F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002)

T.O. GR1F16CJ1

230Change 1

Failure to position the oxygen regula

tor to OFF and 100% may result in

particulate contamination of the regu

lator and subsequent damage.

To avoid damage to the oxygen

regulator, do not pull the knob on the

end of the mode lever when moving the

mode lever from ON to OFF.

7. Canopy-Open.

If winds exceed 30 knots, open the

canopy only as far as needed to enter/exit

the cockpit. Decreasing the canopy angle

reduces the possibility that the canopy

can be blown past full open.

A failure of the canopy actuator

could allow the canopy to fall during

transit. Keep hands and arms out of

the path of canopy travel during

opening or closing.

NOTE

If the internal canopy switch is left in

the up position, the canopy automati

cally opens if closed from the outside.

SCRAMBLE

PREFLIGHT

Perform the following preflight inspections prior to

placing the aircraft on quick response status:

1. EXTERIOR INSPECTION.

2. BEFORE ENTERING COCKPIT.

3. COCKPIT INTERIOR CHECK.

4. BEFORE STARTING ENGINE.

5. STARTING ENGINE.

6. AFTER ENGINE START (include EPU check

but do not remove MLG ground safety pins).

7. Aircraft cocked for scramble-Per local

policies and directives.

AIRCRAFT ON QUICK RESPONSE STATUS

If the above actions were not completed prior to

scramble, normal preflight procedures should be

used.

1. FLCS power-Check.

With MAIN PWR switch in BATT, verify

that FLCS power is good (FLCS PWR lights)

with the aircraft battery.

2. MAIN PWR switch-MAIN PWR.

3. Engine-Start.

4. Canopy-Close and lock.

5. Instruments-Check.

6. SNSR PWR switches-As required.

7. AVIONICS POWER switches-As required.

PX II

INS,

PX III

EGI knob-STOR HDG.

NOTE

Prior to aligning the INS/EGI using a

stored heading alignment, accomplish

a normal alignment, except turn the

PX II

INS,

PX III

EGI knob to OFF from

NORM (prior to power being removed),

and do not move the aircraft.

9. FLCS BIT-Accomplish.

10. MFD's-As desired.

11. SMS-As desired.

*12. HUD/ASHM-As required.

13.

PX II

INS,

PX III

EGI knob-NAV.

A full performance NORM gyrocom

pass ground alignment, or

PX II

extended interrupted alignment (EIA)

with flashing RDY/ALIGN display

should be performed prior to flying any

terrain following mission. If degraded

alignment occurs, terrain following is

prohibited.

T.O. GR1F16CJ1

231

NOTE

When positioning the

PX II

INS,

PX III

EGI knob from STOR HDG to NAV, do

not hesitate in NORM or the alignment

will be lost.

If time permits, the

PX II

INS,

PX III

EGI knob can be moved to NORM at

any time for a normal alignment.

14. EPU GEN and EPU PMG lights-Confirm

off.

If either light is illuminated, cycle the EPU

switch to OFF, then back to NORM. If either

light stays on, abort the aircraft.

If either light is illuminated, the EPU

activates using hydrazine when the

EPU safety pin is removed.

15. EPU-Check (if EPU safety pin was

installed since last EPU check).

If the EPU safety pin is reinstalled for

any reason, the EPU check must be

reaccomplished prior to flight to insure

proper EPU operation.

16. Chocks and safety pins (ground crew) -

Remove.

*17. Brakes and NWS-Check.

*18. Ejection safety lever-Armed (down).

*19. Flight control surfaces-Cycle.

20. IFF-As required.

HOT REFUELING

HOT REFUELING PRECAUTIONS

Perform dearming prior to entry to the hot refueling

pit. If suspected hot brakes or other unsafe

condition exists, do not enter refueling area. Follow

ground crew directions into the refueling area and

establish communications with the ground crew. If

a malfunction is suspected, stop refueling.

Hot refueling is prohibited with an activated EPU,

hung ordnance, hot brakes, or fuel leakage in

vicinity of AR receptacle during AR. Safety pins for

stores and gun must be installed. In the refueling

area, use minimum thrust for taxiing.

PRIOR TO HOT PIT ENTRY

1. AFTER LANDING checks-Complete.

2. AIR REFUEL switch-OPEN; RDY light on.

NOTE

With the AR switch in OPEN, NWS

can be engaged or disengaged from

either cockpit regardless of the posi

tion of the STICK CONTROL switch

and without using the paddle switch.

With the AR switch in OPEN, the

AR/NWS light remains off whenever

NWS is engaged.

*3. TACAN power knob-OFF.

*4. GND JETT ENABLE switch-OFF.

PRIOR TO HOT REFUELING

Perform the following actions prior to refueling:

1. EPU safety pin (ground crew)-Installed.

*2. Personal equipment leads (except oxygen

and communication)-As desired.

3. Canopy-As desired.

Insure all cockpit items are secure

prior to opening the canopy. With the

canopy open, the engine is susceptible

to FOD from loose cockpit items.

4. Brake and tire inspection (ground crew) -

Complete.

5. Intercom with refueling supervisor - Estab

lished.

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:

Key in and enter inbound localizer course.

The inbound localizer course must be

entered to obtain correct command steer

ing.

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.

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.

GUNRNDS COUNTER AND RNDS LIMIT-SET.

EPU EXHAUST PORT-CONDITION.

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

IAW T.O. GR1F16CJ3411CL1).

NAV AND FORM LIGHTS-CONDITION.

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.

VENTRAL FINS, SPEEDBRAKES, HORIZONTAL

TAILS, AND RUDDER-CONDITION.

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

NAV AND FORM LIGHTS-CONDITION.

VERTICAL TAIL LIGHT-CONDITION.

K. FLCS ACCUMULATORS-CHARGED (REFER TO

FIGURE 27).

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.

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

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

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

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

100

120

140

160

180

200

100

DISTANCE FROM EXHAUST NOZZLE FEET

JET W

AKE RADIUS FEET

JET W

AKE RADIUS FEET

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

100

DISTANCE FROM EXHAUST NOZZLE FEET

JET W

AKE RADIUS FEET

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

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

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

RADIATION AND TEMPERATURE

RADAR

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

1
1
1

120

6
6

120

6
6
6
6

RADAR ALTIMETER

INTERNAL ECM

1.5

Figure

28.(Sheet 2)

T.O. GR1F16CJ1

237

100

150

200

250

FEET

95 dBA

IDLE THRUST

MAX AB THRUST (ESTIMATED)

MIL THRUST (ESTIMATED)

NOISE EXPOSURE LIMITS

1F-16X-1-4031X

100

105

110

115

120

125

130

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

120

150

180

LIMIT 15

MINUTES

PER DAY

WITH EAR

PROTECTION

FEET

1000

800

600

400

200

400

600

800

1000

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

Figure

28.(Sheet 3)

F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002) - page 34

F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002) - page 34