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MX
OA
OH
PH
PL
PM
RO
RP
SA
SI
SP
TT
XL
XM
x0
x-r
1 RMX status word error (DPs 40.42.
44)
ORT has been aborted
Overheat (RMO, RX, DD, RDR RSP
ASC) (DPs 184,198,272,397,398,
399)
No PHX channels available (DP 371)
RSP load error (DP 96)
APG-71 liquid cooling pump failure
(DPs 327,331)
RMO status word error (DP
176-183)
Radar power fault (Rx, ARSR RMO,
ANT, ASC, TX) (DPs 197,385,386,
387. 388, 390)
Semi-active decoder error (DP 187)
TID SSI parity error (DP 47)
No sparrow PD channels available
(DP 372)
Test target switch enabled (DP 377)
XMTR dummy load switch failure
(DPs 338-338,340)
XMTR peak power output below
minimum acceptable or XMTR is not
selected (DPs 352,353)
Selected XMTR channel is not phase
locked (DPs 185,189,190)
Transmitter subsystem failure (DPs
320-328,328-330.332-334)
Figure 38-33. Radar Continuous Monitor Acronyms
38-50
NAVAIR WF14AADI
OBCCM
ACRONYM EQUIPMENT
AFC Automatic flight control system
AIC
APC
BAG
BSF
BUS
CAD
CIU
DEU
DLS
DSS
ECM
FEM
GCU
HUD
IFB
IFI
IFX
INS
Air inlet control system
Approach power compensator
Beacon augmentor
Band suppression filters
Data bus
Central air data computer
Converter interface unit
Data entry unit
Data link system
Data storage set
Airborne self-protection jammer
Airborne data acquisition computer,
engine monitoring signal processors
112
Gun control unit
Head-up display
Interference blanker
IFF interrogator
IFF transponder
Inertial navigation system
OBCCM
ACRONYM
IR
MC1
MC2
MFA
MFD
NPS
PDP
POD
RAD
RFP
RFR
RWR
SDI
SMS
SRS
TCN
wow
(BLANKS)
EQUIPMENT
Infrared search and track system
Mission computer no. 1
Mission computer no. 2
Multiple filter assemblies (Left or
Right)
MFD no. 1, MFD no. 2, or MFD no. 3
Navigation power supply
Display processor no. 1 or display
processor no. 2
patcal airborne reconnaissance
Radar altimeter
Radio frequency indicator -Pilot
Radio frequency control indicator
-RIO
Radar warning receiver
Sensor display and indicator set
Stores management system
Standard attitude and heading
reference set
Tactical air navigation
Weight-on/off-wheelssensor
No system failures
Figure 38-34. OBC Continuous Monitor Acronyms
38-u ORIGINAL
NAVAIR 01.F14AAD-1
When theTCS testbegins,thedisplayinFigure38-35
shall appearo n the TID. The TCS test-in-progressm enu
consists of acronyms denoting the conditions of the associated
TCS test function subtest. The RIO has 15
secondst o supply the indicated action for eachp rompt.
Figure 38-36 contains a list of the prompts and associated
RIO responses.
38.5.2.1.8 Digital Display Controls and Dlsplays
Test (C/D Test). The DD has a standalone
built-in self-test capability that must be initiated and
evaluated by the RIO. It tests DD functions as well as
its discrete interfaces with the sensor hand control and
TlD.
C/D test is initiated with the DD radar control panel
C/D TEST pushtile. When the F-14D is airborne, continuous
depressiono f the C/D TEST pushtile clearsD D
display andi nitiates test.R eleasec ausesth e DD to revert
to tactical operation. When the F-14D aircraft is not
airborne, the fmt depression clears the DD display and
initiates test;t he secondd epressionc ausesD D to revert
to tactical operation. While the C/D TEST pushtile is
depressed,a diagonal line should be displayed on the
TlD.
After the C/D TEST is selected, the DD display will
appear as shown in Figure 38-37. Adjust DD BRT and
CONT controls for optimal viewing of the eight displayed
shades of gray. Adjust the SYM control for best
display of stroke symbology. From this display, three
separatet estsm ay be selectedb y pressingt he pushtiles
(along the left edge of the DD display) next to the legends
(1,2, and 3) displayed on the CRT.
a. CID TEST 1 Display. When UDTEST 1 display
is selected, the background will be shades ofgray. Right
to letI sweepss tart as soon as the display appears,w ith
each sweep diminishing the intensity of the shades of
gray (aging). Afler 13 sweeps, the shades of gray will
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F-14D 飞行手册 Flight Manual 3(82)
