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2B).
(Autopilot inop)
Stabilator reconfiguration control laws are automatically
enabled following a single stabilator failure
to compensate for the loss of that surface. If
hydraulics are intact, the failed stabilator is driven
to 2° TEU and locked. Following a dual HYD circuit
failure, the failed stabilator must be driven to
the locked position by aiding airloads. Below 250
KCAS in both UA and PA, flying qualities should
be nearly normal.
· In UA, maximum roll rate is extremely low in the
transonic region below 20,000 feet, especially when
rolling away from the failed stabilator. Significant
roll and yaw coupling may occur with forward
stick inputs at >1.4 Mach and altitude >30,000
feet.
· Upon contact with the deck during a bolter, aircraft
yaws into good stabilator when the flight
control system deflects the good stabilator TEU
in preparation for aircraft nose rotation. Yaw rate
may be sudden and pronounced, but easily controlled
with rudder to counter the yawing motion.
When FCS/FCES procedures complete -
6. Airspeed - Maintain below 250 KCAS.
7. Verify failed stab locked at 2° TEU.
8. AOA - Maintain below 10°
9. Make a controllability check at safe altitude.
For landing -
10. FLAP switch - HALF
11. Fly a straight-in approach (if practical).
12. Fly on-speed AOA to touchdown.
13. Make a precautionary short field arrestment (if
available).
14. Avoid longitudinal stick inputs during landing
rollout (e.g., stab braking).
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 36 of 55)
V-12-38 ORIGINAL
FCES CAUTIONS
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
AOA Fail
FCS
FCES
Caution Light
FOUR CHANNEL AOA FAILURE
· A persistent (> 10 second) mismatch between the
left and right AOA probes has been detected
(15° in UA or 5.5 to 15° in PA depending on
sideslip). Mismatch may be caused by a transient
condition; a stuck, binding, or damaged probe; or
a two-channel probe failure. (Autopilot inop)
If the detected probe split clears in UA, the four
channel AOA Xs are automatically removed. In PA,
an FCS RESET is required to clear the failure indications
if the split was transitory. With a four channel
AOA failure, AOA indications are removed from
the HUD. HUD displayed AOA can be restored by
selecting (boxing) the valid AOA probe on the FCS
format with GAIN ORIDE selected. In UA, the
FCCs utilize the AOA estimator for gain scheduling.
In PA, rudder toe-in is disabled, and the FCCs use
a fixed 8.1° AOA gain for longitudinal control and
the estimator for lateral-directional control. In UA,
flying qualities with gains scheduled by the AOA
estimator should be essentially normal compared to
the fixed gains used in GAIN ORIDE.
If an AOA probe is stuck or damaged (IFR basket
impact, bird strikes, probe icing), AOA errors may
be unannunciated if the AOA split thresholds are
not exceeded.
When FCS/FCES procedures complete -
If Xs remain OR if Xs cleared but stuck/
damaged probe suspected -
For landing -
6. Slow below 180 KCAS at a safe altitude.
7. LDG GEAR handle - DN
8. FLAP switch - HALF or FULL
9. GAIN switch - ORIDE
10. FCS status display - SELECT
11. Identify undamaged probe using center (INS)
AOA value or wingman.
12. Undamaged probe - SELECT
13. Notify LSO that a single probe has been
selected.
14. Fly a straight-in approach (if practical)
15. Fly on-speed AOA to touchdown
(ATC is not available)
Chan Fail
FCS
FCES
SINGLE FCS CH COMPLETELY X'D OUT
· FCC channel failure. (No change in flying qualities.)
Speedbrake function disabled.
Channel 2 or Channel 4
· ATC inop.
· Normal NWS inop.
Channel 2 also
· Loss of HUD baro altitude and IFF reporting
(standby altitude and RALT still available).
· MAD sensor data lost. (Mag heading may degrade).
Channel 4 also
· AOA indexer/approach lights inop.
Pulling the wrong circuit breaker shuts down a second
flight control channel, and may result in degraded
flying qualities or loss of control.
When FCS/FCES procedures complete -
6. Circuit breaker failed channel - PULL, pause
20 seconds, RESET
7. Land as soon as practical.
With CH 2 or CH 4 failed -
8. Consider a precautionary arrested landing (if
available)
(Normal NWS is not available.)
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 37 of 55)
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本文链接地址：
NATOPS Flight Manual 飞行手册 2(36)
