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3. Select STOP or MENU to terminate test pattern
When BIT is initiated, UFCD IN TEST is displayed until BIT is completed. On F/A-18F, selecting
UFCD initiates BIT on both cockpit and rear cockpit displays. The UFCD test pattern is not displayed
if IBIT is not initiated on the UFCD option.
2.21.3.8.5 Radar Altimeter Initiated BIT. If BIT is initiated during RADALT time-in, the status on
the BIT display is NOT READY. If the BIT is initiated after time-in is complete, the display is GO
(indicating the radar altimeter is operating correctly), RESTRT (the BIT was not completed within
the design time limits), or DEGD (a WRA fail signal exists).
2.21.3.8.6 STOP Button. The STOP button allows the aircrew to stop initiated BIT at any time. BIT
is also stopped by pressing MENU, although MENU is not available with the DSPL/EPI/EFD/UFCD
BIT test pattern displayed. When the STOP (or MENU) button is pressed, any test in progress stops
and the equipment returns to normal operation. Exceptions to this are the radar and SMS power-on
BIT and the COMM 1/2, D/L, and TACAN BIT. The radar and SMS power-on BIT cannot be
terminated and indicate SF TEST when the MC detects the system is in BIT without having been
commanded to do so. The same is true of the COMM 1/2, D/L, and TACAN equipment which does a
canned non-interruptable BIT sequence. The mission computer terminates initiated BIT for any
equipment that it determines has taken too long to complete the test.
2.21.3.9 Hydro-mechanical (HYDRO MECH) Initiated BIT. With SELBIT boxed on the top level
BIT format, selecting HYDRO MECH initiates ECS BIT if aircraft is WonW.
FADEC status is also provided on the HYDRO MECH display by L and R ENG A and B status
indications.
Figure 2-56. UFCD Test Pattern
A1-F18EA-NFM-000
I-2-171 ORIGINAL
2.21.3.10 BLIN Codes. BIT Logic INspection (BLIN) codes are octal readouts identifying FCS
failures and can be read from the FCS status display. The following procedures may be used to display
and record BLIN codes. Channel 1 BLIN codes are displayed. Pressing the BLIN button displays the
next channel (1, 2, 3 and 4) BLIN codes.
1. On DDI - PRESS MENU-SUPT/FCS/BLIN
2. DDI BLIN codes - RECORD BY CHANNEL
3. Press BLIN button to view next channel BLIN codes
2.21.4 Non-Avionic BIT. Non-Avionic BIT is implemented in selected hydro-mechanical subsystems
primarily for the purpose of displaying subsystem status in the cockpit(s) (cautions and advisories)
and/or providing fault detection and fault isolation information for maintenance personnel. This status
data is provided to the status monitoring displays by the signal data computer which interfaces with
the following hydro-mechanical areas:
1. Engine/Secondary Power
2. Electrical
3. Hydraulics and landing/arresting gear
4. Fuel
5. Environmental control system and liquid cooling system
6. Controls/mechanisms/miscellaneous
The hydraulic system pressure cautions are interfaced directly by both mission computers, providing
redundancy for safety of flight.
2.21.4.1 Equipment Status Displays. NABIT cautions and advisories are displayed in the same
manner as avionics cautions and advisories.
2.21.5 Status Monitoring Backup. MC2 provides backup status monitoring if MC1 fails. It provides
an MC1 caution on the DDI indicating that MC1 has failed. Except for the HYD 5000, it also provides
HYD cautions.
NOTE
If MC1 fails, all DDI cautions and advisories are lost except MC1,
HYD 1A, HYD 1B, HYD 2A, and HYD 2B. TAC MENU loses the SA
option and SUPT MENU displays only the HSI option.
2.21.6 Non-BIT Status. Equipment status derived by means other than BIT include DDI configuration
display ID numbers and INS terminal data.
2.21.6.1 CONFIG Page Country ID Code. The country identifier code USN is displayed under the
CONFIG legend.
2.21.6.2 CONFIG Page. The ID numbers of the current operational flight program (OFP) loads for
the radar, stores management system, CLC, INS, mission computers, communication system control,
A1-F18EA-NFM-000
I-2-172 ORIGINAL
flight control computer, FLIR, SDC, MU, LDT, DMC, MPCD, DDI, EW equipment, DFIRS, FADECs,
and ECS controller can be determined by selecting the configuration display (see figure 2-57). The
configuration display is selected by the following procedure:
1. Select BIT from the SUPT MENU
2. Select CONFIG
With the configuration display selected, the current ID numbers are displayed to the right of the
equipment acronym. Refer to figure 2-57 for an example.
2.21.6.2.1 MC CONFIG Caution. An MC CONFIG caution indicates MC1 and MC2 OFP loads are
incompatible.
2.21.6.2.2 S/W CONFIG Caution. A S/W CONFIG caution indicates MC1 and MC2 OFP loads are
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NATOPS Flight Manual 飞行手册 1(119)
