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the failed lower level function for their operation. If preflight FCS BIT detects a fault in a subsystem
(e.g., left stabilator) testing of the failed subsystem is discontinued, and testing of unrelated
subsystems (e.g., rudders, trailing edge flaps, etc.) continues. Since testing is not complete, preflight
FCS BIT must be run again after maintenance actions in order to complete all tests.
2.21.3.4.4 FCS IBIT PASS/FAIL. A successful preflight FCS BIT results in a GO indication on the
DDI. An unsuccessful preflight BIT indicates a system degradation. A preflight BIT never sets an X
on the DDI FCS status page (MENU-FCS) since preflight BIT only sets BLIN codes. Launching in a
degraded state (e.g., with BLIN codes) places the aircraft in a situation where a portion of the flight
control system is operating without the normal redundancy.
2.21.3.4.5 Repetition of FCS BIT. If an aircraft fails preflight FCS BIT (e.g., BLIN codes present
after preflight FCS BIT) maintenance should be called to troubleshoot the system. After completing
troubleshooting, a successful preflight FCS BIT is necessary to make sure the system is fully
operational. Except for cold weather operation, preflight FCS BIT failure is indicative of a component
degradation, e.g., hydraulic or electrical components are out of tolerance, or a cable conductor is
intermittent (broken wire, loose connector pin, etc.)
A1-F18EA-NFM-000
I-2-166 ORIGINAL
2.21.3.4.6 FCS Exerciser Mode. In cold weather, actuator components do not respond normally until
hydraulic fluid temperature increases. Exerciser mode should be used to expedite system warm-up.
During exerciser mode, a number of PBIT actuator monitors are ignored to prevent generation of
nuisance BLIN codes. In cold weather it is appropriate to re-attempt preflight BIT after running
exerciser mode. Exerciser mode should not be used as a method to clear BLIN codes in normal start-up
temperature conditions. BLIN codes cleared in this manner could be associated with hydraulic
contamination or sticking control valves which could appear again in flight with catastrophic results.
Repeatedly running exerciser mode in normal and hot weather environments
may lead to hydraulic system overheat.
2.21.3.4.7 Running FCS IBIT after Flight. A good (no codes) preflight BIT on the previous flight is
no assurance against latent failures on the next flight. Electronic components have a propensity to fail
on power application. Damage can occur during deck handling or maintenance activity not associated
with the flight controls. The only insurance is to run preflight BIT prior to flight.
2.21.3.5 SMS Initiated BIT. Safeguards have been built into the weapon system mechanization to
allow SMS initiated BIT to be performed on the ground with weapons loaded and cartridges installed.
During initiated BIT, weapon release signals and associated circuitry are not exercised unless all of the
following interlocks are satisfied simultaneously: master arm switch to ARM, armament safety override
in override, weapon load codes on stores processor set to zero, and no weapon ID detected on any
weapon station. SMS initiated BIT should not be attempted until the above interlocks are in a safe
condition. The SMS initiated BIT should be successfully completed within 180 seconds of initiation.
2.21.3.6 INS Initiated BIT. To perform initiated BIT, the INS must be in the TEST mode and a
ground/carrier selection must be made to indicate where the BIT is being accomplished. When the
BIT/SELBIT/NAV/ALL, BIT/NAV/INS, or BIT/AUTO is actuated, a status message of GND/CV?
appears next to the INS legend in the status display area. At the same time, GND and CV button labels
appear along the bottom of the display. These options allow entry of where the initiated BIT is
performed, e.g., on the ground or on a carrier. A third option, INS LONG (INS long test), identifies if
the platform slew portion of the INS test is desired. The platform slew test, which adds an additional
26 minutes to the normal 12 minutes INS BIT time, is only performed when the INS exhibits degraded
navigation performance during a flight and normal BIT routines do not detect any malfunction. This
option should be selected prior to selecting the ground or carrier option.
1. Check parking brake set.
2. For ground initiated BIT insure waypoint zero is local latitude/longitude.
3. Select MENU/BIT/SELBIT/NAV or MENU/BIT/NAV/INS or MENU/BIT/AUTO or MENU/
BIT/NAV/ALL on the right DDI and TEST on the INS mode switch.
4. Select INS LONG (if required) and GND or CV on DDI, and start clock. At successful completion
of test BIT display status message reads GO. Maximum time for INS initiated BIT is 12 minutes and
maximum time for INS initiated BIT and platform slew test is 45 minutes.
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NATOPS Flight Manual 飞行手册 1(117)
