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(7) CONT IGNITION .................................................................... ON
When ITT is 90°C or less and
N2 is at least 12% (10% if below 10,000 ft):
(8) Affected engine, thrust lever.................................................IDLE
when within start envelope.
(9) Engine indications .......................................................MONITOR
carefully.
NOTE
1. If engine does not ignite in 25 seconds, retard
thrust lever to SHUT OFF, maintain at least 300
KIAS for 30 seconds and repeat procedure. After
ignition is achieved, monitor N2 acceleration rate.
N2 acceleration should be uninterrupted and
positive at all times. Stable idle must be achieved
in 2 minutes of advancing thrust lever to IDLE.
2. During windmilling airstart, attempt to keep the
flight control inputs to a minimum.
ABNORM 1-5
REV 75, Feb 17/09
▼
QUICK REFERENCE HANDBOOK
PSP 604-15
POWER PLANT
MALFUNCTIONS
Windmill Relight (Cont’d)
Engine start is successful (within 25 seconds):
Yes
When engine stabilized at Flight Idle:
(10) Thrust levers................................................AS REQUIRED
(11) CONT IGNITION .......................................................... OFF
(12) 10TH STAGE bleed.....................................AS REQUIRED
(13) APU LCV .....................................................AS REQUIRED
(14) Applicable PACK ............................................................ ON
(15) COWL ANTI-ICE .........................................AS REQUIRED
(16) Applicable GEN .............................................................. ON
(17) Applicable HYDRAULIC pump ...................................AUTO
(18) GPWS/FLAP OVRD
(if installed) ................................................................NORM
− END −
No
(10) Single Engine Procedure......................................ACCOMPLISH
(See Page ABNORM 1–7)
END
ABNORM 1-6
REV 75, Feb 17/09
QUICK REFERENCE HANDBOOK
PSP 604-15
POWER PLANT
MALFUNCTIONS
Single Engine
(1) Affected thrust lever ..........................CONFIRM and SHUT OFF
(2) Affected 10TH STAGE bleed ........................................CLOSED
(3) Operative PACK ..................................................................... ON
(4) Land at the nearest suitable airport.
Approach and Landing With One Engine Inoperative:
(1) PACKs...................................................................... TRANSFER
to APU bleed air.
Prior to the approach:
(2) Go-Around Thrust..................................................................SET
Add 2% N1 to the two-engine take-off N1 and set N1 bug
accordingly.
(3) GPWS/FLAP OVRD (if installed)....................................... OVRD
For the approach and landing:
(4) FLAPS .................................................................................... 20°
(5) Approach speed ...........................................................VREF + 14
minimum.
(6) Actual landing distance (without
thrust reverser) .......................................................... INCREASE
by a factor of 1.55 (55%).
NOTE
If required, use remaining thrust reverser carefully upon
landing.
END
ABNORM 1-7
REV 75, Feb 17/09
QUICK REFERENCE HANDBOOK
PSP 604-15
POWER PLANT
MALFUNCTIONS
L (R) REV UNSAFE
L REV UNSAFE or R REV UNSAFE
Thrust reverser is unsafe to arm in flight. Thrust reverse lever
deploy switches have failed in a commanded deploy state, but
thrust reversers are not unlocked and are not armed:
CAUTION
Do not arm affected thrust reverser during flight.
(1) Affected ARM switch ............................................................ OFF
CAUTION
Use remaining thrust reverser carefully upon landing.
END
Thrust Lever Inoperative
At a safe altitude, before commencing the approach:
(1) Affected ENG FIRE ............................................................PUSH
to shutdown affected engine.
NOTE
1. Ground spoilers may not be available upon
landing.
2. Ground spoilers will operate only if the affected
engine is windmilling above 40% N1.
Affected engine:
(2) In-Flight Engine Failure/Shutdown .......................ACCOMPLISH
(See Page ABNORM 1–2)
(3) Actual landing distance ............................................. INCREASE
by a factor of 1.60 (60%), for a flaps 20° landing without
the use of reverse thrust.
END
ABNORM 1-8
REV 75, Feb 17/09
QUICK REFERENCE HANDBOOK
　
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