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If shore-based -
1. FLAP switch - HALF
If carrier-based -
1. FLAP switch - FULL
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 11 of 55)
V-12-13 ORIGINAL
DDI Cautions and Caution Lights
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
CNI
· CSC MUX FAIL or CNI interface failure.
May also be caused by an MPCD malfunction.
MPCD and UFCD may not operate in some or all
modes. If CSC indicates MUX FAIL, the VOICE/
AUR, FCS, and G-LIM 7.5G cautions are also set,
and the following equipment is inoperative:
RALT, GPWS
Voice alerts
COMM control except by UFC BU
TACAN, beacon, IFF
SDC RESET function
LOCK/SHOOT lights
TACTS functions
ILS control except by ILS panel
EMCON control
1. BIT page - CHECK CSC and MPCD BIT
STATUS
If MPCD indicates DEGD -
2. MPCD knob - OFF, wait 15 seconds, ON
L DC FAIL
R DC FAIL
· All three PMG outputs have failed on the corresponding
side. May also indicate a power transmission
shaft failure (if accompanied by the corresponding
BOOST LO, GEN, and HYD circuit
cautions).
The affected FCC channels are powered by the
essential bus. One level of redundancy for the essential
bus is lost.
1. Electrical RESET button - PRESS
If caution clears -
2. Continue normal operations.
If caution remains -
2. Land as soon as practical.
DECOY
· Deployed decoy/towline failed (electrically or
mechanically) with AUTO DPLY not selected.
· Cable severing signal failed to fire the squib.
· Landing gear or hook lowered with ALE-50
deployed.
Sever decoy in a clear area.
Once CUT/VERIFY is selected, the option is removed
from the display.
If gear or hook lowered -
1. EW format CUT/VERIFY options - SELECT
or JAMMER switch - CUT
If decoy failure and ECM required -
1. Throttle dispenser switch - UP (auto-sever and
redeploy)
If decoy failure and ECM not required -
1. EW format CUT/VERIFY options - SELECT
or JAMMER switch - CUT
If caution remains -
2. JAMMER switch - CUT
3. Get a visual inspection (if possible).
If caution still remains -
4. Set 25° AOA with AB selected.
L DEVC BLD
R DEVC BLD
· A hot air leak from the inlet device anti-ice system
has been detected.
· Inlet device anti-ice capability degraded or lost.
If not secured, a hot air leak can cause structural
damage to the inlet device and possible engine
FOD.
If not in icing conditions -
1. ENG ANTI ICE switch - OFF
If caution remains with switch OFF -
2. Throttle affected engine - IDLE
3. Land as soon as practical.
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 12 of 55)
V-12-14 CHANGE 1
DDI Cautions and Caution Lights
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
DFIR OVRHT · DFIRS reporting an overtemperature condition. Information
DFIRS GONE · DFIRS inadvertently deployed. 1. Land as soon as practical.
DUMP OPEN
· Dump valve open with DUMP switch in OFF.
If the dump valve cannot be closed, fuel continues
to dump until tanks 1 and 4 are empty. Selecting
WING INHBIT diverts recirculation fuel from
the wings to the feed tanks. Stopping external
transfer may make this fuel available if the dump
valve is subsequently closed. When uncommanded
fuel dump ceases (tanks 1 and 4 empty), the feed
tanks should contain between 4,200 and 4,900 lb,
depending on JLS cycling.
1. DUMP switch - CYCLE
2. BINGO setting - Set above internal fuel state.
3. INTR WING switch - INHIBIT
If external fuel remains -
4. EXT TANKS switches - STOP
5. Land as soon as possible.
If fuel continues to dump on deck -
6. Turn aircraft into the wind.
7. Throttles - OFF
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 13 of 55)
V-12-15 ORIGINAL
DDI Cautions and Caution Lights
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
ECS ICING
· The ECS compressor/turbine is icing (e.g., an
ECS valve failure or malfunction in the warm air
system which normally prevents ECS icing has
occurred).
· ECS controller failure with altitude below 30,000
feet (ECS DEGD, MSP 8A0 or 8A1).
· ECS icing sensor failure with altitude below
30,000 feet (MSP 8E1).
For a sensor or ECS controller failure, the caution
is inhibited above 30,000 feet, since insufficient
moisture is present to cause ECS icing.
The ECS system incorporates a bypass valve designed
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 2(22)