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APU fire extinguishing system will automatically shutdown the APU
and, after 10 seconds, will discharge the extinguisher bottle.
If external air start -
a. BLEED AIR knob - OFF
All starts -
Regardless of the engine start air source utilized, the corresponding GEN
switch should be ON, as the generator provides primary overspeed cutout
protection for the ATS.
7. ENG CRANK switch - R
A1-F18EA-NFM-000
III-7-19 ORIGINAL
8. Right throttle - IDLE (10% N2 minimum. Oil pressure should be a minimum of 10 psi within 30
seconds. Maximum transient EGT during start is 871°C).
NOTE
During ground starts only, the FADEC will automatically cut back fuel
flow to prevent EGT from exceeding 815°C. If required, fuel flow will
be reduced to the point of engine flameout. While this mechanization
is provided to prevent engine damage due to an overtemp, the aircrew
should not rely on it to prevent a hot start.
9. GPWS voice alerts - CHECK (OFP 18E: ²ROLL LEFT, ROLL LEFT²) (OFP 13E: ²ROLL OUT,
ROLL OUT²)
NOTE
MC1 does an ACI configuration check after the generator comes on
line during a cold start power-up by commanding the above voice alert.
If the ACI does not contain the appropriate software, the ²ROLL
LEFT, ROLL LEFT² voice alert is not heard and GPWS is disabled
(GPWS is not displayed on the HSI aircraft data sublevel).
10. Battery gauge - VERIFY 28 vdc
NOTE
If the battery gauge fails to reach approximately 28 vdc with one
generator online, a battery charger malfunction has occurred which
requires maintenance action prior to flight.
11. L(R) DDI, HUD, and MPCD knobs - ON (both cockpits)
During a battery start of the right engine, recognition of a R ATS caution
will be delayed until the displays are turned on. Once the displays are
powered, verify that the R ATS caution is not set.
11A. HMD switch (if applicable) - ON
12. EFD - CHECK
A1-F18EA-NFM-000
III-7-20 CHANGE 1
Ground idle -
RPM
TEMP
FF
OIL
NOZ
61% minimum
250 to 500°C
600 to 900 pph
35 to 90 psi (warm oil)
77% to 83%
NOTE
Following the initial start of each engine, engine anti-ice airflow will
turn on automatically 45 seconds after the engine reaches idle power
and will remain on for 30 seconds, provided the throttle remains at
IDLE. The corresponding LHEAT or RHEAT advisory will be
displayed during this engine anti-ice functional test.
If external power start -
a. External electrical power - DISCONNECT
If APU or crossbleed start -
13. BLEED AIR knob - NORM
NOTE
The bleed air shutoff valves close during the fire warning test, so the
BLEED AIR knob must be rotated from OFF to NORM with ac power
applied to reset the valves.
14. LT TEST switch - TEST (both cockpits)
For a crossbleed start ensure the APU switch is OFF. The operating engine should be advanced
to a minimum of 80% N2
15. ENG CRANK switch - L
16. Left throttle - IDLE (10%N2 minimum)
17. ENG CRANK switch - CHECK OFF
18. EFD - CHECK
If external air start -
a. BLEED AIR knob - NORM
7.3 BEFORE TAXI CHECKS
1. WYPT 0 and MVAR - CHECK/SET
2. GPWS - CHECK BOXED
3. INS knob - CV or GND (PARK BRK SET)
A1-F18EA-NFM-000
III-7-21 ORIGINAL
4. RADAR knob - OPR
5. FLIR and LST/FLR switches - AS DESIRED
6. UFCD avionics - TURN ON
a. RALT - ON/SET
b. TCN - ON, T/R, CH SET
c. IFF - ON/MODES UNBOXED
7. WINGFOLD switch - SPREAD
8. FCS RESET button - PUSH (verify RSET advisory displayed)
NOTE
Prior to takeoff (cycle to WoffW), a successful FCS RESET
automatically clears all BLIN codes.
If no reset (RSET advisory displayed) -
a. FCS exerciser mode - INITIATE (push the FCS RESET button while holding the FCS BIT
consent switch up)
In standard or warm conditions, do not initiate the FCS exerciser mode
multiple times in an attempt to get a successful FCS RESET. In such
conditions, multiple initiations may excessively elevate hydraulic system
temperatures, increasing actuator and hydraulic pump seal wear and
potentially decreasing component life.
b. FCS RESET button - PUSH (verify RSET advisory displayed)
After successful FCS reset -
9. FLAP switch - AUTO
10. FCS IBIT - PERFORM
a. FCS BIT consent switch - HOLD UP THEN PRESS THE FCS OPTION
b. AOA warning tone - VERIFY ANNUNCIATION AT FCS IBIT COMPLETION
c. FCS A and FCS B BIT status - VERIFY GO
A1-F18EA-NFM-000
III-7-22 ORIGINAL
d. FCS display - VERIFY NO BLIN CODES
Flight with BLIN codes could result in a FCS failure and aircraft loss.
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(134)