曝光台 注意防骗
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commands only.
Flaps - HALF or FULL:
Good flap frozen.
EFFECTS:
Autopilot inoperative.
Flaps - AUTO:
Flaps schedule as a function of estimated
AOA.
Flaps go to 5°/4° if GAIN ORIDE selected.
Flaps - HALF or FULL/Gear - DOWN:
Nearly normal flying qualities at 8.1° AOA
with GAIN ORIDE selected.
Trailing edge flaps 30° or 40°.
Leading edge flaps at 21°.
Rudder toe-in disabled.
Loss of AOA bracket and AOA approach/
indexer lights without GAIN ORIDE
selected.
Figure 15-32. FCS Failure Indications and
Effects
Figure 15-33. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
V-15-35 CHANGE 1
EFFECTS:
Pitot-static instruments may be inaccurate.
Autopilot inoperative.
Air data blanked from HUD.
Loss of HUD barometric altitude, airspeed, and
vertical velocity.
Standby altimeter may be available.
Flaps - AUTO:
Degraded flying qualities.
Flaps freeze.
Flaps go to 5°/4° if GAIN ORIDE selected.
Flaps - HALF or FULL:
No rudder toe-in.
Flaps freeze.
Flaps go to 21°/30° or 21°/40° if GAIN
ORIDE selected.
Loss of AOA bracket and AOA approach/
indexer lights without GAIN ORIDE
selected.
EFFECTS:
NWS caution is also displayed.
Reduced rudder pedal authority.
Lateral stick gives rudder for roll coordination.
Flaps - AUTO:
Trim gives 10° rudder authority.
Flaps - HALF or FULL:
Trim gives 22.5° rudder authority.
NWS inoperative.
Figure 15-34. FCS Failure Indications and
Effects
Figure 15-35. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
V-15-36 CHANGE 1
NOTE
FCS status display is shown for
lateral accelerometer channels 1 and
2 failure example.
EFFECTS:
No change in flying qualities.
Autopilot inoperative.
EFFECTS:
Pitot-static instruments may be inaccurate.
Autopilot inoperative.
Loss of HUD barometric altitude, airspeed, and
vertical velocity.
Standby altimeter available.
Flaps - AUTO:
Degraded flying qualities.
Flaps schedule with AOA only.
Flaps go to 5°/4° if ORIDE selected.
Flaps - HALF or FULL:
Trailing edge flaps go to 30° or 40°.
Leading edge flaps and rudder toe-in schedule
with AOA.
Figure 15-36. FCS Failure Indications and
Effects
Figure 15-37. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
V-15-37 CHANGE 1
EFFECTS:
Autopilot inoperative.
If third undetected failure occurs, the following
flying qualities will be evident -
Poor roll coordination with large lateral
inputs.
Pitch coupling.
Sluggish pitch response.
EFFECTS:
Autopilot inoperative.
STC inoperative.
Spin recovery arrow not provided, but ASM still
available.
Flaps - AUTO:
Degraded pitch CAS
Degraded yaw CAS
Flaps - HALF or FULL:
Large sideslips with full rudder
Figure 15-38. FCS Failure Indications and
Effects
Figure 15-39. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
V-15-38 ORIGINAL
Do not select flaps HALF or FULL.
NOTE
If detected by the FCCs, the
indications for a three and four
channel failure are the same. A third
undetected channel failure appears as
a two channel failure.
EFFECTS:
Autopilot inoperative.
ATC inoperative.
Sensitive dynamic pitch characteristics.
Aggressive pitch inputs may result in PIO.
Degraded roll CAS.
Reduced roll damping.
ASRM inoperative.
Flaps - AUTO:
Poor dutch roll damping.
Large sideslip with lateral stick.
Degraded roll CAS.
Reduced roll damping.
Flaps - HALF or FULL:
Uncontrollable.
Figure 15-40. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
V-15-39 (Reverse Blank) CHANGE 1
CHAPTER 16
Landing Emergencies
16.1 SINGLE ENGINE FAILURE in LANDING CONFIGURATION
At MIL power and below, the amount of yaw/roll caused by a single engine failure is minimal, and
the aircraft is easily controllable. If an engine fails with both throttles at MAX power (e.g., waveoff),
a significant amount of yaw/roll can be anticipated due to asymmetric thrust. In this case, timely
rudder pedal inputs (up to FULL) are required. Too much rudder pedal is not harmful, but too little
rudder pedal may cause controllability problems. Therefore, FULL rudder pedal to oppose yaw/roll is
prudent. If lateral stick is also required to oppose roll (worst case), inputs should be limited to
approximately ½ displacement. Lateral stick inputs greater than ½ throw may compromise directional
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本文链接地址：NATOPS Flight Manual 飞行手册 2(60)
