SECTION 3A

Model B300/B300C

SUBJECT PAGE

ABNORMAL PROCEDURESTABLE OF CONTENTS

April, 2006 3A-1

Air Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-3Starter Assist (Propeller Feathered Or Windmilling) . . . . . . . . . . . . . . . . . . 3A-3No Starter Assist (Propeller Feathered Or Windmilling) . . . . . . . . . . . . . . . 3A-4

Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-5Flaps Up Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-5One-Engine-Inoperative Approach And Landing . . . . . . . . . . . . . . . . . . . . 3A-6One-Engine-Inoperative Go-Around . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7Propeller Ground Idle Stop Solenoid Failure [PROP GND SOL] . . . . . . . . 3A-7

Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7Engine Oil System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7

Low Oil Pressure Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7High Oil Pressure Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7Chip Detect [L CHIP DETECT] or [R CHIP DETECT] . . . . . . . . . . . . . . 3A-8

Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-8Crossfeed (One-Engine-Inoperative Operation) . . . . . . . . . . . . . . . . . . 3A-8No Fuel Transfer [L NO FUEL XFR] or [R NO FUEL XFR] . . . . . . . . . . 3A-8Fuel Quantity Low [L FUEL QTY] or [R FUEL QTY] . . . . . . . . . . . . . . . 3A-9

Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-9Single Generator Failure [L DC GEN] or [R DC GEN] . . . . . . . . . . . . . . 3A-9Generator Tie Open [L GEN TIE OPEN] or [R GEN TIE OPEN] . . . . . . 3A-9Both Generator Ties Open [L GEN TIE OPEN] & [R GEN TIE OPEN] 3A-10Battery Tie Open [BAT TIE OPEN] . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-10Circuit Breaker Tripped . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-10

Flight Controls. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-11Yaw Damp/Rudder Boost System Inoperative. . . . . . . . . . . . . . . . . . . 3A-11

Landing Gear System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-11Hydraulic Fluid Low [HYD FLUID LOW] . . . . . . . . . . . . . . . . . . . . . . . 3A-11Landing Gear Manual Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-11

Environmental Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-12Duct Overtemperature [DUCT OVERTEMP] . . . . . . . . . . . . . . . . . . . . 3A-12

Ice Protection Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-13Electrothermal Propeller Deice (Auto System) . . . . . . . . . . . . . . . . . . 3A-13Electrothermal Propeller Deice (Manual System) . . . . . . . . . . . . . . . . 3A-13Engine Anti-Ice Failure [L ENG ICE FAIL] or [R ENG ICE FAIL] . . . . . 3A-13Surface Deice Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14Pitot-Static Mast Heat Failure [L PITOT HEAT] or [R PITOT HEAT] . . . 3A-14Brake Deice (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14

Static Air System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14Pilot’s Alternate Static Air Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14

Cracked Or Shattered Windshield . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-15Crack In Any Side Window (Cockpit or Cabin) . . . . . . . . . . . . . . . . . . . . . 3A-16

Model B300/B300C

3A-2 April, 2006

SECTION 3AABNORMAL PROCEDURSTABLE OF CONTENTS (CONT’D)

SUBJECT PAGE

Severe Icing Conditions(Alternate Method Of Compliance With FAA AD 98-04-24) . . . . . . . . . . . . 3A-16

Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-17Avionics Master Power Switch Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-17MFD (Multifunction Display) Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-17Pilot PFD (Primary Flight Display) Failure. . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-17GPWS Alert . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-18EGPWS Terrain Or Obstacle Alert . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-18EGPWS Mode Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-19GPS-FMS Disagree or GPS Not Available FMS Message . . . . . . . . . . . . . . .3A-19Single CDU Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-19Dual CDU Failure (If Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-19RTU Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-19FMS Auto Tune Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-20Single Audio System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-20Autopilot Mistrim Annunciation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-20Miscompare Annunciators. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-21

ALT or IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-21FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-21GS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-22HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-22LOC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-22N1 or N2 or ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-22PIT or ROL or ATT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-22

No Compare Annunciators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-23Crosstalk Fail . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3A-23

ts93910

Rectangle

ts93910

Rectangle

ts93910

Rectangle

ts93910

Rectangle

Section 3AAbnormal Procedures Model B300/B300C

3A-20

FMS AUTO TUNE FAILUREA failure of the FMS to Auto Tune VOR and DME frequencies may be noted byone or more of the following indications:

1. The NAV frequencies are continuously cycling.2. The NAV frequencies are failing to cycle to stations within a reasonable

range of the airplane. 3. Display of the yellow VOR/FMS DISAGREE message on the CDU.

If a failure of the FMS Auto Tune Function is Detected:1. CDU . . . . . . . . . SELECT MAN TUNING ON THE NAV CONTROL PAGE

If the failure is not remedied:

2. Remote Tune Switch (on reversionary panel) . . . . . . . . SELECT DISABLE3. Select VOR 1 or VOR 2 for Navigation.

SINGLE AUDIO SYSTEM FAILUREAudio Switch (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUDIO ALTN

AUTOPILOT MISTRIM [E] or [A]Illumination of a yellow-boxed E (Elevator) or A (Aileron) annunciation on thePFD’s indicates the autopilot is flying the airplane in a mistrimmed condition.

NOTEIntentional or automatic disengagement of the autopilot without re-straining the control wheel during a mistrim condition will produce asignificant airplane response in the direction of the mistrim force.

If A Mistrim Indication Continues For More Than A Few Seconds:

1. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD FIRMLY (Control forces may exceed 15 pounds)

2. A/P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISENGAGE3. Retrim airplane if necessary.4. Fuel Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

(Rebalance if required)5. A/P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

April, 2006

Abnormal ProceduresSection 3A

Model B300/B300C

3A-21

MISCOMPARE ANNUNCIATORSMiscompare annunciators are displayed on the PFD to alert the pilot that redun-dant data from dual systems is not agreeing within limits. Attitude, heading, alti-tude and airspeed data are monitored full time. Full time comparators are providedfor engine N1, N2 and ITT.

Miscompare annunciators are displayed in yellow, flashing for 5 seconds initiallyand then remain illuminated. The annunciators will extinguish when the miscom-pare condition is removed.

Two independent sources are required for each comparator function and the com-parators are disabled if ADC or AHRS reversion is selected or either side hasfailed.

If miscompare annunciators are observed, the crew should attempt to ascertainwhich system/component is erroneous. Use of the Electronic Standby InstrumentSystem may assist this process. The applicable reversionary mode for ADC orAHRS will provide cross-side data for display. No reversionary capability for en-gine miscompares is available.

ALT or IAS

These annunciators indicate a mismatch between the pilot’s and copilot’s dis-played altitude or airspeed. This mismatch could be due to problems in one ormore of the following systems:

• The pilot’s ADC• Copilot’s ADC• The pilot’s pitot-static system• The copilot’s pitot-static system

1. Establish airplane in straight and level, unaccelerated flight.2. Compare pilot and copilot altitude and airspeed with those displayed on the

Electronic Standby Instrument System. Note that the copilot’s pitot-staticsystem also serves the Electronic Standby Instrument System. Thus, an er-ror in that pitot-static system will produce identical displays on the ESIS andthe copilot’s display.

3. Determine which air data computer or pitot-static system is in error. Prob-lems in either pitot-static system may require slight climbs or descents to de-termine the faulty system.

4. Select the ADC for the side which is displaying the proper altitude and air-speed.

FD

This annunciation indicates a mismatch between the pilot’s and copilot’s flight di-rector data, or pilots and copilots navigation source disagree.

1. A/P & YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE2. Determine navigation data matches couple side annunciation.

April, 2006

Section 3AAbnormal Procedures Model B300/B300C

3A-22

3. Continue the approach without use of the flight director if able. Otherwiseexecute a missed approach.

GS

This annunciation indicates a mismatch between the pilot’s and copilot’s dis-played glideslope data.

1. Determine correct NAV source and select as necessary.2. If unable to determine the correct source, proceed visually if able and either

descend to localizer only minimums or execute a missed approach.

HDG

This annunciation indicates a mismatch between the pilot’s and copilot’s dis-played heading data.

1. Establish airplane in straight and level, unaccelerated flight.2. Compare indications with the Electronic Standby Instrument System.3. Determine if pilot’s or copilot’s heading display is in error.4. AHRS Switch. . . . . . . . . . . . . . . . . . . . . . . . . SELECT OPERATIVE AHRS

LOC

This annunciation indicates a mismatch between the pilot’s and copilot’s dis-played localizer data.

1. Determine correct NAV source and select as necessary.2. If unable to determine the correct source, proceed visually if able or execute

a missed approach.

N1 or N2 or ITT

This annunciation indicates a mismatch between the independent sources of en-gine data.• Power . . . . . . . . . . . . . . . . . . . . . . . . . . . IF FLIGHT CONDITIONS WARRANT,

REDUCE AS REQUIRED TO MAINTAIN ENGINE WITHIN LIMITS

PIT or ROL or ATT

This annunciation indicates a mismatch between the pilot’s and copilot’s dis-played attitude data.

1. Establish airplane in straight and level, unaccelerated flight.2. Compare indications with the Electronic Standby Instrument System.3. Determine if pilot’s or copilot’s attitude is in error.4. AHRS Switch. . . . . . . . . . . . . . . . . . . . . . . . . SELECT OPERATIVE AHRS

April, 2006