F16C/D. FLIGHT MANUAL (2002)

T.O. GR1F16CJ1CL2

*Engine at idle and check:

5. JFS switch-Confirm OFF.

6. HYD/OIL PRESS warning light-Off.

7. FUEL FLOW-5001500.

8. OIL pressure-15 psi (minimum).

9. NOZ POS-Greater than 80 percent.

10. RPM-6577 percent.

11. FTIT-625

C or less.

12. HYD PRESS A & B-28503250 psi.

13. Six fuel pump lights (ground crew)-On.

14. Main fuel shutoff valve (ground crew)-Check.

15. JFS doors (ground crew)-Verify closed.

16. Throttle cutoff release-Check.

AFTER ENGINE START

1. TEST switch panel - Check.

a. PROBE HEAT switch - PROBE HEAT.

b. PROBE HEAT switch - TEST.

c. PROBE HEAT switch - OFF.

d. FIRE & OHEAT DETECT button - Test.

e. MAL & IND LTS button - Test.

2. AVIONICS POWER panel - Set.

a. MMC switch - MMC.

b. ST STA switch - ST STA.

c. MFD switch - MFD.

d. UFC switch - UFC.

e. GPS TRK switch - GPS TRK.

(Cont)

T.O. GR1F16CJ1CL2

3. EGI - Align after display visible on the DED.

4. SNSR PWR panel:

a. LEFT HDPT switch - OFF, unless required.

b. RIGHT HDPT switch - As required.

c. FCR switch - FCR.

d. RDR ALT switch - RDR ALT.

*5. HUD/ASHM - As desired.

6. C & I knob - UFC.

7. MFL - Clear.

8. SEC - Check after the engine has run at idle for

at least 30 seconds. May be delayed until the

BEFORE TAKEOFF checklist.

9. Flight controls - Cycle.

10. FLCS BIT - Initiate and monitor.

11. ECM panel - As required.

12. SPD BRK switch - Cycle.

*13. WHEELS down lights - Three green.

*14. SAI - Set.

15. FUEL QTY SEL knob - Check.

16. EPU FUEL quantity - 95102 percent.

17. Avionics - Program as required and verify

(manual or data transfer cartridge).

*18. MFD's - As desired.

19. VHF radio - As desired.

After FLCS BIT completed:
*20. DBU - Check:

a. DIGITAL BACKUP switch - BACKUP.

b. Operate controls - All surfaces respond

normally.

c. DIGITAL BACKUP switch - OFF.

21. Trim - Check.

(Cont)

T.O. GR1F16CJ1CL2

*22.

FLCS override - Check.

*23. MPO - Check.

*24. Operate controls-All surfaces respond nor

mally; no FLCS lights on.

*25. AR system (if required)-Check.

*26. Brakes-Check both channels; then return to

CHAN 1.

27. Antiice-Check.

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

29. EPU switch-OFF.

30. Ground safety pins (ground crew)-Remove.

31. EPU switch-NORM.

32. Intercom (ground crew)-Disconnect.

33. Avionic BIT's-As desired.

34.

Seat-Adjust to design eye.

35. OBOGS-Check (at least 2 minutes after engine

start).

BEFORE TAXI

1. Canopy-Close and lock.

2. HAVE QUICK radio-Set and check (if

required).

*3. Altimeter and altitude indications-Set and

check.

4. Exterior lights-As required.

5. EGI knob-NAV.

6. Chocks (ground crew)-Remove.

TAXI

*1. Brakes and NWS-Check.

*2. Heading-Check.

*3. Flight instruments-Check for proper operation.

T.O. GR1F16CJ1CL2

BEFORE TAKEOFF

*1. ALT FLAPS switch-NORM.

2. MANUAL TF FLYUP switch-ENABLE.

3. Trim-Check pitch and yaw trim centered and

roll trim as required. Refer to figure N1, page

N7.

ENG CONT switch-PRI (guard down).

ENG CONT switch-NORM (guard down).

6. Speedbrakes-Closed.

7. Canopy-Close, lock, light off.

8. IFF-Set and check.

9. External tanks (if installed)-Verify feeding.

10. FUEL QTY SEL knob-NORM.

11. STORES CONFIG switch-As required.

*12. GND JETT ENABLE switch-As required.

*13. Harness, leads, and antig system-Check.

14. EPU-Check.

15. FLIR-As required.

16. TFR-As required.

17. PROBE HEAT switch-PROBE HEAT.

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

*19. Flight controls-Cycle.

*20. OIL pressure-Check psi.

*21. ALOW MSL FLOOR Data-Check.

*22. All warning and caution lights-Check.

23. Adjustable sliding holder (when utility light is

not in use)-

Full forward, rotated cw, and

secured.

24. TGP-Stow.

T.O. GR1F16CJ1CL2

1F-16X-1CL-1-0003X

120

4/6

TAKEOFF SPEED KIAS

STORE ST

TION

Takeoff Roll Trim With Asymmetric Stores

DATA BASIS FLIGHT TEST

CONFIGURATION:

LEF'S SCHEDULED

TEF'S AT 20 DEGREES

NOTES:

INCREASE TAKEOFF SPEED 2 KTS FOR EACH DOT OF

ROLL TRIM APPLIED TO COMPENSATE FOR REDUCED

LIFT. TAKEOFF DISTANCE INCREASES PROPORTION-

IT IS POSSIBLE TO EXCEED THE LATERAL TRIM AU-

THORITY OF THE AIRCRAFT FOR ONSPEED TAKEOFF

WITH A NET ASYMMETRIC (ROLLING) MOMENT LESS

THAN AIRCRAFT TAKEOFF LIMITS.

140

160

180

200

3/7

2/8

FULL

BASELINE

DOTS OF ROLL TRIM

ATELY TO THE SPEED INCREASE.

Figure N1.

T.O. GR1F16CJ1CL2

1F-16X-1CL-1-0004A

Takeoff and Landing Crosswind Limits

NOTES:

HEADWIND COMPONENTS KNOTS

CROSSWIND COMPONENTS KNOTS

CROSSWIND LIMITS FOR RCR VALUES 423 MAY BE

OBTAINED BY INTERPOLATING BETWEEN THE LIMITS

SHOWN.
ENTER CHART WITH STEADY WIND TO DETERMINE

HEADWIND COMPONENT AND WITH MAXIMUM GUST

VELOCITY TO DETERMINE CROSSWIND COMPONENT.

Figure N2.

T.O. GR1F16CJ1CL2

N10

CLIMB/INFLIGHT/OPERATIONAL

CHECKS

1. Fuel-Check quantity/transfer/balance.

2. FUEL QTY SEL knob-NORM.

3. Oxygen system-Check.

4. Cockpit pressurization-Check.

5. Engine instruments-Check.

DESCENT/BEFORE LANDING

1. Fuel-Check quantity/transfer/balance.

2. Final approach airspeed-Compute.

3. DEFOG lever/cockpit heat-As required.

4. Landing light-On.

*5. Altimeter and altitude indications-Check al

timeter setting, ELECT versus PNEU mode

altimeter readings, and ELECT mode altitude

versus altitude displayed in HUD.

*6. Attitude references-Check ADI/HUD/SAI.

7. ANTI ICE switch-As required.

8. TGP-Stow.

AFTER LANDING

1. DRAG CHUTE switch-NORM/REL as re

quired.

2. PROBE HEAT switch-OFF.

3. ECM power-Off.

4. Speedbrakes-Close.

*5. Ejection safety lever-Safe (up).

6. IFF MASTER knob-STBY.

7. IFF M4 CODE switch-HOLD.

8. LANDING TAXI lights-As required.

9. ZEROIZE switch-As required.

10. Canopy handle-Up.

11. Armament switches-Off, safe, or normal.

PRIOR TO ENGINE SHUTDOWN

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

2. EGI-Check.

3. MFL-Record (as required).

4. AVTR power switch-UNTHRD.

5. C & I knob-BACKUP.

6. EGI knob-OFF.

7. Avionics-OFF.

T.O. GR1F16CJ1CL2

N11

ENGINE SHUTDOWN

1. Throttle - OFF.

2. JFS RUN light - Check.

After main generator drops off line:

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

4. MAIN PWR switch - OFF.

5. Oxygen hose, survival kit straps, lapbelt, gsuit

hose, and vest hose-Disconnect, stow.

6. OXYGEN REGULATOR-OFF and 100%.

7. Canopy - Open.

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.

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.

8. EGI knob - STOR HDG.

9. FLCS BIT - Accomplish.

10. MFD's - As desired.

(Cont)

T.O. GR1F16CJ1CL2

N12

11. SMS - As desired.

*12. HUD/ASHM - As required.

13. EGI knob - NAV.

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

15. EPU - Check (if EPU safety pin was installed

since last EPU check).

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

PRIOR TO HOT PIT ENTRY

1. AFTER LANDING checks - Complete.

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

*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.

4. Brake and tire inspection (ground crew) -

Complete.

5. Intercom with refueling supervisor - Established.

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.

T.O. GR1F16CJ1CL2

N13

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.

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.

5. HSI-Set inbound localizer course.

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

EXTERIOR INSPECTION

Refer to figure N3, page N14.

AIRCRAFT SERVICING

Refer to figure N7, page N19.

TAKEOFF AND LANDING DATA CARD

Refer to figure N8, page N20.

STRANGE FIELD PROCEDURES

Refer to Air Force/Command guidance.

T.O. GR1F16CJ1CL2

N14

Exterior Inspection (Typical)

NOTE: Check aircraft for loose doors and fasteners,

cracks, dents, leaks, and other discrepancies.

GR1F-16CJ-1CL-1-0003X37

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;ALIGN

MENT 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.

Figure N3.(Sheet 1)

T.O. GR1F16CJ1CL2

N15

Exterior Inspection (Typical)

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 FIG

URE N5).

C. EPU OIL LEVEL - CHECK.
D. HYD SYS A QTY AND ACCUMULATOR-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 N4).

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. DRAG CHUTE/FLCS ACCUMULATORS-CHARGED

(REFER TO FIGURE N6).

L. JFS DOORS-CLOSED.

Figure N3.(Sheet 2)

T.O. GR1F16CJ1CL2

N16

Exterior Inspection (Typical)

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 ACCUMULATOR - 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 PRES

SURE - WITHIN PLACARD LIMITS (REFER TO FIG

URE N5).

Figure N3.(Sheet 3)

T.O. GR1F16CJ1CL2

N17

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 N4.

T.O. GR1F16CJ1CL2

N18

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 N5.

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 N6.

T.O. GR1F16CJ1CL2

N19

Aircraft Servicing

SERVICEABLE ITEM

SPECIFICATIONS

SERVICEABLE ITEM

USAF

NATO

FUEL

ENGINE/JFS

MILT5624, JP4
MILT5624, JP5

MILT83133, JP8

F40
F43 OR
F44
F34

FUEL

ENGINE/JFS

MIL T 83133, JP 8
JET A, B
(COMMERCIAL)
JET A1
(COMMERCIAL)

F 34
NONE

F35

OIL

ENGINE

MILL7808J OR
LATER

0148

OIL

ADG/CSD/EPU

MILL7808

0148

HYDRAULIC
FLUID

HYDRAULIC SYS
TEMS A AND B

MILH5606
MILH83282

H515
H537

OXYGEN

GASEOUS

MILO27210,
TYPE I

NONE

EXTERNAL ELEC
TRICAL POWER

115 (

15) VAC,

400 (

30) HZ

A/M32A60A

NONE

NITROGEN

GASEOUS

BBN441A, TYPE I,
GRADE B

NONE

FUEL TANK
INERTING
AGENT
(OPTIONAL)

LIQUID

HALON 1301

NONE

MONOPROPEL
LANT (EPU)

LIQUID

HYDRAZINE (70%
N

, 30% H

NONE

IF NECESSARY, ENGINE LUBRICATING OILS MILL7808 (NATO CODE 0148)

AND MILL23699 (NATO CODE 0156) MAY BE MIXED. AT THE FIRST

OPPORTUNITY THEREAFTER, THE OIL SHALL BE DRAINED AND FLUSHED, AND

THE ENGINE SERVICED WITH THE PROPER LUBRICATING OIL AS SPECIFIED IN

THE APPLICABLE ENGINE TECHNICAL ORDERS.

Figure N7.

F16C/D. FLIGHT MANUAL (2002) - page 34

F16C/D. FLIGHT MANUAL (2002) - page 34