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clears if the doors are in the correct position for
flight conditions. The advisory may return if the
failure still exists and the flight conditions reoccur.
No flight restrictions are imposed as long as airspeed
is maintained above 0.4 Mach.
If the aft avionics cooling fan has been disabled, the
OFF/RAM position of the ECS MODE switch will
not energize the aft avionics cooling fan. In this
case, only limited avionics cooling is available using
ram air. With the AV COOL switch set to EMERG,
only the following essential avionics receive adequate
cooling: FCC A, one AHRS, and the right
transformer rectifier. All other avionics systems are
susceptible to failure or shutdown due to heat. Ambient
temperature significantly influences the rate
at which avionics systems fail.
Minimize operation at high power settings below 0.4
Mach with both doors failed closed. A dual bleed
shutdown is possible under such conditions.
GROUND
1. Do not takeoff.
INFLIGHT
1. Accelerate to greater than 0.4 Mach using minimum
power. Maintain airspeed above 0.4 Mach
until landing.
Prior to decelerating below 0.4 Mach for
landing -
2. ECS MODE switch - OFF/RAM
3. AV COOL switch - EMERG
4. Non-essential avionics equipment - OFF (e.g.,
RADAR, UFCD controlled avionics, ECM, MC
2)
5. Land as soon as possible.
F-QTY
· Failure in fuel quantity gaging system that may
affect fuel quantity indications or FUEL XFER
caution display.
1. Fuel format - CHECK
If all fuel quantities invalid -
2. SDC - RESET
3. FLBIT - PERFORM
FADEC
· Left or right FADEC has lost backup redundancy
in one channel.
If advisory remains, a level of redundancy is lost.
Another engine/control system failure may result in
engine shutdown. ABLIM function may not be
available.
GROUND
1. Do not takeoff.
INFLIGHT
Information
FPAH · Autopilot Flight Path Angle Hold mode engaged. Information
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 49 of 55)
V-12-51 ORIGINAL
DDI Advisories
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
FPAS · Flight performance advisory system is unable to
calculate HOME FUEL caution. Information
GPS · GPS NORM mode error > 1,000 feet. 1. INS knob - NAV
GSEL · Autopilot ground track select mode engaged. Information
GTRK · Autopilot ground track hold mode engaged. Information
HDG · Autopilot magnetic heading hold mode engaged. Information
LHEAT
RHEAT
· Designated engine anti-ice system is operating.
Both advisories should be displayed with the
ENG ANTI ICE switch ON. Single advisory displayed
during post-start engine anti-ice functional
test with the switch OFF. Corresponding advisory is
removed if an anti-ice failure is detected.
Information
HEAT
· Engine anti-ice failure detected while the ENG
ANTI ICE switch is OFF.
If the ENG ANTI ICE switch is placed to ON,
the HEAT advisory is replaced by the HEAT FAIL
caution. The corresponding L HEAT or R HEAT
advisory is not displayed on the failed side. Engine
and inlet device anti-ice capability lost on failed
side.
1. Avoid icing conditions.
If icing conditions are encountered -
2. Refer to Extreme Weather Procedures.
HIAOA
· INS attitude data is not being provided to the
FCCs for sideslip calculations. May be caused by
an INS failure (INS ATT caution), by placing
the ATT switch to STBY with good INS data, or
by an FCC detected failure. Autopilot inop.
Above approximately 20° AOA in UA, the FCCs
use sideslip and sideslip rate feedback to provide
roll coordination and departure resistance. If INS
data is not available, sideslip control may be
slightly degraded. During UA to PA mode transitions
(FLAP switch from AUTO to HALF or
FULL), the FCCs use a one time snap shot of INS
attitude data to provide sideslip control. If INS attitude
data is not available, sideslip excursions (3°
to 8°) may occur if the aircraft is banked during
mode transition. Limiting AOB to 15° during mode
transition should minimize these excursions.
1. FCS RESET button - PUSH
If advisory remains -
2. Monitor any sideslip excursions above 20° AOA
in UA.
For landing -
3. Limit bank angle to 15° during mode transition
(FLAP switch from AUTO to HALF or FULL)
HMD
· QDC connector is not connected.
· QDC is not properly secured to hip mount.
· Coarse alignment is invalid or has not been performed.
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊(cè) 2(43)