F16C/D. FLIGHT MANUAL (2002) - page 18

T.O. GR1F16CJ1

232

DURING HOT REFUELING

*1. Be alert for visual or voice signals from

refueling supervisor.

*2. Terminate refueling if intercom contact is

lost - Visual signal.

*3. Ground control radio frequency - Monitor.

*4. Insure hands are visible to ground crew.

HOT REFUELING COMPLETE

1. AIR REFUEL switch - CLOSE.

2. EPU GEN and EPU PMG lights - Confirm off.

3. EPU switch-OFF.

4. EPU safety pin (ground crew) - Removed.

5. EPU switch-NORM.

6. Intercom (refueling supervisor) - Disconnect.

7. Taxi clear of refueling area and configure

aircraft as required.

QUICK TURNAROUND

PRIOR TO ENGINE SHUTDOWN

1. AFTER LANDING checks - Complete.

2. PRIOR TO ENGINE SHUTDOWN checks -

Complete.

3. Communication with ground crew - Establish

(if required).

4. ENGINE SHUTDOWN checks - Complete.

5. Aircraft setup - IAW local procedures.

SPECIAL PROCEDURES

EPU HYDRAZINE SUPPORT AT NONF16 BASES

At nonF16 bases, the pilot is responsible for the

aircraft. Response actions shall be limited to

identification of a hydrazine or EPU problem,

isolation, containment, and minimal dilution with

water (1 part water to 1 part hydrazine). No major

neutralization, maintenance, or hydrazine servicing

capability is planned for transient bases. If a

hydrazine leak or EPU incident occurs on a base

where no disaster response force or bioenvironmental

support is available, the pilot must insure that the

aircraft is isolated and the leak contained. Refer to

ACTIVATED EPU/HYDRAZINE LEAK, Section III.

SUPPLEMENTAL PROCEDURES

ILS PROCEDURES

1. DED - Verify CNI display.

2. TILS button - Depress and release.

3. ILS frequency - Key in and ENTR.

4. DCS - Position asterisks about selectable

items:

S

Key in and enter inbound localizer course.

The inbound localizer course must be

entered to obtain correct command steer

ing.

S

Depress MSEL button to deselect/select

command steering; verify CMD STRG is

highlighted, if selected.

5. HSI - Set inbound localizer course.

6. INSTR MODE knob - ILS/TCN or ILS/NAV.

Verify proper indications/symbology on

ADI, HSI, and HUD.

EXTERIOR INSPECTION

Refer to figure 24 for normal preflight inspection.

DANGER AREAS

Refer to figures 28 and 29.

TURNING RADIUS AND GROUND

CLEARANCE

Refer to figure 210.

GSUIT HOSE ROUTING

Refer to figure 211 for the recommended gsuit hose

routing.

STRANGE FIELD PROCEDURES

Refer to Air Force/Command Guidance.

T.O. GR1F16CJ1

233

Exterior Inspection (Typical)

NOTE: Check aircraft for loose doors and

fasteners, cracks, dents, leaks, and

other discrepancies.

GR1F-16CJ-1-0100X37

NOSE-A

1. FORWARD FUSELAGE:

A. EXTERNAL CANOPY JETTISON DHANDLES

(2)-ACCESS DOORS CLOSED.

B. PITOTSTATIC PROBES (2)-COVERS

REMOVED.

C. AOA PROBES (2)-COVERS REMOVED;SLOTS

CLEAR;FREEDOM OF MOVEMENT CHECKED;

ALIGNMENT CHECKED (ROTATE PROBES FULLY

TOWARD FRONT OF AIRCRAFT (CCW ON THE

LEFT;CW ON THE RIGHT) AND VERIFY

BOTTOM SLOTS SLIGHTLY AFT OF 6

O'CLOCK AND TOP SLOTS FORWARD);SET

IN NEUTRAL POSITION (BOTTOM SLOT AT 4

O'CLOCK ON THE RIGHT SIDE AND 8

O'CLOCK ON THE LEFT SIDE).

D. STATIC PORTS (2)-CONDITION.
E.

RADOME-SECURE.

F.

ENGINE INLET DUCT-CLEAR.

G. PODS AND PYLONS-SECURE (PREFLIGHT IAW

T.O. GR1F16CJ3411CL1).

H. EPU FIRED INDICATOR-CHECK.
I.

ECS RAM INLET DUCTS-CLEAR.

CENTER FUSELAGE & RIGHT WING-B

1. RIGHT MLG:

A. TIRE, WHEEL, AND STRUT-CONDITION.
B. UPLOCK ROLLER-CHECK.
C. DOOR AND LINKAGE-SECURE.
D. LG SAFETY PIN-INSTALLED.

2. RIGHT WING:

A. HYDRAZINE LEAK DETECTOR-CHECK.
B. EPU NITROGEN BOTTLE-CHARGED (REFER TO

FIGURE 26).

C. EPU OIL LEVEL - CHECK.
D. HYD SYS A QTY AND ACCUMULA

TOR-CHECK.

E.

GUNRNDS COUNTER AND RNDS LIMIT-SET.

F.

EPU EXHAUST PORT-CONDITION.

G. LEF-CONDITION.
H. STORES AND PYLONS-SECURE (PREFLIGHT

IAW T.O. GR1F16CJ3411CL1).

I.

NAV AND FORM LIGHTS-CONDITION.

J.

FLAPERON-CONDITION.

AFT FUSELAGE-C

1. TAIL:

A. ADG-CHECK.
B. CSD OIL LEVEL - CHECK.
C. BRAKE/JFS ACCUMULATORS-CHARGED

(REFER TO FIGURE 25).

D. HOOK-CONDITION AND PIN FREE TO MOVE.
E.

DRAG CHUTE ACCUMULATOR-CHARGED.

F.

VENTRAL FINS, SPEEDBRAKES, HORIZONTAL

TAILS, AND RUDDER-CONDITION.

G. DRAG CHUTE HOUSING-CONDITION.
H. ENGINE EXHAUST AREA-CONDITION.
I.

NAV AND FORM LIGHTS-CONDITION.

J.

VERTICAL TAIL LIGHT-CONDITION.

K. FLCS ACCUMULATORS-CHARGED (REFER TO

FIGURE 27).

L.

JFS DOORS-CLOSED.

LEFT WING & CENTER FUSELAGE-D

1. LEFT WING:

A. FLAPERON-CONDITION.
B. NAV AND FORM LIGHTS-CONDITION.
C. STORES AND PYLONS-SECURE (PREFLIGHT

IAW T.O. GR1F16CJ3411CL1).

D. LEF-CONDITION.
E.

FUEL VENT OUTLET-CLEAR.

F.

HYD SYS B QTY AND ACCUMULA

TOR-CHECK.

2. LEFT MLG:

A. TIRE, WHEEL, AND STRUT-CONDITION.
B. UPLOCK ROLLER-CHECK.
C. DOOR AND LINKAGE-SECURE.
D. LG SAFETY PIN-INSTALLED.
E.

LG PIN CONTAINER-CHECK CONDITION.

3. FUSELAGE:

A. GUN PORT-CONDITION.
B. IFF-CHECK.
C. AVTR-CHECK.
D. DOOR 2317, ENGINE AND EMS GONOGO

INDICATORS-CHECK.

4. UNDERSIDE:

A. NLG TIRE, WHEEL, AND STRUT-CONDITION.
B. NLG TORQUE ARMS - CONNECTED, PIN

SECURE AND SAFETIED.

C. NLG DOOR AND LINKAGE-SECURE.
D. LANDING AND TAXI LIGHTS-CONDITION.
E.

LG/HOOK EMERGENCY PNEUMATIC BOTTLE

PRESSURE-WITHIN PLACARD LIMITS (REFER

TO FIGURE 26). 

Figure 24.

T.O. GR1F16CJ1

234Change 1

Brake/JFS

Accumulators

Pneumatic Servicing

TEMPERATURE

°

F

PRESSURE

PSIG

-44 to -36

14751625

-35 to -27

15251675

-26 to -18

15751725

-17 to -9

16251775

-8 to -1

16751825

0 to 8

17251875

9 to 17

17751925

18 to 26

18251975

27 to 35

18752025

36 to 44

19252075

45 to 53

19752125

54 to 62

20252175

63 to 71

20752225

72 to 80

21252275

81 to 89

21752325

90 to 98

22252375

99 to 107

22752425

108 to 116

23252475

117 to 125

23752525

126 to 135

24252575

Figure 25.

EPU Nitrogen &

Alternate LG/Hook

Bottles Pneumatic

Servicing

TEMPERATURE

°

F

PRESSURE

PSIG

100 and higher

32503500

50 to 100

28503250

10 to 50

25002850

-60 to +10

20002500

Figure 26.

Drag Chute/FLCS

Accumulators

Pneumatic Servicing

TEMPERATURE

°

F

PRESSURE

PSIG

100 and higher

13001400

50 to 100

12001300

10 to 50

11001200

-60 to +10

9501100

Figure 27.

T.O. GR1F16CJ1

Change 1235

GR1F-16CJ-1-0101A37

Danger Areas

0

20

40

60

80

100

120

140

160

180

200

0

10

20

30

40

50

60

70

80

90

100

DISTANCE FROM EXHAUST NOZZLE    FEET

DISTANCE FROM EXHAUST NOZZLE    FEET

JET W

AKE RADIUS    FEET

JET W

AKE RADIUS    FEET

8

4

0

4

8

12

20

10

0

10

20

30

TEMPERATURE

VELOCITY

WITH ENGINE OPERATING, EAR

PROTECTION SHOULD BE WORN

DUE TO HIGH NOISE LEVELS

VELOCITY

TEMPERATURE

25 FT

PLANE OF

ROTATION JFS
PLANE OF ROTATION

ENGINE TURBINE

ENGINE INLET

DANGER AREA

MIL THRUST

MAX AB THRUST

25 FT

ENGINE

0

10

20

30

40

50

60

70

80

90

100

DISTANCE FROM EXHAUST NOZZLE    FEET

JET W

AKE RADIUS    FEET

8

4

0

4

8

12

TEMPERATURE

VELOCITY

IDLE THRUST

ENGINE F110-GE-129

100  F TO 1020 FT

2900  F

2000  F

1000  F

150  F TO 365 FT

200  F TO 224 FT

300  F

120 KTS

180 KTS

1200 KTS

600 KTS

300 KTS

60 KTS TO 276 FT

36 KTS TO 512 FT

600  F

400  F

100  F TO 350 FT

500  F

900  F

300  F

300  F

177 KTS TO 107 FT

295 KTS

592 KTS

1270 KTS

950 KTS

415 KTS

59 KTS TO 400 FT

100  F TO 142 FT

150  F

200  F

300  F

120  F

30 KTS

36 KTS

48 KTS

60 KTS

120 KTS

90 KTS

15 FT

ENGINE INLET

DANGER AREA

300 FT

300 FT

ENGINE INLET

DANGER AREA

TIRES

WITH HOT BRAKES, AVOID INFLATED

MLG TIRE SIDE AREA WITHIN 300 FEET

FOR 45 MINUTES AFTER AIRCRAFT HAS

STOPPED. IF REQUIRED, APPROACH

FROM THE FRONT OR REAR FOR

FIREFIGHTING PURPOSES ONLY.

Figure

 28.(Sheet 1)

T.O. GR1F16CJ1

236

GR1F-16CJ-1-0102X37

Danger Areas

UPPER UHF/IFF

ANTENNA

UPPER TACAN

ANTENNA

VHF ANTENNA

LOWER UHF/IFF ANTENNA

JFS EXHAUST 1175 F

EPU EXHAUST 1600 F

ECS EXHAUST 325 F

LOWER TACAN ANTENNA

RADAR

60

60

RADIATION AND TEMPERATURE

RADAR

60

60

ECM POD

Distance from radar disc to for-

ward tip of radome = 5 feet.
ECM radiation is in a fan

pattern fore and aft.

NOTES:

ENGINE F110-GE-129

FORWARD

RADAR

ALTIMETER

ANTENNA

OPERATING

TRANSMITTERS

MINIMUM SAFE DISTANCE

FROM ANTENNAS IN FEET

VOLATILE FLUIDS

PERSONNEL

EED

UPPER AND LOWER UHF/IFF
UPPER AND LOWER TACAN

VHF

FIRE CONTROL RADAR

AN/ALQ-119
AN/ALQ-131
AN/ALQ-176
AN/ALQ-184
AN/ALQ-188

QRC-80-01

30

1
1
1

120

6

15

6

31

6
6

120

6

15

6
6
6
6

RADAR ALTIMETER

1

INTERNAL ECM

21

1.5

4

Figure

 28.(Sheet 2)

T.O. GR1F16CJ1

237

50

100

150

200

250

FEET

0

10

20

30

40

50

60

70

80

95 dBA

IDLE THRUST

MAX AB THRUST (ESTIMATED)

MIL THRUST (ESTIMATED)

NOISE EXPOSURE LIMITS

1F-16X-1-4031X

80

85

90

95

100

105

110

115

120

125

130

0

1

2

3

4

5

6

7

8

SPL   dBA

DURATION   HOURS EXPOSURE LIMIT PER DAY

NOTES:

Attenuation factors and exposure limits are for typical

ear muffs and earplugs.

SPL   Sound pressure level.

dBA   Adjusted (human ear response) decibels.

1000

800
700
600
500
400
300
200

200
300
400
500
600
700
800

1000

0

30

60

90

120

150

180

LIMIT 15

MINUTES

PER DAY

WITH EAR

PROTECTION

FEET

1000

800

600

400

200

200

400

600

800

1000

0

30

60

90

120

150

180

LIMIT 5

MINUTES

PER DAY

WITH EAR

PROTECTION

FEET

NOTE:

Noise levels are

symmetrical and

may be altered

by surrounding

obstacles.

100 dBA

105 dBA

110 dBA

115

dBA

120

dBA

130 dBA

125 dBA

105 dBA

110

dBA

120

dBA

115 dBA

125

dBA

130 dBA

135 dBA

Danger Areas

ENGINE F110-GE-129

HAZARDOUS NOISE LEVEL AREAS

90

Figure 

28.(Sheet 3)

T.O. GR1F16CJ1

238Change 1

GR1F-16CJ-1-1101A37

Danger Areas

0

20

40

60

80

100

120

140

160

180

200

0

10

20

30

40

50

60

70

80

90

100

8

4

0

4

8

12

20

10

0

10

20

30

TEMPERATURE

VELOCITY

WITH ENGINE OPERATING, EAR

PROTECTION SHOULD BE WORN

DUE TO HIGH NOISE LEVELS

VELOCITY

TEMPERATURE

25 FT

PLANE OF

ROTATION JFS
PLANE OF ROTATION

ENGINE TURBINE

ENGINE INLET

DANGER AREA

MIL THRUST

MAX AB THRUST

25 FT

ENGINE

0

10

20

30

40

50

60

70

80

90

100

8

4

0

4

8

12

TEMPERATURE

VELOCITY

IDLE THRUST

1540 KTS

948 KTS

652 KTS

356 KTS

296 KTS

237 KTS TO 215 FT

178 KTS TO 220 FT

1955 KTS

59 KTS TO 850 FT

119 KTS TO 448 FT

178 KTS TO 118 FT

1300 KTS

711 KTS

474 KTS

59 KTS TO 373 FT

296 KTS

237 KTS

119 KTS TO 155 FT

30 KTS TO 108 FT

148 KTS

119 KTS

89 KTS

59 KTS

ENGINE F100-PW-229

15 FT

ENGINE INLET

DANGER AREA

300 FT

300 FT

ENGINE INLET

DANGER AREA

TIRES

WITH HOT BRAKES, AVOID INFLATED

MLG TIRE SIDE AREA WITHIN 300 FEET

FOR 45 MINUTES AFTER AIRCRAFT HAS

STOPPED. IF REQUIRED, APPROACH

FROM THE FRONT OR REAR FOR

FIREFIGHTING PURPOSES ONLY.

DISTANCE FROM EXHAUST NOZZLE

FEET

3200 F

2200 F

1200 F

800 F

600 F

500 F

100 F TO 1160 FT

200 F TO 470 FT

300 F TO 270 FT

400 F

1000 F

600 F

500 F

400 F

100 F TO 378 FT

200 F TO 110 FT

300 F

DISTANCE FROM EXHAUST NOZZLE

FEET

DISTANCE FROM EXHAUST NOZZLE

FEET

400 F

300 F

250 F

100 F TO 132 FT

200 F

150 F

JET W

AKE RADIUS

FEET

JET W

AKE RADIUS

FEET

JET W

AKE RADIUS

FEET

Figure

 29.(Sheet 1)

T.O. GR1F16CJ1

239

GR1F-16CJ-1-1102X37

Danger Areas

OPERATING

TRANSMITTERS

MINIMUM SAFE DISTANCE

FROM ANTENNAS IN FEET

VOLATILE FLUIDS

PERSONNEL

EED

UPPER AND LOWER UHF/IFF
UPPER AND LOWER TACAN

VHF

FIRE CONTROL RADAR

UPPER UHF/IFF

ANTENNA

UPPER TACAN

ANTENNA

VHF ANTENNA

CENC AIR-MOTOR

EXHAUST 1200 F

LOWER UHF/IFF ANTENNA

JFS EXHAUST 1175 F

EPU EXHAUST 1600 F

ECS EXHAUST 325 F

LOWER TACAN ANTENNA

RADAR

60

60

RADIATION AND TEMPERATURE

RADAR

60

60

ECM POD

Distance from radar disc to forward

tip of radome = 5 feet.

ECM radiation is in a fan

pattern fore and aft.

AN/ALQ-119
AN/ALQ-131
AN/ALQ-176
AN/ALQ-184
AN/ALQ-188

QRC-80-01

NOTES:

21

1
1
1

120

6

15

6

31

6
6

120

6

15

6
6
6
6

ENGINE F100-PW-229

RADAR ALTIMETER

1

FORWARD

RADAR

ALTIMETER

ANTENNA

INTERNAL ECM

30

1.5

4

ECM ANTENNA

ECM ANTENNA

  (EACH SIDE)

Figure

 29.(Sheet 2)

T.O. GR1F16CJ1

240

50

100

150

200

250

FEET

0

10

20

30

40

50

60

70

80

95 dBA

IDLE THRUST

MAX AB THRUST

MIL THRUST

NOISE EXPOSURE LIMITS

1F-16X-1-4030X

80

85

90

95

100

105

110

115

120

125

130

0

1

2

3

4

5

6

7

8

SPL   dBA

DURATION   HOURS EXPOSURE LIMIT PER DAY

NOTES:

Attenuation factors and exposure limits are for typical

earmuffs and earplugs.

SPL   Sound pressure level.

dBA   Adjusted (human ear response) decibels.

LIMIT 15

MINUTES

PER DAY

WITH EAR

PROTECTION

LIMIT 5

MINUTES

PER DAY

WITH EAR

PROTECTION

NOTE:

Noise levels are

symmetrical and

may be altered

by surrounding

obstacles.

Danger Areas

ENGINE F100-PW-229

90

HAZARDOUS NOISE LEVEL AREAS

1000

800

600

400

200

200

400

600

800

1000

0

30

60

90

120

150

180

FEET

101 dBA

106 dBA

112 dBA

117 dBA

117 dBA

112 dBA

107 dBA

102 dBA

1000

800
700
600
500
400
300
200

200
300
400
500
600
700
800

1000

0

30

60

90

120

150

180

FEET

97 dBA

102

dBA

107 dBA

112 dBA

117

dBA

122

dBA

102 dBA

Figure 

29.(Sheet 3)

T.O. GR1F16CJ1

241

GR1F-16CJ-1-0104X37

With large asymmetries, reduce taxi speed,

avoid sharp turns and, when possible, turn

toward heavy wing to prevent possible tipping.

2 FEET

*6 INCHES

4 FEET 6 INCHES

5 FEET

5 FEET

3 FEET

2 FEET

3 FEET 6 INCHES

16 FEET 10 INCHES

R MISSILE

L MISSILE

R TAIL

PROBE

NLG

R MLG

L MLG

NOTES:

Turn radius can be

reduced to 38 feet by

using inside brake.
Maximum NWS deflection.

All distances are

approximate.

Avoid arresting cable

support donuts when

taxiing with centerline

stores installed.

*

Turning Radius and Ground Clearance

39 35

25

18

6

PIVOT POINT

FEET

Figure 210.

T.O. GR1F16CJ1

242

1F-16X-1-0015X

G-Suit Hose Routing (Typical)

TORSO

HARNESS

G-SUIT HOSE

SURVIVAL KIT

STRAP

LAPBELT

CANOPY SILL

REFERENCE

LINE

LEFT CONSOLE

REFERENCE LINE

(SEAT AT MIDHEIGHT)

Figure 211.

T.O. GR1F16CJ1

31

SECTION III

EMERGENCY PROCEDURES

TABLE OF CONTENTS

Page

INTRODUCTION

33

. . . . . . . . . . . . . . . . . . . . . . . . . 

WARNING AND CAUTION LIGHT

AND PILOT FAULT

LIST ANALYSIS

34

. . . . . . . . . . . . . . . . . . . . . . . . 

FORMAT

34

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

GROUND EMERGENCIES

326

. . . . . . . . . . . . . . . . 

Fire/Overheat/Fuel Leak (Ground)

326

. . . . . . . . 

Hot Start (Ground)

326

. . . . . . . . . . . . . . . . . . . . . . 

Hung Start/No Start 

PW 229

326

. . . . . . . . . . . . . 

Hung Start/No Start 

129

GE

326

. . . . . . . . . . . . . 

Engine Autoacceleration (Ground)

326

. . . . . . . . 

Antiskid Malfunction (Ground)

326

. . . . . . . . . . . 

Brake Failure

327

. . . . . . . . . . . . . . . . . . . . . . . . . . . 

Hot Brakes

328

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Main Generator Failure (Ground)

329

. . . . . . . . 

Main and Standby Generator Failure

(Ground)

329

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Emergency Entrance and Crew Rescue

329

. . . . 

Emergency Ground Jettison

329

. . . . . . . . . . . . . . 

Ground Egress

329

. . . . . . . . . . . . . . . . . . . . . . . . . . 

Hot Refueling Emergency

332

. . . . . . . . . . . . . . . . 

Activated EPU/Hydrazine Leak

332

. . . . . . . . . . 

NWS Failure/Hardover

332

. . . . . . . . . . . . . . . . . . 

TAKEOFF EMERGENCIES

333

. . . . . . . . . . . . . . . . 

Delayed Rotation

333

. . . . . . . . . . . . . . . . . . . . . . . . 

Abort

333

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Engine Malfunction on Takeoff

334

. . . . . . . . . . . 

Engine Failure on Takeoff

334

. . . . . . . . . . . . . . . 

AB Malfunction on Takeoff

335

. . . . . . . . . . . . . . . 

Low Thrust on Takeoff or at Low

Altitude (NonAB) 

PW 229

335

. . . . . . . . . . . . . 

Low Thrust on Takeoff or at Low

Altitude (NonAB) 

129

GE

336

. . . . . . . . . . . . . 

Engine Fire on Takeoff

336

. . . . . . . . . . . . . . . . . . 

LG Fails To Retract

336

. . . . . . . . . . . . . . . . . . . . . 

LG Handle Will Not Raise

336

. . . . . . . . . . . . . . . 

Blown Tire on Takeoff

337

. . . . . . . . . . . . . . . . . . . 

INFLIGHT EMERGENCIES

338

. . . . . . . . . . . . . . 

CANOPY Warning Light On

338

. . . . . . . . . . . . . 

Canopy Loss/Penetration in Flight

338

. . . . . . . . 

Drag Chute Deployed in Flight

338

. . . . . . . . . . . 

Cockpit Pressure/Temperature

Malfunction

339

. . . . . . . . . . . . . . . . . . . . . . . . . . 

EQUIP HOT Caution Light

340

. . . . . . . . . . . . . . 

Ejection

340

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Ejection (Immediate)

341

. . . . . . . . . . . . . . . . . . 

Ejection (Time Permitting)

341

. . . . . . . . . . . . 

Failure of Canopy To Separate

341

. . . . . . . . . 

Ejection Seat Failure

343

. . . . . . . . . . . . . . . . . . 

Ditching

343

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Electrical System Failures

343

. . . . . . . . . . . . . . . 

FLCS PMG Failure

343

. . . . . . . . . . . . . . . . . . . 

Single Generator Failures

(in Flight)

343

. . . . . . . . . . . . . . . . . . . . . . . . . 

Main and Standby Generator 

Failure (in Flight)

344

. . . . . . . . . . . . . . . . . . 

Main, Standby, and EPU Generator

Failure

345

. . . . . . . . . . . . . . . . . . . . . . . . . . . . 

EPU Malfunctions

347

. . . . . . . . . . . . . . . . . . . . 

Uncommanded EPU Operation

347

. . . . . . 

Abnormal EPU Operation

348

. . . . . . . . . . . 

FLCS RLY Light

349

. . . . . . . . . . . . . . . . . . . . . . 

Partial Electrical Power Loss

349

. . . . . . . . . . 

Aircraft Battery Failure

350

. . . . . . . . . . . . . . . 

Emergency Power Distribution

351

. . . . . . . . . 

Engine Malfunctions 

PW 229

361

. . . . . . . . . . . . . 

Engine Fire 

PW 229

361

. . . . . . . . . . . . . . . . . . . 

OVERHEAT Caution Light 

PW 229

362

. . . . 

Engine Vibrations 

PW 229

363

. . . . . . . . . . . . . 

Oil System Malfunction 

PW 229

363

. . . . . . . . 

ENGINE FAULT Caution 

Light 

PW 229

364

. . . . . . . . . . . . . . . . . . . . . . 

SEC Caution Light 

PW 229

364

. . . . . . . . . . . . 

FTIT Indicator Failure 

PW 229

365

. . . . . . . . 

Zero RPM/Erroneous RPM 

Indication 

PW 229

365

. . . . . . . . . . . . . . . . . . 

Abnormal Engine Response 

PW 229

365

. . . . 

Nozzle Failure 

PW 229

367

. . . . . . . . . . . . . . . . 

AB Blowout/Failure To 

Light 

PW 229

368

. . . . . . . . . . . . . . . . . . . . . . 

T.O. GR1F16CJ1

32

Engine Stalls 

PW 229

368

. . . . . . . . . . . . . . . . . . . . 

ABAssociated Engine 

Stalls 

PW 229

369

. . . . . . . . . . . . . . . . . . . . . . 

NonAB Engine Stalls 

PW 229

369

. . . . . . . . . 

Engine Stall Recovery 

PW 229

369

. . . . . . . . . 

Inlet Buzz 

PW 229

370

. . . . . . . . . . . . . . . . . . . . . . 

Engine Failure or Flameout 

PW 229

370

. . . . . . 

Tower Shaft Failure 

PW 229

370

. . . . . . . . . . . 

Low Altitude Engine Failure or

Flameout 

PW 229

371

. . . . . . . . . . . . . . . . . . 

Airstarts 

PW 229

371

. . . . . . . . . . . . . . . . . . . . . . . . 

High Altitude Airstart

Considerations 

PW 229

378

. . . . . . . . . . . . . 

Low Altitude Airstart 

Considerations 

PW 229

379

. . . . . . . . . . . . . 

Airstart Procedures 

PW 229

379

. . . . . . . . . . . 

Engine Malfunctions 

129

GE

381

. . . . . . . . . . . . . 

Engine Fire 

129

GE

381

. . . . . . . . . . . . . . . . . . . 

OVERHEAT Caution Light 

129

GE

382

. . . . 

Oil System Malfunction 

129

GE

383

. . . . . . . . 

ENGINE FAULT Caution 

Light 

129

GE

384

. . . . . . . . . . . . . . . . . . . . . . 

SEC Caution Light 

129

GE

384

. . . . . . . . . . . . 

FTIT Indicator Failure 

129

GE

385

. . . . . . . . 

Zero RPM/Erroneous RPM 

Indication 

129

GE

385

. . . . . . . . . . . . . . . . . . 

Abnormal Engine Response 

129

GE

386

. . . . 

AB Blowout/Failure To 

Light 

129

GE

387

. . . . . . . . . . . . . . . . . . . . . . 

Engine Stalls 

129

GE

388

. . . . . . . . . . . . . . . . . . . . 

ABAssociated Engine Stalls 

129

GE

388

. . . 

NonAB Engine Stalls 

129

GE

388

. . . . . . . . . 

Engine Stall Recovery 

129

GE

389

. . . . . . . . . 

Inlet Buzz 

129

GE

389

. . . . . . . . . . . . . . . . . . . . . . 

Bird Strike 

129

GE

389

. . . . . . . . . . . . . . . . . . . . . . 

Engine Overspeed 

129

GE

389

. . . . . . . . . . . . . . . 

Engine Failure or Flameout 

129

GE

389

. . . . . . 

Tower Shaft Failure 

129

GE

390

. . . . . . . . . . . 

Low Altitude Engine Failure or

Flameout 

129

GE

390

. . . . . . . . . . . . . . . . . . 

Airstarts 

129

GE

390

. . . . . . . . . . . . . . . . . . . . . . . . 

High Altitude Airstart

Considerations 

129

GE

395

. . . . . . . . . . . . . 

Low Altitude Airstart

Considerations 

129

GE

396

. . . . . . . . . . . . . 

Airstart Procedures 

129

GE

396

. . . . . . . . . . . 

Flameout Landing

398

. . . . . . . . . . . . . . . . . . . . . . 

Overhead Approach

399

. . . . . . . . . . . . . . . . . . . 

StraightIn Approach

3100

. . . . . . . . . . . . . . . . 

IMC Penetration

3100

. . . . . . . . . . . . . . . . . . . . . 

Landing Phase

3105

. . . . . . . . . . . . . . . . . . . . . . 

After Touchdown

3105

. . . . . . . . . . . . . . . . . . . . 

Flameout Landing Procedures

3105

. . . . . . . . 

Jettison

3107

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Selective Jettison

3107

. . . . . . . . . . . . . . . . . . . . 

Emergency Jettison

3108

. . . . . . . . . . . . . . . . . . 

FLCS Failures

3108

. . . . . . . . . . . . . . . . . . . . . . . . . 

Air Data Malfunctions

3108

. . . . . . . . . . . . . . . 

AOA Malfunction

3109

. . . . . . . . . . . . . . . . . . . . 

CADC Malfunction

3110

. . . . . . . . . . . . . . . . . . 

Servo Malfunction

3110

. . . . . . . . . . . . . . . . . . . 

FLCS Electronic Malfunctions

3110

. . . . . . . . 

FLCS Single Electronic Failure

3111

. . . . . 

FLCS Dual Electronic Failure

3111

. . . . . . 

FLCS Temperature Malfunction

3112

. . . . . . 

Autopilot Malfunctions

3112

. . . . . . . . . . . . . . . 

DBU ON Warning Light

3113

. . . . . . . . . . . . . . 

TF FAIL Warning Light

3113

. . . . . . . . . . . . . . 

LEF Malfunction (Symmetric)

3114

. . . . . . . . 

LEF Malfunction (Asymmetric)

3115

. . . . . . . 

Trim Malfunction

3116

. . . . . . . . . . . . . . . . . . . . 

Stick Interference

3116

. . . . . . . . . . . . . . . . . . . . 

Fuel Malfunctions

3117

. . . . . . . . . . . . . . . . . . . . . . 

Fuel Management System PFL

3117

. . . . . . . 

Fuel Leak

3117

. . . . . . . . . . . . . . . . . . . . . . . . . . . 

Fuel Low

3118

. . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Hot Fuel/Oil or Gravity Feed

3118

. . . . . . . . . . 

Fuel Imbalance

3119

. . . . . . . . . . . . . . . . . . . . . . 

Trapped External Fuel

3121

. . . . . . . . . . . . . . . 

Trapped CFT Fuel 

PX III

3122

. . . . . . . . . . . . . 

Hydraulic Malfunctions

3123

. . . . . . . . . . . . . . . . . 

Single Hydraulic Failure

3123

. . . . . . . . . . . . . 

System A Failure

3123

. . . . . . . . . . . . . . . . . . 

System B Failure

3123

. . . . . . . . . . . . . . . . . . 

Dual Hydraulic Failure

3124

. . . . . . . . . . . . . . 

System B and Generator Failure

(PTO Shaft)

3125

. . . . . . . . . . . . . . . . . . . . . . . 

EGI Failure 

PX III

3126

. . . . . . . . . . . . . . . . . . . . . 

INS Failures 

PX II

3127

. . . . . . . . . . . . . . . . . . . . . 

Total INS Failure 

PX II

3128

. . . . . . . . . . . . . . . 

OutofControl Recovery

3128

. . . . . . . . . . . . . . . . 

Oxygen Malfunction 

PX II

3130

. . . . . . . . . . . . . . 

OBOGS Malfunction 

PX III

3131

. . . . . . . . . . . . . 

PBG Malfunction

3131

. . . . . . . . . . . . . . . . . . . . . . 

Smoke or Fumes

3131

. . . . . . . . . . . . . . . . . . . . . . . 

T.O. GR1F16CJ1

33

LANDING EMERGENCIES

3132

. . . . . . . . . . . . . . . 

Straightin Landing

3132

. . . . . . . . . . . . . . . . . . . . 

Simulated Flameout (SFO) Landing

3132

. . . . . 

Controllability Check

3133

. . . . . . . . . . . . . . . . . . . 

Cable Arrestment

3134

. . . . . . . . . . . . . . . . . . . . . . 

Net Arrestment

3135

. . . . . . . . . . . . . . . . . . . . . . . . 

Landing With A Blown Tire

3135

. . . . . . . . . . . . . 

Landing With A Blown Main Gear

Tire

3136

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Landing With A Blown Nose Gear

Tire

3136

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

LG Extension Malfunctions

3137

. . . . . . . . . . . . . 

LG Handle Will Not Lower

3137

. . . . . . . . . . . 

LG Fails To Extend

3138

. . . . . . . . . . . . . . . . . . 

Alternate LG Extension

3139

. . . . . . . . . . . . . . 

Landing With LG Unsafe/Up

3140

. . . . . . . . . 

Antiskid Malfunction (Landing)

3140

. . . . . . . . . 

Asymmetric Stores (Landing)

3141

. . . . . . . . . . . 

NLG WOW Switch Failure

3145

. . . . . . . . . . . . . . 

Drag Chute Failure

3145

. . . . . . . . . . . . . . . . . . . . 

INTRODUCTION

This section covers the operation of the aircraft

during emergency/abnormal conditions. It includes a

discussion of problem indications and corrective

actions as well as procedural steps when applicable.

Adherence to these guidelines insures maximum

safety for the pilot and/or aircraft. The situations

covered are representative of the most probable

malfunctions. However, multiple emergencies, ad

verse weather, or other factors may require

modification of the recommended procedures. Only

those steps required to correct or manage the problem

should be accomplished. When dealing with emergen

cy/abnormal conditions, it is essential to determine

the most correct course of action by using sound

judgment and a full understanding of the applicable

system(s). When practical, other concerned agencies

(i.e., flight lead, tower, etc.) should be advised of the

problem and intended course of action.

When a voice WARNING or CAUTION message is

heard, check cockpit indications; then refer to the

appropriate emergency procedure for corrective

action.

When structural damage or any other failure that

may adversely affect aircraft handling characteris

tics is known or suspected, a controllability check

should be performed.

Certain steps (e.g., MASTER CAUTION reset, ELEC

CAUTION reset) are intentionally omitted from the

numbered procedures. Pilots are expected to perform

these actions without prompting, when warranted.

Three basic rules, which apply to all emergencies, are

established:

1.

MAINTAIN AIRCRAFT CONTROL.

2.

ANALYZE THE SITUATION AND TAKE

PROPER ACTION.

3.

LAND AS THE SITUATION DICTATES.

The following information provides general landing

guidance:

Land As Soon As Possible

An emergency will be declared. A landing should be

accomplished at the nearest suitable airfield

considering the severity of the emergency, weather

conditions, airfield facilities, lighting, aircraft GW,

and command guidance.

Land As Soon As Practical

Emergency conditions are less urgent and, although

the flight is to be terminated, the degree of the

emergency is such that an immediate landing at the

nearest suitable airfield may not be necessary.

F

The canopy should remain closed

during all emergencies that could

result in a crash or fire such as crash

landings, aborted takeoffs, and arrest

ments. The protection the canopy

affords far outweighs the isolated risk

of entrapment due to a canopy

malfunction or overturn.

F

Ejection is preferable to sliding into an

arrestment cable with the NLG col

lapsed. The cable may slide up over the

nose with unpredictable and poten

tially dangerous consequences to any

one in the cockpit(s).

T.O. GR1F16CJ1

34

F

If it appears that the aircraft will

depart a prepared surface above

normal taxi speed during an aborted

takeoff or a landing and goaround is

not possible, eject since breakup of

cockpit structure may occur. Retract

ing the LG to prevent departure from a

prepared surface is not recommended

since the MLG will probably not

retract symmetrically.

F

If remaining with an aircraft that will

depart a prepared surface, shut down

the engine, if feasible. This action

reduces the potential for fire, reduces

engine damage, and permits EPU

turnoff if an MLG WOW signal is lost.

WARNING AND CAUTION LIGHT

AND PILOT FAULT LIST ANALYSIS

Refer to figures 31, 32, and 33 for analysis and

amplification of warning and caution light and Pilot

Fault List procedures. Fault trees show interrela

tionships with examples of problem events and

corrective action.

FORMAT

The format of Emergency Procedures differs slightly

between the Checklist and the Flight Manual.

Procedures in the Checklist have been grouped by

malfunction category (engine, electrical, etc.) to

provide maximum inflight utility. In the Flight

Manual, procedures are listed by the phase of flight

in which the emergency may occur. In the Checklist,

some procedures are split into two independent

sidebyside series of steps and are separated by a

straight line; in the Flight Manual, these sideby

side steps appear in a continuous column and can be

identified by repeat numbering of steps following

conditional statements beginning with the word if.

Amplification following procedural steps in the

Flight Manual is repeated in the Checklist under the

heading Inoperative Equipment, Other Indications,

or Other Considerations. A thorough review of the

layout and content of the Checklist and Flight

Manual is recommended prior to inflight use.

T.O. GR1F16CJ1

35

GR1F-16CJ-1-0106X37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

PROBABLE

MALFUNCTION

IN FIRE DETECT

SYSTEM

THROTTLE TO

MINIMUM PRAC-

TICAL THRUST

ENGINE FIRE

PERSISTS

Are there

other signs of fire?

(Visual, FTIT, OVERHEAT

Caution Light, Engine

Response, etc.)

YES

LAND AS SOON AS POSSIBLE

EJECT

NOTES:

Refer to:

GROUND EMERGENCIES.

GROUND EGRESS.

ENGINE FIRE.

EJECTION.

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

BELOW 10,000 FEET

MSL, <190 KNOTS

AND AT LEAST 250

FPM DESCENT

BELOW 10,000 FEET

MSL, <190 KNOTS

AND AT LEAST 250

FPM DESCENT

Are all

WHEELS down

lights green?

ONE OR

MORE

GREEN

LIGHTS

NOT ON

3 GREEN

LIGHTS

INCREASE AIRSPEED, DECREASE

SINK RATE, OR PLACE LG

HANDLE   DN

ABORT AIRCRAFT

TEF'S NOT FULLY

DOWN

TEF'S NOT FULLY

DOWN

AIR

GND

AIR

YES

NO

SEE B

SEE A

ENG FIRE

ENG FIRE

CONFIG

TO/LDG

CONFIG

TO/LDG

Engine compartment fire

Refer to ENGINE FIRE

NO

A.

For in-flight LG problems, refer to

LANDING EMERGENCIES

If TEF's do not extend, execute land-

ing using normal AOA (approximately

20 knots faster than normal)

Aircraft configuration wrong for

takeoff or landing

Any of the following:

1. LG not down and locked

2. TEF's not fully down

B.

LG/TEF'S NOT

DOWN *

ANY/ALL LG NOT

DOWN AND

LOCKED **

** NOTES:

LG warning horn

sounds.

LG Handle   DN

(Malfunction)

LG Handle   UP

(No Malfunction)

* NOTE:

LG warning horn sounds.

LG handle warning

light illuminates.

Figure 31.(Sheet 1)