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be attempted. The minimum performance is required for
optimum conditions (day, VMC, steady deck, experienced
aircrew, normal wind over deck, etc.). For degraded
conditions, the minimum performance should be
increasedb asedo nj udgment, If the minimum perfomrante
test is not passed, and all other options are exhausted
(stores jettisoned, gross weight minimized,
divert not possible), eject under controlled conditions.
For shore-basedla ndings, conduct a straight-in approachw
ith flaps up and speedbrakesre tracted.I f conditions
warrant a full-flap landing, conduct a
performance test and proceed as in the case of a shipboard
landing. Gross weight should be reduced as much
as practicable to improve flyaway performance. Maintain
10 units AOA in the pattern slowing to 15 units
AOA at touchdown when a safe landing is assured.U se
extreme caution when working off a high and/or fast
situation, avoiding any large power reductions. The
natural tendency will be to underestimate the sluggish
powerresponseresultingin anunderpoweredcondition.
Waveoffcapability is dependento n engine thrust/thmst
response,a imtaft rate of descent,a nd power setting at
waveoff initiation. Waveoffs should be conducted by
rotating toward 14 units (maximum) AOA until a positive
rate ofclimb is attained, then slowly reducing AOA
to 10 units AOA to achieve maximum rate of climb.
Bolters should be conducted by rotating to 10” pitch
attitude not to exceed 14 units AOA. Avoid increasing
AOA, as performance will degrade and wing drop will
occur at 16.5 to 17.5 units AOA.
pi&-,,,,,,,
Waveoff performance from high rates of
descent in SEC mode may be severely
degraded. Extreme care should be used to
avoid anu nderpowered,h igh rate-of-descent
situation.
Shipboard landings in single-engine SEC mode are
not recommended and should be attempted as a last
resort (divert not available) and if the performance
check is successful. Jettison all external stores and reduce
fuel weight as much as practicable to reduce gross
weight and drag. Configure ihe aircraft for landing no
lower than 2,000 feet AGL. Approaches should be conducted
with the flaps and slats fully extended, speedbrake
retracted, and DLC stowed.
Conduct a straight-in approach. Any turns should be
made away from the dead engine using bank angles that
do not exceed 20”. Maintain 10 units AOA until established
on final, at which time the aircraft should be
slowed to 13 units (maximum) AOA. Extreme care
should be used when working off a high and/or fast
condition, as any large power reductions could result in
an underpowereds ituation. A high and/or fast condition
should be corrected using only small power reductions.
Upon detection of a deceleration or settle, immediate
selection of MIL power may be required to correct the
situation in’s timely manner. To minimize the chance of
a hook-skip bolter, it is important to maintain aA stick
pressure on touchdown. Waveoffs should be conducted
by rotating the aircraft to 14 units (maximum) AOA
until a positive rate of climb is attained, then slowly
reducing AOA to I I to 12 units to achieve a maximum
rate of climb. Bolters should be conducted by rotating
to IO0 pitch attitude not to exceed 14 units AOA.
153.1 Single-Engine Landing - SEC Mode
1. FUEL SHUTOFF handle (inoperative engine)
- Pull.
ORIGINAL ’ 15-4
2. In CV environment - Divert.
3. Refer to Single-Engine Cruise Operations, paragraph
14.5.3.2, and Engine Transfer to SEC Mode
procedures,p aragraph1 4.5.6.
If not preparing for CV approach:
See step 6.
If divert is not possible:
Engine thrust and thrust response can be
severely degraded such that level flight
cannot be maintained in the full-flap landing
configuration. DO NOT configure for
landing until the performance test has been
accomplished.
If not configured for landing:
4. Perform constant airspeed climb (i5 knots) at 10
units AOA, landing gear up, maneuvering flaps
down (if possible), above 2,000 feet. Minimum
climb required in 30 seconds is as follows:
CHANGE IN ALTITUDE - FEET
MANEUVER MANEUVER
FLAPS DN FLAPS UP
2,000 feet 950 feet 900 feet
4,000 feet 600 feet 750 feet
6,000 feet 700 feet 650 feet
m
Ifminimumperformance test is passed based
on predicted gross weight, do not lower landing
gear and flaps until predicted gross
weight is reached.
Note
Climb performance will improve by 20 feet
in a 30-second climb for every 1 ,OOO-pound
gross weight reduction. Minimum perfotm-
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F-14D 飞行手册 Flight Manual 2(128)
