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· MC unable to determine which source error correction
to utilize (e.g., configuration discrepancy).
· FCC source error correction disagrees with MC
commanded source error correction.
Only activated WonW.
1. Do not takeoff.
L AMAD PR
R AMAD PR
· Loss of designated AMAD oil pressure.
The AMAD can operate for 30 minutes after loss
of oil without a catastrophic failure. Securing the
GEN (ac output) greatly reduces the heat load imparted
to the AMAD oil and may prevent heatrelated
damage to the generator.
1. GEN switch affected engine - OFF
If more than 30 minutes to landing -
2. Throttle affected engine - OFF
3. Restart for landing.
L ANTI ICE
R ANTI ICE
· Engine anti-ice valves failed to close when commanded
by the FADEC.
Unregulated engine anti-ice airflow may damage the
inlet device and cause potential engine FOD.
1. Throttle affected engine - IDLE
If not in icing conditions -
2. ENG ANTI ICE switch - OFF
If caution is removed -
3. Resume normal engine operation.
If caution remains/returns -
4. Throttle affected engine - IDLE
5. Land as soon as practical.
ANTISKID
· Anti-skid system failed BIT. Anti-skid protection
not available for use with normal braking.
1. Do not cycle the ANTI SKID switch in response
to an ANTISKID caution immediately prior to
landing for the following:
a. The ANTISKID caution is removed for up to
13.5 seconds as the system performs IBIT
even though the anti-skid system may still be
failed.
b. If the system is not failed, wheel motion at
touchdown or during landing rollout may
cause a false BIT failure and a dump of normal
brake pressure when brakes are applied.
2. If the ANTI SKID switch is not placed to OFF
with an ANTISKID caution displayed, normal
braking capability may be lost completely.
GROUND
1. ANTI SKID switch - OFF
INFLIGHT
If more than 30 seconds to landing -
1. ANTI SKID switch - CYCLE ONCE
If caution reappears -
2. ANTI SKID switch - OFF (DO NOT CYCLE)
If less than 30 seconds to landing -
3. ANTI SKID switch - OFF (DO NOT CYCLE)
4. Regulate brake pedal force to prevent wheel
skid.
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 5 of 55)
V-12-7 ORIGINAL
DDI Cautions and Caution Lights
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
APU ACCUM
APU ACC
Caution Light
· APU accumulator pressure low (below 2,450 psi).
The APU ACCUM caution can be expected after
APU start or after emergency gear/probe extension
inflight. With WonW, the APU accumulator recharges
automatically. With WoffW, the HYD ISOL
switch may need to be held for up to 20 seconds
following emergency gear/probe extension to remove
the APU ACCUM caution and provide a full charge
(up to 40 seconds following inflight APU start).
If the APU ACCUM caution appears inflight and is
not related to emergency gear/probe extension or
APU start, it may indicate a possible leak in the
isolated HYD 2B system. In this case, do not select
HYD ISOL ORIDE as this may result in additional
loss of HYD 2B fluid.
INFLIGHT
Following emergency gear/probe extension
(if HYD 2B operative) -
1. HYD ISOL switch - ORIDE (until APU ACCUM
caution removed - approximately 20 seconds)
If caution remains or returns -
2. Do not reselect HYD ISOL ORIDE.
3. Extend landing gear as soon as practical.
ARS DROGUE · ARS PWR switch is OFF and the drogue is not
fully retracted.
1. Maintain airspeed between 175 and 200 KCAS
2. ARS PWR switch - ON
3. HOSE switch - CYCLE TO EXT THEN
RETR
If caution remains -
4. ARS PWR switch - OFF
5. Get a visual inspection.
If drogue appears stowed -
6. Make a normal landing.
If drogue extended and does not retract -
6. HOSE jettison switch - HOLD IN CUT (until
hose is severed)
If hose jettison is unsuccessful -
7. Perform a field landing with the arresting cable
removed.
ASPJ DEGD · ASPJ has failed continuous BIT. 1. Run ASPJ IBIT.
ASPJ LO B · Low band function of the ASPJ failed continuous
BIT. Information
ASPJ HI B · High band function of the ASPJ failed continuous
BIT. Information
ASPJ OVRHT
ASPJ OH
· Overheat condition detected in any of the onboard
jammer weapon replaceable assemblies.
System automatically shuts down in 60 seconds.
Shutdown override is provided on the EW format.
Information
A1-F18EA-NFM-000
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 2(18)