight deck ventilation.]

Flight deck sun visors . . . . . . . . . . . . . . . . . . . . . . Install[Reduces flight deck heating during daylight operations.]

Instruct Flight Attendants to:• select all galley equipment OFF• select in-flight entertainment main power OFF• select main cabin door heaters OFF• reduce cabin lighting to minimum required• close cabin window shades during daylight

operations.

Plan to land at nearest the suitable airport.


2.23June 16, 2008



Condition: The pack INOP light illuminated indicates an automatic control system fault or an overheat.

PACK control selector . . . . . . . . . . . . . . . . . . . . . . . . . STBY–N

If the INOP light remains illuminated:

Wait 5 minutes.[Allows time for any overheat condition to cool.]

PACK RESET switch . . . . . . . . . . . . . . . . . . . . . . . . . . . Push

If the compartment temperature becomes unacceptably warm or cool with STBY–N selected:

PACK control selector . . . . . . . . . . . . . STBY–C / STBY–W

If the INOP light will not extinguish or re–illuminates:

PACK control selector . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Do not accomplish the following checklist:PACK OFF

PACK TEMPERATUREMessage: L PACK TEMP R PACK TEMP

2.24 June 12, 2006



Condition: The recirculation fan INOP light illuminated indicates the fan is failed or not operating.




WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF


Avoid icing conditions1501 through 1506, 1521, 1601 through 1708Thrust reverser on the affected side is inoperative.Do not accomplish the following checklist:

ENGINE BLEED OFF

RECIRCULATION FANMessage: L RECIR FAN R RECIR FAN

STRUT DUCT LEAK

Message: L STRUT DCT LEAK R STRUT DCT LEAK

2.25June 16, 2008



Condition: The trim air OFF light illuminated indicates the trim air switch is OFF.

TRIM AIRMessage: TRIM AIR

2.26 June 16, 2008


Non-Normal Checklists Chapter NNCAnti-Ice, Rain Section 3


Table of ContentsNNC.3 Non-Normal Checklists-Anti-Ice, RainAOA PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1

AUXILIARY PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1CAPTAIN PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2ENGINE ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3ENGINE ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4FIRST/OFFICER PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6ICE DETECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DETECTOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DETECTOR ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICING ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8ICING WING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8PROBE HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.9WINDOW (HEAT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.10WING ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.11WING ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.12

TOC.3.1June 12, 2006


Non-Normal Checklists -Anti-Ice, Rain


IntentionallyBlank

TOC.3.2 June 12, 2006



Condition: An AOA probe heat light illuminated indicates the affected probe heat is inoperative.

Flight in icing conditions may result in some erroneous flight instrument indications.Note: Flight may not be permitted in RVSM airspace.


Condition: An AUX PITOT probe heat light illuminated indicates the affected pitot probe heat is inoperative.



AOA PROBEMessage: L AOA PROBE R AOA PROBE

AUXILIARY PITOTMessage: L AUX PITOT R AUX PITOT

3.1June 12, 2006



Condition: The CAPT PITOT probe heat light illuminated indicates the captain pitot probe heat is inoperative.

Flight in icing conditions may result in some erroneous flight instrument indications. Note: Flight may not be permitted in RVSM airspace.


CAPTAIN PITOTMessage: CAPT PITOT

3.2 June 12, 2006




Condition: The engine anti–ice VALVE light illuminated indicates the engine anti–ice valve disagrees with the commanded position.

If ENGINE ANTI-ICE switch ON:

ENGINE BLEED AIR switch (Affected side) . . . . . . . . . OFF

ENGINE ANTI–ICE switch(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . OFF, then ON

If VALVE light remains illuminated:

Avoid icing conditions.

Leave the ENGINE ANTI-ICE switch ON.[On position provides continuous ignition.]

ENGINE BLEED AIR switch (Affected side) . . . . . . . . . .ON

If ENGINE ANTI-ICE switch OFF:

ENGINE ANTI–ICE switch (Affected engine) . . . . . . . . . .ON[Automatically reduces the thrust limit.]

If total air temperature (TAT) is above 10 degrees C:

Avoid high thrust settings.[Prevents engine inlet damage due to overheat.]

ENGINE ANTI–ICE

Message: L ENG ANTI-ICE R ENG ANTI-ICE

3.3June 16, 2008





If ENGINE ANTI-ICE selector ON:


ENGINE ANTI–ICE selector(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . OFF, then ON



Leave the ENGINE ANTI-ICE selector ON.[On position provides continuous ignition.]


If ENGINE ANTI-ICE selector OFF:

ENGINE ANTI–ICE selector (Affected engine) . . . . . . . .ON[Automatically reduces the thrust limit.]




ENGINE ANTI–ICE


3.4 June 12, 2006




If ENGINE ANTI-ICE selector AUTO:


If VALVE light is extinguished and total air temperature (TAT) is above 10 degrees C:



ENGINE BLEED AIR switch (Affected side) . . . . . . . OFF

ENGINE ANTI–ICE selector(Affected side) . . . . . . . . . . . . . . . . . . . . . . OFF, then ON

If VALVE light re-illuminates:




3.5June 12, 2006



Condition: The FO PITOT probe heat light illuminated indicates the first officer pitot probe heat is inoperative.



FIRST/OFFICER PITOTMessage: F/O PITOT

3.6 June 12, 2006




Condition: The ICE DET light illuminated indicates the ice detection system has failed.

Operate the engine and wing anti–ice system manually.

0121, 0124 through 0139, 1401 through 1404

Condition: Icing is no longer detected.

0121, 0124 through 0139, 1401 through 1404

Condition: The ICING light illuminated indicates icing is detected.

ICE DETECTOR

Message: ICE DET

ICE DETECTOR OFF

Message: ICE DET OFF

ICE DETECTOR ON

Message: ICE DET ON

3.7June 16, 2008




Condition: The ICING light illuminated indicates ice is detected and either engine anti–ice selector is OFF or an engine anti–ice valve is closed.

ENGINE ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . . .ON


Condition: The ICING light illuminated indicates ice is detected and the wing anti–ice selector is OFF or either wing anti–ice valve is closed.

WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

Condition: Two or more probe heat lights illuminated indicates the affected probe heats are inoperative.

Flight in icing conditions may result in some erroneous flight instrument indications. Note: Flight may not be permitted in RVSM airspace.


ICING ENGINE

Message: ICING ENGINE

ICING WING

Message: ICING WING

PROBE HEATMessage: PROBE HEAT

3.8 June 12, 2006



Condition: A TAT probe heat light illuminated indicates the affected probe heat is inoperative.



TAT PROBEMessage: TAT PROBE

3.9June 12, 2006



Condition: A window heat INOP light illuminated indicates the affected window is not being heated.

WINDOW HEAT switch. . . . . . . . . . .OFF 10 seconds, then ON[Allows cooling period and resets controller.]

If INOP light remains illuminated:

WINDOW HEAT switch . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

WINDOW (HEAT)Message: L FWD WINDOW

L SIDE WINDOWWINDOW HEAT

R FWD WINDOWR SIDE WINDOW

3.10 June 12, 2006




Condition: The wing anti–ice VALVE light illuminated indicates a wing anti–ice valve disagrees with the switch position.

If WING ANTI-ICE switch ON:

WING ANTI–ICE switch . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents asymmetrical ice buildup.]


If WING ANTI-ICE switch OFF:

WING ANTI–ICE switch . . . . . . . . . . . . . . . . . . . . . . . . . . .ON[Automatically reduces the thrust limit.]

------------------------DEFERRED ITEMS ------------------------------==> AFTER LANDING

ENGINE BLEED AIR switch(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ISOLATION VALVE switch (Affected side) . . . . . . . . . . OFF[Prevents structural damage due to overheat]

WING ANTI–ICE

Message: L WING ANTI-ICE R WING ANTI-ICE

3.11June 16, 2008




Condition: The wing anti–ice VALVE light illuminated indicates a wing anti–ice valve disagrees with the commanded position.

WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON[Automatically reduces the thrust limit.]


WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents asymmetrical ice buildup.]


If VALVE light extinguished:

After landing:

ENGINE BLEED AIR switch(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ISOLATION VALVE switch (Affected side) . . . . . . . . OFF[Prevents structural damage due to overheat]

WING ANTI–ICE

Message: L WING ANTI-ICE R WING ANTI-ICE

3.12 June 12, 2006


Non-Normal Checklists Chapter NNCAutomatic Flight Section 4


Table of ContentsNNC.4 Non-Normal Checklists-Automatic FlightAUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1

AUTOPILOT DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1AUTOTHROTTLE DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . 4.1

TOC.4.1June 12, 2006


Non-Normal Checklists -Automatic Flight


IntentionallyBlank

TOC.4.2 June 12, 2006



Condition: The AUTOPILOT light illuminated indicates the engaged autopilot is operating in a degraded mode. Engaged roll and/or pitch mode may have failed.

AUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISENGAGENote: Flight may not be permitted in RVSM airspace.


Condition: The A/P DISC light illuminated indicates the autopilot has disconnected.

Note: Flight may not be permitted in RVSM airspace. Contact ATC. Refer to the Airway Manual, Navigation section, for RVSM requirements.

Condition: The A/T DISC light illuminated indicates the autothrottle has disconnected.

AUTOPILOTMessage: AUTOPILOT

AUTOPILOT DISCONNECTMessage: AUTOPILOT DISC

AUTOTHROTTLE DISCONNECTMessage: AUTOTHROT DISC

4.1June 12, 2006



IntentionallyBlank

4.2 June 12, 2006


Non-Normal Checklists Chapter NNCCommunications, Datalink Section 5


Table of ContentsNNC.5 Non-Normal Checklists-Communications, DatalinkACARS - NO COMM (TOUCHSCREEN) . . . . . . . . . . . . . . . . . . . 5.1

ACARS SYSTEM INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . 5.2CABIN INTERPHONE SYSTEM INOPERATIVE . . . . . . . . . . . . 5.4COMM WITH CENTER VHF (TOUCHSCREEN) . . . . . . . . . . . . 5.6DATALINK LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7DATALINK SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7IDU TOUCHSCREEN DATALINK INOPERATIVE . . . . . . . . . . . 5.7PA SYSTEM INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8RADIO TRANSMIT CONTINUOUS

(STUCK MICROPHONE SWITCH) . . . . . . . . . . . . . . . . . . . . . 5.10SATVOICE LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11SAT 1 AND/OR SAT 2 NOT AVAILABLE . . . . . . . . . . . . . . . . . 5.12

TOC.5.1June 12, 2006


Non-Normal Checklists -Communications, Datalink


IntentionallyBlank

TOC.5.2 June 12, 2006



Condition: Frequency changes are automatically controlled by the ACARS unit as long as the aircraft is in range of a datalink ground station. However, within oceanic airspace or isolated areas out of VHF range, a NO COMM condition may occur. In NO COMM, all messages are stored in memory and will be downlinked when comm is automatically re-established at the next landfall.

If NO COMM message exists when in range of a ground station:

Touch INDEX.

Touch MISC MENU.

Touch LINK STATUS.

Touch VHF LINK TEST.• This action should establish a good link if one is

available. If successful, the VHF frequency of the ground station will appear below the VHF MODE/FREQ label.

If NO COMM message remains:

Touch INDEX.

Touch MISC MENU.

Touch LINK STATUS.

Touch VHF CONTROL.• US/PACIFIC, EUR/ASIA, JAPAN.

If NO COMM message remains:

Accomplish ACARS SYSTEM INOP procedure.

ACARS - NO COMM (TOUCHSCREEN)

5.1June 12, 2006



Condition: ACARS system is inoperative.

The following items must be manually completed.• Stations Time Slip.• Required company radio reports.• Written Engine Performance Reports.• 767-300ER ONLY: Oceanic clearances.

Complete the engine performance report as follows.When the aircraft is stabilized in cruise.• Disengage autothrottles• Allow engines to stabilize.• Press EVENT RECORD button on the EICAS control panel.• Autothrottles may be re-engaged.

When desired, the EICAS maintenance panel may be used to call up the PERF/APU DISPLAYS as follows.• Press the PERF/APU button.• Press the MAN button.

Record data on Engine Performance Report form (refer to TOPP 50-10-25 in MDM).Note: Leave throttle, N3, and NAC blank. Return lower

EICAS CRT display to engine mode by pressing ENGINE switch on EICAS control panel.

ACARS SYSTEM INOPERATIVE

5.2 June 12, 2006



IntentionallyBlank

5.3June 12, 2006



Condition: Cabin interphone system is inoperative.

Ensure all cabin handsets are properly stowed.• Improperly stowed handsets may be the cause of the

malfunction.

If interphone still inoperative:

Notify Flight Attendants.• Contact Flight Leader and establish plan for

communications under normal conditions.• Avoid use of PA for direct messages to Flight

Attendants except in an emergency.• Brief the Flight Attendants on the following alternate

emergency procedures.


CABIN INTERPHONE SYSTEM INOPERATIVE

5.4 June 16, 2008



Continued from previous pageCabin Interphone System Inoperative

Source of Non-normal Pilot action Briefing ItemsFlight Deck CabinSmoke/Fire Use PA The emergency signal from

flight deck to cabin may bedesignated as the signal toevacuate, provided the Captainand Flight Leader agree to usethis signal in advance

EmergencyLandingDitchingEvacuationor RejectedTakeoff

Smoke/Fire MonitorPA

Flight Attendant will use theemergency signal to notifypilots to monitor the PA.

Hijacking Flight Attendant will use theemergency signal to notifypilots to monitor the PA.

PassengerProblem(Medical/Disturbance)

Flight Attendant will use theemergency signal to notifypilots to monitor the PA. If notpossible, Flight Attendant willcome to the flight deck door anduse the briefed entry method.

5.5June 16, 2008



Condition: Center VHF is required for voice communication.

Touch INDX.Touch MISC MENU.Touch LINK STATUS.Touch VHF CONTROL.Touch CHANGE MODE.• Note that the MODE prompt at top of page changes from

DATA to VOICE. Frequency tuning is then done manually on the other VHF center control panel.

• Return to DATA by touching CHANGE MODE. The unit will automatically scan for an available frequency to establish link.

• If a data message is attempted with the unit in the VOICE mode, a DATAMD advisory will appear. Touch the advisory message and the IDU will shift to the VHF CTRL page.

• Return to DATA by touching CHANGE MODE.

COMM WITH CENTER VHF (TOUCHSCREEN)

5.6 June 12, 2006



Condition: Datalink is temporarily lost.

Condition: Datalink system has failed.

Condition: IDU or printer is inoperative.

Recycle the following circuit breakers before calling Maintenance:• P11 G5 Flight Deck Printer.• P11 G6 Mgmt Unit.• P11 G7 Dsply Unit.• P6 G5 Mgmt Unit.

Do not attempt to fix any inoperative function by accessing the MAINT MENU submenu on the MAIN MENU page.• This submenu requires special training and is to be used

by Avionics Technicians only.

DATALINK LOSTMessage: DATALINK LOST

DATALINK SYSTEMMessage: DATALINK SYS

IDU TOUCHSCREEN DATALINK INOPERATIVE

5.7June 12, 2006



Condition: PA system is inoperative.

Notify Flight Attendants.Contact Flight Leader and establish a plan for communications under normal conditions, including:Use of standard flight deck/cabin call signals.Advising Flight Leader to review location and operation of portable megaphones with Flight Attendants.Advise Flight Leader 20 minutes (1 hour transoceanic flights) and 5 minutes before landing.Note: With the PA inoperative, the F/As must individually

(few seats at a time) brief passengers before takeoff and landing. Coordinate as required to provide sufficient time to meet these requirements.• Brief Flight Leader on the following alternate

emergency procedures.


PA SYSTEM INOPERATIVE

5.8 June 16, 2008



Continued from previous pagePublic Address System Inoperative

Source of Abnormal Pilot action Briefing ItemsFlight Deck CabinSmoke/Fire Use cabin

interphoneNo changes to currentprocedures. Pilots and FlightAttendants will use the cabininterphone or communication.Any public announcementswill be made by the FlightAttendants using megaphones.

EmergencyLanding

Useemergencysignalfollowed bycabininterphone orface-to-face.

Pilots will use the emergencysignal to alert the FlightAttendants to an emergencysituation. Subsequentcommunication will then bevia the interphone orface-to-face, time permitting.The interphone will be used tocommand an evacuation.

DitchingEvacuationor RejectedTakeoff

Smoke/Fire Use cabininterphone

No changes to currentprocedures. Pilots and FlightAttendants will use the cabininterphone forcommunication. Any publicannouncements will be madeby the Flight Attendants usingmegaphones.

HijackingPassengerProblem(Medical/Disturbance)

5.9June 12, 2006



Condition: A radio is continuously transmitting without crew input.

Microphone selector switches(all audio control panels) . . . . . . . . . . . . . . .Flight interphone

[Deselects radios and stops radio transmissions.]

The microphone/interphone with the stuck switch continuously transmits on flight interphone.The associated audio control panel should remain on flight interphone. All other audio control panels may be used normally.

RADIO TRANSMIT CONTINUOUS (STUCK MICROPHONE SWITCH)

5.10 June 12, 2006



0171 through 0199, 1200 through 1201, 1501 through 1506, 1521,1601 through 1613

Condition: SATCOM voice capability is temporarily lost due to a reason other than SATCOM failure.

SATVOICE LOST

Message: SATVOICE LOST

5.11June 16, 2008



Condition: SATCOM system may not be logged-on to a satellite or SATCOM channels may be failed.

Note: IRUs must be aligned before SATCOM will function.

Select MENU key on MCDUSelect SAT.• SATCOM MAIN MENU should be displayed.

If SAT 1 and/or SAT 2 display NOT available:

Select <SUBMENU AT 6L

SATCOM SUBMENU should be displayed.

If <LOGGED ON AUTO is displayed at 1L:

SATCOM is logged on to a satellite.

Press LOG-ON AT 2L.

Press LOG-OFF* AT 2R.

Pull and reset CB’S.• H8 SATCOM• H9 SATCOM HGA

Press *AUTO LOG-ON AT 2L.• <LOGGED ON AUTO> should be displayed at 1L

Press RETURN> AT 6R• SATCOMM MAIN MENU should be displayed.• SAT 1 AND/OR SAT 2 AVAILABLE should be

displayed.

Reattempt normal SATCOM operation.

Refer to Volume 1, Supplementary Procedures, SP.5, SATCOM Operation.


SAT 1 AND/OR SAT 2 NOT AVAILABLEMessage: SATVOICE LOST

5.12 June 12, 2006




If <LOGGED OFF is displayed at 1L:

Note: SATCOM has not logged-on to a satellite.

Press *AUTO LOG-ON AT 2L.

<LOGGED ON AUTO> should be displayed at 1L

Press RETURN> AT 6R.

SATCOM MAIN MENU should be displayed

SAT 1 AND/OR SAT 2 AVAILABLE should be displayed.

Reattempt normal SATCOM operation.

Refer to Volume 1, Supplementary Procedures, SP.5, SATCOM Operation.

5.13June 12, 2006



IntentionallyBlank

5.14 June 12, 2006


Non-Normal Checklists Chapter NNCElectrical Section 6


Table of ContentsNNC.6 Non-Normal Checklists-ElectricalAC BUS OFF [HDG INSTALLED] . . . . . . . . . . . . . . . . . . . . . . . . . 6.1

AC BUS OFF [HDG NOT INSTALLED] . . . . . . . . . . . . . . . . . . . . 6.8APU GENERATOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14BATTERY OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14BUS ISOLATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14GENERATOR DRIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.15GENERATOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.16MAIN BATTERY DISCHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17STANDBY BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17UTILITY BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.18

TOC.6.1June 16, 2008


Non-Normal Checklists -Electrical


IntentionallyBlank

TOC.6.2 June 16, 2008



0171 through 0199, 1200 through 1201, 1401 through 1404, 1501 through 1506, 1521, 1601 through 1708

(HDG INSTALLED)

Condition: An AC BUS OFF light illuminated indicates the AC bus is unpowered.

GENERATOR CONTROL switch(es) . . . . . . . . . . OFF, then ONAttempt only one reset.

If APU generator available:

APU selector . . . . . . . . . . . . . . . . . . . . . . . .START, then ON[Provides an additional source of electrical power.]

After APU running:

LEFT BUS TIE switch . . . . . . . . . . . . . . .OFF, then AUTOAttempt only one reset.

RIGHT BUS TIE switch . . . . . . . . . . . . . .OFF, then AUTOAttempt only one reset.


AC BUS OFF

Message: L AC BUS OFF R AC BUS OFF

6.1June 16, 2008




If both AC BUS OFF lights were illuminated and AC power is restored:

Note: Accomplish the following steps regardless of availability of APU generator.


FMC performance data . . . . . . . . . . . . . . . . . . . . . . . . . Enter


IRS MODE selector(Affected IRS(s) only) . . . . . . . . . . . . . . . . . . . . . . . . . ATTNote: Maintain straight and level attitude for 30

seconds.

Heading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EnterFMS CDU: Select POS INIT page, enter heading on SET IRS HDG line. OrIRS panel: Select H key, enter heading on number keys, then press ENT key. IRS may require periodic updates.


6.2 June 16, 2008




If both AC BUS OFF lights remain illuminated:


Flight in icing conditions may result in some erroneous flight instrument indications.

Note: The BAT DISCH light will illuminate until the main battery voltage equals the DC output of the HDG.

ALTERNATE IRS switch (First Officers’s) . . . . . . . . . .ALTN[Prevents loss of Captain’s RDMI.]

1501 through 1506If Electronic Engine Control INOP lights illuminated:

Thrust levers . . . . . . . . . . . . . . . . Retard to mid position

LEFT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

RIGHT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Do not accomplish the following checklist:ENGINE EEC

0171 through 0199, 1200 through 1201, 1401 through 14041521, 1601 through 1708If Electronic Engine Control ALTN lights illuminated:


LEFT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

RIGHT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

Do not accomplish the following checklist:ENGINE EEC MODE


6.3June 16, 2008




If both BUS OFF lights remain illuminated: (continued)

If engine inoperative:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . .ON[Allows gravity flow suction feed from both left and right tanks for operating engine.]

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . OVRD[Increases cooling airflow.]

FLIGHT DECK TEMPERATURE control . . . . . . . . . . . MAN0171 through 0199, 1200 through 1201, 1601 through 1708 If Captain’s EFIS is displayed and First Officer’s EFIS is desired:

NAVIGATION SOURCEselector (First Officer’s) . . . . . . . . . . . . . . . . . . . . FMC - L

IRS and AIR DATA switches (First Officer’s) . . . . . . . . . . . . . . . . . . . . .ALTN

FLIGHT INSTRUMENT BUS POWER switch. . . . . .ALTNReturn to OFF when desired to re–power captain flight instruments.

Note: A 10- to 15-second loss of all electronic flight instruments will occur. Return to OFF when desired to repower Captain’s flight instruments.

Note: Configuration warning may occur with either thrust lever at idle.


6.4 June 16, 2008





Master caution inoperative.

All autopilots inoperative.

All flight directors inoperative.

Autothrottles inoperative.

Auto engine and wing anti–ice inoperative (As installed).

Auto speedbrake inoperative.

Antiskid for outboard wheels inoperative.

Flap indicator inoperative.

Use left VHF radio for communications.

Right ILS inoperative; use standby attitude ILS guidance, if required.

Yoke stab trim inoperative; use alternate stab trim.


6.5June 16, 2008




If the left AC BUS OFF light remains illuminated:



FLIGHT DIRECTOR SOURCEselector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . R

[The right flight director can be used in the LNAV and VNAV mode if the left FD switch is turned off.][Localizer and glide slope may arm, but will not capture.]

FMC SOURCE SELECT (As installed)switch (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

NAVIGATION SOURCE (As installed)selector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . .FMC - R

AIR DATA SOURCEswitch (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

[Prevents inaccurate airspeed indications due to probe icing.]

TRANSPONDER selector . . . . . . . . . . . . . . . . . . . . . . . . . . 2


Left and center flight directors inoperative.




6.6 June 16, 2008




If the right AC BUS OFF light remains illuminated:



FLIGHT DIRECTOR SOURCEselector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . C

FMC SOURCE SELECT (As installed)switch (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

NAVIGATION SOURCE (As installed)selector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . FMC - L

AIR DATA SOURCEswitch (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . . .ALTN



Right autopilot inoperative; use center or left autopilot.

Right flight director inoperative.

Autothrottles may be inoperative.

6.7June 16, 2008



0121, 0124 through 0139(HDG NOT INSTALLED)

Condition: An AC BUS OFF light illuminated indicates the AC bus is unpowered.

GENERATOR CONTROL switch(es) . . . . . . . . . . OFF, then ONAttempt only one reset.



After APU running:

LEFT BUS TIE switch . . . . . . . . . . . . . . .OFF, then AUTOAttempt only one reset.

RIGHT BUS TIE switch . . . . . . . . . . . . . .OFF, then AUTOAttempt only one reset.


AC BUS OFF

Message: L AC BUS OFF R AC BUS OFF

6.8 June 16, 2008




If both AC BUS OFF lights were illuminated and AC power is restored:

Note: Accomplish the following steps regardless of availability of APU generator.


FMC performance data . . . . . . . . . . . . . . . . . . . . . . . . . Enter


IRS MODEselector (Affected IRS(s) only) . . . . . . . . . . . . . . . . . ATTNote: Maintain straight and level attitude for 30

seconds.

Heading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EnterFMS CDU: Select POS INIT page, enter heading on SET IRS HDG line. OrIRS panel: Select H key, enter heading on number keys, then press ENT key. IRS may require periodic updates.


6.9June 16, 2008




If both AC BUS OFF lights remain illuminated:


CAUTION: Flight beyond 30 minutes will result in complete loss of electrical power and the inability to extend gear and flaps.


If Electronic Engine Control INOP lights illuminated:


LEFT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

RIGHT ELECTRONIC ENGINECONTROL switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Do not accomplish the following checklist:ENGINE EEC

EQUIPMENT COOLING selector . . . . . . . . . . . . . . OVRD[Increases cooling airflow.]


6.10 June 16, 2008





Master caution inoperative.

Avoid icing conditions.[Wing and engine anti–ice inoperative.]

All autopilots, autothrottles, and flight directors inoperative.


LNAV and VNAV inoperative.


Auto speedbrake inoperative.

Antiskid for outboard wheels inoperative.

Thrust reversers inoperative.

Yoke stab trim inoperative; use alternate stab trim.

Use standby attitude ILS guidance, if required.

Accomplish the following checklist:CABIN AUTOMATIC INOPERATIVE


6.11June 16, 2008




If the left AC BUS OFF light remains illuminated:



FLIGHT DIRECTOR SOURCEselector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . R

[The right flight director can be used in the LNAV and VNAV mode if the left FD switch is turned off.][Localizer and glide slope may arm, but will not capture.]

FMC SOURCE SELECT (As installed)switch (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

NAVIGATION SOURCE (As installed)selector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . .FMC - R

AIR DATA SOURCEselector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN




All flight directors inoperative.


LNAV and VNAV inoperative.



6.12 June 16, 2008




If the right AC BUS OFF light remains illuminated:



FLIGHT DIRECTOR SOURCEselector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . C

FMC SOURCE SELECT (As installed)switch (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

NAVIGATION SOURCE (As installed)selector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . FMC - L

AIR DATA SOURCEselector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . . . .ALTN



Right autopilot inoperative; use left or center autopilot.

Right flight director inoperative.

Autothrottles may be inoperative.

6.13June 16, 2008



Condition: The APU generator OFF light illuminated indicates the APU generator control breaker is open due to a fault with the APU running.

GENERATOR CONTROL switch . . . . . . . . . . . . . OFF, then ONAttempt only one reset.

If there is only one AC power source available:


Condition: The battery OFF light illuminated indicates the battery switch is OFF.

Condition: The AC bus ISLN light illuminated indicates the bus tie breaker is open due to an AC electrical system fault.

APU GENERATOR OFFMessage: APU GEN OFF

BATTERY OFFMessage: BATTERY OFF

BUS ISOLATEDMessage: L BUS ISOLATED R BUS ISOLATED

6.14 June 16, 2008



Condition: The generator DRIVE light illuminated indicates the generator drive oil pressure is low or the generator drive oil temperature is high.

CAUTION: The engine must be rotating when the GENERATOR DRIVE DISCONNECT switch is pushed.

GENERATOR DRIVE DISCONNECT switch . . . . . . . . . . . Push[Prevents generator drive damage.]



Do not accomplish the following checklist:GENERATOR OFF

If APU generator is unavailable:


Do not accomplish the following checklist:GENERATOR OFF

GENERATOR DRIVEMessage: L GEN DRIVE R GEN DRIVE

6.15June 16, 2008



Condition: The generator OFF light illuminated indicates the generator control breaker is open.


If an engine generator control OFF light remains illuminated:


APU selector . . . . . . . . . . . . . . . . . . . . . .START, then ON[Provides an additional source of electrical power.]

If APU generator is unavailable:


GENERATOR OFFMessage: L GEN OFF R GEN OFF

6.16 June 16, 2008



Condition: The DISCH light illuminated indicates the main battery is discharging.

Condition: The standby power bus OFF light illuminated indicates the standby AC or DC bus is unpowered.

STANDBY POWER selector . . . . . . . . . . . . . . . . . . . . . . . . . BATThe battery will provide standby bus power for approximately 30 minutes.

If the standby power bus OFF light remains illuminated and right AC bus power is available:

STANDBY POWER selector . . . . . . . . . . . . . . . . . . . . AUTO[Restores the battery charger.]

MAIN BATTERY DISCHARGEMessage: MAIN BAT DISCH

STANDBY BUS OFFMessage: STANDBY BUS OFF

6.17June 16, 2008



Condition: The utility bus OFF light illuminated indicates the galley and utility busses are unpowered.

If two generator sources available:

UTILITY BUS switch . . . . . . . . . . . . . . . . . . . . OFF, then ON

UTILITY BUS OFFMessage: L UTIL BUS OFF R UTIL BUS OFF

6.18 June 16, 2008


Non-Normal Checklists Chapter NNCEngines, APU Section 7


Table of ContentsNNC.7 Non-Normal Checklists-Engines, APUABORTED ENGINE START . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1

APU BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1APU BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1APU FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2APU FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2APU FUEL VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.3APU GENERATOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.3DUAL ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.4EEC OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6ENGINE ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7ENGINE ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.8ENGINE BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.10ENGINE BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11ENGINE BLEED OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12ENGINE BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13ENGINE BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13ENGINE CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14ENGINE EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14ENGINE EEC MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.15ENGINE FAILURE OR SHUTDOWN . . . . . . . . . . . . . . . . . . . . . 7.16ENGINE FIRE OR SEVERE DAMAGE OR

SEPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18ENGINE FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21ENGINE FUEL LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.22ENGINE FUEL VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.26ENGINE HIGH STAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.27ENGINE HSVOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.28

TOC.7.1June 16, 2008


Non-Normal Checklists -Engines, APU


ENGINE IN–FLIGHT START . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.30ENGINE LIMIT OR SURGE OR STALL . . . . . . . . . . . . . . . . 7.34ENGINE LIMIT PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . 7.36ENGINE LOW IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36ENGINE OIL PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.37ENGINE OIL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . 7.38ENGINE OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.40ENGINE PRV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.42ENGINE RPM LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE TAILPIPE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.44FUEL SPAR VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45IDLE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.46OIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.46REVERSER ISOLATION VALVE . . . . . . . . . . . . . . . . . . . . . . . . 7.47REVERSER UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.48STARTER CUTOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.51VOLCANIC ASH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.52

TOC.7.2 June 16, 2008



Condition: During a ground start, an abort engine start condition occurs.

If the ENGINE START selector is in GND:



If the ENGINE START selector is in AUTO:

After N2 decreases below 20%:

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . GND


ENGINE START selector . . . . . . . . . . . . . . . . . . . . AUTO

Condition: The APU bleed air VALVE light illuminated indicates the valve position disagrees with the commanded position.

Condition: The APU BTL 1 DISCH or APU BTL 2 DISCH light illuminated indicates that APU fire extinguisher bottle 1 or bottle 2 pressure is low.

ABORTED ENGINE START

FUEL CONTROL switch . . . . . . . . . . . . . . . . . . . . . . . CUT OFF

APU BLEED VALVEMessage: APU BLEED VAL

APU BOTTLEMessage: APU BTL 1 APU BTL 2

7.1June 16, 2008



Condition: The APU FAULT light illuminated indicates the APU has automatically shut down.

APU selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, then ON[Attempts to reset APU controller.]

If the FAULT light extinguishes:

APU selector . . . . . . . . . . . . . . . . . . . . . . . .START, then ON

Condition: Fire is detected in the APU.

After 30 seconds, APU fire warning light stays illuminated:

APU fire switch . . . . . . . . . . . . . . . . . . . . . . Rotate and holdRotate to the other stop and hold for 1 second.

If APU fire warning light stays illuminated:


Do not accomplish the following checklists:APU BOTTLEAPU FAULT

APU FAULTMessage: APU FAULT

APU FIREMessage: APU FIRE

APU fire switch . . . . . . . . . . . . . . . . . . . . .Pull, rotate, and holdRotate to the stop and hold for 1 second.

7.2 June 16, 2008



Condition: The APU FAULT light illuminated indicates the APU fuel valve position disagrees with the commanded position.

APU selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFDo not start the APU.

Condition: The APU generator OFF light illuminated indicates the APU generator control breaker is open due to a fault with the APU running.


APU FUEL VALVEMessage: APU FUEL VAL

APU GENERATOR OFFMessage: APU GEN OFF

7.3June 16, 2008



Condition: Thrust or thrust lever response is lost from both engines.

If engine appears stalled or EGT approaches the Standby Engine Indicator (SEI) placard limit:

Repeat the above step as necessary.[Reduces EGT and improves airflow.]

Note: SEI maximum EGT limit is in–flight start EGT limit.

RAM AIR TURBINE switch . . . . . . . . . . . . . . . . . . . . . . UNLKD[Backs up automatic deployment of the RAT.]

Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ______ knots0121, 0124 through 0139:• Above 30,000 feet use 240 knots.• 30,000 feet or below use 260 knots minimum.

0171 through 0199, 1200 through 1201, 1401 through 1404:• Above 35,000 feet use 240 knots.• Above 20, 000 to 35,000 feet use 250 knots minimum.• 20,000 feet and below use 200 knots minimum.

1501 through 1506, 1521, 1601 through 1708:• Above 30,000 feet use 240 knots.• 30,000 feet or below use 220 knots minimum.

Note: OVSPD light and associated aural warning will indicate Vmo/Mmo exceedances.


DUAL ENGINE FAILURE


Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Close

FUEL CONTROL switches (Both) . . . . . . .CUT OFF, then RUN

7.4 June 16, 2008





Do not wait for successful engine start(s) prior to starting the APU.

If both engines remain failed:

Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE

FUEL CONTROL switches(Both) . . . . . . . . . . . . . . . . . . . . . . . . . . .CUT OFF, then RUN

Remain approximately 30 second in each position during start attempts.Repeat until engine start is achieved.Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.


After restarting one or both engines:



FMC Performance data . . . . . . . . . . . . . . . . . . . . . . . . . Enter


IRS MODE selector(Affected IRS(s) only) . . . . . . . . . . . . . . . . . . . . . . . . . ATT

Heading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EnterEnter heading on IRS control panel or FMC POS INIT page.


If one engine remains failed:


7.5June 16, 2008



0121, 0124 through 0139, 1501 through 1506

Condition: The EEC INOP light illuminated indicates the electronic engine control switch is OFF.

EEC OFF

Message: L EEC OFF R EEC OFF

7.6 June 16, 2008





If ENGINE ANTI-ICE switch ON:


ENGINE ANTI–ICE switch(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . OFF, then ON



Leave the ENGINE ANTI-ICE switch ON.[On position provides continuous ignition.]


If ENGINE ANTI-ICE switch OFF:

ENGINE ANTI–ICE switch (Affected engine) . . . . . . . . . .ON[Automatically reduces the thrust limit.]



ENGINE ANTI–ICE


7.7June 16, 2008





If ENGINE ANTI-ICE selector ON:


ENGINE ANTI–ICE selector(Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . OFF, then ON





If ENGINE ANTI-ICE selector OFF:





ENGINE ANTI–ICE


7.8 June 16, 2008




If ENGINE ANTI-ICE selector AUTO:


If VALVE light is extinguished and total air temperature (TAT) is above 10 degrees C:



ENGINE BLEED AIR switch (Affected side) . . . . . . . OFF

ENGINE ANTI–ICE selector(Affected side) . . . . . . . . . . . . . . . . . . . . . . OFF, then ON

If VALVE light re-illuminates:




7.9June 16, 2008









ISOLATION switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ENGINE BLEED OFF


7.10 June 16, 2008





WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents asymmetrical wing anti–icing.]




WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . AUTO


WING ANTI–ICE selector . . . . . . . . . . . . . . . . . . . . . . OFF


1601 through 1708:

Thrust reverser on the affected side may be inoperative.

ENGINE BLEED OFF


7.11June 16, 2008




Condition: The engine bleed air OVHT light illuminated indicates engine bleed air temperature is excessive.



If OVHT light remains illuminated or re–illuminates:







WING ANTI–ICEselector / switch. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


1501 through 1506, 1521, 1601 through 1708:

Thrust reverser on the affected side is inoperative.


ENGINE BLEED OVERHEAT

Message: L ENG BLD OVHT R ENG BLD OVHT

7.12 June 16, 2008



0121, 0124 through 0139

Condition: The engine BLEED light illuminated indicates the engine high pressure bleed valve is open when commanded closed.








Condition: The ENG BTL 1 DISCH or ENG BTL 2 DISCH light illuminated indicates that engine fire extinguisher bottle 1 or bottle 2 pressure is low.

ENGINE BLEED VALVE

Message: L ENG BLEED VAL R ENG BLEED VAL

ENGINE BOTTLEMessage: ENG BTL 1 ENG BTL 2

7.13June 16, 2008




Condition: Faults are detected in the engine control systems.

0121, 0124 through 0139, 1501 through 1506

Condition: The INOP light illuminated indicates the electronic engine control is inoperative.


Thrust levers (Both) . . . . . . . . . . . . . . . Retard to mid position[Prevents exceeding thrust limits when selecting the electronic engine controls to off.]

ELECTRONIC ENGINE CONTROLswitches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Select both switches to OFF, one switch at a time.[Prevents undesired thrust lever stagger.]

Observe thrust limits.

ENGINE CONTROL(S)

Message: ENGINE CONTROLSL ENG CONTROL R ENG CONTROL

ENGINE EEC

Message: L ENG EEC R ENG EEC

7.14 June 16, 2008




Condition: The ALTN light illuminated indicates the electronic engine control is not receiving adequate inputs and an alternate N1 control mode is being used by the EEC to control thrust.


Thrust levers (Both) . . . . . . . . . . . . . . . Retard to mid position[Prevents exceeding thrust limits when selecting the alternate mode on the electronic engine controls.]

ELECTRONIC ENGINE CONTROLswitches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

Select both switches to ALTN, one switch at a time.

Observe thrust limits.

ENGINE EEC MODE

Message: L ENG EEC MODE R ENG EEC MODE

7.15June 16, 2008



Condition: Engine has failed, engine has flamed out, or when prescribed by another non–normal procedure.

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . . OFF[Autothrottle use not recommended under engine inoperative conditions.]

Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE[Assists in recognition of affected engine.]

Engine conditions permitting, operate at idle for two minutes to allow engine to cool and stabilize.FUEL CONTROL switch. . . . . . . . . . . . . . . . . . . . . . . .CUT OFF





WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


Plan to land at the nearest suitable airport.Continued on next page

ENGINE FAILURE OR SHUTDOWN

7.16 June 16, 2008











go–around.


7.17June 16, 2008

















7.18 June 16, 2008


















go–around.


7.19June 16, 2008





7.20 June 16, 2008



Condition: An impending fuel filter bypass condition exists on the affected engine.

Erratic engine operation and flameout may occur due to fuel contamination. If message indicated for both engines, consider landing at nearest suitable airport.

ENGINE FUEL FILTERMessage: L ENG FUEL FILT R ENG FUEL FILT

7.21June 16, 2008










ENGINE FUEL LEAK

7.22 June 16, 2008










7.23June 16, 2008






Thrust lever (Affected engine) . . . . . . . . . . . . . . . . . . .Close














WING ANTI-ICEselector / switch. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF



7.24 June 16, 2008









for go–around.








7.25June 16, 2008



Condition: The ENG VALVE light illuminated indicates the engine fuel valve position disagrees with commanded position.

If the ENG VALVE light remains illuminated when the fuel control switch is positioned to CUT OFF, the engine may continue to run for approximately 1 minute.On the ground:

Do not attempt engine start.[Prevents possibility of not being able to shutdown the engine if the spar valve subsequently fails open.]

ENGINE FUEL VALVEMessage: L ENG FUEL VAL R ENG FUEL VAL

7.26 June 16, 2008



0121, 0124 through 0139

Condition: The engine HI STAGE light illuminated indicates engine bleed air temperature is excessive.



If HI STAGE light remains illuminated or re-illuminates:








ENGINE HIGH STAGE

Message: L ENG HI STAGE R ENG HI STAGE

7.27June 16, 2008




Condition: The engine BLEED light illuminated indicates the high pressure bleed air valve is open when commanded closed.


WING ANTI–ICE selector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF










ENGINE HPSOV

Message: L ENG HPSOV R ENG HPSOV

7.28 June 16, 2008



IntentionallyBlank

7.29June 16, 2008



Condition: Engine start is needed after a shutdown with no fire or apparent damage.

Note: Do not attempt restart unless greater emergency exists.

Altitude and airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . CheckStarts not assured outside EICAS envelope.

If X–BLD is not shown:

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . . FLT










ENGINE IN–FLIGHT START

7.30 June 16, 2008




If X–BLD is shown:

PACK control selector (Affected side). . . . . . . . . . . . . . OFF[Reduces pneumatic demand.]


IGNITION selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . BOTH

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . GND












7.31June 16, 2008




If X–BLD is shown: (continued)

Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.

After engine started:


PACK control selectors (Both) . . . . . . . . . . . . . . . . . . AUTO

LEFT and RIGHT ISOLATION switches . . . . . . . . . . . . . OFF

GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

7.32 June 16, 2008



IntentionallyBlank

7.33June 16, 2008



Condition: Engine EGT or RPM are abnormal or are approaching or exceeding limits, abnormal engine noises are heard, or there is no response to thrust lever movement.

Note: If an engine compressor surge/stall occurs during ground operations, or takeoff is rejected due to an engine compressor surge/stall, a maintenance inspection is required prior to flight.

Note: Do not initiate an over-water crossing when a surge or stall has occurred.

Note: EGT may take up to two minutes to recover to normal range.

If indications abnormal or EGT continues to increase:


If indications stabilized and EGT stabilized or decreasing:

Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AdvanceAdvance slowly. Check that RPM and EGT follow thrust lever movement.[Attempts to restore normal control of engine operation.]


ENGINE LIMIT OR SURGE OR STALL

AUTOTHROTTLE ARM switch . . . . . . . . . . . . . . . . . . . . . .OFF[Allows thrust lever to remain where manually positioned.]

Thrust lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RetardRetard until indications remain within normal limits or the thrust lever is closed.

7.34 June 16, 2008




If indications stabilized and EGT stabilized or decreasing: (continued)

If RPM and EGT follow thrust lever movement and some or all thrust is restored:


If RPM does not follow thrust lever movement and EGT is normal:

[Engine is hung due to improper position of the bleed valve.]

ENGINE BLEED AIR switch . . . . . . . . . . . . . . . . . . . . OFF[Improves engine acceleration.]

If engine responds:



If engine does not respond:

Operate engine at idle.


If operating engine at idle or at a reduced thrust level which is surge and stall free:




Note: Use flaps 20 and VREF 20 for landing and flaps 5 for go-around.

7.35June 16, 2008




Condition: The ALTN light illuminated indicates the EEC is operating in the alternate control mode and the commanded N1 exceeds maximum N1.

Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RetardRetard until N1 remains within limits.


Condition: An engine has failed to go to approach idle.

Thrust lever (Affected side) . . . . . . . . . . . . . . . . . . . . AdvanceAdvance thrust lever until message extinguishes.

ENGINE LIMIT PROTECTION

Message: L ENG LIM PROT R ENG LIM PROT

ENGINE LOW IDLE

Message: L ENG LOW IDLE R ENG LOW IDLE

7.36 June 16, 2008



Condition: The L or R ENG OIL PRESS light illuminated or the oil pressure reaching the red line limit indicates engine oil pressure is low.

Oil pressure indication . . . . . . . . . . . . . . . . . . . . . . . . . . Check

If oil pressure at or below red line limit:


If oil pressure normal:


ENGINE OIL PRESSUREMessage: L ENG OIL PRESS R ENG OIL PRESS

7.37June 16, 2008



Condition: The oil temperature in the amber band or the oil temperature above the red line limit indicates engine oil temperature is high.


Thrust lever (Affected engine) . . . . . . . . . . . . . . . . . . . . Decrease gradually

Retard thrust lever slowly until temperature decreases.







ENGINE OIL TEMPERATURE

7.38 June 16, 2008



IntentionallyBlank

7.39June 16, 2008



Condition: The L or R ENG OVHT light illuminated indicates an overheat is detected in the engine.

ENGINE BLEED AIR switch. . . . . . . . . . . . . . . . . . . . . . . . . OFF[Attempts to stop the flow of bleed air through the leak.]


Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RetardRetard thrust lever slowly until ENG OVHT light is no longer illuminated or thrust lever is closed.[Reduces temperature in the nacelle and strut.]

If ENG OVHT light no longer illuminated:

Operate engine at reduced thrust level for the remainder of flight.


GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRDNote: Use flaps 20 and Vref 20 for landing and flaps 5 for

go-around.

If ENG OVHT light remains illuminated:





ENGINE OVERHEATMessage: L ENG OVHT R ENG OVHT

7.40 June 16, 2008












7.41June 16, 2008




Condition: The engine BLEED light illuminated indicates the pressure regulating valve is open when commanded closed.












ENGINE PRV

Message: L ENG PRV R ENG PRV

7.42 June 16, 2008




Condition: N1 or N2 RPM is at the red line limit.

Condition: Engine was shutdown by the FUEL CONTROL switch or fire switch.

Condition: The engine start VALVE light illuminated indicates the engine start valve is not in the commanded position.

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . . AUTO[Prevents bleed air from entering starter if valve subsequently opens.]

In flight:

Increase airspeed until X–BLD no longer displayed.[Assures sufficient air flow for windmill start.]

ENGINE RPM LIMIT

Message: L ENG RPM LIM R ENG RPM LIM

ENGINE SHUTDOWNMessage: L ENG SHUTDOWN R ENG SHUTDOWN

ENGINE STARTERMessage: L ENG STARTER R ENG STARTER

7.43June 16, 2008






LEFT and RIGHT ISOLATION switches . . . . . . . . . . . . . .ON[Ensures bleed air is available to either engine’s starter.]








FUEL CONTROL switch (Affected engine) . . . . . . . .CUT OFF

7.44 June 16, 2008



Condition: The SPAR VALVE light illuminated indicates the spar valve position disagrees with commanded position.

On the ground:

Do not attempt engine start.[Prevents possibility of not being able to shutdown the engine if the engine fuel valve subsequently fails open.]

0171 through 0199, 1200 through 1201, 1401 through 1404,1601 through 1708

Condition: The engines are at different idle settings.

In flight:

Thrust lever (Side with lowest thrust) . . . . . . . . . . AdvanceAdvance thrust lever until message disappears.

On ground:

Crew awareness.

FUEL SPAR VALVEMessage: L FUEL SPAR VAL R FUEL SPAR VAL

IDLE DISAGREE

Message: IDLE DISAGREE

7.45June 16, 2008



0121, 0124 through 0139, 1501 through 1506, 1521, 1601 through 1708

Condition: Affected engine oil filter contamination has been detected.


Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RetardRetard thrust lever slowly until message disappears and continue operating at reduced thrust.

If OIL FILTER message remains displayed:


0171 through 0199, 1200 through 1201, 1401, through 1404

Condition: Primary oil filter is in bypass mode and secondary oil filter is being utilized.

CLOSELY MONITOR ALL OTHER ENGINE PARAMETERS.

OIL FILTER

Message: L OIL FILTER R OIL FILTER

OIL FILTER

Message: L OIL FILTER R OIL FILTER

7.46 June 16, 2008



Condition: The REV ISLN light illuminated indicates a fault is detected in the affected engine reverser system.

Additional system failures may cause inflight deployment.Expect normal reverser operation after landing.

REVERSER ISOLATION VALVEMessage: REV ISLN VAL

L REV ISLN VAL R REV ISLN VAL

7.47June 16, 2008



Condition: REV annunciation displayed and reverse thrust not intentionally selected.

Reverse thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DownVerify reverse thrust lever is in the full down position.

With no yaw, loss of airspeed, or buffet:


With yaw, loss of airspeed, or buffet:

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Retract[Prevents slat damage from turbulence created by the open cowl.]


Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Close





TRANSPONDER mode selector . . . . . . . . . . . . . . . . . . . . TA [Prevents climb commands which can exceed single engine performance capability.]





REVERSER UNLOCKED

7.48 June 16, 2008




With yaw, loss of airspeed, or buffet: (continued)






WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF




7.49June 16, 2008




With yaw, loss of airspeed, or buffet: (continued)------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Use ALTERNATE FLAP OPERATION to extend trailing edge flaps.

Do not extend leading edge slats.

ENGINE START selectors (Both) . . . . . . . . . . . . . . . . CONT[Provides ignition for landing with leading edge slats retracted.]

ALTERNATE FLAP OPERATION:

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . SETPosition to agree with FLAP lever.


ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . SETExtend or retract trailing edge flaps as required.


7.50 June 16, 2008



Condition: The engine start VALVE light illuminated indicates the valve is open when commanded closed.

ENGINE START selector . . . . . . . . . . . . . . . . . . . . . . . . . AUTO


ENGINE BLEED AIR switch (Affected side) . . . . . . . . . OFF[Removes bleed air source from starter.]

ISOLATION switch (Affected side) . . . . . . . . . . . . . . . . . OFF[Removes bleed air source from starter.]

If on the ground:

Ground air source (If in use) . . . . . . . . . . . . .Disconnect[Removes bleed air source from starter.]




Do not accomplish the following checklist:ENGINE BLEED OFFICING WING

STARTER CUTOUTMessage: L STARTER CUTOUT R STARTER CUTOUT

7.51June 16, 2008



Condition: Static discharge around the windshield, bright glow in the engine inlets, smoke or dust on the flight deck, or acrid odor indicates the airplane is in volcanic ash.

CAUTION: Exit volcanic ash as quickly as possible. Consider a 180 degree turn.

Oxygen masks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On, 100%

Crew Communications . . . . . . . . . . . . . . . . . . . . . . . Establish


Thrust levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CloseConditions permitting, operate engines at idle.[Reduces possible engine damage and/or flameout by decreasing EGT.]


RECIRCULATION FANswitches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Increases bleed air extraction to improve engine stall margin by putting packs into high flow.]

ENGINE ANTI–ICEselectors / switches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . .ON


WING ANTI–ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON



[Provides an electrical power source in the event one or both engines flame out.]


VOLCANIC ASH

7.52 June 16, 2008



Continued from previous pageNote: Volcanic ash can cause non–normal system reactions

such as:• engine malfunctions, increasing EGT, engine stall or

flameout• decrease or loss of airspeed indications• equipment overheat or smoke indications• cargo fire indications.

Note: Engine may accelerate to idle very slowly, especially at high altitude. Slow acceleration may be incorrectly interpreted as a hung start or an engine malfunction. If N2 is steadily increasing, and EGT remains within limits, the start is progressing normally.

If engines flamed out or stalled, or EGT rapidly approaching or exceeding limit:

Accomplish the DUAL ENGINE FAILURE checklist.

Plan to land at the nearest suitable airport.Do not accomplish the following checklist:

RECIRCULATION FAN

7.53June 16, 2008



IntentionallyBlank

7.54 June 16, 2008


Non-Normal Checklists Chapter NNCFire Protection Section 8


Table of ContentsNNC.8 Non-Normal Checklists-Fire ProtectionAPU BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.1

APU FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.2CARGO BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3CARGO FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4ENGINE BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6ENGINE FIRE OR SEVERE DAMAGE OR

SEPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.8ENGINE OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.12ENGINE TAILPIPE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.14EQUIPMENT SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.15FIRE/OVERHEAT SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.16SMOKE OR FIRE OR FUMES . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.18SMOKE OR FUMES REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . 8.21WHEEL WELL FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.22

TOC.8.1June 16, 2008


Non-Normal Checklists -Fire Protection


IntentionallyBlank

TOC.8.2 June 16, 2008



Condition: The APU BTL 1 DISCH or APU BTL 2 DISCH light illuminated indicates that APU fire extinguisher bottle 1 or bottle 2 pressure is low.

APU BOTTLEMessage: APU BTL 1 APU BTL 2

8.1June 12, 2006



Condition: Fire is detected in the APU.

After 30 seconds, APU fire warning light stays illuminated:

APU fire switch . . . . . . . . . . . . . . . . . . . . . . Rotate and holdRotate to the other stop and hold for 1 second.

If APU fire warning light stays illuminated:


Do not accomplish the following checklists:APU BOTTLEAPU FAULT

APU FIREMessage: APU FIRE

APU fire switch . . . . . . . . . . . . . . . . . . . . .Pull, rotate, and holdRotate to the stop and hold for 1 second.

8.2 June 12, 2006



Condition: The cargo fire bottle 1 or bottle 2 DISCH light illuminated indicates that cargo fire extinguisher bottle 1 or bottle 2 pressure is low.

CARGO BOTTLEMessage: CARGO BTL 1 CARGO BTL 2

8.3June 12, 2006



Condition: The FWD or AFT light illuminated indicates smoke is detected in a cargo compartment.

CARGO FIRE ARM switch(Forward or aft) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED

NO.1 CARGO FIRE BOTTLE DISCHARGE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Push

Push and hold for 1 second.Note: DISCH light may require approximately 30 seconds to

illuminate.

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . OVRD

If forward cargo fire:

CARGO HEAT switch (FWD). . . . . . . . . . . . . . . . . . . . . . OFF

If aft cargo fire:

CARGO HEAT switches (AFT and BULK) . . . . . . . . . . . OFF

FLIGHT DECK TEMPERATURE control . . . . . . . . . . . Full cool[Assists equipment cooling while operating in OVRD mode with only one air conditioning pack.]


LANDING ALTITUDE selector . . . . . . . . . . . . . . . . . . . . . .Set

FWD cargo fire – 7,500 feetAFT cargo fire – 7,500 feet

CABIN ALTITUDE AUTO RATE control . . . . . . . . . . . . MAX

PACK control selector (Either) . . . . . . . . . . . . . . . . . . . . OFF[Minimizes airflow around cargo compartment and slow loss of fire extinguishing agent.]


CARGO FIREMessage: AFT CARGO FIRE FWD CARGO FIRE

8.4 June 12, 2006





Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AccomplishDescend to 35,000 feet or below.

LANDING ALTITUDE selector . . . . . . . . . . . . . . . . . . . . . . . .SetSet landing field elevation prior to descent for landing.


WARNING:After landing, inform ground personnel not to open the cargo door until all passengers and crew have exited the airplane and fire fighting equipment is nearby.

Do not accomplish the following checklists:CARGO BOTTLEPACK OFFRECIRCULATION FAN

8.5June 12, 2006



Condition: The ENG BTL 1 DISCH or ENG BTL 2 DISCH light illuminated indicates that engine fire extinguisher bottle 1 or bottle 2 pressure is low.

ENGINE BOTTLEMessage: ENG BTL 1 ENG BTL 2

8.6 June 12, 2006



IntentionallyBlank

8.7June 12, 2006

















8.8 June 12, 2006


















go–around.


8.9June 12, 2006





8.10 June 12, 2006



IntentionallyBlank

8.11June 12, 2006



Condition: The L or R ENG OVHT light illuminated indicates an overheat is detected in the engine.

ENGINE BLEED AIR switch. . . . . . . . . . . . . . . . . . . . . . . . . OFF[Attempts to stop the flow of bleed air through the leak.]


Thrust lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RetardRetard thrust lever slowly until ENG OVHT light is no longer illuminated or thrust lever is closed.[Reduces temperature in the nacelle and strut.]

If ENG OVHT light no longer illuminated:

Operate engine at reduced thrust level for the remainder of flight.


GROUND PROXIMITY FLAPOVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRDNote: Use flaps 20 and Vref 20 for landing and flaps 5 for

go-around.

If ENG OVHT light remains illuminated:





ENGINE OVERHEATMessage: L ENG OVHT R ENG OVHT

8.12 June 12, 2006












8.13June 12, 2006






LEFT and RIGHT ISOLATION switches . . . . . . . . . . . . . .ON[Ensures bleed air is available to either engine’s starter.]








FUEL CONTROL switch (Affected engine) . . . . . . . .CUT OFF

8.14 June 12, 2006



Condition: The equipment cooling SMOKE light illuminated indicates smoke is detected in the forward equipment cooling ducts.

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . OVRDThe SMOKE light will extinguish when smoke clears.

If NO COOLING light illuminates after a one minute delay:

EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . .STBY

EQUIPMENT SMOKEMessage: FWD EQPT SMOKE

8.15June 12, 2006



Condition: The fire/overheat system FAIL light illuminated indicates an engine, APU, or cargo fire or overheat detection system is inoperative.

FIRE/OVERHEAT SYSTEMFAIL RESET switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Push

[Resets fault monitoring for the remaining systems.]

FIRE/OVERHEAT SYSTEMMessage: FIRE/OVHT SYS

8.16 June 12, 2006



IntentionallyBlank

8.17June 12, 2006



Condition: Smoke, fire, or fumes are identified

Diversion may be needed.Oxygen masks (As required) . . . . . . . . . . . . . . . . . . On, 100%

Crew communications. . . . . . . . . . . . . . . . . . . . . . . . Establish

Advise the cabin crew to turn off main IFE and PC power switches (As installed).Advise cabin crew that main cabin lighting will be turned off.UTILITY BUS switches (Both) . . . . . . . . . . . . . . . . . . . . . . . OFF

APU BLEED AIR switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Any time the smoke or fumes become the greatest threat, do the SMOKE OR FUMES REMOVAL checklist. If the source of the smoke, fire, or fumes is both obvious and can be extinguished quickly:

Source . . . . . . . . . . . . . . . . . . . . . . . Isolate and extinguish

If possible, remove power from the affected equipment by switch or circuit breaker in the flight deck or cabin.

If both of the following are true:• The source is visually confirmed to be

extinguished, and• The smoke or fumes are decreasingContinue the flight at the Captain’s discretion.Restore unpowered items at the Captain’s discretion.Do the SMOKE OR FUMES REMOVAL checklist if needed.


SMOKE OR FIRE OR FUMES

8.18 June 17, 2008




EQUIPMENT COOLING selector . . . . . . . . . . . . . . . . . . . .STBY[Selects standby fan operating mode to remove normal fan operations as a possible source of fumes.]

Initiate a diversion to the nearest suitable airport while continuing the checklist.Consider an immediate landing if the smoke, fire, or fumes situation becomes uncontrollable.Do not delay landing in an attempt to complete all of the following steps.LEFT AND RIGHT ISOLATION switches. . . . . . . . . . . . . . . OFF

[Isolates left and right sides of the bleed air system.]

RIGHT PACK CONTROL selector . . . . . . . . . . . . . . . . . . . . OFF[Removes right side of the air conditioning system as a possible source of smoke or fumes.]

Wait 2 minutes unless the smoke or fumes are increasing.[Allows time for the smoke or fumes to clear.]


RIGHT PACK CONTROL selector . . . . . . . . . . . . . . . . AUTO[Restores right side of the air conditioning system]

LEFT PACK CONTROL selector . . . . . . . . . . . . . . . . . . . OFF[Removes left side of the air conditioning system as a possible source of smoke or fumes]

Wait 2 minutes unless the smoke or fumes are increasing.

[Allows time for the smoke or fumes to clear.]


LEFT PACK CONTROL selector . . . . . . . . . . . . . . AUTO[Restores left side of the air conditioning system.]

Consider an immediate landing.


8.19June 17, 2008




Do the SMOKE OR FUMES REMOVAL checklist if needed.Do not accomplish the following checklists:

UTILITY BUS OFFPACK OFFRECIRCULATION FAN

8.20 June 17, 2008



Condition: Smoke or fumes removal is needed

Do this checklist only when directed by the SMOKE OR FIRE OR FUMES checklist.Do not delay landing in an attempt to complete the following steps.

WARNING:Do not turn an operating pack OFF. Selecting packs OFF will result in increased smoke concentrations. Do not activate passenger oxygen system.

Flight deck door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Close[Prevents smoke or fumes from penetrating onto flight deck.]

EQUIPMENT COOLING SELECTOR . . . . . . . . . . . . . . . . OVRD

LANDING ALTITUDE selector . . . . . . . . . . . . . . . . . . 9,500 feet

CABIN ALTITUDE AUTO RATE control . . . . . . . . . . . . . . MAX[Increases the ventilation rate.]

If smoke or fumes is persistent:

Descend to 9,500 feet or below as soon as conditions permit.

At 9,500 feet:


CABIN ALTITUDE MANUAL control . . . . . . . . . . .CLIMBPosition outflow valve fully open[Depressurizes the airplane and provides maximum ventilation rate.]


When smoke has dissipated:

EQUIPMENT COOLING selector . . . . . . . . . . . . . . .STBY


SMOKE OR FUMES REMOVAL

8.21June 17, 2008




Return to the SMOKE OR FIRE OR FUMES checklist and complete the remaining steps.

Condition: The WHL WELL FIRE light illuminated indicates a fire is detected in a main wheel well.

Observe gear EXTEND limit speed (270K/.82M).Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN

[Attempts to remove and extinguish the fire source.]


Note: Do not use FMC fuel predictions with gear extended.

Flight with gear down increases fuel consumption and decreases climb performance. Refer to Landing gear extended in the ODM ferry section for flight planning.If landing gear must be retracted for airplane performance:

When WHL WELL FIRE light is no longer illuminated:

Wait 20 minutes.[Attempts to ensure that wheel well fire is extinguished.]

Landing gear lever . . . . . . . . . . . . . . . . . . . UP, then OFF

WHEEL WELL FIREMessage: WHEEL WELL FIRE

8.22 June 17, 2008


Non-Normal Checklists Chapter NNCFlight Controls Section 9


Table of ContentsNNC.9 Non-Normal Checklists-Flight ControlsAILERON LOCKOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1

ALL FLAPS AND SLATS UP LANDING . . . . . . . . . . . . . . . . . . . 9.2AUTO SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3FLAP LOAD RELIEF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLIGHT CONTROL VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4JAMMED OR RESTRICTED FLIGHT CONTROLS . . . . . . . . . . 9.5LEADING EDGE SLAT ASYMMETRY . . . . . . . . . . . . . . . . . . . . 9.6LEADING EDGE SLAT DISAGREE . . . . . . . . . . . . . . . . . . . . . . . 9.8RUDDER RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.10SPEEDBRAKES EXTENDED . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.11SPOILERS [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.12SPOILERS [ADVISORY] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.13STABILIZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.14STABILIZER TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.15TAIL HYDRAULIC VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.16TRAILING EDGE FLAP ASYMMETRY . . . . . . . . . . . . . . . . . . . 9.17TRAILING EDGE FLAP DISAGREE . . . . . . . . . . . . . . . . . . . . . 9.18UNSCHEDULED STABILIZER TRIM . . . . . . . . . . . . . . . . . . . . 9.20WING HYDRAULIC VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.21YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.22

TOC.9.1June 12, 2006


Non-Normal Checklists -Flight Controls


IntentionallyBlank

TOC.9.2 June 12, 2006



Condition: The AIL LOCK light illuminated indicates an aileron lockout actuator disagrees with the commanded position.

At high airspeed, avoid large or abrupt control wheel inputs.At low airspeed, roll rates may be reduced.

AILERON LOCKOUTMessage: AILERON LOCKOUT

9.1June 12, 2006



Condition: Leading edge slats and trailing edge flaps cannot be extended.

CAUTION: Accomplish this checklist only when directed by the LEADING EDGE SLAT ASYMMETRY checklist.

Note: Do not slow below VREF 30 + 80 until established on final approach.

Note: Limit bank angle to 15 degrees below VREF 30 + 80.


ENGINE START selectors (Both) . . . . . . . . . . . . . . . . . . CONT


Use VREF 30 + 50 for landing.Refer to Non-Normal Maneuvers section in QRH for All Flaps and Slats Up Landing.

ALL FLAPS AND SLATS UP LANDING

9.2 June 12, 2006



Condition: The AUTO SPDBRK light illuminated indicates a fault is detected in the automatic speedbrake system.

Do not arm SPEEDBRAKE lever.[Prevents inadvertent inflight extension.]

Manually extend speedbrakes after landing.Note: Refer to ODM, Approach/Landing section, Dry

Landing Field Length, for landing distances.

AUTO SPEEDBRAKEMessage: AUTO SPEEDBRAKE

9.3June 12, 2006



Condition: The TRAILING EDGE light illuminated indicates the flap load relief system fails to operate when required.

Check flap position and maintain the appropriate speed.

Condition: The CONFIG light illuminated indicates the flaps are not in a takeoff position when either engine’s thrust is in the takeoff range on the ground.

Condition: The flight control shutoff OFF lights illuminated indicate two or more flight control valves are closed.

All switches must be ON for flight.

FLAP LOAD RELIEFMessage: FLAP LD RELIEF

FLAPSMessage: FLAPS

FLIGHT CONTROL VALVESMessage: FLT CONT VALS

9.4 June 12, 2006



Condition: Jammed or restricted flight controls is experienced in roll, pitch, or yaw.

Jammed or restricted system . . . . . . . . . . . . . . . . . OverpowerUse maximum force, including a combined effort of both pilots, if required.

Do not turn off any flight control hydraulic power switch.If freezing water is the suspected cause:

Consider descent to warmer air if conditions permit and reattempt to override the jammed or restricted controls.

If the faulty system cannot be overpowered:

Use operative flight controls, trim, and thrust as required for airplane control.

Plan to land at the nearest suitable airport

JAMMED OR RESTRICTED FLIGHT CONTROLS

9.5June 12, 2006



Condition: The LEADING EDGE light illuminated indicates the leading edge slats are not symmetrically extended.

CAUTION: Do not arm the leading edge (LE) alternate flaps switch.

Note: Do not use FMC fuel predictions with flaps extended.


If indicated flap position greater than 20:

Use current flaps and VREF 30 + 20 for landing.

If indicated flap position 20 or less:


ENGINE START selectors (Both) . . . . . . . . . . . . . . . . CONT

FLAP lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract trailing edge flaps as required.


LEADING EDGE SLAT ASYMMETRYMessage: LE SLAT ASYM

9.6 June 12, 2006




If unable to extend or retract trailing edge flaps using FLAP lever:

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . .SetPosition to agree with FLAP lever.

TRAILING EDGE (TE) ALTERNATEFLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . .SetExtend or retract trailing edge flaps as required.Use trailing edge flaps 20 and VREF 30 + 30 for landing.


Note: Autothrottle may disconnect during alternate flap extension.

If unable to extend trailing edge flaps and the flap indicator is less than 5:

Do not accomplish the following checklists:TRAILING EDGE FLAP ASYMMETRYTRAILING EDGE FLAP DISAGREE

Accomplish the ALL FLAPS AND SLATS UP LANDING checklist.

9.7June 12, 2006



Condition: The LEADING EDGE light illuminated indicates the leading edge slat positions disagree with commanded position.



Use current flaps and VREF 20 for landing.


Use flaps 20 and VREF 20 for landing.

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetIf FLAP lever position 20 or less, position selector to agree with FLAP lever.If FLAP lever position greater than 20, position selector to 20.

LEADING EDGE (LE) ALTERNATE FLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

If, after selecting ALTN, the LEADING EDGE light remains illuminated:

LEADING EDGE (LE) ALTERNATE FLAPSswitch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Accomplish the LEADING EDGE SLAT ASYMMETRY checklist.


LEADING EDGE SLAT DISAGREEMessage: LE SLAT DISAGREE

9.8 June 12, 2006




If indicated flap position 20 or less: (continued)

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract leading edge slats as required.Use flaps 20 and VREF 20 for landing.

FLAP lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract trailing edge flaps as required.

If unable to extend or retract trailing edge flaps using FLAP lever:

Do not accomplish the following checklist:TRAILING EDGE FLAP DISAGREE

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . .SetPosition to agree with Flap lever.


ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . .SetExtend or retract trailing edge flaps as required.

9.9June 12, 2006



Condition: The RUDDER RATIO light illuminated indicates the rudder ratio system has failed.

Above 160 knots, avoid large or abrupt rudder inputs.If normal left hydraulic system pressure is available:

Crosswind limit is 15 knots.

Do not attempt autoland.

RUDDER RATIOMessage: RUDDER RATIO

9.10 June 12, 2006



Condition: The SPEED BRAKES light illuminated indicates the speedbrakes are extended when the flaps are in a landing position, or when the radio altitude is 800 feet or below.

SPEEDBRAKES EXTENDEDMessage: SPEEDBRAKES EXT

9.11June 12, 2006



Condition: The CONFIG light illuminated indicates the SPEEDBRAKE lever is not DOWN when either engine’s thrust is in the takeoff range on the ground.

SPOILERS [WARNING]

Message: SPOILERS

9.12 June 12, 2006



Condition: The SPOILERS light illuminated indicates that one or more spoiler pairs are inoperative.

Roll rate may be reduced in flight.Speedbrake effectiveness may be reduced in flight and during landing.

SPOILERS [ADVISORY]

Message: SPOILERS

9.13June 12, 2006



Condition: The CONFIG light illuminated indicates the stabilizer is not within the greenband with either engine’s thrust in the takeoff range on the ground.

STABILIZERMessage: STABILIZER

9.14 June 12, 2006



Condition: The STAB TRIM light illuminated indicates the stabilizer trim rate is one–half of the normal control wheel stabilizer trim switch rate.

If normal stabilizer trim rate desired:

ALTERNATE STABILIZER TRIMswitches / levers (Both) . . . . . . . . . . . . . . . . . . . . . . . . Push

Push and hold when trim is desired.[May allow stabilizer to trim at the normal rate.]

STABILIZER TRIMMessage: STAB TRIM

9.15June 12, 2006



Condition: A tail flight control shutoff OFF light illuminated indicates the tail flight control valve is closed.


TAIL HYDRAULIC VALVEMessage: C TAIL HYD VAL

L TAIL HYD VALR TAIL HYD VAL

9.16 June 12, 2006



Condition: The TRAILING EDGE light illuminated indicates the trailing edge flaps are not symmetrically extended.

Note: Accomplish this checklist when directed by the TRAILING EDGE FLAP DISAGREE checklist.

CAUTION: Do not arm the TRAILING EDGE (TE) ALTERNATE FLAPS switch.

Note: Do not use FMC fuel predictions with flaps extended.


If indicated flap position at or greater than 20:

Use VREF 20 for landing.

If indicated flap position greater than 5 and less than 20:

Use VREF 30 + 20 for landing.


Use VREF 30 + 30 for landing.


TRAILING EDGE FLAP ASYMMETRYMessage: TE FLAP ASYM

9.17June 16, 2008



Condition: The TRAILING EDGE light illuminated indicates the trailing edge flap positions disagree with commanded position.

Note: Check that the FLAP lever is secure in the desired detent.



Use current flaps and VREF 20 for landing.



ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetIf FLAP lever position 20 or less, position selector to agree with FLAP lever.If FLAP lever position greater than 20, position selector to 20.

TRAILING EDGE (TE) ALTERNATEFLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

If, after selecting ALTN, the TRAILING EDGE light remains illuminated:

TRAILING EDGE (TE) ALTERNATEFLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Accomplish the TRAILING EDGE FLAP ASYMMETRY checklist.


TRAILING EDGE FLAP DISAGREEMessage: TE FLAP DISAGREE

9.18 June 16, 2008




If indicated flap position 20 or less: (continued)

If, after selecting ALTN, the TRAILING EDGE light is extinguished:

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . .SetExtend or retract flaps as required.Use flaps 20 and VREF 20 for landing.

FLAP lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SetPosition to agree with ALTERNATE FLAPS selector.[Extends or retracts leading edge slats.]

If leading edge slats fail to extend or retract using FLAP lever:

LEADING EDGE (LE) ALTERNATE FLAPS switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

9.19June 16, 2008



Condition: The UNSCHED STAB TRIM light illuminated indicates uncommanded stabilizer motion is detected.

STABILIZER TRIM CUT OUT switches (Both) . . . . . CUT OUT[Prevents subsequent uncommanded or inappropriate stabilizer motion.]

AUTOPILOT DISENGAGE switch . . . . . . . . . . . . . . . . . . . PushHigher than normal control column force may be required to prevent unwanted pitch change during autopilot disengagement.

CENTER STABILIZER TRIM CUT OUT switch . . . . . . . . NORMVerify proper stabilizer trim movement.

If unscheduled trim occurs:

CENTER STABILIZER TRIMCUT OUT switch . . . . . . . . . . . . . . . . . . . . . . . . . . CUT OUT

LEFT STABILIZER TRIMCUT OUT switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM

Verify proper stabilizer trim movement.

If unscheduled trim occurs:

LEFT STABILIZER TRIMCUT OUT switch . . . . . . . . . . . . . . . . . . . . . . . . CUT OUT

Do not accomplish the following checklist:STABILIZER TRIM

UNSCHEDULED STABILIZER TRIMMessage: UNSCHD STAB TRIM

9.20 June 12, 2006



Condition: A wing flight control shutoff OFF light illuminated indicates the wing flight control valve is closed.


WING HYDRAULIC VALVEMessage: C WING HYD VAL

L WING HYD VALR WING HYD VAL

9.21June 12, 2006



Condition: The yaw damper INOP light illuminated indicates the yaw damper is inoperative.

YAW DAMPER switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

YAW DAMPERMessage: L YAW DAMPER R YAW DAMPER

9.22 June 12, 2006


Non-Normal Checklists Chapter NNCFlight Instruments, Displays Section 10


Table of ContentsNNC.10 Non-Normal Checklists-Flight Instruments, DisplaysADI OR HSI BLANK OR ABNORMAL . . . . . . . . . . . . . . . . . . . 10.1

AIRSPEED OR ALTIMETER FAIL . . . . . . . . . . . . . . . . . . . . . . . 10.1AIRSPEED UNRELIABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.2ALTITUDE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.4ATTITUDE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5IAS DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5INSTRUMENT SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6RADIO ALTIMETER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6

TOC.10.1June 12, 2006


Non-Normal Checklists -Flight Instruments, Displays


IntentionallyBlank

TOC.10.2 June 12, 2006



Condition: ADI or HSI is blank or displaying abnormal data.

EFI SOURCE SELECTswitch (Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

Condition: Airspeed or altimeter indicator(s) have failed or displaying abnormal data.

AIR DATA SOURCEswitch (Affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTNNote: TAS/SAT indicator is supplied data from right ADC

only. It does not switch to opposite ADC when ALTN is pushed.

Note: MNPS Airspace In-flight contingencies found on applicable charts.


ADI OR HSI BLANK OR ABNORMAL

AIRSPEED OR ALTIMETER FAIL

10.1June 12, 2006



Condition: Airspeed/Mach indication is suspected to be unreliable.

One or more of the following may be evidence of unreliable airspeed/Mach indication:• Speed/altitude information not consistent with pitch

attitude and thrust setting• Speed/Airspeed/Mach failure flags• Blank or fluctuating airspeed displays• Variation between Captain and First Officer airspeed

displays• Amber line through one or more ADI flight mode

annunciations• Overspeed indications• Radome damage or loss• Simultaneous overspeed and stall warnings• Display of one or more of the following EICAS messages:

Pitch attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . Check

If pitch attitude or thrust is not normal for phase of flight:

AUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISENGAGE

AUTOTHROTTLE . . . . . . . . . . . . . . . . . . . . . . . . .Disconnect

FLIGHT DIRECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . AdjustEstablish normal pitch attitude and thrust setting for phase of flight.

Note: Normal pitch attitude and thrust settings are available in the ODM, ABNORMAL section, OPERATION WITHOUT AIRSPEED INDICATION.


AIRSPEED UNRELIABLE

AILERON LOCKOUTALT DISAGREECAPT PITOTF/O PITOTIAS DISAGREE

L AUX PITOTOVERSPEEDPROBE HEATR AUX PITOTRUDDER RATIO

10.2 June 12, 2006




Altitude information, vertical speed information, limit N1/EPR, Reference N1/EPR, and N1/EPR bug may be unreliable.Note: Flight may not be permitted in RVSM airspace.


Speed indications . . . . . . . . . . . . . . . . . . . . . . . . .Cross checkCross check Captain and First Officer airspeed indications and standby airspeed indicator. An airspeed display differing by more than 15 knots from the standby indicator should be considered unreliable.

If the reliable airspeed data source can be determined:

AIR DATA SOURCEswitch (Unreliable side) . . . . . . . . . . . . . . . . . . . . . . . .ALTN

Invalid overspeed warning and invalid input to AFDS and autothrottle may occur or continue.

If the reliable airspeed data source cannot be determined:

Attitude and thrust . . . . . . . . . . . . . . . . . . . . . . . . . . .AdjustMaintain normal pitch attitude and thrust setting for phase of flight. Refer to the ODM, ABNORMAL section, OPERATION WITHOUT AIRSPEED INDICATION.

------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Maintain visual conditions if possible.

Establish landing configuration early.

Use electronic and visual glideslope indicators, where available, for approach and landing.

Refer to IRS ground speed on the CDU POS REF page and reported wind on approach.

10.3June 12, 2006



Condition: Captain’s and First Officer’s altitude indications disagree.


Transponder altitude received by ATC may be unreliable.----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Maintain visual conditions if possible.Establish landing configuration early.Radio altitude reference available below 2,500 feet.Use electronic and visual glide slope indicators, where available, for approach and landing.

ALTITUDE DISAGREEMessage: ALT DISAGREE

10.4 June 12, 2006



Condition: Captain’s and First Officer’s attitude indications disagree.

Condition: Captain’s and First Officer’s airspeed indications disagree.

Accomplish AIRSPEED UNRELIABLE checklist.

ATTITUDE DISAGREEMessage: ATT DISAGREE

IAS DISAGREEMessage: IAS DISAGREE

10.5June 12, 2006



Condition: Both EFI switches are in the ALTN position.

Both ADIs and HSIs are displaying information from the center symbol generator.

Condition: RA flag is displayed on ADI.


INSTRUMENT SWITCHMessage: INSTR SWITCH

RADIO ALTIMETER

10.6 June 12, 2006


Non-Normal Checklists Chapter NNCFMC Management, Navigation Section 11


Table of ContentsATC FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.1BOTH FMCS AND CDUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.2COMPLETE FMC/CDU/IRU FAILURE . . . . . . . . . . . . . . . . . . . . . 11.3FMC FAIL

Alternate navigation system installed [NAVIGATION SOURCE selector] . . . . . . . . . . . . . . . . . . . . . 11.4

Alternate navigation system not installed [FMC SOURCE SELECT switch] . . . . . . . . . . . . . . . . . . . . . . 11.6

FMC MESSAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7

GPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7ILS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7IRS DC FAIL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8IRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8IRS ON DC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8RADAR MALFUNCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.9UNABLE RNP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.10

TOC.11.1June 16, 2008


Non-Normal Checklists -FMC Management, Navigation


IntentionallyBlank

TOC.11.2 June 16, 2008



Condition: The ATC FAIL light illuminated indicates the selected transponder has failed.


ATC FAULTMessage: ATC FAULT

11.1June 16, 2008



Condition: Both FMCs and CDUs have failed.

Alternate navigation system not availableHDG SEL switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Push

If in navigation radio range:

Do not initiate flight into MNPS airspace.

Manually tune navigation radios.

0171 through 0199, 1200 through 1201, 1401 through 1404,1501 through 1506, 1521, 1601 through 1708If out of navigation radio range:

HDG REF switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRUENote: True track will be displayed at the top of the HSI.

IRS DISPLAY SELECT . . . . . . . . . . . . . . . . . . . . . . . . . PPOSNote time crossing last waypoint.Select appropriate average true course for route of flight from Part II, Loss of Nav Data, of the flight plan.Turn to a heading to maintain the average true course.Monitor track (TK) and update to maintain constant trackPlot position frequently, suggest every 2 degrees.Approaching next waypoint, select and monitor PPOS in the IRS display window and adjust heading to cross waypoint at correct LAT/LON.Repeat above steps for each oceanic route segment of flight until within radio navigation range.

CAUTION: When in radar contact return heading reference switch to NORM.

BOTH FMCS AND CDUS FAILMessage: L FMC FAIL R FMC FAIL

11.2 June 16, 2008



Condition: The magnetic compass is the only source of heading information available with a complete failure of all IRUs, FMCs, and CDUs.

The LOSS OF NAV DATA section of the master flight plan must be used and includes the following data:

Mid-point magnetic headings based on forecast winds.Zone distances and times for each leg of the flight plan.

To fly the correct magnetic heading (M/H):

Apply compass deviation to average M/H published.Obtain M/H to next fix by reading the NAV DATA information straight acrossUse the deviation correction derived from the COMPASS CARD. If updated wind data from Flight Control or other aircraft becomes available adjust the M/H accordingly.

Note: Use the LOSS OF NAV DATA information to compute ETAs, position report information, etc.

Note: Use ADF, VOR, or HF/VHF steer, if available. Watch for contrails or position of other aircraft to aid in maintaining as close to desired track as possible.

COMPLETE FMC/CDU/IRU FAILUREMessage: L FMC FAIL

L IRS FAULTC IRS FAULT

R FMC FAILR IRS FAULT

11.3June 16, 2008



Alternate navigation system installed[NAVIGATION SOURCE selector]

Condition: The FMC FAIL light illuminated indicates the FMC has failed.

If a single FMC failed:

NAVIGATION SOURCEselector (Select operable FMC) . . . . . . . .FMC - L / FMC - R

Select both pilots HSI range selectors to the same position.Select Left, Center or Right autopilot on side with operating FMC.If necessary, re-engage autothrottles.During VOR approaches, one pilot must have raw data from the VOR associated with the approach displayed on the RDMI (RMI) or HSI in a VOR mode, no later than the final approach fix.

Note: Flight into MNPS airspace is authorized with one FMC and alternate navigation system operable.


FMC FAIL

Message: L FMC FAIL R FMC FAIL

11.4 June 16, 2008




If both FMCs failed:

Select autopilot roll and pitch modes appropriate for the desired flight path.

[LNAV and VNAV modes fail when both FMCs fail.]

Do not initiate flight into MNPS airspace if in radio navigation range.

NAVIGATION SOURCEselector (Captain’s) . . . . . . . . . . . . . . . . . . . . . . . . . .CDU - L

NAVIGATION SOURCEselector (First Officer’s) . . . . . . . . . . . . . . . . . . . . . .CDU - R

Route modifications must be entered into both CDUs. Enter any new waypoints by latitude and longitude.

Manually tune navigation radios.

Refer to ODM for VREF speed and other applicable performance information.

11.5June 16, 2008



Alternate navigation system not installed[FMC SOURCE SELECT switch]

Condition: The FMC FAIL light illuminated indicates the FMC has failed.

FMC SOURCE SELECT switch . . . . . . . . . . . . . . . . . . . . .ALTN

Select both pilots HSI range selectors to the same position.If necessary, re-engage autothrottles.If left FMC failed:

Use right autopilot.[Allows LNAV and VNAV operation.]

If right FMC failed:

Use left or center autopilot.[Allows LNAV and VNAV operation.]

Do not initiate flight into MNPS airspace if in radio navigation range.During VOR approaches, one pilot must have raw data from the VOR associated with the approach displayed on the RDMI (RMI) or HSI in VOR mode, no later than the final approach fix.

FMC FAIL

Message: L FMC FAIL R FMC FAIL

11.6 June 16, 2008



Condition: The FMC light illuminated indicates a message in the FMC scratchpad.

If the CDU message is FUEL QTY ERROR–PROG 2, FUEL DISAGREE–PROG 2 or INSUFFICIENT FUEL:

Accomplish the following checklist:ENGINE FUEL LEAK

For all other messages:

Take action as required by the message.

Condition: GPS has failed.

If L GPS or R GPS message is displayed:

The indicated GPS has failed.

If GPS message is displayed:

Both GPSs have failed.

Condition: LOC or G/S failure flags are displayed on ADI.


FMC MESSAGEMessage: FMC MESSAGE

GPSMessage: L GPS

GPSR GPS

ILS FAIL

11.7June 16, 2008



Condition: The IRS DC FAIL light illuminated indicates the IRS DC backup power has failed and the IRS AC normal power is being used.

Condition: The IRS FAULT light illuminated indicates an IRS fault is detected.

If the left IRS FAULT light is illuminated:

IRS SOURCE SELECT switch (Captain’s) . . . . . . . . . .ALTN

If the right IRS FAULT light is illuminated:

IRS SOURCE SELECT switch (First Officer’s) . . . . . .ALTN

Condition: The IRS ON DC light illuminated indicates IRS AC normal power has failed and the IRS DC backup power is being used.

IRS DC FAILMessage: L IRS DC FAIL

C IRS DC FAILR IRS DC FAIL

IRS FAULTMessage: L IRS FAULT

C IRS FAULTR IRS FAULT

IRS ON DCMessage: L IRS ON DC

C IRS ON DCR IRS ON DC

11.8 June 16, 2008



Condition: MAJOR FAULTS.

If one or more of the following codes appear on the radar scope:

MODE selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents possible further damage.]

PARTIAL FAILURESWhen the system is in WX or MAP mode, partial failures will appear as yellow caution annunciations in the corner of the display unit. Radar data will still be displayed but the flight crew should be aware that the display may not be accurate.

RADAR MALFUNCTIONS

R/T FAULT IND FAULTANT FAULT ATT FAULTCON FAULT COOL FAULT

ANNUNCIATION EFFECT/CREW ACTIONCAL Weak targets, use caution.STAB System stabilized with respect to

aircraft, no pitch or rollstabilization.

COOL System may fail if operation iscontinued. Use only long enough toanalyze weather, then turn off toallow cooling of the transceiver.

11.9June 16, 2008



Condition: Navigation performance not meeting required accuracy.

If on a procedure or airway that has an RNP alerting requirement:

Select alternate procedure or airway, or initiate a go–around.

If on a procedure or airway without RNP:

Verify position.

UNABLE RNPMessage: UNABLE RNP

11.10 June 16, 2008


Non-Normal Checklists Chapter NNCFuel Section 12


Table of ContentsNNC.12 Non-Normal Checklists-FuelENGINE FUEL LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.1

FUEL CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.6FUEL CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.8FUEL JETTISON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.9FUEL JETTISON NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.10FUEL JETTISON PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11FUEL JETTISON TRANSFER VALVE . . . . . . . . . . . . . . . . . . . 12.11FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12FUEL SPAR VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.13FUEL SYSTEM PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.14LOW FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.15LOW FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.16

TOC.12.1June 16, 2008


Non-Normal Checklists -Fuel


IntentionallyBlank

TOC.12.2 June 16, 2008










ENGINE FUEL LEAK

12.1June 12, 2006










12.2 June 12, 2006






Thrust lever (Affected engine) . . . . . . . . . . . . . . . . . . Close














WING ANTI-ICEselector / switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF



12.3June 12, 2006









for go–around.








12.4 June 12, 2006



IntentionallyBlank

12.5June 12, 2006



Condition: The FUEL CONFIG light illuminated indicates both center pump switches are off with fuel in the center tank, or a fuel imbalance between main tanks, or fuel quantity is low in either main tank.

The FUEL CONFIGURATION message may be caused by an engine fuel leak. For indications of an engine fuel leak, check:

• total fuel quantity remaining compared to planned fuel remaining

• fuel flow indications, for an engine with excessive fuel flow

• individual tank quantities• totalizer compared to calculated quantities (PROGRESS

page2). The TOTALIZER value is the sum of the individual tank quantities. The CALCULATED value is the totalizer value at engine start minus fuel used (calculated using fuel flow rates and time).

If there is any indication of an engine fuel leak:

Accomplish the ENGINE FUEL LEAK checklist.

If the FUEL CONFIGURATION message occurs without any indications of an engine fuel leak:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . .ON[Allows fuel from the high tank to feed both engines.]

FORWARD and AFT FUEL PUMP switches(Low tank) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Allows fuel from the high tank to feed both engines.]


FUEL CONFIGURATIONMessage: FUEL CONFIG

12.6 June 12, 2006




If the FUEL CONFIGURATION message occurs without any indications of an engine fuel leak: (continued)

When fuel balancing complete:

FORWARD and AFT FUEL PUMP switches(All) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

[Restores fuel feed from the low tank.]

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . OFF[Restores main tank–to–engine fuel feed.]

If fuel quantity is low in either main tank:

Accomplish the LOW FUEL checklist.

12.7June 12, 2006



Condition: The VALVE light illuminated indicates the fuel crossfeed valve position disagrees with commanded position.

0121, 0124 through 0139, 0171 through 0180:

If VALVE is failed closed, vary engine thrust as required to maintain fuel balance, flight conditions permitting.

0181 through 0199, 1200 through 1201, 1401 through 1404,1501 through 1506, 1521, 1601 through 1708:

If both FUEL CROSSFEED switches ON and one valve is open, fuel will crossfeed.

FUEL CROSSFEEDMessage: AFT FUEL X-FEED

FUEL CROSSFEEDFWD FUEL X-FEED

12.8 June 16, 2008




Condition: Fuel jettison must be accomplished.

FUEL JETTISON selector . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

FUEL JETTISON NOZZLE switches (Both) . . . . . . . . . . . . .ONFuel jettison is from center tank only.Time required to empty full center tank is approximately 30 minutes.

When jettison is complete:

FUEL JETTISON NOZZLE switches (Both) . . . . . . . . . . OFF

FUEL JETTISON selector . . . . . . . . . . . . . . . . . . . . . . . . OFF----------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST

Verify VREF speed for new gross weight.Do not accomplish the following checklist:

WINDOW (HEAT)

FUEL JETTISON

12.9June 12, 2006




Condition: The Fuel Jettison Nozzle VALVE light illuminated in flight indicates the associated fuel nozzle valve is not in the commanded position. The VALVE light illuminated on the ground indicates one or both fuel nozzle valves are open.

In flight:

If FUEL JETTISON NOZZLE switch ON:

Fuel jettison time will be extended.

If FUEL JETTISON NOZZLE switch OFF:

Fuel Jettison Nozzle valve failed open.

On ground:

FUEL JETTISON NOZZLE switches . . . . . . . . . . . . . . . . OFF

FUEL JETTISON NOZZLE

Message: FUEL JET NOZ

12.10 June 12, 2006




Condition: The fuel jettison FAULT light illuminated indicates the associated fuel jettison pump is inoperative.



Condition: The fuel jettison FAULT light illuminated indicates the associated fuel jettison transfer valve is not in the commanded position.

If FUEL JETTISON selector is ON;


If FUEL JETTISON selector is OFF;

Fuel jettison valve has failed open.

FUEL JETTISON PUMP

Message: L FUEL JET PUMP R FUEL JET PUMP

FUEL JETTISON TRANSFER VALVE

Message: L JET XFER VALVE R JET XFER VALVE

12.11June 12, 2006



Condition: A fuel pump PRESS light illuminated indicates fuel pump output pressure is low.

Do not reset any tripped fuel pump circuit breaker.If either center pump PRESS light illuminated:

PUMP switch (Affected pump) . . . . . . . . . . . . . . . . . . . . OFF

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . .ON[Prevents fuel imbalance by feeding both engines from the same center fuel pump.]

When center tank fuel depleted:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . OFF

If both center pump PRESS lights illuminated:

PUMP switches (Both) . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . OFF

Check available left and right main tank quantity is sufficient for the planned flight.

[Center tank fuel is not available.]

If either a left or a right main pump PRESS light illuminated:

PUMP switch (Affected pump) . . . . . . . . . . . . . . . . . . . . OFF

FUEL PUMPMessage: CTR L FUEL PUMP

L AFT FUEL PUMPL FWD FUEL PUMP

CTR R FUEL PUMPR AFT FUEL PUMPR FWD FUEL PUMP

12.12 June 16, 2008



Condition: The SPAR VALVE light illuminated indicates the spar valve position disagrees with commanded position.

On the ground:

Do not attempt engine start.[Prevents possibility of not being able to shutdown the engine if the engine fuel valve subsequently fails open.]

FUEL SPAR VALVEMessage: L FUEL SPAR VAL R FUEL SPAR VAL

12.13June 16, 2008



Condition: All PRESS lights on one side illuminated with fuel crossfeed valve closed indicate the respective engine is on suction feed.

Note: At high altitude, thrust deterioration or engine flameout may occur.

If unable to maintain required thrust on affected engine:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . . . . .ON[Allows fuel feed from operative pump side.]

Note: Continued operation with the fuel crossfeed valve open will result in a progressive fuel imbalance when both engines are feeding from the same main tank.

Do not balance fuel.

Do not accomplish the following checklist:FUEL CONFIGURATION

When FUEL CONFIG light illuminates due to main tank imbalance:

FUEL CROSSFEED switch(es) . . . . . . . . . . . . . . . . . OFF

Continue suction feed operation. Sufficient roll control is available to compensate for any main tank fuel imbalance.

If unable to maintain required thrust on affected engine, operate at lower altitude.

FUEL SYSTEM PRESSUREMessage: L FUEL SYS PRESS R FUEL SYS PRESS

12.14 June 16, 2008



Condition: The FUEL CONFIG light illuminated indicates fuel quantity is low in either left or right main tank.

The LOW FUEL message may be caused by an engine fuel leak. For indications of an engine fuel leak, check:

• total fuel quantity remaining compared to planned fuel remaining

• fuel flow indications, for an engine with excessive fuel flow

• individual tank quantities• totalizer compared to calculated quantities (PROGRESS

page2). The TOTALIZER value is the sum of the individual tank quantities. The CALCULATED value is the totalizer value at engine start minus fuel used (calculated using fuel flow rates and time).

If there is any indication of an engine fuel leak:

Accomplish the ENGINE FUEL LEAK checklist.

If the LOW FUEL message occurs without any indication of an engine fuel leak:





LOW FUEL Message: LOW FUEL

12.15June 16, 2008



Condition: Fuel temperature is approaching minimum.

When fuel temperature is approaching fuel temperature limit (3° C above the fuel freeze point):

Increase speed, change altitude, and or deviate to a warmer air mass to achieve a TAT equal to or higher than the fuel temperature limit.

TAT will increase approximately 0.5 to 0.7° C for each .01 Mach increase in speed. In extreme conditions it may be necessary to descend as low as FL250.

LOW FUEL TEMPERATURE

12.16 June 16, 2008


Non-Normal Checklists Chapter NNCHydraulics Section 13


Table of Contentsf NNC.13 Non-Normal Checklists-HydraulicsDEMAND HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . 13.1

HYDRAULIC DEMAND PUMP . . . . . . . . . . . . . . . . . . . . . . . . . 13.1HYDRAULIC (1 OR 2) OVERHEAT . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC PRIMARY (1 OR 2) . . . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC PRIMARY PUMP . . . . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC QUANTITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.3HYDRAULIC SYSTEM PRESSURE (C ONLY) . . . . . . . . . . . . . 13.4HYDRAULIC SYSTEM PRESSURE (L ONLY) . . . . . . . . . . . . . 13.7HYDRAULIC SYSTEM PRESSURE (R ONLY) . . . . . . . . . . . . . 13.8HYDRAULIC SYSTEM PRESSURE (L AND C) . . . . . . . . . . . 13.10HYDRAULIC SYSTEM PRESSURE (L AND R) . . . . . . . . . . . 13.13HYDRAULIC SYSTEM PRESSURE (R AND C) . . . . . . . . . . . 13.14PRIMARY HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . 13.17RAT UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.18

TOC.13.1June 12, 2006


Non-Normal Checklists -Hydraulics


IntentionallyBlank

TOC.13.2 June 12, 2006



Condition: The demand pump OVHT light illuminated indicates the demand pump temperature is high.

DEMAND PUMP selector . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Attempts to eliminate source of overheat.]

Do not accomplish the following checklist:HYDRAULIC DEMAND PUMP

Condition: The demand pump PRESS light illuminated indicates the demand pump output pressure is low.

DEMAND PUMP selector . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

If PRESS light remains illuminated:

DEMAND PUMP selector . . . . . . . . . . . . . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

DEMAND HYDRAULIC OVERHEATMessage: C DEM HYD OVHT

L DEM HYD OVHTR DEM HYD OVHT

HYDRAULIC DEMAND PUMPMessage: C HYD DEM PUMP

L HYD DEM PUMPR HYD DEM PUMP

13.1June 12, 2006



Condition: The electric primary pump OVHT light illuminated indicates the electric pump temperature is high.

ELECTRIC PRIMARY PUMP switch . . . . . . . . . . . . . . . . . . OFF[Attempts to eliminate source of overheat.]

Do not accomplish the following checklist:HYDRAULIC PRIMARY (1 OR 2)

Condition: The electric primary pump PRESS light illuminated indicates the electric pump output pressure is low.

ELECTRIC PRIMARY PUMP switch . . . . . . . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Condition: The engine primary pump PRESS light illuminated indicates the engine pump output pressure is low.

ENGINE PRIMARY PUMP switch . . . . . . . . . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

HYDRAULIC (1 OR 2) OVERHEATMessage: C HYD 1 OVHT C HYD 2 OVHT

HYDRAULIC PRIMARY (1 OR 2)Message: C HYD PRIM 1 C HYD PRIM 2

HYDRAULIC PRIMARY PUMPMessage: L HYD PRIM PUMP R HYD PRIM PUMP

13.2 June 12, 2006



Condition: The RSVR light illuminated indicates hydraulic quantity is low.

HYDRAULIC QUANTITYMessage: C HYD QTY

L HYD QTYR HYD QTY

13.3June 12, 2006



Condition: Only the center hydraulic SYS PRESS light illuminated indicates center hydraulic system pressure is low.

DEMAND PUMP selector (Center) . . . . . . . . . . . . . . . . . . . .ON

If SYS PRESS light remains illuminated:

DEMAND PUMP selector (Center) . . . . . . . . . . . . . . . . . OFF

ELECTRIC PRIMARY PUMP switches (Both) . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Note: Inoperative items:• C autopilot• R autopilot stabilizer trim (use the L autopilot).• automatic speedbrake

Note: Autoland not authorized.



HYDRAULIC SYSTEM PRESSURE (C ONLY)

Message: C HYD SYS PRESS

13.4 June 16, 2008




If SYS PRESS light remains illuminated: (continued)------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST


ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetPosition to agree with FLAP lever.

LEADING EDGE (LE) ALTERNATE FLAPSswitch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

TRAILING EDGE (TE) ALTERNATE FLAPSswitch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTN

If FLAP lever in UP position:

FLAP lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1[Prevents uncommanded autothrottle disengagement.]

ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract flaps as required.Use flaps 20and VREF 20 for landing.

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF[Prevents gear door interference during extension.]

ALTERNATE GEAR EXTENDswitch (Max 250K/.75M) . . . . . . . . . . . . . . . . . . . . . . . . . . DN

After gear down lights illuminate:

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN


13.5June 12, 2006




If SYS PRESS light remains illuminated: (continued)

RESERVE BRAKES/STEERING switch . . . . . . . . . . . . . .ON[Provides nose wheel steering and reserve brakes capability.]

If center electric primary 1 hydraulic pump PRESS light remains illuminated:

Nose wheel steering is inoperative.

Do not accomplish the following checklists:GEAR DOORSHYDRAULIC DEMAND PUMPHYDRAULIC PRIMARY (1 OR 2)RESERVE BRAKE VALVE

13.6 June 12, 2006



Condition: Only the left hydraulic SYS PRESS light illuminated indicates left hydraulic system pressure is low.

DEMAND PUMP selector (Left) . . . . . . . . . . . . . . . . . . . . . . .ON


DEMAND PUMP selector (Left). . . . . . . . . . . . . . . . . . . . OFF

ENGINE PRIMARY PUMP switch (Left) . . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Note: Inoperative items:• L autopilot

0121, 0124 through 0139, 0171 through 0199, 1200 through 1201,1401 through 1404:

• L thrust reverserNote: Autoland not authorized.

Do not accomplish the following checklists:HYDRAULIC DEMAND PUMPHYDRAULIC PRIMARY PUMP

HYDRAULIC SYSTEM PRESSURE (L ONLY)

Message: L HYD SYS PRESS

13.7June 16, 2008



Condition: Only the right hydraulic SYS PRESS light illuminated indicates right hydraulic system pressure is low.

DEMAND PUMP selector (Right) . . . . . . . . . . . . . . . . . . . . .ON


DEMAND PUMP selector (Right) . . . . . . . . . . . . . . . . . . OFF

ENGINE PRIMARY PUMP switch (Right) . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Note: Inoperative items:• R autopilot• autobrakes


• R thrust reverserNote: Autoland not authorized.


HYDRAULIC SYSTEM PRESSURE (R ONLY)

Message: R HYD SYS PRESS

13.8 June 16, 2008



IntentionallyBlank

13.9June 12, 2006



Condition: Both the left and center hydraulic SYS PRESS lights illuminated indicate left and center hydraulic system pressures are low.

DEMAND PUMP selectors (Left and center) . . . . . . . . . . . .ON

If SYS PRESS lights remain illuminated:

DEMAND PUMP selectors (Left and center) . . . . . . . . . OFF

ELECTRIC PRIMARY PUMP switches (Both) . . . . . . . . OFF

ENGINE PRIMARY PUMP switch (Left) . . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Plan to land at the nearest suitable airport.Note: Inoperative items:

• automatic speedbrakes• elevator feel• all autopilots• stabilizer trim operates at 1/4 rate with yoke

switches only


• L thrust reverserNote: Autoland not authorized.


Use flaps 20 and VREF 30 + 20 for landing.


HYDRAULIC SYSTEM PRESSURE (L AND C)

Message: L and C HYD SYS PRESS

13.10 June 16, 2008




If SYS PRESS lights remain illuminated: (continued)------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST







ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract flaps as required.Use flaps 20 and VREF 30 + 20 for landing .






13.11June 12, 2006




If SYS PRESS lights remain illuminated: (continued)




Do not accomplish the following checklists:GEAR DOORSHYDRAULIC DEMAND PUMPHYDRAULIC PRIMARY (1 OR 2)RESERVE BRAKE VALVE

13.12 June 12, 2006



Condition: Both the left and right hydraulic SYS PRESS lights illuminated indicate left and right hydraulic system pressures are low.

DEMAND PUMP selectors (Left and right) . . . . . . . . . . . . . .ON


DEMAND PUMP selectors (Left and right) . . . . . . . . . . OFF

ENGINE PRIMARY PUMPswitches (Left and right) . . . . . . . . . . . . . . . . . . . . . . . . . OFF

[Avoids system contamination and/or pump damage.]

Plan to land at the nearest suitable airport.Note: Inoperative items

• auto brakes• L and R autopilots


• both thrust reversers

Note: Autoland not authorized.





HYDRAULIC SYSTEM PRESSURE (L AND R)

Message: L and R HYD SYS PRESS

13.13June 16, 2008



Condition: Both the right and center hydraulic SYS PRESS lights illuminated indicate right and center hydraulic system pressures are low.

DEMAND PUMP selectors (Right and center) . . . . . . . . . . .ON


DEMAND PUMP selectors (Right and center). . . . . . . . OFF

ELECTRIC PRIMARY PUMP switches (Both) . . . . . . . . OFF

ENGINE PRIMARY PUMP switch (Right) . . . . . . . . . . . . OFF[Avoids system contamination and/or pump damage.]

Plan to land at the nearest suitable airport.Note: Inoperative items:

• automatic speedbrake• R and C autopilots• normal brakes• primary source to alternate brakes• auto brakes

0121, 0124, through 0139, 0171 through 0199, 1200 through 1201,1401 through 1404:

• R thrust reverserNote: Autoland not authorized.




HYDRAULIC SYSTEM PRESSURE (R AND C)

Message: R and C HYD SYS PRESS

13.14 June 16, 2008




If SYS PRESS lights remain illuminated: (continued)------------------------DEFERRED ITEMS ------------------------------==> APPROACH CHECKLIST







ALTERNATE FLAPS selector . . . . . . . . . . . . . . . . . . . . . .SetExtend or retract flaps as required.Use flaps 20 and VREF 30 + 20 for landing.






13.15June 12, 2006




If SYS PRESS lights remain illuminated: (continued)




Only accumulator pressure is available for brakes.

Apply steady, increasing brake pedal pressure and hold to a full stop. Do not taxi.

[Prevents possible loss of braking due to accumulator depletion.]

Do not accomplish the following checklists:GEAR DOORSHYDRAULIC DEMAND PUMPHYDRAULIC PRIMARY (1 OR 2)HYDRAULIC PRIMARY PUMPRESERVE BRAKE VALVE

13.16 June 12, 2006



Condition: The engine primary pump OVHT light illuminated indicates the engine pump temperature is high.

ENGINE PRIMARY PUMP switch . . . . . . . . . . . . . . . . . . . . OFF[Attempts to eliminate source of overheat.]

Do not accomplish the following checklist:HYDRAULIC PRIMARY PUMP

PRIMARY HYDRAULIC OVERHEATMessage: L PRIM HYD OVHT R PRIM HYD OVHT

13.17June 12, 2006



Condition: The RAT UNLKD light illuminated indicates the ram air turbine is not stowed and locked.

RAT UNLOCKEDMessage: RAT UNLOCKED

13.18 June 12, 2006


Non-Normal Checklists Chapter NNCLanding Gear Section 14


Table of ContentsNNC.14 Non-Normal Checklists-Landing GearAIR/GROUND SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1

ANTISKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1ANTISKID OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1AUTOBRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2BRAKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2DRAG BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.3GEAR DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.4GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6GEAR LEVER WILL NOT MOVE UP . . . . . . . . . . . . . . . . . . . . 14.6GEAR NOT DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6NOSE AIR/GROUND SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7PARKING BRAKE [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . . 14.7PARKING BRAKE [ADVISORY] . . . . . . . . . . . . . . . . . . . . . . . . 14.7RESERVE BRAKE VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.8SIDE BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.9TAILSKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.10WHEEL WELL FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.10

TOC.14.1June 16, 2008


Non-Normal Checklists -Landing Gear


IntentionallyBlank

TOC.14.2 June 16, 2008



Condition: The air/ground sensing system has failed.

One or both thrust reversers inoperative.Auto speedbrake inoperative. When deployed manually, spoiler capability is reduced.Auto brakes inoperative.

Condition: The ANTISKID light illuminated indicates a fault is detected in the antiskid system.

ANTISKID switch (As installed) . . . . . . . . . . . . . . . . . . . . . .ON[Partial antiskid protection will be available.]

Use minimum braking consistent with runway conditions to reduce possibility of tire blowout

Condition: The antiskid OFF light illuminated indicates the antiskid system is off/and or the system is inoperative.

Use minimum braking consistent with runway conditions to reduce possibility of tire blowout

AIR/GROUND SYSTEMMessage: AIR/GND SYS

ANTISKIDMessage: ANTISKID

ANTISKID OFFMessage: ANTISKID OFF

14.1June 12, 2006



Condition: The AUTO BRAKES light illuminated indicates the autobrakes are disarmed or inoperative.

AUTO BRAKES selector . . . . . . . . . . . . . . . . . . . . . . . Reselect

If AUTO BRAKES light re–illuminates:

AUTO BRAKES selector . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Condition: The BRAKE SOURCE light illuminated indicates the normal and alternate brake system pressures are low.

RESERVE BRAKES/STEERING switch . . . . . . . . . . . . . . . .ON

If BRAKE SOURCE light remains illuminated:

AUTO BRAKES selector . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Only accumulator pressure is available for braking. During landing rollout, apply steady, increasing brake pressure and hold to a full stop. Do not taxi.


AUTOBRAKESMessage: AUTOBRAKES

BRAKE SOURCEMessage: BRAKE SOURCE

14.2 June 12, 2006



Condition: The GEAR light illuminated indicates the main gear drag brace is not locked down.


Observe gear EXTEND OR EXTENDED limit speed (270K/.82M).Increase airspeed until GEAR light extinguishes.If DRAG BRACE message remains displayed:

Use flaps 30 for landing.[Provides slowest landing speed.]

Do not arm SPEEDBRAKE lever.

Manually extend speedbrakes after landing.[Allows coordinated speedbrake extension.]



PACK control selectors (Both) . . . . . . . . . . . . . . . . . OFF[Ensures cabin depressurization prior to landing.]

FUEL PUMP switches (All) . . . . . . . . . . . . . . . . . . . . . OFF[Reduces possibility of fire.]

Do not accomplish the following checklists:FUEL SYSTEM PRESSUREPACK OFF

DRAG BRACE Message: L DRAG BRACE R DRAG BRACE

14.3June 12, 2006



Condition: The GEAR light illuminated indicates the gear position disagrees with landing gear lever position.


If landing gear lever UP:

Observe gear EXTEND OR EXTENDED limit speed (270K/.82M).

Flight with gear down increases fuel consumption and decreases climb performance. Refer to Landing Gear Extended in the ODM Ferry section for flight planning.

If landing gear lever DN and all gear down (green) lights illuminated:


Accomplish normal landing.

If landing gear lever DN and any gear down (green) light not illuminated:

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ALTERNATE GEAR EXTEND switch (Maximum 250K/.75M) . . . . . . . . . . . . . . . . . . . . . . . . . . . DN

If all gear down lights illuminate:


Accomplish normal landing.


GEAR DISAGREEMessage: GEAR DISAGREE

14.4 June 16, 2008




If any gear down (green) light not illuminated:

Plan to land on available gear.

Consider an evacuation 0171 through 0199, 1200 through 1201, 1501 through 1506, 1521, 1601 through 1708:

Consider jettisoning fuel to reduce touchdown weight and speed.

0121, 0124 through 0139, 1401 through 1404:Consider burning off fuel to reduce touchdown weight and speed.

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN




When stopping distance is critical, extend the speedbrakes after all gear, or the nose or engine nacelle have contacted the runway.

Do not use the thrust reversers unless stopping distance is critical.





14.5June 16, 2008



Condition: The DOORS light illuminated indicates one or more gear doors are not closed.


If landing gear lever UP or DN:

Observe gear EXTEND OR EXTENDED limit speed (270K/.82M).

The gear doors may close when airspeed is reduced to normal flap extension speed.

If landing gear lever OFF:


Condition: Landing gear lever cannot be positioned to UP.

LEVER LOCK OVERRIDE switch . . . . . . . . . . . Push and hold

Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . UP, then OFF[Landing gear is automatically tilted permitting proper gear retraction.]

Condition: The CONFIG light illuminated indicates any gear is not down and locked when either thrust lever closed below 800 feet radio altitude or when flaps are in a landing position.

GEAR DOORSMessage: GEAR DOORS

GEAR LEVER WILL NOT MOVE UP

GEAR NOT DOWNMessage: GEAR NOT DOWN

14.6 June 16, 2008



Condition: The nose air/ground sensing system has failed.

Takeoff configuration warning system inoperative.

Condition: The CONFIG light illuminated indicates the parking brake is set when either engine’s thrust is in the takeoff range on the ground.

Condition: The PARK BRAKE light illuminated indicates the parking brake is set.

Antiskid is inoperative.

NOSE AIR/GROUND SYSTEMMessage: NOSE A/G SYS

PARKING BRAKE [WARNING]

Message: PARKING BRAKE

PARKING BRAKE [ADVISORY]


14.7June 16, 2008



Condition: The reserve brakes and steering VALVE light illuminated indicates a reserve brake valve(s) position disagrees with the commanded position.

If center hydraulic system is inoperative:


If center and right hydraulic systems are inoperative:


Only accumulator pressure is available for brakes.

Apply steady, increasing brake pressure and hold to a full stop. Do not taxi.


RESERVE BRAKE VALVEMessage: RSV BRAKE VAL

14.8 June 16, 2008



Condition: The GEAR light illuminated indicates the main gear side brace is not locked down.


Observe gear EXTEND OR EXTENDED limit speed (270K/.82M).Decrease airspeed until GEAR light extinguishes (VREF minimum).If SIDE BRACE message remains displayed:



Manually extend speedbrakes after landing.[Allows coordinated speedbrake extension.]






SIDE BRACE Message: L SIDE BRACE R SIDE BRACE

14.9June 16, 2008



Condition: The tailskid position disagrees with landing gear lever position.

GROUND PROXIMITY/CONFIGURATION/GEAR OVERRIDE switch . . . . . . . . . . . . . . . . . . . . . . . . OVRD

CAUTION: If tailstrike is suspected, refer to TAILSTRIKE checklist in Section 0.

Condition: The WHL WELL FIRE light illuminated indicates a fire is detected in a main wheel well.

Observe gear EXTEND limit speed (270K/.82M).Landing gear lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN

[Attempts to remove and extinguish the fire source.]



Flight with gear down increases fuel consumption and decreases climb performance. Refer to Landing gear extended in the ODM ferry section for flight planning.If landing gear must be retracted for airplane performance:

When WHL WELL FIRE light is no longer illuminated:

Wait 20 minutes.[Attempts to ensure that wheel well fire is extinguished.]

Landing gear lever . . . . . . . . . . . . . . . . . . . UP, then OFF

TAILSKID

Message: TAILSKID

WHEEL WELL FIREMessage: WHEEL WELL FIRE

14.10 June 16, 2008


Non-Normal Checklists Chapter NNCWarning Systems Section 15


Table of ContentsNNC.15 Non-Normal Checklists-Warning SystemsALTITUDE ALERT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1

ALTITUDE CALLOUTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EICAS CONTROL PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EICAS DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1GEAR NOT DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2GROUND PROXIMITY SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . 15.2OVERSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2PARKING BRAKE [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . . 15.2SPOILERS [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3STABILIZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TCAS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TCAS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TERRAIN OVERRIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4TERRAIN POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4WINDSHEAR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4

TOC.15.1June 16, 2008


Non-Normal Checklists -Warning Systems


IntentionallyBlank

TOC.15.2 June 16, 2008



Condition: The ALT ALERT light illuminated indicates the airplane has deviated from the selected altitude.


Condition: Altitude callouts are no longer provided.

Condition: The EICAS control panel is inoperative.

Condition: One EICAS CRT is inoperative.

Condition: The CONFIG light illuminated indicates the flaps are not in a takeoff position when either engine’s thrust is in the takeoff range on the ground.

ALTITUDE ALERTMessage: ALTITUDE ALERT

ALTITUDE CALLOUTSMessage: ALT CALLOUTS

EICAS CONTROL PANELMessage: EICAS CONT PNL

EICAS DISPLAYMessage: EICAS DISPLAY

FLAPSMessage: FLAPS

15.1June 16, 2008



Condition: The CONFIG light illuminated indicates any landing gear is not down and locked when either thrust lever closed below 800 feet radio altitude or when flaps are in a landing position.

Condition: Ground proximity alerts may not be provided.

Some or all ground proximity alerts are not available.Ground proximity alerts which occur are valid.

Condition: The OVSPD light illuminated indicates the airspeed has exceeded Vmo/Mmo.

Condition: The CONFIG light illuminated indicates the parking brake is set when either engine’s thrust is in the takeoff range on the ground.

GEAR NOT DOWNMessage: GEAR NOT DOWN

GROUND PROXIMITY SYSTEMMessage: GND PROX SYS

OVERSPEEDMessage: OVERSPEED

PARKING BRAKE [WARNING]


15.2 June 16, 2008



Condition: The CONFIG light illuminated indicates the SPEEDBRAKE lever is not DOWN when either engine’s thrust is in the takeoff range on the ground.

Condition: The CONFIG light illuminated indicates the stabilizer is not within the greenband with either engine’s thrust in the takeoff range on the ground.

Condition: The TCAS system has failed or is inoperative.

Condition: The TCAS system is off.

SPOILERS [WARNING]

Message: SPOILERS

STABILIZERMessage: STABILIZER

TCAS FAILMessage: TCAS FAIL

TCAS OFFMessage: TCAS OFF

15.3June 16, 2008



(As installed)

Condition: Ground proximity terrain override switch is in OVRD.

Look–ahead terrain alerts and the terrain display are not provided.

(As installed)

Condition: Terrain position data has been lost.

Position data for the HSI terrain map and look-ahead terrain alerts are lost. Ground proximity alerts which occur are valid.

1404, 1603 through 1613, 1705 through 1708

Condition: Windshear alerts may not be provided.

Some or all windshear alerts are not available.Windshear alerts which occur are still valid.

TERRAIN OVERRIDE

Message: TERR OVRD

TERRAIN POSITION

Message: TERR POS

WINDSHEAR SYSTEM

Message: WINDSHEAR SYS

15.4 June 16, 2008


Manuevers Chapter MANTable of Contents Section 0


MAN.0 Manuevers-Table of Contents

Non-Normal Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.1

All Flaps and Slats Up Landing . . . . . . . . . . . . . . . . . . . . . . . MAN.1.1Approach Set Up Considerations: . . . . . . . . . . . . . . . . . . MAN.1.1Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.1On Final . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.1Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.2

Approach to Stall Recovery . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.3Overweight Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.4

Overweight Landing Considerations . . . . . . . . . . . . . . . . MAN.1.4Rejected Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.6

Rejected Takeoff Decision . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.6Rejected Takeoff Maneuver . . . . . . . . . . . . . . . . . . . . . . . MAN.1.7

Terrain Avoidance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.9Ground Proximity Caution . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.9Ground Proximity Warning . . . . . . . . . . . . . . . . . . . . . . MAN.1.10

Traffic Avoidance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.11Upset Recovery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.13

Nose High Recovery . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.14Nose Low Recovery . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.14

Windshear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.15Predictive Windshear Warning . . . . . . . . . . . . . . . . . . . . MAN.1.15Predictive Windshear Caution . . . . . . . . . . . . . . . . . . . . MAN.1.15Windshear Indications . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.15Windshear Encounter . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.1.16Windshear Escape Maneuver With Flight Director Guidance . . . . . . . . . . . . . . . . . . . MAN.1.17Windshear Escape Maneuver Without Flight Director Guidance . . . . . . . . . . . . . . . . . MAN.1.18

MAN.TOC.0.1June 12, 2006


Manuevers -Table of Contents


Flight Patterns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.1

Flight Pattern Principles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.1Takeoff Profile - Engine Failure . . . . . . . . . . . . . . . . . . . . . . . MAN.2.2ILS Approach Profile - One Engine Inoperative . . . . . . . . . . MAN.2.3Instrument Approach Using VNAV Profile -One Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.4Instrument Approach Using V/S Profile -One Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.5Circling Approach Profile - One Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.6Visual Traffic Pattern Profile -One Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.7Go-Around and Missed Approach Profile -One Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN.2.8

MAN.TOC.0.2 June 12, 2006


Maneuvers Chapter MANNon-Normal Maneuvers Section 1


MAN.1 Maneuvers-Non-Normal ManeuversAll Flaps and Slats Up LandingThe following information should be considered by the pilot during an all flaps and slats up landing. Ensure completion of the QRH procedure.

Approach Set Up Considerations:• Use longest available runway.• Reduce airplane gross weight (time and conditions permitting, burn off

fuel) to reduce final approach speed.• Use of the autopilot during approach phase is acceptable. Do not

autoland.• The G/A mode of the F/D and the autopilot will not be armed, unless an

ILS approach is executed. Glide slope capture is required to arm the G/A mode if the flaps are not out of the up position.

• See ODM Abnormal Section for abnormal flap/slat landing distances for runway shorter than 8,000 feet.

• Use auto brakes consistent with runway length, consider MAX AUTO.

ApproachPrior to final approach, fly a wide pattern to allow for the increased turning radius required for the higher maneuvering speed. Maintain no slower than flaps up maneuvering speed (VREF 30 + 80) until established on final. Use normal bank angles. Establish a 10 mile final.Use normal landing aimpoint and plan to land in the normal touchdown zone of the runway. Final approach body attitude is approximately four degrees higher than normal. Do not make a flat approach or aim short. This may result in main gear touching down short of the runway. Use precision glideslope, VNAV path, and/or visual landing system indicators as a cross check, if available.

On FinalEstablish approach/landing speed (VREF 30 + 50) as soon as possible. Limit bank angle to 15 degrees. The approach/landing speed does not provide normal bank angle maneuvering capability. Extend the gear at the first indication of G/S movement, if available.Use manual control of thrust levers. Disregard ALPH indications. Use caution with engines at or near idle for longer engine acceleration times. Do not use speedbrakes below 800 feet. Arm the auto speedbrakes. If landing is anticipated beyond the normal touch down zone, go around.


MAN.1.1June 12, 2006


Maneuvers -Non-Normal Maneuvers



LandingWhen landing is assured, retard thrust levers to idle at 100 feet above field elevation. Fly the aircraft unto the runway. Little or no flare is required. Flare only enough to reduce the rate of descent. Floating above the runway surface to deplete additional speed wastes available runway and increases the possibility of a tail strike.After landing, verify speedbrakes up. Immediate initiation of full reverse thrust at main gear touchdown (reverse thrust is more effective at high speeds) allows the autobrake system to reduce brake pressure to the minimal level. Less than maximum reverse thrust increases brake energy requirements and may result in excessive brake temperatures. Use manual braking if deceleration is not suitable for the desired stopping distance.

MAN.1.2 June 12, 2006




Approach to Stall RecoveryThe following is immediately accomplished at the first indication of stall buffet or stick shaker.

Note: *At high altitudes it may be necessary to decrease pitch attitude below the horizon to achieve acceleration.

Pilot Flying Pilot Monitoring

• Advance thrust levers to maximum thrust

• Smoothly adjust pitch attitude* to avoid ground contact or obstacles

• Level the wings (do not change flaps or landing gear configuration)

• Retract the speedbrakes

• Verify maximum thrust

• Monitor altitude and airspeed

• Call out any trend toward terrain contact

When ground contact is no longer a factor:

• Adjust pitch attitude to accelerate while minimizing altitude loss

• Return to a speed appropriate for the configuration

MAN.1.3June 12, 2006




Overweight LandingThe decision to land above the maximum landing weight limitation of the aircraft rests with the Captain. The Captain may deem an overweight landing the safest course of action based upon the urgency of the situation and other operational factors specific to that particular event. Refer to the FOM, Ch. 10 for additional guidance.There are no special procedures for conducting landings at greater than maximum certificated weight. There are, however, considerations that may affect choice of landing runway, configuration, pilot technique, and after landing procedures.

Overweight Landing ConsiderationsThe following information should be considered by the pilot during an overweight landing.

Approach• Consider landing on the longest available runway.• Landing distance is always less than takeoff distance at all gross weights

when landing with flaps 25 or 30.• Flight Control can provide landing/climb weight restrictions and other

assistance, time permitting.• ER aircraft should jettison as much fuel as time permits considering the

urgency of the situation.• Brake energy limits will not be exceeded for flaps 25 or 30 landings at all

gross weights.• For slippery or contaminated runways, or non-normal procedures

resulting in other than 25 or 30 flap landings, landing distances should be verified by referencing the ODM landing charts.

• Use the autobrake setting as determined from the ODM, Autobrake Landing Distance guidance.

• If approach VREF (including additives) is within 10 knots of the flaps 30 placard speed, use flaps 25 and VREF 25 (plus additives) for landing.

• Maneuvering speeds are close to maximum flap extension speeds due to high gross weights. Avoid excessive maneuvering with landing flaps extended.

• The vertical speed required to maintain glide path may be significantly higher than normal. The Captain should brief contingencies if "Sink Rate" cautions are received on short final.

• Do not carry excess airspeed on final. This is especially important when landing during an engine inoperative or other non-normal condition.

• The autopilot may be used for the approach, but should be disconnected prior to the flare and a manual landing accomplished.

MAN.1.4 June 12, 2006




• The aircraft is not certified to Autoland at greater than maximum landing weight. If the Captain determines that an autoland is the safest course of action, the approach, flare, and landing must be closely monitored at all times.

• Use normal go-around procedures if the approach or landing is abandoned.

Landing• Ensure that a higher than normal rate of descent does not develop.• Do not hold the airplane off waiting for a smooth landing.• Fly the airplane onto the runway at the normal touchdown point.• If a long landing is likely to occur, go-around.• After touchdown, immediately apply maximum reverse thrust using all of

the available runway for stopping to minimize brake temperatures.• Do not attempt to make an early runway turnoff.

After Landing• Coordinate taxi to an uncongested ramp area if hot brakes are suspected.• Refer to the ODM, abnormal section for Landing Brake Cooling

Schedule.• Be alert for the possibility of a tire, grease, or hydraulic fluid fire.• Make a log book entry including the phraseology "overweight landing".

Include actual landing weight (minus unused AWABS tolerances) and maximum landing weight.

MAN.1.5June 12, 2006




Rejected Takeoff

Rejected Takeoff DecisionThe Captain has the sole responsibility for the decision to reject the takeoff. The decision must be made in time to start the Rejected Takeoff Maneuver by V1.During the takeoff, the crew member recognizing a malfunction will call it out clearly and precisely.The takeoff should be rejected for the following:

If the Captain is making the takeoff, the Captain must:• clearly announce "ABORT," and• immediately start the Rejected Takeoff Maneuver.

If the Captain is not making the takeoff, the Captain must:• clearly announce "ABORT,"• immediately start the Rejected Takeoff Maneuver,• assume control of the airplane, and• announce "I HAVE THE AIRCRAFT."

Note: The First Officer will maintain control of the airplane until the Captain makes a positive input to the controls and states, "I HAVE THE AIRCRAFT."

Event Prior to 80knots

80 knots to V1

Above V1

Activation of the Master Caution XSystem Failures XUnusual noise or vibration XTire Failure XAbnormally slow acceleration XUnsafe takeoff configuration warning XEngine failure X XFire or fire warning X XPredictive Windshear Caution or Warning X XIf the airplane is unsafe or unable to fly X X X

MAN.1.6 June 12, 2006




Rejected Takeoff Maneuver

*The Captain has the option to manually deploy the speedbrakes prior to thrust reverser actuation.


Captain First OfficerWithout delay, simultaneously:

• Close the thrust levers.• Disengage the A/T(s).• Apply maximum manual wheel

brakes or verify operation of RTO autobrakes.

Note: If RTO autobrakes is selected, monitor performance and apply manual wheel brakes if the AUTO BRAKES DISARM light is displayed or deceleration is not adequate.

Verify actions as follows:

• Thrust levers closed.• A/T(s) disengaged.• Maximum brakes applied.

Apply maximum reverse thrust consistent with conditions.

Verify reverse thrust applied.

Raise SPEEDBRAKE lever*. If SPEEDBRAKE lever UP,Call "SPEEDBRAKES UP".

If SPEEDBRAKE lever not UP,Call "SPEEDBRAKES NOT UP."

Continue maximum braking until certain the airplane will stop on the runway.

Call out any omitted action items.

Field length permitting:

Initiate movement of the reverse thrust levers to reach the idle reverse detent by taxi speed.

Call out 60 knots.

Notify the tower of the abort and request emergency equipment, if necessary.

As soon as practical, make the appropriate RTO PA in accordance with the FOM.

MAN.1.7June 12, 2006





Captain First OfficerPost Reject Considerations:

• Complete Non-Normal checklist for the condition causing the RTO.• Brake cooling schedule and precautions in the ODM.• The possibility of wheel fuse plugs melting and/or remote parking.• The need to clear the runway. Check entry door/exit status and ensure

passengers are seated prior to taxi.• Wind direction in case of fire.• Not setting the parking brake unless evacuation is necessary.• Advising the ground crew of the hot brake hazard.• Contact Flight Control.

MAN.1.8 June 12, 2006




Terrain Avoidance

Ground Proximity CautionAccomplish the following maneuver for any of these aural alerts*:• CAUTION TERRAIN• TERRAIN• DON’T SINK• GLIDESLOPE• SINK RATE• TOO LOW FLAPS• TOO LOW GEAR• TOO LOW TERRAIN• BANK ANGLE

The below glideslope deviation alert may be cancelled or inhibited for:• localizer or backcourse approach• circling approach from an ILS• when conditions require a deliberate approach below glideslope• unreliable glideslope signal.

Note: If a terrain caution occurs when flying under daylight VMC, and positive visual verification is made that no obstacle or terrain hazard exists, the alert may be regarded as cautionary and the approach may be continued.

Note: * As installed, some repeat.


Correct the flight path or the airplane configuration.

MAN.1.9June 16, 2008




Ground Proximity WarningAccomplish the following maneuver for any of these conditions:• activation of the “PULL UP” warning• activation of the “TERRAIN TERRAIN PULL UP” warning• other situations resulting in unacceptable flight toward terrain.

Note: Aft control column force increases as the airspeed decreases. In all cases, the pitch attitude that results in intermittent stick shaker or initial buffet is the upper pitch attitude limit. Flight at intermittent stick shaker may be required to obtain positive terrain separation. Smooth, steady control will avoid a pitch attitude overshoot and stall.

Note: Do not use flight director commands.

Note: * Maximum thrust can be obtained by advancing the thrust levers to the takeoff or go-around limit. On airplanes with EECs operating normally, the pilot may advance the thrust levers full forward. Regardless of EEC status, if terrain contact is imminent, advance thrust levers full forward.

Note: If positive visual verification is made that no terrain hazard exists when flying under daylight VMC conditions prior to a terrain warning, the alert may be regarded as cautionary and the approach may be continued


• Disconnect autopilot.• Disconnect autothrottle.• Aggressively apply maximum* thrust.• Simultaneously roll wings level and

rotate to an initial pitch attitude of 20°.• Retract speedbrakes.• If terrain remains a threat, continue

rotation up to the pitch limit indicator or stick shaker or initial buffet.

• Verify maximum* thrust.

• Verify all required actions have been completed and call out any omissions.

• Do not change gear or flap configuration until terrain separation is assured.

• Monitor radio altimeter for sustained or increasing terrain separation.

• When clear of the terrain, slowly decrease pitch attitude and accelerate.

• Monitor vertical speed and altitude(radio altitude for terrain clearance and barometric altitude for a minimum safe altitude).

• Call out any trend toward terrain contact.

MAN.1.10 June 12, 2006




Traffic AvoidanceThe following is accomplished immediately by recall whenever a TCAS traffic advisory (TA) or resolution advisory (RA) occurs.

WARNING: Comply with the RA if there is a conflict between the RA andair traffic control.

WARNING: Once an RA has been issued, safe separation could becompromised if current vertical speed is changed, except asnecessary to comply with the RA. This is becauseTCAS II–to–TCAS II coordination may be in progress withthe intruder aircraft, and any change in vertical speed thatdoes not comply with the RA may negate the effectiveness ofthe other aircraft’s compliance with the RA.

Note: If stick shaker or initial buffet occurs during the maneuver, immediately accomplish the APPROACH TO STALL RECOVERY procedure.

Note: If high speed buffet occurs during the maneuver, relax pitch force as necessary to reduce buffet, but continue the maneuver.

Note: Do not use flight director pitch commands until clear of conflict.

For TA:



Look for traffic using traffic display as a guide. Call out any conflicting traffic.

If traffic is sighted, maneuver as required.

MAN.1.11June 12, 2006





For RA, except a climb in landing configuration:

For a climb RA in landing configuration:


If maneuvering is required, disengage the autopilot and autothrottle. Smoothly adjust pitch and thrust to satisfy the RA command. Follow the planned lateral flight path unless visual contact with the conflicting traffic requires other action.

Attempt to establish visual contact. Call out any conflicting traffic.


Disengage the autopilot and autothrottle. Advance thrust levers forward to ensure maximum thrust is attained and call for FLAPS 20. Smoothly adjust pitch to satisfy the RA command. Follow the planned lateral flight path unless visual contact with the conflicting traffic requires other action.

Verify maximum thrust set. Position flap lever to 20 detent.

Verify a positive rate of climb on the altimeter and call "GEAR UP."

Verify a positive rate of climb on the altimeter and call "POSITIVE RATE."

Set the landing gear lever to UP.

Attempt to establish visual contact. Call out any conflicting traffic.

MAN.1.12 June 16, 2008




Upset RecoveryAn upset can generally be defined as unintentionally exceeding the following conditions:• pitch attitude greater than 25 degrees nose up, or• pitch attitude greater than 10 degrees nose down, or• bank angle greater than 45 degrees, or• within above parameters but flying at airspeeds inappropriate for the

conditions.The following techniques represent a logical progression for recovering the airplane. The sequence of actions is for guidance only and represents a series of options to be considered and used depending on the situation. Not all the actions may be necessary once recovery is underway. If needed, use pitch trim sparingly. Careful use of rudder to aid roll control should be considered only if roll control is ineffective and the airplane is not stalled. These techniques assume that the airplane is not stalled. A stalled condition can exist at any attitude and may be recognized by continuous stick shaker activation accompanied by one or more of the following:• buffeting, which could be heavy at times• lack of pitch authority and/or roll control• inability to arrest descent rate.

If the airplane is stalled, recovery from the stall must be accomplished first by applying and maintaining nose down elevator until stall recovery is complete and stick shaker activation ceases.


MAN.1.13June 12, 2006





Nose High Recovery

Nose Low Recovery

WARNING: * EXCESSIVE USE OF PITCH TRIM OR RUDDER MAYAGGRAVATE AN UPSET SITUATION OR MAY RESULTIN LOSS OF CONTROL AND/OR HIGH STRUCTURALLOADS.


• Recognize and confirm the situation.

• Disconnect autopilot and autothrottle.• Apply as much as full nose down

elevator.• *Apply appropriate nose down

stabilizer trim.• Reduce thrust.• *Roll (adjust bank angle) to obtain a

nose down pitch rate.• Complete the recovery:

- when approaching the horizon, roll to wings level

-check airspeed and adjust thrust-establish pitch attitude.

• Call out attitude, airspeed and altitude throughout the recovery.



• Recognize and confirm the situation.

• Disconnect autopilot and autothrottle.• Recover from stall, if required.• *Roll in the shortest direction to wings

level (unload and roll if bank angle is more than 90 degrees).

• Recover to level flight:- apply nose up elevator- *apply nose up trim, if required- adjust thrust and drag as required.

• Call out attitude, airspeed and altitude throughout the recovery.


MAN.1.14 June 12, 2006




Windshear

Predictive Windshear CautionPredictive windshear caution alert on takeoff (“MONITOR RADAR DISPLAY” aural):• If on takeoff roll, accomplish the Rejected Takeoff Maneuver.• Once airborne, ensure maximum takeoff thrust is set (normal power).

Maneuver as required to avoid the windshear.Predictive windshear caution alert during approach (“MONITOR RADAR DISPLAY” aural):• perform normal go-around. Maneuver as required to avoid the windshear.

WARNING: If actual windshear conditions are encountered, perform theWindshear Escape Maneuver.

Predictive Windshear Warning

Predictive windshear warning on takeoff : (“WINDSHEAR AHEAD, WINDSHEAR AHEAD” aural):• Prior to V1, accomplish the Rejected Takeoff Maneuver.• Once airborne, perform the Windshear Escape Maneuver.

Predictive windshear warning during approach: (“GO–AROUND, WINDSHEAR AHEAD” aural):• Perform Windshear Escape Maneuver or, at pilot’s discretion, perform a

normal go–around.

Windshear Indications The following are indications the airplane is encountering a windshear:• Unacceptable flight path deviations; recognized as uncontrolled changes

from normal steady state flight conditions below 1,000 feet AGL, in excess of any of the following:• 15 knots indicated airspeed• 500 FPM vertical speed• 5 degrees pitch attitude• 1 dot displacement from the glideslope• unusual thrust lever position for a significant period of time.

• Windshear Immediate-Alert Warning (two-tone siren followed by “WINDSHEAR,WINDSHEAR,WINDSHEAR”)


MAN.1.15June 16, 2008





Windshear EncounterWindshear encountered during takeoff roll:• If windshear is encountered prior to V1, there may not be sufficient

runway remaining to stop if an RTO is initiated at V1. At VR, rotate at a normal rate toward a 15 degree pitch attitude. Once airborne, perform the Windshear Escape Maneuver.

• If windshear is encountered near the normal rotation speed and airspeed suddenly decreases, there may not be sufficient runway left to accelerate back to normal takeoff speed. If there is insufficient runway left to stop, initiate a normal rotation at least 2,000 feet before the end of the runway even if airspeed is low. Higher than normal attitudes may be required to lift off in the remaining runway. Ensure maximum thrust is set.

Windshear encountered in flight:• perform the Windshear Escape Maneuver.

MAN.1.16 June 16, 2008




Windshear Escape Maneuver

WARNING: Severe windshear may exceed the performance capability ofthe AFDS.

Note: Aft control column force increases as the airspeed decreases. In all cases, the pitch attitude that results in intermittent stick shaker or initial buffet is the upper pitch attitude limit. Flight at intermittent stick shaker may be required to obtain positive terrain separation. Smooth, steady control will avoid a pitch attitude overshoot and stall.

Note: * Maximum thrust can be obtained by advancing the thrust levers to the takeoff or go-around limit. On airplanes with EECs operating normally, the pilot may advance the thrust levers full forward. Regardless of EEC status, if terrain contact is imminent, advance thrust levers full forward.


• Disconnect autopilot.• Push either go–around switch.• Aggressively apply maximum*

thrust.• Disconnect autothrottle.• Simultaneously roll wings level and

rotate toward an initial pitch attitude of 15°.

• Retract speedbrakes.• Follow Flight Director GA

guidance (if available).

• Verify maximum* thrust.• Verify all required actions

have been completed and call out any omissions.

• Do not change gear or flap configuration until windshear is no longer a factor.

• Monitor vertical speed and altitude.• Do not attempt to regain lost

airspeed until windshear is no longer a factor.

• Monitor vertical speed and altitude.

• Call out any trend toward terrain contact, descending flight path, or significant airspeed changes.

MAN.1.17June 16, 2008




IntentionallyBlank

MAN.1.18 June 16, 2008


Maneuvers Chapter MANFlight Patterns Section 2


MAN.2 Maneuvers-Flight PatternsFlight Pattern PrinciplesFlight patterns in this section are not designed to be comprehensive in nature.They have been developed as a tool for the experienced crew member. A quickreview may be obtained by referencing a flight pattern and its associated text. Fora complete analysis of a particular maneuver, the Flight Crew Training Manualshould be referenced in addition to the material found in this section.Flight patterns in this section do not include all standard callouts.Flight patterns in this section do not include every pilot action recommended tofly a particular flight pattern.Certain maneuver depictions in this section may imply a certain order in which checklists should be accomplished. However, the Captain, after assessing the situation, shall determine the order and call for the appropriate checklist(s) to be accomplished.

MAN.2.1June 12, 2006


Maneuvers -Flight Patterns


Takeoff Profile - Engine Failure

Take

off r

oll

•Se

t tak

eoff

thru

st b

y 80

kno

ts•

Mon

itor a

irspe

ed•

Mai

ntai

n lig

ht fo

rwar

d pr

essu

re

Acc

eler

atio

n he

ight

(n

orm

ally

1,0

00 fe

et A

FE)

•Se

lect

V/S

0 to

+20

0 fp

m

•R

etra

ct fl

aps o

n sc

hedu

le

Aft

er p

lann

ed fl

aps s

etan

d at

or

abov

e fla

p m

aneu

veri

ng sp

eed

•Se

lect

FLC

H•

Sele

ct/v

erify

CO

N th

rust

•D

o th

e N

NC

•D

o th

e A

fter T

akeo

ff ch

eckl

ist

Abo

ve 4

00 fe

et R

A•

Sele

ct ro

ll m

ode

Thr

ust s

et•

Man

ually

adv

ance

th

rust

to st

abili

ze•

Enga

ge a

utot

hrot

tle

VR •Ro

tate

Posi

tive

rate

of c

limb

•R

etra

ct g

ear

Initi

al c

limb

spee

d•

V2

to V

2+15

kno

ts

V1

Not

e:Fo

r an

imm

edia

te tu

rn a

fter

take

off,

mai

ntai

n in

itial

clim

b sp

eed

with

take

off f

laps

whi

le

man

euve

ring.

Fol

low

AFD

S ba

nk

limits

.

The

auto

pilo

t may

be e

ngag

ed af

ter a

ro

ll m

ode

and

V/S

are

sele

cted

.

MAN.2.2 June 12, 2006




ILS Approach Profile - One Engine Inoperative

•Fl

aps 1

Loc

aliz

er c

aptu

re•

Fina

l App

roac

h co

urse

he

adin

g

Fix

(LO

M, M

KR

, DM

E)•

Verif

y cr

ossi

ng a

ltitu

de

Glid

e sl

ope

inte

rcep

t•

Ensu

re m

isse

d ap

proa

ch al

titud

e in

MC

P by

1,0

00 fe

et A

GL

Glid

eslo

pe a

live

•G

ear d

own

•Fl

aps 2

0(la

ndin

g fla

ps)

•A

rm sp

eedb

rake

•D

o th

e La

ndin

g ch

eckl

ist

App

roac

hing

inte

rcep

t hea

ding

•Fl

aps 5

•Fl

aps 5

On

RA

DA

R v

ecto

rs•

HD

G S

EL•

Pitc

h m

ode

(as n

eede

d)

Inte

rcep

t Hea

ding

•IL

S tu

ned

and

iden

tifie

d•

LOC

and

G/S

poi

nter

s sho

wn

•A

rm A

PP

Enr

oute

to fi

x•

LNAV

or o

ther

roll

mod

e•

VN

AV o

r oth

er p

itch

mod

e

MAN.2.3June 12, 2006




Instrument Approach Using VNAV Profile -One Engine Inoperative

App

roac

hing

inte

rcep

t hea

ding

•Fl

aps 5

•Fl

aps 5

Inte

rcep

t hea

ding

•A

rm L

NAV

or

sele

ct o

ther

ro

ll m

ode

Des

cend

to D

A/D

DA

•M

onito

r VN

AV p

ath

•En

sure

mis

sed

appr

oach

alti

tude

in

MC

P by

1,0

00 fe

et A

GL

•Fl

aps 1

Prio

r to

FA

F•

Gea

r dow

n•

Flap

s 20

(land

ing

flaps

)•

Arm

spee

dbra

ke•

Do

the

Land

ing

chec

klis

t

Enr

oute

to fi

x•

LNAV

or o

ther

roll

mod

e•

VN

AV o

r oth

er p

itch

mod

e

At D

A/D

DA

•In

terc

ept l

andi

ng p

rofil

e•

Dis

conn

ect a

utop

ilot b

yD

A -5

0 fe

et /

DD

A -1

00 fe

et

FAF

FAF

altit

ude

assu

red

•C

onfir

m T

DZE

roun

ded

up, s

et•

Sele

ct V

NAV

•

Spee

d In

terv

entio

n

On

RA

DA

R v

ecto

rs•

HD

G S

EL•

Pitc

h m

ode

(as n

eede

d)

MAN.2.4 June 12, 2006




Instrument Approach Using V/S Profile -One Engine Inoperative

App

roac

hing

DD

A/M

DA

•E

nsur

e m

isse

d ap

proa

ch a

ltitu

de in

MC

P by

1,0

00 f

eet A

GL

(at

ALT

CA

P fo

r M

DA

)

App

roac

hing

inte

rcep

t he

adin

g•

Fla

ps 5

•Fl

aps

5

Inte

rcep

t H

eadi

ng•

Arm

LN

AV

or

sele

ct

othe

r ro

ll m

ode

Des

cend

to

DD

A (

MD

A fo

r ci

rclin

g)•

Set V

/S

•Fl

aps

1

FAF

Pri

or t

o FA

F•

Gea

r do

wn

•F

laps

20

(lan

ding

fla

ps)

•A

rm s

peed

brak

e•

Con

firm

TD

ZE ro

unde

d up

, set

(M

DA

for

cir

clin

g)

•D

o th

e L

andi

ng c

heck

list

Lea

ving

DD

A/M

DA

•In

terc

ept l

andi

ng p

rofi

le•

Dis

enga

ge a

utop

ilot b

yD

DA

-10

0 fe

et /

MD

A-5

0 fe

et

Enr

oute

to fi

x•

LNAV

or o

ther

roll

mod

e•

VN

AV o

r oth

er p

itch

mod

e

On

RA

DA

R v

ecto

rs•

HD

G S

EL•

Pitc

h m

ode

(as n

eede

d)

MAN.2.5June 12, 2006




Circling Approach Profile - One Engine InoperativeC

onfig

urat

ion

at M

DA

•G

ear d

own

•Fl

aps 2

0 (la

ndin

g fla

ps)

•Sp

eedb

rake

arm

ed

Turn

ing

Bas

e•

Do

the

Land

ing

chec

klis

t

Inte

rcep

ting

Lan

ding

Pro

file

•D

isen

gage

aut

opilo

t by

MD

A -

50 fe

et

Min

imum

Des

cent

Alti

tude

•Se

lect

ALT

HLD

(a

s nee

ded)

•Se

t mis

sed

appr

oach

alti

tude

•Se

lect

HD

G S

EL

If a

mis

sed

appr

oach

is n

eede

d at

any

tim

e w

hile

circ

ling,

mak

e an

initi

al

clim

bing

turn

in th

e sh

orte

st d

irect

ion

tow

ard

the

land

ing

runw

ay a

nd in

terc

ept

the

mis

sed

appr

oach

cou

rse.

MAN.2.6 June 12, 2006




Visual Traffic Pattern Profile - One Engine Inoperative

Bas

e•

Do

the

Land

ing

chec

klis

t

1,50

0 Fe

et 2 N

M

Ent

erin

g do

wnw

ind

•Fl

aps 5

Prio

r to

turn

ing

base

•G

ear d

own

•Fl

aps 2

0 (la

ndin

g fla

ps)

•A

rm sp

eedb

rake

•St

art d

esce

nt a

s nee

ded

700

– 50

0 Fe

et•

Stab

ilize

d on

pr

ofile

MAN.2.7June 12, 2006




Go-Around and Missed Approach Profile -One Engine Inoperative

Acc

eler

atio

n he

ight

(nor

mal

ly 1

,000

feet

AFE

)•

Set s

peed

for p

lann

ed fl

ap se

tting

•R

etra

ct fl

aps o

n sc

hedu

le•

Do

the

Afte

r Tak

eoff

chec

klis

t

Initi

atio

n•

Push

GA

or T

O/G

A, f

laps

5•

Verif

y go

-aro

und

attit

ude

•Ve

rify

or a

djus

t thr

ust a

s nee

ded

•Po

sitiv

e ra

te o

f clim

b - g

ear u

p

Aft

er p

lann

ed fl

aps s

et a

nd a

t or

abov

e fla

p m

aneu

veri

ng sp

eed

•Se

lect

FLC

H o

r VN

AV if

des

ired

•Se

lect

/ver

ify C

ON

thru

st if

des

ired

•Ve

rify

altit

ude

capt

ure

Abo

ve 4

00 fe

et R

A•

Sele

ct ro

ll m

ode

•Ve

rify

mis

sed

appr

oach

alti

tude

set

•Ve

rify

rout

e tra

ckin

g

For a

man

ual g

o-ar

ound

:•

Rot

ate

man

ually

•Se

lect

or v

erify

go-

arou

nd th

rust

•En

gage

aut

opilo

t as n

eede

d

MAN.2.8 June 12, 2006


Non-Normal Checklists Chapter NNCIndex Section Index


NNC.Index Non-Normal Checklists-IndexAABORTED ENGINE START . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.1, 7.1AC BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.1, 6.8ACARS - NO COMM (TOUCHSCREEN) . . . . . . . . . . . . . . . . . . . . . . 5.1ACARS SYSTEM INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.2ACCESS DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1ADI OR HSI BLANK OR ABNORMAL . . . . . . . . . . . . . . . . . . . . . . . 10.1AILERON LOCKOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1AIR/GROUND SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1AIRSPEED OR ALTIMETER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.1AIRSPEED UNRELIABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.2, 10.2ALL FLAPS AND SLATS UP LANDING . . . . . . . . . . . . . . . . . . . 0.4, 9.2ALTITUDE ALERT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1ALTITUDE CALLOUTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1ALTITUDE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.4ANTISKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1ANTISKID OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1AOA PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1APU BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1, 7.1APU BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2, 8.1APU FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2APU FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2, 8.2APU FUEL VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.3APU GENERATOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14, 7.3ATC FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.1ATTITUDE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5AUTO SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3AUTOBRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2AUTOMATIC UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.4, 1.2AUTOPILOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1AUTOPILOT DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1AUTOTHROTTLE DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1

NNC.Index.1June 16, 2008




AUXILIARY PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1

BBATTERY OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14BLEED DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2, 2.3BLEED ISOLATION VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4BODY DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5BOTH FMCS AND CDUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.2BRAKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.2BUS ISOLATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.14

CCABIN ALTITUDE OR RAPID DEPRESSURIZATION . . . . . . . . 0.5, 2.6CABIN AUTOMATIC INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7CABIN INTERPHONE SYSTEM INOPERATIVE . . . . . . . . . . . . . . . . 5.4CABIN TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8CAPTAIN PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2CARGO BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3CARGO DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3, 1.4CARGO FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4CARGO OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9COMM WITH CENTER VHF (TOUCHSCREEN) . . . . . . . . . . . . . . . . 5.6COMPLETE FMC/CDU/IRU FAILURE . . . . . . . . . . . . . . . . . . . . . . . 11.3

DDATALINK LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7DATALINK SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7DEMAND HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . 13.1DITCHING PREPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.6, 1.6DRAG BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.3DUAL ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.8, 7.4

EEEC OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6EICAS CONTROL PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EICAS DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.1EMERGENCY DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.9

NNC.Index.2 June 16, 2008




ENGINE ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3, 3.4, 7.7, 7.8ENGINE BLEED OFF . . . . . . . . . . . . . . . . . . . . . . . 2.10, 2.11, 7.10, 7.11ENGINE BLEED OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . 2.12, 7.12ENGINE BLEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.13, 7.13ENGINE BOTTLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13, 8.6ENGINE CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14ENGINE EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.14ENGINE EEC MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.15ENGINE FAILURE OR SHUTDOWN . . . . . . . . . . . . . . . . . . . 0.10, 7.16ENGINE FIRE OR SEVERE DAMAGE

OR SEPARATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.12, 7.18, 8.8ENGINE FUEL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21ENGINE FUEL LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.15, 7.22, 12.1ENGINE FUEL VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.26ENGINE HIGH STAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.14, 7.27ENGINE HPSOV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.15, 7.28ENGINE HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . 7.25, 13.1ENGINE IN–FLIGHT START . . . . . . . . . . . . . . . . . . . . . . . . . . 0.20, 7.30ENGINE LIMIT OR SURGE OR STALL . . . . . . . . . . . . . . . . . 0.24, 7.34ENGINE LIMIT PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36ENGINE LOW IDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.36ENGINE OIL PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.37ENGINE OIL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . 0.26, 7.38ENGINE OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.40, 8.12ENGINE PRV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.16, 7.42ENGINE RPM LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.43ENGINE TAILPIPE FIRE . . . . . . . . . . . . . . . . . . . . . . . . . 0.27, 7.44, 8.14ENTRY DOOR(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10EQUIPMENT COOLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.17EQUIPMENT OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.18EQUIPMENT SMOKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.19, 8.15EQUIPMENT VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Back Cover.2





FFIRE/OVERHEAT SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.16FIRST/OFFICER PITOT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6FLAP LOAD RELIEF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4, 15.1FLIGHT CONTROL VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4FLIGHT DECK TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.21FMC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.4, 11.6FMC MESSAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7FUEL CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.6FUEL CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.8FUEL JETTISON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.28, 12.9FUEL JETTISON NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.10FUEL JETTISON PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.11FUEL JETTISON TRANSFER VALVE . . . . . . . . . . . . . . . . . . . . . . . 12.11FUEL PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.12FUEL SPAR VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45, 12.13FUEL SYSTEM PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.14

GGEAR DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.4GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6GEAR LEVER WILL NOT MOVE UP . . . . . . . . . . . . . . . . . . . 0.29, 14.6GEAR NOT DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6,15.2GENERATOR DRIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.15GENERATOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.16GPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7GROUND PROXIMITY SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2

HHYDRAULIC (1 OR 2) OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC DEMAND PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.1HYDRAULIC PRIMARY (1 OR 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC PRIMARY PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.2HYDRAULIC QUANTITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.3HYDRAULIC SYSTEM PRESSURE (C ONLY) . . . . . . . . . . . . . . . . . 13.4





HYDRAULIC SYSTEM PRESSURE (L AND C) . . . . . . . . . . . . . . . 13.10HYDRAULIC SYSTEM PRESSURE (L AND R) . . . . . . . . . . . . . . . 13.13HYDRAULIC SYSTEM PRESSURE (L ONLY) . . . . . . . . . . . . . . . . . 13.7HYDRAULIC SYSTEM PRESSURE (R AND C) . . . . . . . . . . . . . . . 13.14HYDRAULIC SYSTEM PRESSURE (R ONLY) . . . . . . . . . . . . . . . . 13.8

IIAS DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5ICE DETECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DETECTOR OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICE DETECTOR ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7ICING ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8ICING WING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8IDLE DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.45IDU TOUCHSCREEN DATALINK INOPERATIVE . . . . . . . . . . . . . . . 5.7ILS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.7INSTRUMENT SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6IRS DC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8IRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8IRS ON DC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.8

JJAMMED OR RESTRICTED FLIGHT CONTROLS . . . . . . . . . 0.30, 9.5

LLEADING EDGE SLAT ASYMMETRY . . . . . . . . . . . . . . . . . . . . . . . . 9.6LEADING EDGE SLAT DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . 9.8LOCK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.31, 1.11LOW FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12.15LOW FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . 0.32, 12.16

MMAIN BATTERY DISCHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17

NNOSE AIR/GROUND SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7

OOIL FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.46, 7.46OVERSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2





PPA SYSTEM INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8PACK OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.22PACK TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.24PARKING BRAKE [ADVISORY] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7PARKING BRAKE [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . 14.7, 15.2PASSENGER OXYGEN ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.12PRIMARY HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . 13.17PROBE HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8

RRADAR MALFUNCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.9RADIO ALTIMETER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6RADIO TRANSMIT CONTINUOUS

(STUCK MICROPHONE SWITCH) . . . . . . . . . . . . . . . . . . . . 0.33, 5.10RAT UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.18RECIRCULATION FAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25RESERVE BRAKE VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.8REVERSER ISOLATION VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.47REVERSER UNLOCKED . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.34, 7.48RUDDER RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.10

SSATVOICE LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11SAT 1 AND/OR SAT 2 NOT AVAILABLE . . . . . . . . . . . . . . . . . . . . . 5.12SIDE BRACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.9SMOKE OR FIRE OR FUMES . . . . . . . . . . . . . . . . . . . . . . . . 0.38, 8.18SMOKE OR FUMES REMOVAL . . . . . . . . . . . . . . . . . . . . . . . 0.41, 8.21SPEEDBRAKES EXTENDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.11SPOILERS [ADVISORY] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.13SPOILERS [WARNING] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.12, 15.3STABILIZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.14, 15.3STABILIZER TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.15STANDBY BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17STARTER CUTOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.51STRUT DUCT LEAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25





TTAIL HYDRAULIC VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.16TAIL STRIKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.43TAILSKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.10TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.9TCAS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TCAS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3TERRAIN OVERRIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4TERRAIN POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4TRAILING EDGE FLAP ASYMMETRY . . . . . . . . . . . . . . . . . . . . . . . 9.17TRAILING EDGE FLAP DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . 9.18TRIM AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.26

UUNABLE RNP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.10UNSCHEDULED STABILIZER TRIM . . . . . . . . . . . . . . . . . . . . . . . . 9.20UTILITY BUS OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.18

VVOLCANIC ASH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.44, 7.52

WWHEEL WELL FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.22, 14.10WINDOW (HEAT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.14, 3.10WINDOW DAMAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.46, 1.13WINDOW OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.47, 1.15WINDSHEAR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.4WING ANTI–ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.11, 3.12WING HYDRAULIC VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.21WING SLIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.16

YYAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.22





IntentionallyBlank



Back Cover.1


Back Cover.1 EVACUATION

Evacuation Checklist is on the reverse side of this page.

Back Cover.1June 12, 2006


Back Cover.2


Condition: Evacuation is needed.PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETCabin altitude MODE SELECT . . . . . . . . . . . . . . . . . . . . . MANCabin altitude MANUAL control . . . . . . . . . . . . . . . . . . .CLIMB

Hold until the outflow valve is fully open.FUEL CONTROL switches (Both) . . . . . . . . . . . . . . . .CUT OFFAdvise the cabin to evacuate.Advise the tower.Engine and APU fire switches (All) . . . . . . . . . . . . . . . . . . . . OVERRIDE AND PULL

If an engine or APU fire warning light is illuminated:Related fire switch. . . . . . . . . . . . . . . . . . . . Rotate and hold

Rotate to the stop and hold for 1 second.

EVACUATION

Back Cover.2 June 12, 2006

Documents

767-300 - Aviation For All - Aviação sem mistérios! · PDF fileNon-Normal Checklists - Index QA.Index.2 June 17, 2008 REVIEWED BY: _____ Michael Bihuniak 757/767-300 - Technical