F-14D. FLIGHT MANUAL (2004) - page 20
NAVAIR 01-F14AAP-1B
18. Report
Ready for Shutdown
After shutdown of both engines:
19. CANOPY handle
OPEN
Alert pilot.
20. Flightcrew
Egress
HOT REFUELING PROCEDURES
1. Fire extinguishing equipment
Available
2. All emitters
STBY or OFF
3. Right throttle
OFF
4. Wheels
Chocked
5. Parking brake
Pull
CAUTION
If heavy braking is used during landing or taxi-
ing followed by application of the parking
brake, normal brake operation may not be
available following release of the parking
brake if the brakes are still hot. Check for nor-
mal brake operation after releasing the parking
brake and before commencing taxiing.
6. REFUEL PROBE switch
FUS EXTD/
ALL EXTD (as desired)
7. WING/EXT TRANS switch
As Desired
8. REFUEL PROBE switch
RET
9. WING/EXT TRANS switch
OFF
246
NAVAIR 01-F14AAP-1B
ON-DECK, MAINTENANCE TROUBLESHOOTING
CAUTION
To ensure a safe in-cockpit maintenance trou-
bleshooting evolution, the following proce-
dures should be used.
1. Parking brake
PULL
2. THROTTLE MODE switch
MAN
3. Throttle friction lever
INC
4. Ejection seats
SAFED, CMD — PILOT
5. Flightcrew
Remain strapped in
HOT SWITCH PROCEDURES
1. Parking brake
Pull
2. HYD TRANSFER PUMP switch
NORMAL
3. WCS switch
OFF
4. IR/TV power switch
OFF
5. RECORD switch
OFF
6. [T] CPS system switch
OFF
7. Left throttle
OFF
8. ASYM LIMITER switch
ON (guard down)
9. ENG MODE SELECT switch
PRI
10. THROTTLE MODE switch
MAN
11. Throttle friction lever
Increase
12. Ejection seats
Safe
13. Flightcrew
Unstrap
14. Cockpit
Check for FOD
15. CANOPY handle
OPEN
16. Flightcrews
Switch
17. Flightcrew
Strap In
247
NAVAIR 01-F14AAP-1B
18. Ejection seats
Armed
19. CANOPY handle
CLOSE
20. FIRE DET/TEST
TEST
21. THROTTLE MODE switch
BOOST
22. Throttle friction lever
As Desired
23. Left engine
Start
24. WCS switch
STBY
CAUTION
Ensure that TARPS maintenance personnel
have loaded sensors and cleared aircraft before
initiating power to TARPS pod.
25. [T] CPS system switch
RDY
IN-FLIGHT REFUELING CHECKLIST
The in-flight refueling checklist shall be completed before plug-in.
1. WCS switch
STBY
2. Arming switches
Safe
3. DUMP switch
OFF
4. AIR SOURCE pushbutton
L ENG
5. REFUEL PROBE switch
As Desired
(transition light out)
6. Wing-sweep mode — MAN/
wing-sweep angle
As Desired
7. Visors
Recommended Down
When clear of the drogue:
1. REFUEL PROBE switch
RET
2. Probe transition light
Check OFF
3. AIR SOURCE pushbutton
BOTH ENG
4. Wing-sweep mode switch
AUTO
248
NAVAIR 01-F14AAP-1B
WING
LE = 20_
MILITARY POWER
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
HARD DRY RUNWAY
0_ FLAPS
DATE: JANUARY 1990
GEAR DOWN
DATA BASIS: ESTIMATED BASED
ON FLIGHT TEST
DISTANCE IN FEET
PRESSURE ALTITUDE
(FEET)
HEAD-
GROSS
TAKEOFF
ROTATION
RUNWAY
SEA
4000
8000
WIND
WEIGHT
SPEED
SPEED
TEMP
_F
LEVEL
(KNOTS)
(POUNDS)
(KNOTS)
KNOTS
20
2070
2810
3875
59
2255
3060
4225
0
90
2510
3440
4770
120
2990
4105
5720
20
1630
2245
3140
59
1790
2465
3455
20
58,000
150
140
90
2000
2305
3285
120
2400
2780
3970
20
1315
1835
2605
59
1455
2030
2880
40
90
1635
2305
3285
120
1970
2780
3970
20
2650
3615
4995
59
2900
3940
5450
0
90
3225
4430
6170
120
3845
5325
7460
20
2110
2925
4095
59
2325
3210
4505
20
65,000
159
149
90
2605
3630
5130
120
3125
4385
6230
20
1725
2420
3425
59
1915
2670
3790
40
90
2155
3035
4335
120
2590
3680
5285
20
3330
4560
6300
59
3635
4960
6875
0
90
4065
5600
7830
120
4865
6780
9545
20
2665
3725
5225
59
2950
4085
5740
20
72,000
168
158
90
3320
4635
6570
120
3995
5640
8040
20
2190
3110
4405
50
2450
3425
4870
40
90
2765
3905
5595
120
3340
4770
6875
TAKEOFF SPEED AND GROUND
ROLL DISTANCE — FLAPS UP
249
NAVAIR 01-F14AAP-1B
WING SWEEP
LE = 20_
MILITARY POWER
CG = 6%
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
HARD DRY RUNWAY
35_ FLAPS
DATE: JANUARY 1990
GEAR DOWN
DATA BASIS: ESTIMATED BASED
ON FLIGHT TEST
DISTANCE IN FEET
PRESSURE ALTITUDE
(FEET)
HEAD-
GROSS
TAKEOFF
ROTATION
RUNWAY
SEA
4000
8000
WIND
WEIGHT
SPEED
SPEED
TEMP
_F
LEVEL
(KNOTS)
(POUNDS)
(KNOTS)
KNOTS
20
2535
3595
5190
59
2775
3925
5690
0
90
3125
4475
6590
120
3850
5585
8460
20
2000
2885
4225
59
2210
3170
4665
20
58,000
152
142
90
2505
3640
5435
120
3100
4565
7010
20
1620
2365
3510
59
1800
2620
3900
40
90
2055
3020
4565
120
2555
3805
5910
20
3245
4630
6785
59
3555
5060
7440
0
90
4030
5820
8755
120
4990
7405
—
20
2585
3750
5575
59
2860
4130
6155
20
65,000
160
150
90
3260
4775
7280
120
4055
6105
9690
20
2115
3105
4665
59
2350
3440
5185
40
90
2695
3995
6160
120
3365
5125
8225
20
4130
5940
8836
59
4515
6500
9710
0
90
5160
7570
—
120
6475
9855
—
20
3325
4855
7325
59
3665
5350
8100
20
72,000
168
158
90
4215
6265
9800
120
5315
8200
—
20
2740
4050
6175
59
3040
4485
6870
40
90
3510
5275
8345
120
4445
6930
—
DISTANCES NOT SHOWN EXCEED 10,000 FEET
TAKEOFF SPEED AND GROUND
ROLL DISTANCE — FLAPS DOWN (Sheet 1 of 2)
250
NAVAIR 01-F14AAP-1B
WING SWEEP
LE = 20_
MILITARY POWER
CG = 16.2%
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
HARD DRY RUNWAY
35_ FLAPS
DATE: JANUARY 1990
GEAR DOWN
DATA BASIS: ESTIMATED BASED
ON FLIGHT TEST
DISTANCE IN FEET
PRESSURE ALTITUDE
(FEET)
HEAD-
GROSS
TAKEOFF
ROTATION
RUNWAY
SEA
4000
8000
WIND
WEIGHT
SPEED
SPEED
TEMP
_F
LEVEL
(KNOTS)
(POUNDS)
(KNOTS)
KNOTS
20
1795
2500
3535
59
1960
2730
3875
0
90
2200
3065
4390
120
2640
3745
5415
20
1370
1945
2795
59
1510
2140
3090
20
58,000
132
122
90
1710
2420
3520
120
2060
2975
4365
20
1080
1555
2270
59
1200
1730
2525
40
90
1365
1960
2890
120
1655
2420
3600
20
2340
3270
4690
59
2550
3570
5125
0
90
2860
4045
5860
120
3475
4980
7340
20
1810
2575
3755
59
1995
2835
4135
20
65,000
140
130
90
2250
3230
4760
120
2750
4005
5990
20
1450
2085
3080
59
1605
2310
3415
40
90
1820
2645
3945
120
2335
3295
4985
20
2940
4150
6015
59
3215
4540
6580
0
90
3625
5155
7585
120
4425
6425
9665
20
2300
3305
4865
59
2540
3645
5365
20
72,000
147
137
90
2885
4165
6215
120
3540
5220
7960
20
1855
2695
4020
59
2060
2995
4460
40
90
2355
3440
5195
120
2900
4325
6680
TAKEOFF SPEED AND GROUND
ROLL DISTANCE — FLAPS DOWN (Sheet 2)
251
NAVAIR 01-F14AAP-1B
ANGLE-OF-ATT
FLIGHT CONDITION
ACK UNITS
CATAPULT (15 KNOTS EXCESS)
MRT
14.0
TRANSITION FROM CATAPULT
AB
13.0
MILITARY POWER CLIMB
ALL DRAG INDEXES
SEA LEVEL
6.0
COMBAT CEILING
9.5
MAXIMUM POWER CLIMB
ALL DRAG INDEXES
SEA LEVEL
5.0
COMBAT CEILING
8.0
CRUISE AT ALTITUDES BELOW 20,000 FEET
(ALL GROSS WEIGHTS)
DRAG INDEX = 8
8.0
DRAG INDEX = 100
9.0
CRUISE AT OPTIMUM ALTITUDE
DRAG INDEXES
8.0
MAXIMUM ENDURANCE
ALL DRAG INDEXES
10.0
ALL ALTITUDES
IDLE
250 KNOTS
9.0
MAXIMUM RANGE
10.0
GEAR AND FLAPS EXTENSION
SAFE GEAR EXTENSION (FLAPS UP) AT 280 KNOTS
6.5
SAFE FLAP EXTENSION (GEAR DN) AT 225 KNOTS
9.0
APPROACH
CCA/GCA PATTERN, 220 KNOTS;
9.0
GEAR UP; FLAPS UP; 54,000 POUNDS.
FINAL ON SPEED APPROACH (GEAR DN):
TWO ENGINES (ALL FLAPS CONFIGURATIONS)
15.0
SINGLE ENGINES/PRI:
FULL FLAP, DLC ENGAGE
15.0
FULL FLAP, DLC STOWED, AND NO FLAP
14.0
SINGLE ENGINES/SEC:
FULL FLAP (CV ONLY)
13.0
NO FLAP (FIELD ONLY)
15.0
DRAG INDEX .
CONFIGURATION
8
(4) AIM-7
100
(6) AIM-54
(2) 267-gallon external tanks
AIRSPEED INDICATOR FAILURE
252
NAVAIR 01-F14AAP-1B
FUEL REMAINING — POUNDS
LANDING
4000
8000
12,000
16,000
20,000
WEIGHT
LB
ALT/SPEED
ALT/SPEED
ALT/SPEED
ALT/SPEED
ALT/SPEED
TIME (MIN)
TIME (MIN)
TIME (MIN)
TIME (MIN)
TIME (MIN)
15,000/200
34,000/205
32,000/210
31,000/220
31,000/220
46,000
29
98
162
220
273
13,000/205
32,000/215
30,000/220
29,000/225
29,000/230
51,000
27
89
148
202
231
56,000
11,000/215
30,000/220
28,000/230
27,000/225
27,000/240
25
82
136
186
231
46,000
14,000/195
34,000/205
32,000/210
31,000/220
31,000/220
27
90
150
203
252
51,000
13,000/205
32,000/210
30,000/220
29,000/225
29,000/230
25
82
136
186
232
56,000
11,000/210
30,000/220
29,000/230
27,000/235
27,000/235
23
75
125
172
213
46,000
14,000/195
34,000/200
32,000/205
30,000/215
30,000/220
25
84
139
188
234
51,000
13,000/200
32,000/210
30,000/215
29,000/225
29,000/225
23
76
126
173
215
56,000
8,000/215
30,000/220
29,000/225
27,000/230
27,000/235
21
69
116
159
199
46,000
14,000/190
29,000/200
32,000/205
34,000/215
34,000/215
23
78
130
177
219
51,000
10,000/205
27,000/205
30,000/215
32,000/220
32,000/225
22
71
118
161
201
56,000
4,000/215
15,000/215
28,000/225
31,000/230
31,000/230
20
65
108
149
185
0-F52P 8 0
TWO-ENGINE MAXIMUM ENDURANCE ON STATION
253
NAVAIR 01-F14AAP-1B
FUEL REMAINING — POUNDS
LANDING
4000
8000
12,000
16,000
20,000
WEIGHT
LB
ALT/SPEED
ALT/SPEED
ALT/SPEED
ALT/SPEED
ALT/SPEED
TIME (MIN)
TIME (MIN)
TIME (MIN)
TIME (MIN)
TIME (MIN)
500/195
8,000/200
13,000/205
12,000/210
12,000/215
46,000
29
86
140
190
234
500/210
6,000/210
11,000/215
10,000/220
10,000/225
51,000
26
78
128
173
214
56,000
500/220
3,000/215
9,000/225
8,000/230
8,000/230
24
72
118
160
198
46,000
500/190
7,000/200
13,000/205
11,000/210
11,000/215
28
82
134
180
217
51,000
500/210
4,000/210
10,000/215
9,000/220
9,000/225
25
75
122
165
199
56,000
500/215
2,000/215
8,000/220
7,000/225
7,000/235
23
69
112
152
183
46,000
500/195
6,000/195
12,000/200
10,000/210
10,000/215
26
77
125
168
203
51,000
500/205
3,000/205
10,000/210
8,00/220
8,000/225
23
70
113
152
186
56,000
500/220
2,000/215
7,000/220
6,000/225
6,000/230
22
64
104
140
172
46,000
500/195
5,000/195
11,000/200
9,000/210
9,000/215
24
72
117
156
191
51,000
500/200
2,000/205
9,000/210
8,000/220
8,000/220
22
66
106
142
175
56,000
500/210
1,000/215
7,000/220
6,000/230
6,000/230
21
60
98
130
162
0-F52P 8 0
SINGLE-ENGINE MAXIMUM ENDURANCE ON STATION
254
NAVAIR 01-F14AAP-1B
DATE: SEPTEMBER 1987
FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST
FUEL DENSITY: 6.8 lb/gal.
ALL DRAG INDEXES, 35_ FLAP,
GEAR DOWN
EMERGENCY OPERATION
(WING SWEEP LESS THAN OR EQUAL TO 50_)
AIRSPEED CORRECTION TO BE
ADDED TO DLC STOWED APPROACH SPEED
AUXILIARY
ALL
FLAPS
FLAPS/SLATS
SLAT RETRACTED
WING
RETRACTED
RETRACTED
MANEUVER FLAPS
SWEEP (_)
(KIAS)
(KIAS)
EXTENDED (KIAS)
20
6
27
22
25
14
33
28
30
20
38
33
35
25
44
39
40
30
49
44
LANDING APPROACH AIRSPEED
(15 UNITS AOA) (SHEET 1 OF 2)
255
NAVAIR 01-F14AAP-1B
EMERGENCY OPERATION
(WING SPEED GREATER THAN 50_)
AIRSPEED CORRECTION TO BE ADDED
TO DCL STOWED APPROACH SPEED
15 UNITS
17 UNITS
WING SWEEP (_)
AOA (KIAS)
AOA (KIAS)
51
55
45
60
58
48
68
60
50
LANDING APPROACH AIRSPEED
(15 UNITS AOA) (SHEET 2)
256
NAVAIR 01-F14AAP-1B
MAXIMUM BRAKING — HARD DRY RUNWAY
WING
LE = 20_
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
IDLE POWER
ALL DECELERATION DEVICES
DATE: JANUARY 1990
FULL ANTISKID BRAKING
DATA BASIS: ESTIMATED BASED
35_ FLAPS, GEAR DOWN
ON FLIGHT TEST
DISTANCE IN FEET
RUNWAY
HEADWIND
PRESSURE
GROSS
TOUCH-
TEMP
(KNOTS)
ALTITUDE
WEIGHT
DOWN
_
F
(FEET)
(LBS)
SPEED
0
10
20
30
40
(KNOTS)
20
2065
1775
1550
1360
1210
59
2230
1930
1690
1490
1330
SEA
90
2360
2050
1805
1595
1425
LEVEL
120
2485
2170
1915
1700
1520
20
2355
2050
1805
1600
1425
59
2545
2230
1965
1750
1570
4000
45,000
126
90
2695
2370
2095
1870
1680
120
2845
2505
2225
1990
1790
20
2735
2405
2130
1905
1710
59
2955
2610
2325
2080
1875
8000
90
3130
2775
2475
2225
2010
120
2290
1990
1745
1545
1375
20
2290
1990
1745
1545
1375
59
2475
2160
1905
1690
1515
SEA
90
2620
2295
2030
1810
1625
LEVEL
120
2760
2430
2155
1925
1730
20
2620
2300
2035
1815
1625
59
2830
2495
2215
1985
1785
4000
50,000
134
90
3000
2650
2365
2120
1915
120
3160
2805
2505
2255
2040
20
3045
2695
2400
2155
1950
59
3290
2925
2620
2360
2135
8000
90
3480
3105
2790
2520
2290
120
3665
3280
2955
2675
2435
LANDING DISTANCE GROUND ROLL — FLAPS DOWN
(Sheet 1 of 2)
257
NAVAIR 01-F14AAP-1B
MAXIMUM BRAKING — HARD DRY RUNWAY
WING
LE = 20_
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
IDLE POWER
ALL DECELERATION DEVICES
DATE: JANUARY 1990
FULL ANTISKID BRAKING
DATA BASIS: ESTIMATED BASED
35_ FLAPS, GEAR DOWN
ON FLIGHT TEST
DISTANCE IN FEET
RUNWAY
HEADWIND
PRESSURE
GROSS
TOUCH-
TEMP
(KNOTS)
ALTITUDE
WEIGHT
DOWN
_
F
(FEET)
(LBS)
SPEED
0
10
20
30
40
(KNOTS)
20
2525
2210
1995
1740
1555
59
2730
2400
2130
1900
1710
SEA
90
2890
2555
2270
2035
1855
LEVEL
120
3050
2700
2410
2160
1955
20
2895
2560
2275
2040
1840
59
3130
2775
2480
2230
2020
4000
55,000
141
90
3315
2950
2645
2390
2165
120
3495
3120
2805
2535
2305
20
3365
2995
2690
2426
2200
59
3635
3255
2930
2650
2415
90
3850
3455
3120
2830
2585
8000
120
4055
3650
3305
3005
2745
20
2775
2445
2170
1940
1750
59
3000
2655
2370
2125
1920
SEA
90
3180
2820
2525
2270
2055
LEVEL
120
3350
2985
2675
2415
2190
20
3185
2830
2535
2280
2065
59
3445
3075
2760
2495
2265
4000
60,000
149
90
3650
3265
2940
2665
2425
120
3845
3450
3120
2830
2580
20
3700
3315
2990
2710
2470
59
4000
3600
3255
2960
2705
8000
90
4415
3985
3615
3295
3015
120
4815
4355
3960
3615
3320
LANDING DISTANCE GROUND ROLL — FLAPS DOWN
(Sheet 2)
258
NAVAIR 01-F14AAP-1B
MAXIMUM BRAKING — HARD DRY RUNWAY
WING
LE = 20_
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
IDLE POWER
INBD SPOILERS SPEED BRAKES
DATE: JANUARY 1990
FULL ANTISKID BRAKING
DATA BASIS: ESTIMATED BASED
0_ FLAPS, GEAR DOWN
ON FLIGHT TEST
DISTANCE IN FEET
RUNWAY
HEADWIND
PRESSURE
GROSS
TOUCH-
TEMP
(KNOTS)
ALTITUDE
WEIGHT
DOWN
_
F
(FEET)
(LBS)
SPEED
0
10
20
30
40
(KNOTS)
20
2890
2545
2260
2020
1820
59
3120
2760
2460
2210
1995
SEA
90
3305
2935
2625
2360
2140
LEVEL
120
3485
3105
2780
2510
2275
20
3305
2935
2625
2385
2140
59
3570
31 5
2860
2585
2350
4000
45,000
148
90
3780
3385
3050
2760
2515
120
3985
3780
3230
2930
2675
20
3840
3440
3100
2810
2555
59
4145
3730
3375
3065
2800
8000
90
4390
3960
3590
3275
2995
120
4625
4185
3800
3475
3185
20
3185
2825
2520
2265
2045
59
3440
3065
2745
2475
2245
SEA
90
3645
3255
2925
2645
2405
LEVEL
120
3840
3440
3100
2810
2560
20
3650
3260
2930
2650
2410
59
3940
3535
3195
2900
2645
4000
50,000
156
90
4175
3760
3400
3095
2830
120
4400
3970
3605
3285
3010
20
4240
3820
3455
3145
2880
59
4605
4160
3785
3455
3170
8000
90
5130
4650
4240
3880
3565
120
5660
5145
4700
4310
3965
LANDING DISTANCE GROUND ROLL — FLAPS UP
(Sheet 1 of 2)
259
NAVAIR 01-F14AAP-1B
MAXIMUM BRAKING — HARD DRY RUNWAY
WING
LE = 20_
AIRCRAFT CONFIGURATION:
ENGINES (2) F110-GE-400
ALL DRAG INDEXES
IDLE POWER
INBD SPOILERS, SPEED BRAKES
DATE: JANUARY 1990
FULL ANTISKID BRAKING
DATA BASIS: ESTIMATED BASED
35_ FLAPS, GEAR DOWN
ON FLIGHT TEST
DISTANCE IN FEET
RUNWAY
HEADWIND
PRESSURE
GROSS
TOUCH-
TEMP
(KNOTS)
ALTITUDE
WEIGHT
DOWN
_
F
(FEET)
(LBS)
SPEED
0
10
20
30
40
(KNOTS)
20
3480
3100
2780
2510
2275
59
3760
3360
3030
2740
2495
SEA
90
3980
3570
3225
2930
2670
LEVEL
120
4295
3865
5500
3180
2910
20
3990
3585
3235
2940
2680
59
4475
4035
3655
3330
3050
4000
55,000
164
90
4985
4510
4095
3740
3430
120
5485
4975
4530
4145
3810
20
5105
4620
4205
3840
3525
59
5860
5320
4855
4450
4100
8000
90
6480
5900
5400
4960
4570
120
7085
6470
5930
5460
5040
20
3770
3375
3040
2755
2510
59
4360
3920
3540
3220
2940
SEA
90
4850
4375
3965
3615
3305
LEVEL
120
5335
4825
4385
4005
3670
20
4840
4365
3960
3610
3305
59
5570
5045
4590
4200
3855
4000
60,000
171
90
6150
5585
5045
4670
4295
120
6720
6120
5595
5155
4735
20
6290
5715
5220
4785
4405
59
7180
6545
5995
5515
5090
8000
90
7905
7230
6635
6115
5655
120
8600
7885
7250
6695
6205
LANDING DISTANCE GROUND ROLL — FLAPS UP
(Sheet 2)
260
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS AND
SERVICING DATA
Index
Ac Essential No. 1 Circuit Breaker Panel
(Right Side) (Panel No. 5)
282
Ac Essential No. 2 Phase A Circuit
Breaker Panel (Left) (Panel No. 3)
280
Ac Essential No. 2 Phase B and C Circuit
Breaker Panel (Left) (Panel No. 4)
281
Ac Left Main Circuit Breaker Panel (Left Aft)
(Panel No. 1 — Lower Segment)
278
Ac Left Main Circuit Breaker Panel (Left Aft)
(Panel No. 1 — Upper Segment)
277
Ac Right Main Circuit Breaker Panel (Left Aft)
(Panel No. 2)
279
Aircraft Servicing Data
292
Aircraft Servicing Locations
291
Circuit Breaker Alphanumeric Index
263
Crosswind Chart
Inside Back Cover
Dc Essential No. 1 Circuit Breaker Panel
(Right Side) (Panel No. 6)
283
Dc Essential No. 2 Circuit Breaker Panel
(Right Aft) (Panel No. 7 — Lower Segment)
285
Dc Essential No. 2 Circuit Breaker Panel
(Right Aft) (Panel No. 7 — Upper Segment)
284
Dc Main Circuit Breaker Panel (Right Aft)
(Panel No. 8 — Lower Segment)
287
Dc Main Circuit Breaker Panel (Right Aft)
(Panel No. 8 — Upper Segment)
286
DFCS In-Flight Fault Matrix Cards
301
Engine Oil
289
Ground Refueling
288
Hydraulic Systems
290
Integrated Drive Generator
290
Pilot Ac Essential (Left Knee)
Circuit Breaker Panel
276
Pilot Dc Essential (Right Knee)
Circuit Breaker Panel
276
Pneumatic Systems
290
Servicing Data
288
Change 2
261/(262 blank)
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
3F6
AC ESS BUS NO. 2 FDR PH A
4F1
AC ESS BUS NO. 2 FDR PH B
4F4
AC ESS BUS NO. 2 FDR PH C
2I4
ACM LT/SEAT ADJ/STEADY POS LT
4B6
ACM PNL LT/INS SYNC
6D5
ACM PNL PWR
RB2
AFCS/NOSE WHEEL STEER
3C6
AHRS PH A
4C1
AHRS PH B
4C5
AHRS PH C
LF2
AICS L
2I5
AICS L HTR
7E2
AICS L LKUP PWR/EMER GEN TEST
6A6
AICS L RAMP STOW
LG2
AICS R
2I8
AICS R HTR
7E1
AICS R LKUP PWR/ANTI-SKID
6A5
AICS R RAMP STOW
8A4
AIM-54 MSL
8G4
AIM-7 L BATT ARM
8G3
AIM-7 R BATT ARM
RC2
AIR SOURCE CONTR
8B6
ALE-47 CHAFF/FLARE DISP
8B5
ALE-47 SEQ 1 & 2 SQUIBS
7C8
ALPHA COMP/PEDAL SHAKER
4B3
ALPHA HTR
6C1
ALQ-126 DECM
1C2
ALQ-126 PH A
1C5
ALQ-126 PH B
1C6
ALQ-126 PH C
1I4
ALR-67 CMPTR
2G4
ALR-67 RCVR PH A
2H3
ALR-67 RCVR PH B
2I10
ALR-67 RCVR PH C
6B6
ALT LOW WARN
Change 3
263
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
8D1
AMC BIT/R DC TEST
8G1
AMCS ENABLE
8F5
AN/ALR-67 CONT
3D7
AN/ARA-50
7D6
AN/ARA-50
1D2
AN/AWG-9 CMPTR PH A
1D5
AN/AWG-9 CMPTR PH B
1D6
AN/AWG-9 CMPTR PH C
2G3
AN/AWG-9 PUMP PH A
2G6
AN/AWG-9 PUMP PH B
2G7
AN/AWG-9 PUMP PH C
8H6
AN/AWW-4
1B3
AN/AWW-4 PH A
1C4
AN/AWW-4 PH B
1B6
AN/AWW-4 PH C
3C3
ANGLE OF ATTK IND AC
7E3
ANGLE OF ATTACK IND DC
4F5
ANL ATTK TOTAL TEMP HTR
7C1
ANN PANEL PWR
7F3
ANN PILOT PANEL AUX PWR/TR-ADVSY
8C2
ANN PNL/DDI DIM CONTR
8G2
ANT LOCK EXCIT
1F2
ANT SVO HYD PH A
1F4
ANT SVO HYD PH B
2
1F5
ANT SVO HYD PH B
1
1F6
ANT SVO HYD PH C
2I1
ANTICOLL/SUPP POS/POS LTS
7C2
ANTI-ICE RAIN RPL/HK CONT
RG2
ANTI-ICE/ENG/PROBE
7E1
ANTI-SKID/R AICS LKUP PWR
7E7
APN-154
5C4
APX-72 AC
6F7
APX-72 DC
8I6
APX-72 TEST SET
7C7
ARA-63 ILS DC
264
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
3A6
ARA-63 ILS PH A
4A3
ARA-63 ILS PH B
4A5
ARA-63 ILS PH C
6B3
ARC-159 NO. 1
6D1
ARC-159 NO. 2
8D7
ARMT GAS INGEST PWR
4E6
AS/ARA-48 ANT
1J2
ASW-27 (AC)
8G6
ASW-27 (DC)/DDI
LA3
AUTO PITCH DRIVE TRIM
1J1
AUTO THROT AC
8B7
AUTO THROT DC
7G3
AUX FLAP/FLAP CONTR
6B7
AWG-15 DC
5B5
AWG-15 PH A NO. 1
5B4
AWG-15 PH A NO. 2
5D5
AWG-15 PH B NO. 1
5D4
AWG-15 PH B NO. 2
5F5
AWG-15 PH C NO. 1
5F4
AWG-15 PH C NO. 2
3D3
BARO ALTM AC
7C6
BARO ALT/TURN SLIP
4F6
BDHI INST PWR/TACAN AC
7E8
BDHI/TACAN DC
7F6
BINGO/OXY CAUTION
7F2
BLEED AIR/L OIL HOT
4A4
BLEED DUCT AC
8D5
BRAKE ACCUM SOV
7A1
CABIN PRESS
7C5
CAN/LAD CAUTION/EJECT CMD IND
8D4
CDNU
LA2
CHAN 1 CADC PH A
LB2
CHAN 1 CADC PH B
Change 2
265
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
LC2
CHAN 1 CADC PH C
LH2
CHAN 2 CADC
3D1
COMB HYD PRESS IND
8A5
CONTR/DISPL SUBSYS
1G2
CONTR/DISPLAY PH A
1G3
CONTR/DISPLAY PH B
1G6
CONTR/DISPLAY PH C
8D2
COUNTING ACCEL/TARPS/FEMS
7D5
CSDC
3B7
CSDC PH A
4B2
CSDC PH B
4B5
CSDC PH C
6B5
DC ESS NO. 1 FDR
7A2
DC ESS NO. 2 BUS FDR
7G7
DC L TEST/RUDDER TRIM
8D1
DC R TEST/AMC BIT
1I1
DDI AC
8C2
DDI/ANN PNL DIM CONTR
8G6
DDI DC ASW-27
7B1
DFCS BUS FDR
7D8
DISPLAY PWR
RD1
DUMP/FUEL FEED
8E7
DYHR UNIT
7D4
ECS TEMP CONTR DC
8B1
EGI
6C3
EIG NO. 1
6C2
EIG NO. 2
5F3
EIG WHT LTS
7C5
EJECT CMD IND/CAN-LAD CAUTION
8H4
ELEC COOLING
6B2
EMERG FLT HYD AUTO
6B1
EMERG FLT HYD MAN
7E2
EMER GEN TEST/L AICS LKUP PWR
266
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
8I2
EMERG GEN CONTR
7G8
ENG AFT FAULT
RB1
ENG ANTI-ICE/VALVES
4C6
ENG L OIL PRESS
7D1
ENG OIL COOL
RG2
ENG/PROBE/ANTI-ICE
4D6
ENG R OIL PRESS
7F10
ENG STALL TONE
6A4
ENG STALL WARN LT
RE1
ENG START
7A5
EXHAUST NOZZLE/R ENG AFT CONT
7G10
EXT LT CONTR
8D2
FEMS/COUNTING ACCEL
7C4
FIRE L DET LT
6C5
FIRE L EXT
7C3
FIRE R DET LT
6C4
FIRE R EXT
7G3
FLAP CONTR/AUX FLAP
3E3
FLAP IND/TAIL/RUDDER
RE2
FLAP/SLAT CONTR SHUT-OFF
LD1
FLT CONTR AUTH AC
RF2
FLT CONTR AUTH DC
2A1
FLT HYD BACKUP PH A
2C1
FLT HYD BACKUP PH B
2E1
FLT HYD BACKUP PH C
3D2
FLT HYD PRESS IND
2H2
FORM/TAXI LT
RD1
FUEL FEED/DUMP
7F7
FUEL LOW CAUTION
RC1
FUEL MGT PNL
RG1
FUEL P/MOTIVE FLOW ISOL V (P-PUMP)
7F1
FUEL PRESS ADVSY
3F2
FUEL QTY IND AC
7D3
FUEL QTY IND DC
267
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
7E4
FUEL TRANS ORIDE
7F9
FUEL VENT VALVE
7F5
GEN L CAUTION
7F4
GEN R CAUTION
8F4
GND PWR/COOLING INTERLK
7G1
GND ROLL BRAKING/SPOILER POS IND
8D6
GND TEST
8C3
GUN ARMED POWER
8B3
GUN CLR/GUN CONTR PWR DC
2H5
GUN CONTR PWR AC
8B3
GUN CONTR PWR DC/GUN CLR
8I3
GYRO PWR
1B1
HSD/ECMD PH A
1B4
HSD/ECMD PH B
1B7
HSD/ECMD PH C
8C4
HUD CAMERA DC
1F1
HUD CAMERA PH A
1D4
HUD CAMERA PH B
1E5
HUD CAMERA PH C
3C7
HUD PH A
4C2
HUD PH B
4C4
HUD PH C
1A1
HV PWR SUP PH A
1A2
HV PWR SUP PH B
1A3
HV PWR SUP PH C
7E6
HYD PRESS IND
7G11
HYD PUMP SPOILER CONTR
7E5
HYD VALVE CONTR
LD3
ICE DET
6F3
ICS NFO
6F2
ICS PILOT
1I7
IFF A/A AC
268
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
8F6
IFF A/A DC
7C7
ILS ARA-63 DC
3A6
ILS ARA-63 PH A
4A3
ILS ARA-63 PH B
4A5
ILS ARA-63 PH C
7G9
INBD SPOILER CONTR
4B6
INS SYNC/ACM PNL LT
5D3
INST BUS FDR
5A1
INST LT
1I2
INTEG TRIM AC
8F3
INTEG TRIM DC
4A2
INTRF BLANKER
8I1
INTRPT FREE DC BUS FDR NO. 1
8C6
INTRPT FREE DC BUS FDR NO. 2
6E3
JETT 1
6E2
JETT 2
7D7
JULIET 28
LF2
L AICS
2I5
L AICS HTR
7E2
L AICS LKUP PWR/EMER GEN TEST
6A6
L AICS RAMP STOW
8G4
L AIM-7 BATT ARM
7G7
L DC TEST/RUDDER TRIM
7A4
L ENG AFT CONT/ARMT/RATS IND
5A4
L ENG BACK-UP IGN
4C6
L ENG OIL PRESS
7C4
L FIRE DET LT
6C5
L FIRE EXT
7F5
L GEN CAUTION
1A5
L MAIN XFMR/RECT
7F2
L OIL HOT/BLEED AIR
3E6
L PH A TEST/P. ROLL TRIM
4E2
L PH B TEST/P. ROLL TRIM
269
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
4E5
L PH C TEST/P. ROLL TRIM
4D1
L PITOT STATIC HTR
3B1
L TIT IND
7A3
LCH BAR NLG STRUT ADVSY
2H10
LIQUID COOLING CONTR AC
8B4
LIQUID COOLING CONTR DC
3
LD2
MACH TRIM AC
RD2
MACH TRIM DC
LE2
MANUV FLAP/WG SWP DRIVE NO. 2
6B4
MASTER ARM
8H5
MASTER TEST
8H3
MECH FUZING STA 1/8
8H2
MECH FUZING STA 3/4
8H1
MECH FUZING STA 5/6
7G5
MLG HANDLE RLY NO. 1
7G4
MLG HANDLE RLY NO. 2
6F5
MLG SAFETY RLY NO. 1
6F4
MLG SAFETY RLY NO. 2
8D3
MONITOR BUS CONTR
8I5
MOTOR FIRE A
8I4
MOTOR FIRE B
1G1
MSL AUX PH A
1G4
MSL AUX PH B
1G7
MSL AUX PH C
8A1
MSL AUX SUBSYS
2G2
MSL HTR PH A
2G5
MSL HTR PH B
2G8
MSL HTR PH C
1I3
NAV PWR SUP PH A
1I5
NAV PWR SUP PH B
1I6
NAV PWR SUP PH C
2I2
NFO CONSOLE LT
7A3
NLG STRUT LCH BAR ADVSY
270
Change 2
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
RB2
NOSE WHEEL STEER/AFCS
5F6
NVG FLOOD LT
7F2
OIL L HOT/BLEED AIR
7D2
OIL R HOT
8C5
OUTBD SPOILER CONTR
2B2
OUTBD SPOILER PUMP
7F6
OXY/BINGO CAUTION
3F3
OXY QTY IND
7C8
PEDAL SHAKER/ALPHA COMP
3E6
P. ROLL TRIM/L PH A TEST
4E2
P. ROLL TRIM/L PH B TEST
4E5
P. ROLL TRIM/L PH C TEST
RA2
P. ROLL TRIM/SPD BK ENABLE
3E6
PH A L TEST/P. ROLL TRIM
2H1
PH A R TEST
4E2
PH B L TEST/P. ROLL TRIM
2H4
PH B R TEST
4E5
PH C L TEST/P. ROLL TRIM
2H8
PH C R TEST
2I3
PILOT CONSOLE LT
5A1
PILOT INST LT
LB1
PITCH A AC
7B7
PITCH A DC
LH1
PITCH B AC
7B3
PITCH B DC
4D1
PITOT L STATIC HTR
4D2
PITOT R STATIC HTR
7E3
PLT ANN PNL AUX PWR/TR-ADVSY
2I1
POS/ANTICOLL/SUPP POS LTS
RG2
PROBE/ENG/ANTI-ICE
4F2
PROBE LT
LG2
R AICS
2I8
R AICS HTR
Change 3
271
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
7E1
R AICS LKUP PWR/ANTI-SKID
6A5
R AICS RAMP STOW
8G3
R AIM-7 BATT ARM
8D1
R DC TEST/AMC BIT
7C2
RAIN REPL/ANTI-ICE CONTR/HKCONTR
8G7
RECON ECS CONT DC
2G4
RECON ECS CONT AC
2B1
RECON HTR PWR PH A
2D1
RECON HTR PWR PH B
2F1
RECON HTR PWR PH C
1F4
RECON POD
8F7
RECON POD CONTR
8F1
RECON POD DC PWR NO. 2
8F2
RECON POD DC PWR NO. 1
7A5
R ENG AFT CONT/EXHAUST NOZZLE
5A3
R ENG BACK UP IGN
3C2
R ENG N2 TACH
4D6
R ENG OIL PRESS
7C3
R FIRE DET LT
6C4
R FIRE EXT
7F4
R GEN CAUTION
2E3
R MAIN XFMR RECT
7D2
R OIL HOT
2H1
R PH A TEST
2H4
R PH B TEST
2H8
R PH C TEST
4D2
R PITOT STATIC HTR
5D6
RADAR ALTM
3B2
R TIT IND
8A3
RADAR SUBSYS NO. 1
8A2
RADAR SUBSYS NO. 2
LB3
ROLL A / YAW M
7B4
ROLL A DC
LA1
ROLL B AC
272
Change 3
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
7B2
ROLL B DC
3E3
RUDDER/TAIL/FLAP IND
7G7
RUDDER TRIM/L DC TEST
3E7
RUDDER TRIM PH A
4E1
RUDDER TRIM PH B
4E4
RUDDER TRIM PH C
2I4
SEAT ADJ/ACM LT/STEADY POS LT
1E2
SEMI REG PWR SUP PH A
1E4
SEMI REG PWR SUP PH B
1E6
SEMI REG PWR SUP PH C
1J6
SIGNAL DATA CONVERTER
1H1
SOL PWR SUP PH A
1H5
SOL PWR SUP PH B
1H7
SOL PWR SUP PH C
RA2
SPD BK/P-ROLL TRIM ENABLE
7G11
SPOILER CONTR HYD PUMP
7G9
SPOILER CONTR INBD
8C5
SPOILER CONTR OUTBD
7G1
SPOILER POS IND/GND ROLL BRAKING
8E4
STA 1 AIM-9 COOL PWR
6D4
STA 1 AIM-9 REL PWR
6C7
STA 1 REL PWR A
6C6
STA 1 REL PWR B
8E6
STA 1A AIM-9 PWR
2H7
STA 1A AIM-9 PWR PH B
8E5
STA 1B AIM-9 PWR
2H9
STA 1B AIM-9 PWR PH C
1E1
STA 1/8 AIM-7 PH A
1E3
STA 1/8 AIM-7 PH B
1E7
STA 1/8 AIM-7 PH C
6D7
STA 2, 3, & 4 REL PWR A
6D6
STA 2, 3, & 4 REL PWR B
8H2
STA 3/4 MECH FUZING
1D1
STA 3/6 AIM-7/AIM-54 PUMP PH A
273
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
1D3
STA 3/6 AIM-7/AIM-54 PUMP PH B
1 D7
STA 3/6 AIM-7/AIM-54 PUMP PH C
1C1
STA 4/5 AIM-7 PH A
1C3
STA 4/5 AIM-7 PH B
1C7
STA 4/5 AIM-7 PH C
6E7
STA 5, 6, & 7 REL PWR A
6E6
STA 5, 6, & 7 REL PWR B
8E1
STA 8 AIM-9 COOL PWR
6D3
STA 8 AIM-9 REL PWR
6E5
STA 8 REL PWR A
6E4
STA 8 REL PWR B
8E3
STA 8A AIM-9 PWR
2I7
STA 8A AIM-9 PWR PH B
8E2
STA 8B AIM-9 PWR
2I9
STA 8B AIM-9 PWR PH C
7F8
STARTER VALVE LT/THRUST LIM
5A5
STBY ATTD IND PH A
5C5
STBY ATTD IND PH B
2I4
STEADY POS LT/ACM LT/SEAT ADJ
2I1
SUPP POS/ANTICOLL/POS LTS
3D6
TACAN ARM-84
7E8
TACAN/BDHI
4F6
TACAN/BDHI INST PWR
3E3
TAIL/RUDDER/FLAP IND
2H2
TAXI/FORM LT
1H2
TCS PH A
1H3
TCS PH B
1H6
TCS PH C
8A6
TCS SEL
4D4
TEMP CONT AC
7D4
TEMP CONTR ECS DC
7F3
TR-ADVSY/PLT ANN PNL AUX PWR
6F6
UHF CONTR
274
NAVAIR 01-F14AAP-1B
CIRCUIT BREAKERS ALPHANUMERIC INDEX
4D5
UTILITY LT
3B6
VDI PH A
4B1
VDI PH B
4B4
VDI PH C
LE2
WG SWP DR NO. 2/MANUV FLAP
7G6
WHEELS POS IND
2H6
WHITE FLOOD LT
3B3
WING POS IND AC
7G2
WING POS IND DC
LE1
WING SWEEP DRIVE NO. 1
7C2
WSHD AIR/ANTI-ICE/HK CONTR
8B2
WSHLD DEFOG CONTR
1A5
XFMR RECT L MAIN
2E3
XFMR RECT R MAIN
7B6
YAW A DC
7B5
YAW B DC
LC1
YAW A AC
LC3
YAW B AC
LB3
YAW M / ROLL A
3F7
26 VAC BUS FDR
1B2
28 VDC PWR SUP PH A
1B5
28 VDC PWR SUP PH B
1B8
28 VDC PWR SUP PH C
EFFECTIVITY
1
TARPS aircraft only.
2
Labeled RECON POD on TARPS aircraft.
TARPS aircraft with ALQ-167 pod circuit breaker is labeled LIQ
3
CLG/ALQ-167 CONT DC.
Change 3
275
NAVAIR 01-F14AAP-1B
276
Change 3
NAVAIR 01-F14AAP-1B
AC LEFT MAIN CIRCUIT BREAKER PANEL
(LEFT AFT) (PANEL NO. 1 — UPPER SEGMENT)
277
NAVAIR 01-F14AAP-1B
AC LEFT MAIN CIRCUIT BREAKER PANEL
(LEFT AFT) (PANEL NO. 1 — LOWER SEGMENT)
278
NAVAIR 01-F14AAP-1B
AC RIGHT MAIN CIRCUIT BREAKER PANEL
(LEFT AFT) (PANEL NO. 2)
279
NAVAIR 01-F14AAP-1B
AC ESSENTIAL NO. 2 PHASE A CIRCUIT
BREAKER PANEL (LEFT) (PANEL NO. 3)
280
NAVAIR 01-F14AAP-1B
AC ESSENTIAL NO. 2 PHASE B AND C CIRCUIT
BREAKER PANEL (LEFT) (PANEL NO. 4)
281
NAVAIR 01-F14AAP-1B
AC ESSENTIAL NO. 1 CIRCUIT BREAKER
PANEL (RIGHT SIDE) (PANEL NO. 5)
282
Change 2
NAVAIR 01-F14AAP-1B
DC ESSENTIAL NO. 1 CIRCUIT BREAKER
PANEL (RIGHT SIDE) (PANEL NO. 6)
283
NAVAIR 01-F14AAP-1B
DC ESSENTIAL NO. 2 CIRCUIT BREAKER PANEL
(RIGHT AFT) (PANEL NO. 7 — UPPER SEGMENT)
284
Change 2
NAVAIR 01-F14AAP-1B
DC ESSENTIAL NO. 2 CIRCUIT BREAKER PANEL
(RIGHT AFT) (PANEL NO. 7 — LOWER SEGMENT)
285
NAVAIR 01-F14AAP-1B
DC MAIN CIRCUIT BREAKER PANEL
(RIGHT AFT) (PANEL NO. 8 — UPPER SEGMENT)
286
NAVAIR 01-F14AAP-1B
DC MAIN CIRCUIT BREAKER PANEL
(RIGHT AFT) (PANEL NO. 8 — LOWER SEGMENT)
287
NAVAIR 01-F14AAP-1B
SERVICING DATA
GROUND REFUELING
Single-point refueling is through a standard pressure refueling
receptacle on the forward right fuselage. Refueling is con-
trolled by two selector valves and the vent pressure gauge adja-
cent to the refueling receptacle. When aircraft fuel tanks are
full, fueling stops automatically.
The maximum refueling rate is approximately 500 gallons per
minute at a pressure of 50 psi. Nominal and minimum pressure
is approximately 15 psi, and maximum pressure is 50 psi.
Ensure that both the fueling unit and aircraft
are properly grounded, bonding cable is con-
nected between aircraft and refueling source,
and fire extinguishing equipment is readily
available.
CAUTION
During ground refueling operations, the
direct-reading vent pressure indicator shall be
observed and refueling stopped if pressure
indications are in the red band (above 4 psi).
288
NAVAIR 01-F14AAP-1B
Note
D If the aircraft is serviced with JP-4 fuel, the
main fuel-control fuel-grade (specific gravity
adjustment) selector on each engine should
be reset to the JP-4 position. If the aircraft is
being regularly serviced with JP-8 or JP-5
fuel, the fuel control fuel-grade
(specific
gravity adjustment) selector on each engine
should be reset to the JP-5 position.
D Removal of JP-8 from the aircraft is not
required before refueling with JP-5. If
removal of JP-8 from the aircraft aboard
ship is necessary, it shall not be defueled
into storage tanks containing JP-5.
ENGINE OIL
For normal servicing, sight gauge on the oil storage tank is the
primary indicator as to whether servicing is required. During
servicing, overflow oil exits the overflow discharge port when
the tank is properly serviced. Servicing is accomplished using
PON-6 servicing cart. Normal oil consumption is 0.03 gallon
per hour with the maximum being 0.1 gallon per hour.
Lubricating oil, MIL-L-23699, is toxic and flam-
mable. Protection:
chemical splash-proof
goggles, gloves, and good ventilation. Keep
sparks, flames, and heat away. Keep lubricating
oil off skin, eyes, and clothes; do not breathe
vapors. Wash hands thoroughly after handling.
289
NAVAIR 01-F14AAP-1B
Do not overservice oil storage tank. Overserv-
icing can cause scavenge pump failure and
subsequent engine failure.
Note
Engine oil quantity must be checked within 30
minutes after engine shutdown, otherwise, run
engineat 80 percent rpmor greater for 10 min-
utes to ensure proper servicing.
INTEGRATED DRIVE GENERATOR
IDG oil level is checked at the IDG mounted on the forward
right side of the forward accessory gearbox of each engine. It is
serviced at the pressure fill port on the right side. To obtain a
valid fluid level check, the sight gauge must be checked no
sooner than 5 minutes and no later than 60 minutes after
shutdown.
HYDRAULIC SYSTEMS
Hydraulic servicing is required on the flight and combined sys-
tems, outboard spoiler backup module, main landing gear,
nosewheel shock struts, and arresting hook dashpot. A hydrau-
lic pressure filling cart is required to service the systems with
fluid and an air-nitrogen cart to preload the reservoirs. The tem-
perature recording gauge in the flight and combined systems
indicates the maximum temperature attained by the hydraulic
fluid.
PNEUMATIC SYSTEMS
Pneumatic servicing is required for normal operations of the
canopy, emergency landing gear extension, auxiliary canopy
opening, both hydraulic systems, servicing panels, brake sys-
tems, and arresting hook.
290
Change 2
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING LOCATIONS
291
NAVAIR 01-F14AAP-1B
DOD IFR
DESIGNATION
NATO
COMMERCIAL
SUPPLEMENT
ITEM
SPECIFICATION
CODE
EQUIVALENT
CODE
REMARKS
FUEL
MIL-T-5624 (JP-5)
F-44
NONE
JP-5
SELECTOR ON MAIN
ENG. CONT. SHALL BE
MIL-T-5624 (JP-4)
F-40
JET B
JP-4
SET TO JP5, JP4, OR
DENSITY OF OTHER
MIL-T-83133 (JP-8)
F-34
JET A-1
JP-8
FUEL USED
(STRAW COLOR)
ENGINE OIL
MIL-L-23699
0-156
NONE
0-156
USE MIL-L-7808 WHEN
GROUND TEMPERATURE
MIL-L-7808
0-148
NONE
0-148
IS -40_F (-40_C).
INTEGRATED
MIL-L-23699
0-156
NONE
0-156
USE MIL-L-7808 WHEN
DRIVE (IDG)
GROUND TEMPERATURE
MIL-L-7808
0-148
NONE
0-148
IS -40_F (-40_C).
HYDRAULIC
MIL-H-83282
NONE
NONE
NONE
FLUID
OXYGEN
MIL-0-27210
NONE
NONE
LOX
(LIQUID)
TYPE II
OXYGEN
ML-0-27210
NONE
NONE
HPOX
SURVIVAL KIT SHALL BE
(GASEOUS)
REMOVED FROM AIR-
TYPE I
LHOX
CRAFT FOR SERVICING
EMERGENCY OXYGEN
BOTTLE.
NITROGEN
BB-N-411C
NONE
NONE
NONE
USE CLEAN, OIL FREE
(TYPE I, GRADE A)
FILTERED DRY AIR, IF
NITROGEN IS NOT
AVAILABLE.
LIQUID
COOLANT 25, 25R
NONE
NA
NONE
EITHER COOLANT MAY
COOLANT
(MONSANTO
BE MIXED WITHOUT
CHEMICAL CO)
ADVERSE REACTION.
CHEVRON
NONE
NA
NONE
FLO-COOL 180
(CHEVRON
CHEMICAL CO)
WIPE ON
MIL-W-6882
NONE
NONE
NONE
CLEAN AND DRY WIND-
RAIN
SHIELD. APPLY WITH
REPELLANT
CLOTH USING OVER-
FLUID
LAPPING WIPES. AFTER
1-MINUTE DRYING. WIPE
CLEAN WITH SOFT
CLOTH.
POWER UNITS
PNEUMATIC
ELECTRICAL
AIR
STARTING
POWER
CONDITIONING
HYDRAULICS
ACCEPTABLE
ASHORE:
NC8A
NR 5C
USN UNITS
(ELECTRICAL)
NCPP-105
MD-3
RCPT-105
MD-3A
NR 8 (DIESEL)
AHT 63/64 TTU-228/E
A/M47A-4
MD-3M
MA-1
(AHT-73) MJ-3
MA-3MPSU
MA-1A
AFLOAT:
A/M32A-60
A/M32C-5
A/S47A-1
A/M32A-60A
A/M32C-6
GROUND
200 lb/min AT
115+/-20 V ac,
70 lb/ min AT
50 gal/min MAXIMUM
SUPPORT
75 3 psi
400+/-25 Hz,
3 psi AND 60 F
AT 3000 PSI
EQUIPMENT
(STD. DAY)
60 kVA, 3
REQUIREMENTS
PHASE
ROTATION
AIRCRAFT SERVICING DATA (Sheet 1 of 8)
292
Change 2
NAVAIR 01-F14AAP-1B
PNEUMATIC PRESSURE
SYSTEM
PRESSURE
EMERGENCY LANDING GEAR
3000 PSI AT 70_ F
COMBINED HYDRAULIC
1800 PSI AT 70_ F
FLIGHT HYDRAULIC
1800 PSI AT 70_ F
CANOPY NORMAL (1200 PSI MINIMUM)
3000 PSI AT 70_ F
CANOPY AUXILIARY (800 PSI MINIMUM)
3000 PSI AT 70_ F
WHEEL BRAKE ACCUMULATORS (2)
1900 PSI AT 70_ F
ARRESTING HOOK DASHPOT
800 ± 10 PSI
MAIN GEAR SHOCK STRUTS (2)
980 PSI
NOSEGEAR SHOCK STRUT
1300 PSI
WINDSHIELD AIR
75 PSI
NOTE
DRY NITROGEN, SPECIFICATION BB-N-411C, TYPE
1, GRADE A, IS PREFERRED FOR TIRE INFLATION
AND CHARGING PNEUMATIC SYSTEMS SINCE IT IS
INERT, AND THEREFORE WILL NOT SUPPORT
COMBUSTION.
TIRES
TYPE
OPERATION
PRESSURE
NOSE (2)
ASHORE
105 PSI
22 X 6.6-10
AFLOAT
350 PSI
20 PLY
MAIN (2)
ASHORE
245 PSI
37 X 11.50-16
AFLOAT
350 PSI
28 PLY
AIRCRAFT SERVICING DATA (SHEET 2)
Change 2
293
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 3)
294
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 4)
295
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 5)
296
Change 2
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 6)
297
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 7)
298
NAVAIR 01-F14AAP-1B
AIRCRAFT SERVICING DATA (SHEET 8)
299/(300 blank)
CARD 1 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
How to use the DFCS IN FLIGHT FAULT MATRIX:
These cards are organized according to the relative level of severity" of the six individual DFCS
caution lights six pack". When a DFCS related failure is detected in flight, the aircrew can resolve the
cause of that failure by identifying the caution/advisory lights illuminated and the AFC acronyms
reported in the maintenance file. First, identify the highest level of severity" caution light observed in
the cockpit (as indicated by the order of the fault cards). For example, if the ARI/SAS OUT caution
light is not illuminated, proceed to the next card. Likewise if the ARI DGR caution light is not
illuminated proceed to the next card. Proceed until one of the lights is recognized. Then identify the
matching set of caution lights observed in the cockpit with those in the LIGHT(S)" column (note that
the lights for each fault are organized by level of severity as well). Now within this row, identify the
subĆlevel row that matches the associated AFC acronyms ACRO(S)" observed in the cockpit. Note
that the aircraft configuration CONFIG" is sometimes important for the proper resolution of certain
faults. This process should identify a single failure (or family of failures) in the FAILURE CAUSE(S)"
column, the degraded functionality associated with that fault in the FUNCTIONALITY DEGRADE"
column, and the reported DCP FLT group codes that can be expected in the DCP CODE(S)" column.
CARD 2 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
The DFCS IN FLIGHT FAULT MATRIX cards are organized as follows:
How to use the DFCS IN FLIGHT FAULT MATRIX (CARD 1/2 of 10)
DFCS IN FLIGHT FAULT MATRIX ć ARI/SAS OUT (CARD 3/4 of 10)
DFCS IN FLIGHT FAULT MATRIX ć ARI DGR (CARD 5/6 of 10)
DFCS IN FLIGHT FAULT MATRIX ć ROLL DGR (CARD 7 of 10)
DFCS IN FLIGHT FAULT MATRIX ć PITCH SAS (CARD 7 of 10)
DFCS IN FLIGHT FAULT MATRIX ć FCS CAUTION (CARD 8 of 10)
DFCS IN FLIGHT FAULT MATRIX ć MISC LIGHTS (CARD 9 of 10)
DFCS IN FLIGHT FAULT MATRIX ć NO LIGHTS (CARD 10 of 10)
Abbreviations used in these cards:
ARI
automatic rudder interconnect functions (listed below)
LSRI
lateral stick to rudder interconnect
DTFO
differential tail fadeout
WRS
wing rock suppression
LSXC
low speed cross control
Notes used in the FAILURE CAUSE(S) column:
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
2 Will also illuminate MACH TRIM caution light.
3 Will also illuminate HZ TAIL AUTH caution light.
4 Will also illuminate RUDDER AUTH caution light.
5 Will also illuminate SPOILERS caution light.
6 Will also illuminate L INLET and R INLET caution light respectively.
CARD 3 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
ARI SAS/OUT
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADE
DCP FLT CODE(S)
ARI/SAS OUT
PC, RC,
PA or UA
1. Internal DFCC test failure.
1.
Total DFCS failure. Pitch,
1.
_C##, POR.
ARI DGR
YC
1. Power on Reset.
Roll, Yaw SAS, ARI, SR, &
2.
_C##, POR.
YAW DGR
spoilers inop. Authority stops
CAUTION ć Depressing the
ROLL DGR
inop. DLC, Autopilot, Mach trim
MASTER RESET pushbutton with
PITCH SAS
inop.
this condition is the equivalent of
FCS CAUTION
executing a POR. See PCL POR
procedures.
ARI/SAS OUT
PA, PS,
PA or UA
1.
YAW A & B computer fault. 1,3,4,5
1.
Yaw SAS, ARI, SR inop. Roll
1.
DCP inop
ARI DGR
RS, YA,
SAS basic. OB spoilers inop.
(YC## codes
YAW DGR
YC, YS,
Authority stops inop. DLC,
blanked).
ROLL DGR
AM
Autopilot inop. DCP inop.
FCS CAUTION
PS, RS, YS
UA
1.
Yaw rate 2F.
1.
Roll SAS, ARI, SR inop. Yaw
1.
YGY#.
SAS, ARI, SR inop. PQVM inop.
AM
UA
1.
Lateral accel 2F.
1.
Roll SAS, ARI, SR inop. Yaw
1.
LAT#.
SAS, ARI, SR inop.
ARI/SAS OUT
YA
UA
1.
Yaw series actuator 2F. 1
1.
Roll SAS, ARI, SR inop. Yaw
1.
YSA#.
ARI DGR
SAS, ARI, SR inop.
YAW DGR
YC
UA
1.
Yaw bridge monitor 2F. 5
1.
Same as YAW A or YAW B
1.
YC##.
ROLL DGR
computer failure degrade.
ARI/SAS OUT
PS, RS, YS
PA
1.
Yaw rate 2F.
1.
Roll SAS basic.
1.
YGY#.
ARI DGR
Yaw SAS, ARI, SR inop.
YAW DGR
PQVM inop.
FCS CAUTION
AM
PA
1.
Lateral accel 2F.
1.
Roll SAS basic.
1.
LAT#.
Yaw SAS, ARI, SR inop.
ARI/SAS OUT
YA
PA
1.
Yaw series actuator 2F. 1
1.
Roll SAS basic.
1.
YSA#.
ARI DGR
2.
YAW SAS switch fault.
Yaw SAS, ARI, SR inop.
2.
DCP3.
YAW DGR
YC
PA
1.
Yaw bridge monitor 2F. 5
1.
Same as YAW A or YAW B
1.
YC##.
computer failure degrade.
CARD 4 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
ARI SAS/OUT
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADE
DCP FLT CODE(S)
ARI/SAS OUT
PS
UA
1.
Mach 2F.
1.
Pitch SAS inop.
1.
AD01, 03, 04,
ARI DGR
Roll SAS/ARI inop.
05 & MACL/
ROLL DGR
Yaw SAS basic.
MACR.
PITCH SAS
FCS CAUTION
ARI/SAS OUT
PS, RA, RC,
PA or UA
1.
ROLL A & B computer fault. 1,2,5
1.
Roll SAS, ARI, SR inop.
1.
RC##.
ARI DGR
RS
Yaw SAS basic.
ROLL DGR
IB spoilers inop. DLC, Autopilot,
FCS CAUTION
Mach trim inop.
PS
UA
1.
AOA 2F.
1.
Roll SAS, ARI inop.
1.
AOAC/AC28, AOAT,
Yaw SAS basic.
& AOAL/AOAR.
RC
PA or UA
1.
Roll bridge monitor 2F. 1,2,5
1.
Same as ROLL A or ROLL B
1.
RC##.
computer failure degrade.
RS
PA or UA
1.
Roll Rate 2F1.
1.
Roll SAS, ARI inop.
1.
RGY#.
Yaw SAS basic.
2.
Lateral stick position 2F. 5
2.
Roll SAS, ARI, SR inop.
2.
RCP#.
Yaw SAS basic.
Spoilers inop.
ARI/SAS OUT
RA
PA or UA
1.
Roll series actuator 2F. 1
1.
Roll SAS, ARI inop.
1.
RSA#.
ARI DGR
2.
ROLL SAS switch fault.
Yaw SAS basic.
2.
DCP2.
ROLL DGR
ARI/SAS OUT
RS
PA
1.
Gear handle 2F.
1.
UA−ARI control laws in PA
1.
LDG#.
(flaps dn)
configuration.
None
PA or UA
1. Roll and/or yaw axis disengaged (SAS
1.
Roll and/or Yaw SAS + ARI
1.
None.
switch OFF).
disengaged. Other basic SAS.
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
2 Will also illuminate MACH TRIM caution light.
3 Will also illuminate HZ TAIL AUTH caution light.
4 Will also illuminate RUDDER AUTH caution light.
5 Will also illuminate SPOILERS caution light.
6 Will also illuminate L INLET and R INLET caution light respectively.
CARD 5 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
ARI DGR
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
ARI DGR
PS, YA,
PA or UA
1.
YAW A computer fault. 3,4
1.
Yaw SAS, ARI, SR half auth.
1.
DCP inop (YC##
YAW DGR
YC, YS,
Authority stops inop. DLC, Mach
blanked).
FCS CAUTION
AM
trim inop. DCP inop.
PA, PS, YA,
PA or UA
1.
YAW B computer fault. 1,3,4,5
1.
Yaw SAS, ARI, SR half auth.
1.
YC##.
YC, YS,
OB spoilers inop. Authority stops
AM
inop. DLC, Autopilot, Mach trim
inop.
YC
PA or UA
1.
Yaw bridge monitor 1F
1.
Same as YAW A or YAW B
1.
YC##.
(command). 3,4,5
computer failure degrade.
ARI DGR
YA
PA or UA
1.
Yaw series actuator 1F.
1.
Yaw SAS, ARI half authority
1.
YSA#.
YAW DGR
(gain doubled).
ARI DGR
PS
PA or UA
1.
Mach 1F ( > 600 kts & AICS
1.
Pitch SAS inop.
1.
MACL/MACR &
ROLL DGR
cross check).
Roll SAS degrade (low gain).
AICX.
PITCH SAS
ARI degrade (fixed Mach gains).
FCS CAUTION
ARI DGR
PS, RA,
PA or UA
1.
ROLL A computer fault. 1,2,5
1.
Roll SAS, ARI half auth.
1.
RC##.
ROLL DGR
RC, RS
IB spoilers inop. DLC, Autopilot,
FCS CAUTION
Mach trim inop. ARI DGR after
maneuvering (WRS, LSXC inop).
PS, RC, RS
PA or UA
1.
ROLL B computer fault. 1,2
1.
Roll SAS, ARI half auth.
1.
RC##.
Autopilot, Mach trim inop.
RC
PA or UA
1.
Roll bridge monitor 1F
1.
Same as ROLL A or ROLL B
1.
RC##.
(command). 2,5
computer failure degrade.
ARI DGR
RA
PA or UA
1.
Roll series actuator 1F.
1.
Roll SAS, ARI half auth.
1.
RSA#.
ROLL DGR
ARI DGR
PA, PC,
PA or UA
1.
PITCH A & B computer fault. 1,5
1.
Pitch SAS inop.
1.
PC##.
PITCH SAS
PS, RA, RS
Spoilers inop. DLC, Autopilot
FCS CAUTION
inop. ARI DGR after
maneuvering (WRS, LSXC inop).
CARD 6 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
ARI DGR
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
ARI DGR
PA, PC,
PA or UA
1. PITCH B computer fault. 1,5
1. Pitch SAS half auth.
1.
PC##.
PITCH SAS
PS, RS
2. DLC trim servo isolation fault. 1,5
OB spoilers inop. DLC, Autopilot
2.
DLT2.
FCS CAUTION
inop. ARI DGR after
maneuvering (WRS, LSXC
inop).
ARI DGR
PS
PA or UA
1.
SCADC Mach invalid fault. 1
1. ARI degrade (fixed Mach gains).
1.
AD01.
FCS CAUTION
2.
SCADC valid to roll computer
2. Autopilot, Mach trim inop. YAW
2.
AD04.
fault. 1,2
DGR after maneuvering (WRS,
3.
AD01, 04.
3.
Air data computer (CADC) fault.
LSXC inop).
4.
AOAL, MACL, &
1,2,3,4
3. ARI degrade (fixed Mach gains).
AICX.
4.
L AICS computer fault. 6
Autopilot, Mach trim inop. YAW
5.
AOAR, MACR,
5.
R AICS computer fault. 6
DGR after maneuvering (WRS,
& AICX.
LSXC inop).
4−5. Equivalent of AOA /Mach 1F.
PA
1.
AOA 2F.
1. PA−ARI degrade (fixed AOA
1.
AOAC/AC28,
2.
Mach 1F (< 600 kts).
gains).
AOAT, &
3.
Mach 2F.
2−3. ARI degrade (fixed Mach
AOAL/AOAR.
gains).
2−3. AD01, 03, 04,
05 & MACL/R.
UA
1.
Mach 1F (< 600 kts).
1. ARI degrade (fixed Mach gains).
1. AD01, 03, 04,
LSXC, WRS inop.
05 & MACL/R.
YS
PA or UA
1.
Rudder pedal position 2F.
1. ARI degrade.
1. RPP#.
UA ć LSXC, WRS inop.
PA ć pedal fadeout for LSRI,
RRC inop (slipped approach).
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
2 Will also illuminate MACH TRIM caution light.
3 Will also illuminate HZ TAIL AUTH caution light.
4 Will also illuminate RUDDER AUTH caution light.
5 Will also illuminate SPOILERS caution light.
6 Will also illuminate L INLET and R INLET caution light respectively.
CARD 7 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
ROLL DGR
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
ROLL DGR
PS
UA
1. AICS cross check (> 600 kts or
1−2. Pitch SAS inop.
1−2. AICX.
PITCH SAS
invalid Qbar).
Roll SAS degrade (low gain).
FCS CAUTION
2. SCADC Qbar & AICS cross
check. 3,4
3 Will also illuminate HZ TAIL AUTH caution light.
4 Will also illuminate RUDDER AUTH caution light.
PITCH SAS
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
PITCH SAS
PC, PS,
PA or UA
1. PITCH A computer fault. 1,5
1. Pitch SAS half auth.
1. PC##.
FCS CAUTION
RA, RS
IB spoilers inop. DLC, Auto
pilot inop. ARI DGR after
maneuvering (WRS, LSXC
inop).
PC
PA or UA
1. Pitch bridge monitor 1F
1−2. Same as PITCH A or PITCH
1−2. PC##.
(command). 5
B computer failure degrade.
2. Pitch bridge monitor 2F. 1,5
PS
PA or UA
1. Pitch rate 2F. 1
1. Pitch SAS inop.
1. PGY#.
PITCH SAS
PA
PA or UA
1. Pitch series actuator 1F.
1. Pitch SAS half auth.
1. PSA#.
2. Pitch series actuator 2F. 1
2. Pitch SAS inop.
2. PSA#.
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
5 Will also illuminate SPOILERS caution light.
CARD 8 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
FCS CAUTION
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADE
DCP FLT CODE(S)
FCS CAUTION
PS, RS
PA or UA
1.
IMU related fault. 1
1. No effect, pitch and roll axes
1.
IMU#.
one failure away from loss of
SAS.
PS
PA or UA
1.
AOA 1F.
1−3. No effect, one failure away
1.
AOAC, AOAT, or
2.
28V alpha computer cb.
from degraded ARI.
AOAL/AOAR.
3.
AICS cross check 1F with valid
4.
No effect, one failure away
2.
AC28.
SCADC (> 600 kts).
from loss of pitch SAS.
3.
AICX.
4.
Pitch rate 1F.
4.
PGY#.
PA
PA or UA
1.
PITCH SAS switch fault.
1.
Pitch SAS inop.
1.
DCP1.
RS
PA or UA
1.
Lateral stick position 1F.
1.
No effect, one failure away
1.
RCP#.
2.
Roll rate 1F.
from loss of roll SAS/ARI/
2.
RGY#.
spoilers.
2.
No effect, one failure away
from loss of roll SAS/ARI.
YS
PA or UA
1.
Rudder pedal position 1F.
1.
No effect, one failure away
1.
RPP#.
2.
Yaw rate 1F.
from degraded ARI.
2.
YGY#.
2.
No effect, one failure away
from loss of yaw SAS/ARI.
AM
PA or UA
1.
Lateral accel 1F.
1.
No effect, one failure away
1.
LAT#.
from loss of yaw SAS/ARI.
None
PA or UA
1.
Pitch bridge monitor 1F
1−3. No effect (failure of monitor
1.
PC##.
(monitor).
channel only), one failure
2.
RC##.
2.
Roll bridge monitor 1F (monitor).
away from loss of affected
3.
YC##.
3.
Yaw bridge monitor 1F (monitor).
axis.
4.
CSDC.
4.
CIU/CSDC fault. 1
4. Autopilot degrade (HDG hold
5.
_C##.
5.
CCDL fault.
inop), IBIT inop.
6.
_C##.
6.
Relay voter 1F.
5−6. No effect, one failure away
from loss of function.
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
CARD 9 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
SPOILERS
PA
PA or UA
1.
Outboard spoiler(s) fault. 1
1.
Affected L/R spoiler(s) inop.
1.
SP3L, SP3R,
SP4L, &/or SP4R
RA
PA or UA
1.
Inboard spoiler(s) fault. 1
1.
Affected L/R spoiler(s) inop.
1.
SP1L, SP1R,
SP2L, &/or
SP2R.
HZ TAIL
−
PA or UA
1.
Flight controls authority 28 VDC
1−2.
Lateral & rudder authority
1.
CA28.
AUTH
power fault.
stops inop.
2.
AD05.
RUDDER
2.
SCADC valid to yaw computer.
AUTH
1,3,4
HZ TAIL
−
PA or UA
1.
Lateral authority actuator fault.
1−3.
Lateral authority stops inop.
1.
HZTA.
AUTH
2.
28 VDC lateral authority fault.
2.
HT28.
3.
Lateral authority schedule fault.
2.
AD07.
RUDDER
−
PA or UA
1.
Rudder authority actuator fault.
1−3.
Rudder authority stops inop.
1.
RUDA.
AUTH
2.
28 VDC rudder authority fault.
2.
RD28.
3.
Rudder authority schedule fault.
2.
AD08.
MACH TRIM
−
PA or UA
1.
Mach trim actuator fault.
1−3.
Mach trim inop.
1.
MTRM.
2.
28 VDC Mach trim fault..
2.
MT28.
3.
Mach trim schedule fault.
3.
AD06.
AUTOPILOT
PA
PA or UA
1.
Pitch parallel actuator fault (w/
1.
ACLS inop.
1.
PPA.
ACL engaged).
ACLS/AP
AUTOPILOT
PA
PA or UA
1.
Pitch autotrim actuator fault. 1
1.
Autopilot degraded.
1.
PTRM.
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
CARD 10 of 10
DFCS IN FLIGHT FAULT MATRIX CARDS
OFP 4.4
LIGHT(S)
ACRO(S)
CONFIG
FAILURE CAUSE(S)
FUNCTIONALITY DEGRADED
DCP FLT CODE(S)
–
PS, RS,
PA or UA
1.
Weight−on−wheels 2F.
1.
Autopilot inop. Ground roll
1.
DCP inop
YS
braking inop. DCP display
(WOW# codes
blank on deck.
blanked).
PA
PA
1.
DLC trim actuator fault.
1−2.
No DLC functionality.
1.
DLT1.
PS
PA or UA
1.
Weight−on−wheels 1F.
1.
No effect, one failure away
1.
WOW1.
from loss of function.
RS
PA or UA
1.
Main landing gear handle 1F.
1−2.
No effect, one failure away
1.
LDG#.
2.
WeightĆonĆwheels 1F.
from loss of function in PA
2.
WOW2.
configuration.
RS
UA
1.
Main landing gear handle 2F.
1.
No effect, loss of function in
1.
LDG#.
PA configuration only.
YS
PA or UA
1.
WeightĆonĆwheels 1F.
1.
No effect, one failure away
1.
WOW3.
from loss of function.
−
PA or UA
1.
Wing sweep discrete fault.
1.
Spoilers inop (flaps up).
1.
WSP#.
PA or UA
1.
AHRS valid fault (w/INS invalid).1
1.
AHRS inop. Autopilot & ACLS
1.
AHR#.
inop w/ IMU failure.
PA or UA
1.
Emergency disengage to pitch/roll
1.
Emergency paddle off capability
1.
EDPS.
computer fault. 1
inop. DLC and autopilot inop.
PA or UA
1.
PITCH SAS switch fault.
1−4.
Loss of switch functionality.
1.
DCP1.
2.
ROLL SAS switch fault.
2.
DCP2.
3.
YAW SAS switch fault.
3.
DCP3.
4.
AUTOPILOT switch fault. 1
4.
DCP4.
PA or UA
1.
SCADC valid to pitch computer. 1
1.
Autopilot degrade (HDG hold
1.
AD03.
inop), IBIT inop.
PA or UA
1.
MASTER RESET pushbutton 1F.
1
No effect, one failure away
1.
MRS#.
2.
MASTER RESET pushbutton 2F.
from loss of function.
2.
MRS#.
2.
MASTER RESET inop − DFCS.
PA
1.
Flap fault (w/ ACL engaged). 1
1.
Autopilot ACL inop.
1.
FLAP.
PA
1.
Rudder pedal shaker fault.
1.
Rudder pedal shaker inop.
1.
SHKR.
2.
Ground roll braking fault.
2.
Ground roll braking inop.
2.
GRBS.
1 May also illuminate AUTOPILOT and ACLS A/P caution lights.
2 Will also illuminate MACH TRIM caution light.
3 Will also illuminate HZ TAIL AUTH caution light.
4 Will also illuminate RUDDER AUTH caution light.
NAVAIR 01−F14AAP−1B
F−14 DFCS UP/DOWN STATUS CARDS
FLEET OFP 4.4 Card 1 of 2
F−14 DFCS SELF−TEST AND FAULT REPORTING
DFCS self−tests include: a power−up BIT (PBIT), automatic−BIT (ABIT), and initiated−BIT (IBIT) modes.
DFCS self−tests PBIT and ABIT are together referred to as the operational flight program (OFP) self−test mode.
DFCS fault reporting is indicated by CAI panel lights, maintenance file acronyms, and DCP FAULT DISPLAY codes.
DFCS fault reporting CAI panel lights and DCP FAULT DISPLAY codes indicate results of all self−test modes.
DFCS fault reporting maintenance file acronyms immediately following IBIT are not valid and may be ignored.
DCP FAULT DISPLAY codes are grouped into "IBIT" (IBIT self−test) and "FAIL" or "FLT" (PBIT and ABIT self−tests).
DCP FAULT DISPLAY codes include some that have sequential alphanumeric codes (for example AD## & AHR#).
DFCS IBIT is the most robust flight control system self−test possible on deck (compared to PBIT and ABIT).
DFCS IBIT CAI panel lights are cleared upon master reset and any remaining lights are ABIT (OFP) detected failures.
DFCS IBIT shall be exected on initial startup and following any on deck POR prior to flight operations.
DFCS IBIT shall be executed with flaps down (shorebased ops) or wings aft (shipboard ops or boat launch).
DFCS IBIT will only detect and report aircraft flight control system related degrades/failuires.
DFCS UP/DN STATUS CRITERIA may be modified by squadron SOP at the discretion of the commanding officer.
DFCS UP/DOWN STATUS CRITERIA:
DFCS UP/DOWN status determined based upon the DCP FAULT DISPLAY "FAIL", "FLT", and "IBIT" fault codes.
DFCS UP/DOWN status for sequential alphanumeric fault codes is further resolved by associated CAI panel lights.
If DFCS IBIT reports "PASS" and no CAI panel lights, aircraft considered UP with respect to flight control system.
If DFCS IBIT reports "NOGO", identify the illuminated CAI panel lights prior to depressing MASTER RESET.
Refer to DFCS UP/DOWN STATUS TABLE for DCP fault codes, IBIT/OFP, failure indications, and functions lost.
DFCS DN status troubleshooting may include POR, master reset, cycle flight controls & trim, followed by IBIT.
DFCS DN or SW status may be further resolved by the DOWN (DN) / SOP WAIVER (SW) NOTES (see below).
Aircraft UP/DOWN status regarding other systems shall be considered independent of DFCS IBIT test results.
DOWN (DN) / SOP WAIVER (SW) NOTES:
Numbers = Fault Description:
1
Two or more AOA redundancy failures is DN unless all are AICS (tertiary source) related failures.
2
Check for additional CADC failure / CAI panel light indications to resolve aircraft status.
SW if HZ TAIL AUTH or RUD AUTH caution light following IBIT, but not in ABIT.
Verify full flight control authority. DN if full flight control authority is not available.
3
IMU# fault code + single RGY# fault code is DN.
4
Adhere to IBIT CAI PANEL CAUTION LIGHT CRITERIA (see below).
5
POR,master reset, cycle flight controls & trim, and run IBIT in attempt to clear fault.
PSA# DN only if autuator hydraulic leak.
RSA# and/or YSA# is DN.
6
Two or more roll gyro fault codes is DN (unless both RGY1& RGY3 or RGY2&RGY5). RGY7 is DN.
7
POR, master reset, cycle wings & flight controls, and run IBIT in attempt to clear fault.
If WSP# fault code(s), the affected spoilers will work with flaps down, but not flaps up.
8
Two or more yaw gyro fault codes is DN (unless both YGY1&YGY4, YGY2&YGY5, or YGY3&YGY6).
9
If during shipboard IBIT wait for ship motion to steady out and re−run IBIT in attempt to clear fault.
0
Minimum pilot flight hour requirement in type 500 hrs.
Letters = Imposed aircraft limitations:
A Remain below 600 KIAS / 1.3 IMN / 20 units AOA.
B Remain below .93 IMN / at or below 15 units AOA.
C Adhere to NATOPS limitations for any ABIT detected caution lights.
D No limitations.
IBIT CAI PANEL CAUTION LIGHT CRITERIA
UP =
FCS CAUTION and/or PITCH SAS only (DFCS 6−pack)
AUTOPILOT, MACH TRIM
DOWN = ROLL DGR, YAW DGR, ARI DGR, and/or ARI/SAS OUT (DFCS 6−pack)
SPOILERS, HZ TAIL AUTH, and/or RUDDER AUTH
ABBREVIATIONS:
APC
Autothrottle approach power compensator fault
I Initiated BIT (BIT) self−test
ARI
Automatic rudder interconnect
O OFP mode (PBIT & ABIT) self−tests
LSRI
Lateral stick to rudder interconnect
1x Single fault code = single fault, 1st fault, 1F
DTFO
Differential tail fadeout
2x Two fault codes = dual fault, 2nd fault, 2F
WRS
Wing rock suppression
A Channel A of flight control computer
LSXC
Low speed cross control
B Channel B of flight control computer
SAS
Stability augmentaion system
SR
Spin recovery
ą
Change 2
311
NAVAIR 01−F14AAP−1B
F−14 DFCS UP/DOWNSTATUS CARDS
FLEET OFP 4.4 Card 2 of 2
FAULT CODES
DFCS UP/DOWN STATUS TABLE
DCP
IBIT
OFP
FAILURE INDICATION
UP
DN
SW
FUNCTIONS LOST
115V
I
Aircraft 115 VAC power supply fault.
X
Computer problems
28DC
I
Aircraft 28 VDC power supply fault.
X
Computer problems
AC28
I
O
Alpha computer 28 VDC power fault.
A1
AOA redundancy, rudder pedal shaker
AD##
I
O
Air data computer (CADC) related fault.
C2
CADC related degrade/failure
AHR#
O
AHRS related fault.
X
1x − Redundancy, 2x − Autopilot (IMU backup)
AICX
O
AICS crosscheck fault.
B1
Degraded ARI, LSXC, WRS, AOA redundancy
AOAC
I
O
Alpha computer fault.
A1
AOA redundancy (primary source)
AOAL
O
Left AICS AOA fault.
B1
Degraded ARI, LSXC, WRS, AOA redundancy
AOAR
O
Right AICS AOA fault.
B1
LSXC, WRS, Degraded ARI, AOA redundancy
AOAT
I
O
ADD transmitter fault.
A1
AOA redundancy (secondary source)
APCA
I
Normal accelerometer sensor fault.
X
Degraded APC, autopilot ACL mode
APCS
I
Scheduled outputs to APC fault.
X
Degraded APC
CA28
I
Flight controls authority 28 VDC fault.
X
Lateral & rudder authority actuators
CSDC
I
CIU / CSDC interface fault.
X
Autopilot HDG, GT, VEC/PCD, ACL modes
DCP1
O
PITCH STAB AUG switch fault.
X
Pitch SAS control switch (default ON)
DCP2
O
ROLL STAB AUG switch fault.
X
Roll SAS control switch (defalut ON)
DCP3
O
YAW STAB AUG switch fault.
X
Yaw SAS control switch (default ON)
DCP4
I
O
AUTOPILOT switch fault.
X
Autopilot control switch (default OFF)
DLCT
I
DLC thumbwheel fault.
D0
DLC, autopilot ACL mode
DLT1
I
O
DLC trim actuator fault.
D0
DLC, autopilot ACL mode
DLT2
I
O
DLC trim actuator fault.
X4
Pitch SAS & spoilers degrade/failure
DPSL
I
Left AICS delta pressure sensor fault.
A1
AOA redundancy (tertiary source)
DPSR
I
Right AICS delta pressure sensor fault.
A1
AOA redundancy (tertiary source)
EDPS
O
Emergency disengage paddle switch fault.
X
DLC, autopilot modes
FLAP
O
Flaps > 25 deg switch fault.
D0
DLC, autopilot ACL mode
GRBS
O
Ground roll braking switch fault.
D0
Ground roll braking
HT28
O
HZ TAIL AUTH 28 VDC power fault.
X
Lateral stick authority actuator
HZTA
I
O
HZ TAIL AUTH actuator fault.
X
Lateral stick authority actuator
IMU#
O
Inertial measurement unit fault.
A3
1x − IMU failure
LAT#
I
O
Lateral accelerometer fault.
X9
1x − Redundancy, 2x − Yaw SAS/ARI
LDG#
O
Main landing gear handle discrete fault.
D0
1x − Redundancy, 2x − Default UA control laws
MACL
O
Left AICS Mach fault.
B1
Degraded ARI, LSXC, WRS, Mach redundancy
MACR
O
Right AICS Mach fault.
B1
Degraded ARI, LSXC, WRS, Mach redundancy
MRS#
O
MASTER RESET pushbutton fault.
X
1x − Redundancy, 2x − Master reset pushbutton
MT28
I
O
MACH TRIM 28 VDC power fault.
X
Mach trim actuator
MTRM
I
O
MACH TRIM actuator fault.
X
Mach trim actuator
PC##
I
O
Pitch flight control computer related fault.
X4
Pitch SAS & spoilers degrade/failure
PGY#
I
O
Pitch sensor (gyro) fault.
X
1x − Redundancy, 2x − Pitch SAS
POR
O
In−flight Power on Reset.
X
Complete master reset and IBIT before flight
PPA
I
O
Pitch parallel actuator fault.
X
Autopilot ACL mode
PSA#
I
O
Pitch series servo actuator fault.
D5
1x − Degrade, 2x − Pitch SAS
PTRM
I
O
Auto pitch trim actuator fault.
X
Degraded autopilot modes
RC##
I
O
Roll flight control computer related fault.
X4
Roll SAS/ARI & spoilers degrade/failure
RCP#
O
Roll stick transducer fault.
X
1x − Redundancy, 2x − Roll SAS/ARI & spoilers
RD28
O
RUDDER AUTH 28 VDC power fault.
X
Rudder authority actuator
RGY#
I
O
Roll rate gyro fault.
X6
1x − Redundancy, 2x − Roll SAS/ARI
RPP#
O
Rudder pedal position sensor fault.
D0
1x − Redundancy, 2x − LSXC, WRS
RSA#
I
O
Roll series servo actuator fault.
X5
1x − Degrade, 2x − Roll SAS/ARI
RUDA
I
O
RUDDER AUTH actuator fault.
X
Rudder authority actuator
SHKR
O
Pedal shaker motor fault.
D0
Rudder pedal shaker
SP#L
I
O
Left spoiler actuator fault.
X7
Left spoiler actuator
SP#R
I
O
Right spoiler actuator fault.
X7
Right spoiler actuator
SPSL
I
Left AICS static pressure sensor fault.
B1
Degraded ARI, LSXC, WRS, AOA/Mach redncy
SPSR
I
Right AICS static pressure sensor fault.
B1
Degraded ARI, LSXC, WRS, AOA/Mach redncy
TPSL
I
Left AICS total pressure sensor fault.
B1
Degraded ARI, LSXC, WRS, AOA/Mach redncy
TPSR
I
Right AICS total pressure sensor fault.
B1
Degraded ARI, LSXC, WRS, AOA/Mach redncy
WOW#
O
Weight−on−wheels discrete fault.
D0
1x − Redundancy, 2x − Default W−Off−W
WSP#
O
Wingsweep roll/pitch computer fault.
X7
#1 − outbd spoilers, #2 − inbd spoilers (flaps up)
YC##
I
O
Yaw flight control computer related fault.
X4
Yaw SAS/ARI & spoilers degrade/failure
YGY#
I
O
Yaw rate gyro fault.
X8
1x − Redundancy, 2x − Yaw SAS/ARI
YSA#
I
O
Yaw series servo actuator fault.
X5
1x − Degrade, 2x − Yaw SAS/ARI
312 Change 2
NAVAIR 01−F14AAP−1B
SAR ON SCENE
COMMANDER CHECKLIST
1.
Maintain sight
Do not fly through any cloud layers.
Parachute fall rate is about 1000 ft/min.
2.
Squak 7700
3.
Switch guard (243.0) for initial call
Mayday, Mayday, Mayday."
This is _____ on guard."
(Downed A/C)" is on the (Radial/ DME) of TACAN
Station _____."
I am taking station overhead at angels
____,
switching to frequency _____."
4.
Switch to a controlling agency
Repeat initial call
Controlling agency will initialize SAR.
5.
Note the time, Lat/Long, and winds.
6.
Monitor guard. When contact is established with SAR
Helo, switch to SAR primary (282.8).
7.
Warn non−participating A/C to stay clear.
8.
Leave frequency open during Helo hover/recovery.
9.
Make positive transfer of on scene commander
responsibilities prior to RTB.
S Do not run yourself out of gas (know your
bingo profile).
S Do not descend through a cloud layer until
you are sure that the aircrew are in the water.
S Monitor your own A/C altitude, attitude and
airspeed.
Rules of 25
Don’t go below 2.5 on fuel.
Don’t descend below 2.5K’AGL.
Don’t decel below 250 KTS.
Don’t exceed 25_ AOB.
ą
Change 2
313/(314 blank)
TO USE, DETERMINE WIND ANGLE RELATIVE TO RUN-
WAY HEADING. ENTER CHART FROM LOWER LEFT
ALONG WIND ANGLE LINE TO REPORTED VELOCITY
ARC. FROM (INTERSECTION OF WIND ANGLE AND
VELOCITY DETERMINE HEADWIND COMPONENT BY
PROJECTING HORIZONTALLY TO LEFT; DETERMINE
CROSSWIND COMPONENT BY DROPPING VERTICALLY
TO BASELINE.
UNTIL FURTHER FLIGHT TEST DATA IS AVAILABLE,
CROSSWIND TAKEOFFS AND LANDINGS ARE NOT TO
EXCEED 20 KNOTS AT 90_.
2-F052-2-0
CROSSWIND CHART