Limitations b407

BHT-407-FM-1

REISSUE — 17 DECEMBER 2002REVISION 7 — 30 JUL 2008

ROTORCRAFTFLIGHT MANUAL

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

TYPE CERTIFICATE NO. ________

REGISTRATION NO. ______________________ SERIAL NO. ____________________

APPROVED BY DATE _____________________

DIRECTOR — AIRCRAFT CERTIFICATION BRANCHDEPARTMENT OF TRANSPORT

THE AVIATION REGULATORY AUTHORITY FOR THIS FLIGHT MANUAL IS THECANADIAN DEPARTMENT OF TRANSPORT, AIRCRAFT CERTIFICATION BRANCH.

U.S. REGISTERED HELICOPTERS ARE APPROVED BY THE FAA IN ACCORDANCE WITH THE PROVISIONS OF 14 CFR SECTION 21.29 ON

H-92

9 FEBRUARY 1996

23 FEBRUARY 1996

COPYRIGHT NOTICECOPYRIGHT 2008BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRONCANADA LTD.

ALL RIGHTS RESERVED

NOTICE PAGE

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NP———17 DEC 2002

BHT-407-FM-1

The following Warning is not applicable to helicopters on which all kits and customizinginstallations have been qualified and approved by Bell Helicopter.

WARNING

THE HELICOPTER MAY CONTAIN INSTALLATIONS, PARTS, ORPROCESSES CERTIFIED BY PARTIES OTHER THAN BELLHELICOPTER TEXTRON. BELL HELICOPTER CAN NOTCONFIRM THAT SUCH INSTALLATIONS HAVE BEEN FULLYQUALIFIED OR CONFORMED TO BELL HELICOPTER DESIGNCRITERIA. AS A RESULT OF SUCH INSTALLATIONS, BELLHELICOPTER SUPPLIED DATA MAY NOT BE VALIDCONCERNING IN-FLIGHT HANDLING QUALITIES, WEIGHT ANDBALANCE, OR HELICOPTER PERFORMANCE. IF MULTIPLE STCKITS OR SIMILAR INSTALLATIONS ARE INCORPORATED,THERE MAY BE NOT VALID TEST DATA TO QUALIFY THEHELICOPTER AS MODIFIED BY THESE INSTALLATIONS. FORREVISED DATA, CONTACT THE OWNER OF THE INSTALLEDSTC OR THE SUPPLIER FOR THE APPLICABLE APPROVAL OFEACH INSTALLATION.

30 JUL 2008—Rev. 7———A/B

BHT-407-FM-1

LOG OF PAGES

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NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

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LOG OF REVISIONS

APPROVED DATE

CHIEF, FLIGHT TESTFORDIRECTOR — AIRCRAFT CERTIFICATIONTRANSPORT CANADA

30 JUL 2008—Rev. 7———C/D

BHT-407-FM-1

Original ..................... 0...................... 09 FEB 96Revision .................... 1..................... 08 MAR 96Revision .................... 2......................09 MAY 96Revision .................... 3.......................30 JUL 96Revision .................... 4......................04 NOV 96Revision .................... 5...................... 24 JUN 97Revision .................... 6.......................03 JUL 98Revision .................... 7...................... 04 SEP 98Revision .................... 8...................... 17 APR 00

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LOG OF TC APPROVED REVISIONS

LOG OF FAA APPROVED REVISIONS

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30 JUL 2008—Rev. 7———E/F

BHT-407-FM-1

TC APPROVED BHT-407-FM-1

19 FEB 2007—Rev. 5———1-3

Section 1LIMITATIONS

11-1. INTRODUCTION

Compliance with Limitations section isrequired by appropriate operating rules.Anytime an operating limitation is exceeded,an appropr iate entry shal l be made inhelicopter logbook. Entry shall state whichlimit was exceeded, duration of time, extremevalue attained, and any additional informationessential in determining maintenance actionrequired.

In ten t iona l use o f t rans ient l imi ts isprohibited.

Torque events shall be recorded. A torqueevent is defined as a takeoff or lift, internal orexternal load (BHT-407-MD-1).

Landings shall be recorded. Run-on landingsshall be recorded separately.

A run-on landing is defined as one wherethere is fo rward ground t rave l o f thehelicopter greater than 3 feet with the weighton the skids.

1-2. BASIS OF CERTIFICATION

This helicopter is certified under FARs Parts27 and 36, Appendix J. Additionally, it isapproved under Canadian AirworthinessManual Chapters 516 (ICAO Chapter 11) and527, Sections 1093 (b) (1) (ii) and (iii), 1301-1,1557 (c) (3), 1581 (e) and 1583 (h).

1-3. TYPES OF OPERATION

1-3-A. PASSENGERS

Basic configured helicopter is approved forseven place seating and is certified for land

operation under day or night VFR non-icingconditions.

1-3-B. CARGO

The maximum allowable cabin deck loadingfor cargo is 75 pounds per square foot (3.7 kgper 100 cm2). The maximum al lowablebaggage compartment deck loading is 86pounds per square foot (4.2 kg per 100 cm2)with a maximum allowable weight of 250pounds (113.4 kg). Refer to BHT-407-MD-1 forcargo restraint and tie-down locations.

Cargo must be properly secured by tie-downdevices to prevent the load from shiftingunder ant ic ipated f l igh t and g roundoperations. If the mission requires bothpassengers and cargo to be transportedtogether, the cargo must be loaded andsecured so tha t i t does no t obs t ructpassenger access to exits.

1-4. FLIGHT CREW

Minimum flight crew consists of one pilot whoshall operate helicopter from right crew seat.

Left crew seat may be used for an additionalpi lot when approved dual controls areinstalled.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

A functional flashlight is required for nightflights.

FADEC system software shall be version5.202.

BHT-407-FM-1 TC APPROVED

1-4———Rev. 7—30 JUL 2008

1-5-B. OPTIONAL EQUIPMENT

The snow deflector kit (BHT-407-FMS-4) shallbe ins ta l led when conduct ing f l ightoperations in falling and/or blowing snow.

Refer to appropr ia te f l ight manualsupplement (s ) (FMS) for addi t iona llimitations, procedures, and performance datafor optional equipment.

1-5-C. DOORS REMOVED

NOTE

Indicated altitude may be up to 100feet lower than actual altitude withcrew door(s) removed.

Flight with any combination of doors removedis approved. With litter door removed, leftpassenger door shall be removed. Refer toAirspeed limitations.

With door(s) removed, determine weightchange and adjust ballast if necessary. Referto Section 5.

NOTE

Al l unsecured i tems sha l l beremoved from cabin when any dooris removed.

1-6. WEIGHT AND CENTER OFGRAVITY

1-6-A. WEIGHT

Maximum approved internal GW for takeoffand landing is 5000 pounds (2268 kg).

Minimum GW for f l ight is 2650 pounds(1202 kg).

Minimum weight at fuselage station 65.0 is170 pounds (77.1 kg).

CAUTION

LOADS THAT RESULT IN GWABOVE 5000 POUNDS (2268 KG)SHALL BE CARRIED ON THECARGO HOOK AND MUST BEJETTISONABLE.

Maximum approved GW for f l ight wi thjettisonable external load is 6000 pounds(2722 kg).

1-6-B. CENTER OF GRAVITY

The pilot is responsible for determiningweight and balance to ensure gross weightand center of gravity will remain within limitsthroughout each flight. Refer to Section 5 forloading tables and instructions.

NOTE

Ballast as required to maintain mostforward or most aft CG within GWflight limits (Figure 1-1). For standardpassenger and fue l load ings ,applicable Weight Empty Center ofGravity Chart in BHT-407-MM-1 maybe used to determine requiredballast.

For longitudinal CG limits, refer to GrossWeight Longitudinal Center of Gravity Limitschart (Figure 1-1).

For lateral CG limits, refer to Gross WeightLateral Center of Gravity Limits (Figure 1-2).

1-7. AIRSPEED

Basic VNE is 140 KIAS, sea level to 3000 feetHD. Decrease VNE for ambient conditions inaccordance with AIRSPEED LIMITATIONSPlacards and Decals (Figure 1-3).

VNE at 93.5 to 100% TORQUE (takeoff power)is 100 KIAS, not to exceed placarded VNE.


30 JUL 2008—Rev. 7———1-5

VNE is 100 KIAS or placarded VNE, whicheveris less, when takeoff loading is in shaded areaof the Gross Weight Lateral Center of GravityLimits (Figure 1-2).

VNE is 100 KIAS with any door(s) removed, notto exceed placarded VNE.

VNE is 100 KIAS or placarded VNE, whicheveris less for steady state autorotation.

Maximum allowable airspeed for sidewardand rearward flight or crosswind hover is 35KTAS.

1-8. ALTITUDE

Maximum operating altitude is 20,000 feet HDor 20,000 feet HP, whichever is lower.

1-9. MANEUVERING

1-9-A. PROHIBITED MANEUVERS

Aerobatic maneuvers are prohibited.

1-9-B. CLIMB AND DESCENT

Maximum rate of climb is 2000 feet perminute.

1-9-C. SLOPE LANDING

CAUTION

SLOPE LANDINGS HAVE BEENDEMONSTRATED TO THE SLOPELANDING L IMITS. OTHERCONDITIONS INCLUDING, BUT NOTLIMITED TO, WIND DIRECTION ANDVELOCITY, CENTER OF GRAVITY,AND THE CONDIT ION OF THESLOPE (LOOSE ROCK, SOFT MUD,SNOW, WET GRASS, ETC.) MAYLIMIT MAXIMUM SLOPE TO A VALUELESS THAN THE PUBLISHEDLIMITS.

Slope landings are limited to 10° side slopes,10° nose up slope or 5° nose down slope.

1-10. NOT USED

1-11. AMBIENT TEMPERATURES

Maximum sea level ambient air temperaturefor operation is 51.7°C (125°F) and decreaseswith HP at standard lapse rate of 2°C (3.6°F)per 1000 fee t . Refer to Ambien t A i rTemperature Limitations chart (Figure 1-4).

Min imum ambient a i r temperature foroperation at all altitudes is -40°C (-40°F).

ENG ANTI ICE shall be ON in visible moisturewhen OAT is below 5°C (40°F).

1-12. ELECTRICAL

1-12-A. GENERATOR

1-12-B. STARTER

Continuous operation,up to 10,000 feet Hp

0 to 180 amps

Maximum continuous up to 10,000 feet Hp

180 amps

Continuous operation,above 10,000 feet Hp

0 to 170 amps

Maximum continuous above 10,000 feet Hp

170 amps

Transient, 2 minutes 180 to 300 amps

Transient, 5 seconds 300 to 400 amps

External Power Start Battery Start

40 seconds ON 60 seconds ON

30 seconds OFF 60 seconds OFF


30 seconds OFF 60 seconds OFF


30 minutes OFF 30 minutes OFF


1-6———Rev. 7—30 JUL 2008

NOTE

28 VDC GPU for starting shall belimited to 500 amps.

1-13. POWER PLANT

Rolls-Royce model 250-C47B.

NOTE

Inten t iona l use o f any powertransient is prohibited.

1-13-A. GAS PRODUCER RPM (NG)

NOTE

FADEC will limit NG in accordancewith GAS PRODUCER RPM (NG)LIMIT placard. NR decay will result ifpower demand exceeds placard limit.

Maximum cont inuous NG is l im i ted inaccordance with GAS PRODUCER RPM (NG)LIMIT placard (Figure 1-3) when operatingabove 10,000 feet HP and with OAT below-30°C (-22°F).

1-13-B. POWER TURBINE RPM (NP)

NOTE

ENGINE OVSPD warning light willilluminate when NP versus TORQUEis between 102.4% NP at 100%TORQUE and 108.6% NP at 0%TORQUE.

When operating in MANUAL mode NPshould be maintained between 95and 100%.

1-13-C. MEASURED GAS TEMPERATURE(MGT)

GAUGE P/N 407-375-001-101/-103

NOTE

Either MGT gauge may be installed.

GAUGE P/N 407-375-001-105 AND SUB

Continuous operation 63 to 105%

Maximum continuous operation

105%

Transient, 10 seconds 105.1 to 106%

Avoid continuousoperations

68.4 to 87.1%

Minimum 99%


Maximum continuous 100%

Maximum transient, 15 seconds

102.1 to 107% NP

Continuous operation 100 to 727°C

Maximum continuous 727°C

Takeoff, 5 minutes 727 to 779°C

Maximum for takeoff 779°C

Transient, 12 seconds 780 to 826°C

Maximum starting, do not exceed 10 seconds above 826°C or 1 second at 927°C.

927°C


Maximum continuous 727°C

Takeoff, 5 minutes 727 to 779°C

Maximum for takeoff 779°C

Transient, 12 seconds 780 to 905°C

Maximum starting, do not exceed 10 seconds above 843°C or 1 second at 927°C.

927°C


30 JUL 2008—Rev. 7———1-7

1-13-D. ENGINE TORQUE

NOTE

Use of takeoff power is limited to 100KIAS, not to exceed placarded VNE.

1-13-E. FUEL PRESSURE

1-13-F. ENGINE OIL PRESSURE

NOTE

When 130 PSI is exceeded duringstart, operate engine at idle until oilpressure drops below 130 PSI.

1-13-G. ENGINE OIL TEMPERATURE

NOTE

Positive temperature indication iswhen the second segment of thetrend arc is illuminated.

1-14. TRANSMISSION

1-14-A. TRANSMISSION OIL PRESSURE

1-14-B. TRANSMISSION OILTEMPERATURE

1-15. ROTOR

1-15-A. ROTOR RPM — POWER ON

NOTE

When operating in MANUAL modeNR should be maintained between95% and 100%.

1-15-B. ROTOR RPM — POWER OFF

CAUTION

FOR AUTOROTATIVE TRAINING,MAINTAIN STEADY STATE N RABOVE 90%.

1-16. HYDRAULIC

Hydraulic fluid MIL-PRF-5606 (NATO H-515)may be used at all ambient temperatures.

Continuous operation 0 to 93.5%

Maximum continuous 93.5%

Takeoff, 5 minute 93.5 to 100%

Transient, 5 seconds 105%

Minimum 8 PSI

Continuous operation 8 to 25 PSI

Maximum 25 PSI

Minimum below 79% NG 50 PSI

Minimum from 79 to 94% NG

90 PSI

Minimum above 94% NG 115 PSI

Maximum 130 PSI

Maximum cold starts only 200 PSI


Maximum 107°C

Minimum 30 PSI

Continuous operation 40 to 70 PSI

Maximum 70 PSI


Maximum 110°C


Maximum continuous 100%

Minimum 85%


Maximum 107%


1-8———Rev. 7—30 JUL 2008

1-17. FUEL AND OIL

1-17-A. FUEL

Fuel conforming to following specificationsmay be used at all ambient temperatures:

ASTM-D-6615, Jet B

MIL-DTL-5624, Grade JP-4 (NATO F-40)

Fuels conforming to following specificationsare limited to ambient temperatures of -32°C(-25°F) and above:

ASTM-D-1655, Jet A or A-1

MIL-DTL-5624, Grade JP-5 (NATO F-44)

MIL-DTL-83133, Grade JP-8 (NATO F-34).

For operations below -32°C (-25°F), refer toRolls-Royce Operation and MaintenanceManual for cold weather fuel and blendinginstructions.

1-17-B. OIL

1-17-B-1. OIL — ENGINE

Oil conforming to MIL-PRF-7808 (NATOO-148), DOD-PRF-85734 or MIL-PRF-23699(NATO O-156) is l im i ted to ambienttemperatures above -40°C (-40°F).

NOTE

Refer to Rolls-Royce Operation andMaintenance Manual andBHT-407-MD-1 manual for approvedoils and mixing of oils of differentbrands, types, and manufacturers.

1-17-B-2. OIL — TRANSMISSION AND TAILROTOR GEARBOX

NOTE

It is recommended DOD-PRF-85734oil be used in transmission and tailrotor gearbox to maximum extentallowed by temperature limitations.

Oil conforming to DOD-PRF-85734 is limitedto ambient temperatures above -40°C (-40°F).

Oil conforming to MIL-PRF-7808 (NATO O-148)is limited to ambient temperatures below-18°C (0°F).

1-18. ROTOR BRAKE

Rotor brake (if installed) application is limitedto ground operation after engine has beenshut down and NR has decreased to 40% orlower.

For emergency stops, apply rotor brake anytime after engine is shut down.

Engine starts with rotor brake engaged areprohibited.

1-19. NOT USED

1-20. INSTRUMENT MARKINGSAND PLACARDS

Refer to Figure 1-3 for Placards and Decals.Refer to Figure 1-5 for Instrument Markings.

Illustrations shown in Figure 1-5 are artistrepresentations and may or may not depictactual approved instruments due to printinglimitations. Instrument operating ranges andlimits shall agree with those presented in thissection.


30 JUL 2008 Rev. 7 1-15

Figure 1-3. Placards and Decals (Sheet 3 of 3)

FADEC SOFTWARE VERSION 5.202

WITH DIRECT REVERSION TO

MANUAL INSTALLED. REFER TO

FLIGHT MANUAL FOR OPERATION

Location: Instrument panel

MAX ALLOWABLE WEIGHT 250 LBS.

MAX ALLOWABLE WEIGHT PER SQ. FT. 86 LBS.

Location: Inside of baggage door

FUEL CAPACITY

BASIC 869 LBS

WITH AUX 1005 LBS

(JET A AT 15ºC)

Location: Instrument panel

GAS PRODUCER RPM (NG) LIMIT

WHEN ABOVE 10,000 FT HP

MAXIMUM Ng % RPM WITH OAT IS AS FOLLOWS

Location: Above pilot windshield

OAT

ºC

MAX

Ng %99.0

-40

99.2

-39

99.4

-38

99.6

-37

99.8

-36

100.0

-35

100.2

-34

100.4

-33

100.6

-32

100.8

-31

101.1

-30

Location: Instrument panel and passenger compartment

407_FM_1_0002


1-16 17 DEC 2002

Figure 1-4. Ambient air temperature limitations

-40 -30 -20 -10 0 10 20 30 40 50 60

AMBIENT AIR TEMPERATURE - °C

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PR

ES

SU

RE

ALT

ITU

DE

- F

T

-40 -20 0 20 40 60 80 100 120 140

AMBIENT AIR TEMPERATURE - °F M

INIM

UM

OA

T FL

IGH

T LI

MIT

MAXIM

UM O

AT

EXAMPLE: AT HP = 7000 FTMAX OAT = 37.8°C (100°F)MIN OAT = - 40°C (- 40°F)

FLIGHT LIM

IT

MAXIMUM HD FLIGHT LIMIT

M407_FM-1__FIG_1-4.EMF


17 DEC 2002 1-17

Figure 1-5. Instrument markings (Sheet 1 of 4)

ENGINE OIL PRESSURE

50 PSI

50 to 90 PSI

90 to 115 PSI

115 to 130 PSI

130 PSI

200 PSI

ENGINE OIL TEMPERATURE

0 to 107°C

107°C

Minimum

Operation below 79% NG RPM

Continuous operation below 94% NG RPM

Maximum for continuous operation

Maximum for cold start

Continuous operation

Maximum


TRANSMISSION OIL PRESSURE

30 PSI

40 to 70 PSI

70 PSI

TRANSMISSION OIL TEMPERATURE

15 to 110°C

110°C

Minimum


Maximum


Maximum

NG (GAS PRODUCER RPM)

63 to 105%

105%

106%


Maximum continuous operation


M407_FM-1__FIG_1-5_(1_OF_4).EPS


1-18 Rev. 7 30 JUL 2008

Figure 1-5. Instrument Markings (Sheet 2 of 4)

TRQ (TORQUE)

MGT (MEASURED GAS TEMPERATURE)


5 minute takeoff range

Maximum for takeoff

Beginning of 10 seconds

range for starting

Maximum for start and shutdown

(1 second maximum)

407_FM_1_0003


Maximum for autorotation

Maximum

407-375-001-105 AND SUB.

Either gauge may be installed*

*

AIRSPEED

0 to 93.5%

93.5 to 100%

100%

0 to 140 Knots

100 Knots

140 Knots

100 to 727°C

727 to 779°C

779°C

826°C

or

843°C

927°C


5 minute takeoff range

Maximum


30 JUL 2008 Rev. 7 1-19

Figure 1-5. Instrument Markings (Sheet 3 of 4)

99%

99 to 100%

100%

Minimum


Maximum continuous

NP (POWER TURBINE RPM)

407_FM_1_0004

FUEL QUANTITY

0 LBS

195 LBS

869 LBS

1005 LBS

(Jet A 6.8 lbs/gal)

All tanks empty (zero useable)

Forward tank empty

Forward and aft tanks full

Forward, aft and auxiliary

tanks full

85%

85 to 107%

107%

Minimum (power off)

Continuous operation (power off)

Maximum (power off)

NR (ROTOR RPM)

407-375-008-101/-103


1-20 Rev. 3 26 APR 2005

Figure 1-5. Instrument markings (Sheet 4 of 4)

407FM_1_0001

DC LOAD

DC LOAD

FUEL PRESSURE

FUEL PRESSURE

* Either gauge may be installed.

* P/N 407-075-024-101

* P/N 407-075-024-103, 407-375-007-105 or 407-375-007-107

170 Amps

0 to 180 Amps

180 Amps

180 Amps

170 Amps

300 Amps

400 Amps

8 PSI

8 PSI

8 to 25 PSI

8 to 25 PSI

25 PSI

25 PSI

Maximum continuous above 10,000 FT Hp


Maximum

Maximum

Maximum continuous above 10,000 FT Hp

Maximum transient, 2 minutes




Maximum

Maximum

Minimum

Minimum

VERTICAL SPEED INDICATOR

2,000 Feet per minute up Maximum


19 FEB 2007—Rev. 5———2-7

7. Control linkages to swashplate —Condition, security of attachmentbolts and locking hardware.

8. Control tube hydraulics-off balancesprings — Condition and security.

9. Hydraulic reservoir filler cap —Closed and locked.

10. Hydraulic system filters — Bypassindicator retracted.

11. Hydraulic actuators and lines —Condition, security, interference,leakage.

2-3-B-7. FUSELAGE — CABIN LEFT SIDE

1. Forward fairing and access door —Secured.

2. Cabin doors and hinge bolts —Condition and security.

3. Windows — Condition and security.

4. Hydraulic reservoir — Check fluidlevel.

5. Landing gear — Condition andground handling wheel removed.

6. Forward and aft crosstube fairings (ifinstalled) — Secured, condition, andaligned.

7. Left static port — Condition.

2-3-B-8. FUSELAGE — FRONT

1. Exterior surfaces — Condition.

2. Windshield — Condition andcleanliness.

3. Battery and vent lines — Conditionand security.

4. HOUR METER circuit breaker — In.

5. Battery access door — Secured.

6. Pitot tube — Cover removed, clear ofobstructions.

7. External power door — Conditionand security.

8. Landing light lamps — Condition.

9. Antennas — Condition and security.

2-4. INTERIOR AND PRESTARTCHECK

1. Cabin interior — Clean, equipmentsecured.

2. Fire extinguisher — Installed andsecured.

3. Cabin loading — Maintain CG withinlimits.

4. Passenger seat belts — Secured.

5. Copilot seat belt — Secured (if solo).

6. Doors — Secured.

7. Throttle — Closed.

8. LDG LTS switch — OFF.

9. Communications switches — Set.

10. Altimeter — Set.

11. Instruments — Correct indications.

12. Overhead switches — Set:

a. BATT switch — OFF.

b. GEN switch — OFF.

c. PART SEP switch (if installed) —OFF.

d. ANTI COLL LT switch — ANTICOLL LT (on).

e. HYD SYS switch — HYD SYS(on).

f. CABIN LT/PASS switch — OFF.

g. POS LT switch — As desired.

h. DEFOG switch — OFF.

i. PITOT HEATER switch — OFF.


2-8———Rev. 7—30 JUL 2008

j. ENG ANTI ICE switch — OFF.

k. AVIONICS MASTER switch —OFF.

l. HEATER switch (if installed) —OFF.

m. INSTR LT rheostat — OFF.

13. Overhead circuit breaker switches —OFF.

14. Overhead circuit breakers — In.

15. Rotor brake handle (if installed) — Upand latched.

CAUTION

28 VDC GPU SHALL BE 500AMPERES OR LESS TO REDUCERISK OF STARTER DAMAGE FROMOVERHEATING.

16. GPU — Connected (if used).

17. BATT switch — ON for battery start,ON for GPU start, OFF for battery cartstart. Observe the following:

a. Low rotor audio horn activated.

NOTE

With “Ah lers” NR/NP gaugeinstalled, NR/NP needles do not selftest.

b. For 8 seconds,

(1) Trend arcs on LCDinstruments indicate fullscale.

(2) TORQUE and NG digitsdisplay 8188.8.

(3) MGT and FUEL digitsdisplay 81888.

(4) NR and NP needles move to107% and 100%,respectively.

c. After 3 seconds; ENG OUT,FADEC DEGRADE, FADECFAULT, RESTART FAULT, andENGINE OVSPD lightsilluminate with activation ofengine out audio for 3 seconds.

d. ENG OUT light re-illuminateswith reactivation of engine outaudio, after 3 seconds.

18. HORN MUTE button — Press to mute.

19. Caution lights — ENG OUT, XMSNOIL PRESS, RPM, HYDRAULICSYSTEM, GEN FAIL, L/FUEL BOOST,R/FUEL BOOST, L/FUEL XFR, and R/FUEL XFR will be illuminated.

NOTE

L/FUEL XFR and R/FUEL XFR will notbe illuminated when forward fueltank is empty.

20. PEDAL STOP PTT switchannunciator:

Pedals — Centered.

Press — Verify PEDAL STOP cautionand ENGAGED annunciatorilluminated and left pedal travelrestricted.

Release — Verify PEDAL STOPcaution and ENGAGED annunciatorextinguished and both pedals travelunrestricted.

21. Flight controls — Loosen frictions;check travel and verify CYCLICCENTERING light operation; positionfor start. Tighten friction as desired.

22. Throttle — Check freedom of traveland appropriate operation at OFF, I(idle), FLY and MAX positions.Return throttle to OFF position.

NOTE

With INSTR LT rheostat on and CAUTLT switch positioned to DIM, caution


30 JUL 2008—Rev. 7———2-9

lights are dimmed to a fixed intensityand cannot be adjusted by INSTR LTrheostat.

23. INSTR LT rheostat — As desired.

24. CAUT LT switch — As desired.

25. FUEL BOOST/XFR circuit breakerswitches — LEFT (on) and RIGHT(on) and verify all boost and transfercaution lights extinguish.

26. FUEL pressure — Check.

27. CAUTION LT TEST button — Press totest.

28. INSTR CHK button — Press andcheck for exceedances.

29. LCD TEST button — Press to test, ifdesired.

30. FADEC HORN TEST button — Pressto test.

31. FADEC MODE switch — AUTO.

32. FUEL VALVE switch — ON, guardclosed, FUEL VALVE lightilluminates then extinguishes.

33. FUEL QTY — Check TOTAL and FWDtank quantity.

34. OAT/VOLTS display — Check OATand select VOLTS.

CAUTION

ANY ATTEMPT TO START ENGINEWHEN VOLTAGE IS BELOW 24VOLTS MAY RESULT IN A HOTSTART. MONITOR FOR FADECFAILURE. IF FADEC FAILS (FADECFAIL WARNING LIGHT), ABORTSTART BY ROLLING THROTTLE TOCUTOFF AND ENGAGE STARTERTO REDUCE MGT.

2-5. ENGINE START

1. Collective — Full down.

2. Cyclic and pedals — Centered andCYCLIC CENTERING lightextinguished.

NOTE

If throttle is positioned in idle formore than 60 seconds, starterlatching is disabled and throttle mustbe repositioned to cut off and thenback to idle to enable it for another 60seconds.

It is recommended that MGT bebelow 150°C when below 10,000 feetHP or below 65 °C when above 10,000feet HP prior to attempting an enginesta r t . Compl iance w i th th isrecommendation will allow for coolerstarts and reduce potentia l ofreaching hot start abort limits. Referto DRY MOTORING RUN, paragraph2-5-A.

3. Throttle — Idle position.

4. START switch — Momentarily press(hold for approximately 1 second)and observe START and AUTORELIGHT lights are illuminated.

5. MGT — Monitor.

CAUTION

IF MAIN ROTOR IS NOT ROTATINGBY 25% NG, ABORT START BYROLLING THROTTLE TO CUTOFF.ENSURE STARTER HASDISENGAGED WHEN MGTDECREASES BELOW 150°C.

6. START light — Extinguished at 50%NG (starter has disengaged).

7. AUTO RELIGHT light — Extinguishedat 60% NG.

8. ENG and XMSN OIL pressures —Check.


2-10———Rev. 5—19 FEB 2007

CAUTION

IF ENGINE HAS BEEN SHUT DOWNFOR MORE THAN 15 MINUTES,STABILIZE AT IDLE FOR 1 MINUTEBEFORE INCREASING THROTTLE.

NOTE

During cold temperature operations,normal transmission and engine oilpressure limits may be exceededduring start. Stabilize engine at idleuntil minimum temperature andpressure limits are attained.

9. Idle — 63 ±1% NG.

10. BATT switch — ON (if applicable).

11. GPU — Disconnect and close door (ifapplicable).

12. GEN switch — GEN (on); observeGEN FAIL light extinguishes.

NOTE

Turn generator OFF if ammeterindication drops to zero amps afteran initial full scale indication. Onereset is allowed. RESET generatorand then turn generator back ON(applicable with AMPS/FUEL PSIgauge PN 407-075-024-101 and sub.).Refer to BHT-407-MD-1.

13. Voltmeter — 28.5 ±0.5 volts.

14. FLIGHT INSTR circuit breakerswitches (3) (if installed) — DG, ATTand TURN (on).

NOTE

If dual controls are installed, guardthrottle to prevent inadvertentmanipulation from co-pilot position.

2-5-A. DRY MOTORING RUN

The following procedure is used to reduceresidual MGT to recommended levels forengine start.

1. Throttle — Closed position.

2. START switch — Hold engaged for 15seconds, then release.

Follow ENGINE START procedure, paragraph2-5, once 0% NG is indicated.

2-5-B. ALTERNATE ENGINE START

This procedure may be used in hot and/orhigh altitude environment where aborted hotstarts have been experienced and when priortroubleshooting has not revealed any enginemaintenance issues.



NOTE

It is recommended that MGT bebelow 150°C when below 10,000 feetHP or below 65°C when above 10,000feet HP prior to attempting an enginesta r t . Compl iance w i th th isrecommendation will allow for coolerstarts and reduce potentia l ofreaching hot start abort limits. Referto DRY MOTORING RUN, paragraph2-5-A.

3. Throttle — Closed position.

4. START switch — Hold engaged andobserve START and AUTO RELIGHTlights are illuminated.

a. Throttle — Open to IDLE atapproximately 16% NG.

5. MGT — Monitor.


20 JUN 2007—Rev. 6———2-15

2-11. ENGINE SHUTDOWN



3. Cyclic friction — Increase so thatcyclic maintains centered position.

4. LDG LTS switch — OFF.

5. Throttle — Reduce to idle stop.Check RPM warning light illuminatedand audio on at 95% NR.

NOTE

If dual controls are installed, guardthrottle to prevent inadvertentmanipulation from co-pilot position.


7. MGT — Stabilize at idle for 2 minutes.

8. ENG ANTI ICE switch — OFF.

9. FLIGHT INSTR circuit breakersswitches (if installed) — OFF.

10. FUEL BOOST/XFR LEFT circuitbreaker switch — OFF.

NOTE

Left fuel boost and transfer pumpswill continue to operate until eitherLEFT FUEL BOOST/XFR circuitbreaker switch (highlighted withyellow border) or FUEL VALVEswitch is positioned to OFF. Thesepumps operate directly from batteryand will not be deactivated whenBATT switch is OFF. Battery powerwill be depleted if both switchesremain on.

11. ELT (if installed) — Check forinadvertent transmission.

12. AVIONICS MASTER switch — OFF.

13. GEN switch — OFF.

14. OVSPD TEST button — If required;press, hold 1 second, and release.

NOTE

Overspeed shutdown test should beaccompl ished on f i rs t eng ineshutdown of the day . ENGINEOVSPD l ight wi l l momentar i lyilluminate in addition to those lightsthat il luminate during a normalshutdown.

15. IDLE REL switch — Press and hold.

CAUTION

POSITIONING THROTTLE OUT OFCUT-OFF DURING NG SPOOL DOWNMAY CAUSE POST ENGINESHUTDOWN FIRE.

16. Throttle — Closed; check MGT andNG decreasing, ENGINE OUTwarning light illuminated and audioon at 55 ±1%.


CAUTION

AVOID RAPID ENGAGEMENT OFROTOR BRAKE IF HELICOPTER ISON ICE OR OTHER SLIPPERY ORLOOSE SURFACE TO PREVENTROTATION OF HELICOPTER.

18. Rotor brake (if installed) — Apply fullrotor brake at or below 40% NR.Return rotor brake handle to stowedposition just prior to main rotorstopping.

19. FUEL VALVE switch — OFF.


2-16———Rev. 7—30 JUL 2008

CAUTION

DO NOT INCREASE COLLECTIVE ORAPPLY LEFT TAIL ROTOR PEDALTO SLOW ROTOR DURINGCOASTDOWN.

20. Pilot — Remain on flight controlsuntil rotor has come to a completestop.

21. All overhead switches, except HYDSYS switch — OFF.

NOTE

Ensure engine ro ta t ion hascomplete ly s topped pr io r topositioning BATT switch to OFF.

22. BATT switch — OFF, with NG at 0%.

CAUTION

APPLICABLE MAINTENANCEACTION MUST BE PERFORMEDPRIOR TO FURTHER FLIGHT IF AFADEC LIGHT HAS ILLUMINATEDDURING THE PREVIOUS FLIGHT ORON ENGINE SHUTDOWN.

NOTE

If shutting down at, or refueling to,between approximately 195 to 213

pounds total fuel quantity, up to 18pounds of fuel may remain in forwardfuel cell as unusable.

2-12. POSTFLIGHT CHECK

If any of following conditions exist:

• Thunderstorms are in local area orforecasted.

• Winds in excess of 35 knots or agust spread of 15 knots exists or isforecasted.

• Helicopter is parked within 150 feetof hovering or taxiing aircraft thatare in excess of basic GW ofhelicopter.

• Helicopter to be left unattended.

Perform following:

1. Install main rotor blade tie-downs.

2. Secure tail rotor loosely to tailboomwith tie-down strap to preventexcessive flapping.

3. Install exhaust cover, engine inletprotective plugs and pitot cover.

NOTE

Refer to BHT-407-MD-1 for additionaltie-down data.


30 JUL 2008 Rev. 7 3-1/3-2

Section 3EMERGENCY/MALFUNCTION PROCEDURES

3TABLE OF CONTENTS

Paragraph PageSubject Number Number

Introduction ............................................................................................ 3-1 ........... 3-3Definitions .............................................................................................. 3-2 ........... 3-3Engine ..................................................................................................... 3-3 ........... 3-3

Engine Failure .................................................................................... 3-3-A ....... 3-3Engine Restart in Flight..................................................................... 3-3-B ....... 3-4Engine Underspeed ........................................................................... 3-3-C ....... 3-6Engine Overspeed ............................................................................. 3-3-D ....... 3-6Engine Compressor Stall .................................................................. 3-3-E ....... 3-6Engine Hot Start/Shutdown .............................................................. 3-3-F........ 3-7Engine Oil Pressure Low or Fluctuating.......................................... 3-3-G....... 3-7Engine Oil Temperature High ........................................................... 3-3-H ....... 3-7Driveshaft Failure............................................................................... 3-3-J........ 3-8FADEC Failure.................................................................................... 3-3-K ....... 3-8

Fire .......................................................................................................... 3-4 ........... 3-9Engine Fire on Ground ...................................................................... 3-4-A ....... 3-9Engine Fire During Flight .................................................................. 3-4-B ....... 3-9Cabin Smoke or Fumes ..................................................................... 3-4-C ....... 3-9

Tail Rotor ................................................................................................ 3-5 ........... 3-10Complete Loss of Tail Rotor Thrust................................................. 3-5-A ....... 3-10Fixed Pitch Failures ........................................................................... 3-5-B ....... 3-10

Hydraulic System................................................................................... 3-6 ........... 3-11Loss of Hydraulic Pressure .............................................................. 3-6-A ....... 3-11Flight Control Actuator Malfunction ................................................ 3-6-B ....... 3-12

Electrical System ................................................................................... 3-7 ........... 3-12Generator Failure ............................................................................... 3-7-A ....... 3-12Excessive Electrical Load ................................................................. 3-7-B ....... 3-12

Fuel System............................................................................................ 3-8 ........... 3-13Cyclic Jam .............................................................................................. 3-9 ........... 3-13Warning, Caution, and Advisory Lights/Messages ............................ 3-10 ......... 3-14

LIST OF TABLES

Table PageSubject Number Number

Warning (Red) Lights............................................................................. 3-1 ........... 3-15Caution (Amber) and Advisory (White/Green) Lights......................... 3-2 ........... 3-16


30 JUL 2008 Rev. 7 3-3

Section 3EMERGENCY/MALFUNCTION PROCEDURES

33-1. INTRODUCTIONFollowing procedures contain indications offailures or malfunctions which affect safety ofcrew, hel icopter, ground personnel orproperty; use of emergency features ofprimary and backup systems; and appropriatewarnings, cautions, and explanatory notes.Tables 3-1 and 3-2 list fault conditions andcorrective actions for warning lights andcaution/advisory lights respectively.

NOTE

All corrective action procedureslisted herein assume pilot gives firstpriority to helicopter control and asafe flight path.

A tripped circuit breaker should notbe reset in flight unless deemednecessary for safe completion of theflight.

If a tripped circuit breaker is deemednecessary for safe completion of theflight, it should only be reset onetime.

Helicopter should not be operated followingany precautionary landing until cause ofmalfunct ion has been determined andcorrective maintenance action taken.

3-2. DEFINITIONSFollowing terms indicate degree of urgency inlanding helicopter.

Fo l lowing terms are used to descr ibeoperating condition of a system, subsystem,assembly, or component.

3-3. ENGINE3-3-A. ENGINE FAILURE

3-3-A-1. ENGINE FAILURE — HOVERING

INDICATIONS:

1. Left yaw.

2. ENGINE OUT and RPM warninglights illuminated.

LAND AS SOON AS POSSIBLE

Land without delay at nearest suitable area (i.e., open field) at which a safe approach and landing is reasonably assured.

LAND AS SOON AS PRACTICAL

Landing site and duration of flight are at discretion of pilot. Extended flight beyond nearest approved landing area is not recommended.

Affected Fails to operate in intended or usual manner.

Normal Operates in intended or usual manner.


3-4 17 DEC 2002

3. Engine instruments indicate powerloss.

4. Engine out audio activated when NGdrops below 55%.

5. NR decreasing with RPM warninglight and audio on when NR dropsbelow 95%.

PROCEDURE:

1. Maintain heading and attitudecontrol.

2. Collective — Adjust to control NRand rate of descent. Increase prior toground contact to cushion landing.

NOTE

Amplitude of collective movement isa function of height above ground.Any forward airspeed will aid inability to cushion landing.

3. Land.

4. Shut down helicopter.

3-3-A-2. ENGINE FAILURE — INFLIGHT

INDICATIONS:

1. Left yaw.

2. ENGINE OUT and RPM warninglights illuminated.

3. Engine instruments indicate powerloss.

4. Engine out audio activated when NGdrops below 55%.

5. NR decreasing with RPM warninglight and audio on when NR dropsbelow 95%.

PROCEDURE:

1. Maintain heading and attitudecontrol.

2. Collective — Adjust as required tomaintain 85 to 107% NR.

NOTE

Mainta in ing NR a t h igh end ofoperat ing range w i l l p rov idemaximum rotor energy toaccomplish landing, but will causean increased rate of descent.

3. Cyclic — Adjust to obtain desiredautorotative AIRSPEED.

NOTE

Maximum AIRSPEED for steady stateautorotation is 100 KIAS. Minimumrate of descent airspeed is 55 KIAS.Maximum glide distance airspeed is80 KIAS.

4. Attempt engine restart if amplealtitude remains. (Refer to ENGINERESTART, paragraph 3-3-B).


6. At low altitude:

a. Throttle — Closed.

b. Flare to lose airspeed.

7. Apply collective as flare effectdecreases to further reduce forwardspeed and cushion landing. Uponground contact, collective shall bereduced smoothly while maintainingcyc l ic in neut ra l or cente redposition.

8. Complete helicopter shutdown.

3-3-B. ENGINE RESTART IN FLIGHT

An engine restart may be attempted in flight iftime and altitude permit.


30 JUL 2008 Rev. 7 3-9

PROCEDURE:

WARNING

WITHIN 2 TO 7 SECONDS AFTERTHE FADEC FAIL WARNING NR/NPMAY INCREASE RAPIDLY,REQUIRING POSITIVE MOVEMENTSOF COLLECTIVE AND THROTTLETO CONTROL NR.

1. Throttle — If time permits, matchthro t t le beze l pos i t ion to NGindication.

2. NR/NP — Maintain 95 to 100% withcollective and throttle.

3. FADEC MODE switch — Depress onetime, muting FADEC fail audio.

NOTE

Depressing FADEC MODE switchone time, will only mute FADEC failaudio. This step should not beaccomplished until pilot is firmlyestablished in MAN control.

4. Land as soon as practical.

5. Normal shutdown if possible.

3-4. FIRE3-4-A. ENGINE FIRE ON GROUND

INDICATIONS:

1. Smoke

2. Fumes

3. Fire

PROCEDURE:



3. GEN switch — OFF.

4. BATT switch — OFF.

5. Rotor brake (if installed) — Engage.

6. Exit helicopter.

3-4-B. ENGINE FIRE DURING FLIGHT

INDICATIONS:

1. Smoke

2. Fumes

3. Fire

PROCEDURE:

1. Inflight — Immediately enterautorotation.



4. If time permits, FUEL BOOST/XFRcircuit breaker switches — OFF.

5. Execute autorotative descent andlanding.

6. BATT switch — OFF.

NOTE

Do not restart engine until correctivemaintenance has been performed.

3-4-C. CABIN SMOKE OR FUMES

INDICATIONS:

1. Smoke

2. Fumes


3-10 17 DEC 2002

PROCEDURE:

1. Inflight — Start descent

2. AIR COND BLO switch (if installed)— OFF

3. HEATER switch (if installed) — OFF

4. All vents — Open

5. Side windows — Open

If time and altitude permits:

6. Source — Attempt to identify andsecure.

7. If source is identified and smokeand/or fumes still persist — Land assoon as possible.

8. If source is identified and smokeand/or fumes are cleared — Land assoon as practical.

3-5. TAIL ROTORThere is no single emergency procedure forall types of antitorque malfunctions. One keyto a pilot successfully handling a tail rotoremergency lies in the abil ity to quicklyrecognize the type of malfunction that hasoccurred.

3-5-A. COMPLETE LOSS OF TAIL ROTOR THRUST

This is a situation involving a break in drivesystem (e.g., severed driveshaft), wherein tailrotor stops turning and delivers no thrust.

INDICATIONS:

1. Uncontrollable yawing to right (leftside slip).

2. Nose down tucking.

3. Possible roll of fuselage.

NOTE

Sever i ty o f in i t ia l react ion ofhe l icopter wi l l be a f fected byAIRSPEED, CG, power being used,and HD.

PROCEDURE:

3-5-A-1. HOVERING

Close thrott le and perform a hoveringautorotation landing. A slight rotation can beexpected on touchdown.

3-5-A-2. IN-FLIGHT

Reduce throttle to idle, immediately enterautorotat ion, and maintain a minimumAIRSPEED of 55 KIAS during descent.

NOTE

When a suitable landing site is notavailable, vertical fin may permitcontrolled flight at low power levelsand sufficient AIRSPEED. Duringfinal stages of approach, a mild flareshould be executed, making sure allpower to rotor is off . Maintainhelicopter in a slight f lare andsmoothly use collective to execute asoft, slightly nose-high landing.Landing on aft portion of skids willtend to correct side drif t . Thistechnique will, in most cases, resultin a run-on type landing.

CAUTION

IN A RUN-ON TYPE LANDINGAFTER TOUCHING DOWN, DO NOTUSE C Y C L I C T O R E D U C EFORWARD SPEED.

3-5-B. FIXED PITCH FAILURES

This is a situation involving inability tochange tail rotor thrust (blade angle) with anti-torque pedals.

Documents

Limitations b407