Content .. 14 15 16 17 ..

F16C/D. FLIGHT MANUAL (2002) - page 16

T.O. GR1F16CJ1

1226

Servicing Diagram (Typical)

SERVICEABLE ITEM

SPECIFICATIONS

SERVICEABLE ITEM

USAF

NATO

FUEL

ENGINE/JFS

MILT5624, JP4
MILT5624, JP5
MILT83133, JP8
JET A, B (COMMERCIAL)
JET A1 (COMMERCIAL)

F40
F43 OR F44
F34
NONE
F35

OIL

ENGINE *

229

MILL7808J OR LATER

0 148

OIL

ENGINE *

129

MILL7808

0148

ADG/CSD/EPU

MILL7808

0148

HYDRAULIC FLUID

HYDRAULIC SYSTEMS A AND B

MILH5606

MILH83282

H515

H537

OXYGEN

GASEOUS

MILO27210, TYPE I

NONE

OXYGEN

LIQUID

MILO27210, TYPE II

NONE

EXTERNAL ELECTRICAL

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

MONOPROPELLANT (EPU)

LIQUID

HYDRAZINE (70% N

, 30%

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 196.(Sheet 2)

T.O. GR1F16CJ1

SECTION II

NORMAL PROCEDURES

TABLE OF CONTENTS

Page

Introduction

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

Flight Planning

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

Takeoff and Landing Data Card

. . . . . . . . .

Cockpit Designation Code

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

Weight and Balance

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

Preflight Check

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

Exterior Inspection

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

Cockpit Access

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

Before Entering Cockpit

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

Cockpit Interior Check

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

Left Console

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

Left Auxiliary Console

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

Instrument Panel

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

Right Auxiliary Console

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

Right Console

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

After Cockpit Check Is

Complete Verify

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

Before Starting Engine

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

Starting Engine

PW 229

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

Starting Engine

129

210

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

After Engine Start

211

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

Before Taxi

217

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

Taxi

218

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

Before Takeoff

218

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

Takeoff

220

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

Normal Takeoff

220

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

Takeoff With Asymmetric Stores

222

. . . . . . . . .

Climb

222

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

Climb/InFlight/Operational Checks

222

. . . . . . . .

Air Refueling Procedures

223

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

Descent/Before Landing

223

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

Landing

223

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

Normal Landing

223

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

Short Field Landing (Dry Runway)

226

. . . . . .

Crosswind Landing

226

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

TouchandGo Landing

227

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

After Landing

227

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

Prior to Engine Shutdown

228

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

Engine Shutdown

229

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

Scramble

230

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

Preflight

230

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

Aircraft On Quick Response Status

230

. . . . . .

Hot Refueling

231

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

Hot Refueling Precautions

231

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

Prior to Hot Pit Entry

231

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

Prior to Hot Refueling

231

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

During Hot Refueling

232

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

Hot Refueling Complete

232

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

Quick Turnaround

232

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

Prior to Engine Shutdown

232

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

Special Procedures

232

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

EPU Hydrazine Support at NonF16

Bases

232

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

Supplemental Procedures

232

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

ILS Procedures

232

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

Exterior Inspection

232

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

Danger Areas

232

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

Turning Radius and Ground Clearance

232

. . . .

GSuit Hose Routing

232

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

Strange Field Procedures

232

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

INTRODUCTION

This section provides the actions required for normal

operation of the aircraft. Amplification is included

only when special considerations or techniques

should be observed. A complete knowledge of Section

III, EMERGENCY PROCEDURES, and Section V,

OPERATING LIMITATIONS, is required prior to

flight.

FLIGHT PLANNING

Refer to T.O. GR1F16CJ11.

TAKEOFF AND LANDING DATA CARD

A takeoff and landing data card is provided in the

Flight Crew Checklist for recording computed data.

COCKPIT DESIGNATION CODE

An asterisk (*) preceding steps is used to highlight

procedures for

aircraft which apply to both

cockpits.

WEIGHT AND BALANCE

For maximum GW limitations, refer to Section V,

OPERATING LIMITATIONS. For weight and

balance information, refer to the individual aircraft

Form F (DD Form 3654) and the Weight and Balance

Handbook.

T.O. GR1F16CJ1

PREFLIGHT CHECK

Check AFTO Form 781 for aircraft release and stores

status.

EXTERIOR INSPECTION

Refer to figure 24 for normal preflight inspection.

COCKPIT ACCESS

Refer to figure 21.

1. Canopy-Open by positioning external cano

py switch to the up position.

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.

2. Ladder-Position on cockpit sill.

A failure of the canopy actuator

could allow the canopy to fall during

transit. Do not position the ladder

until the canopy motion has stopped.

NOTE

Cockpit access is gained by the use

of two entrance ladders or moving one

ladder as required.

BEFORE ENTERING COCKPIT

*1. Ejection seat-Check.

Ejection safety lever-Safe (up).

Safety pins (2)-Removed (ejection safety

lever and EMERGENCY MANUAL CHUTE

handle).

1F-16X-1-1045A

Cockpit Access

(Typical)

EXTERNAL CANOPY SWITCH

(LOWER SURFACE OF LEFT

STRAKE)

Figure 21.

Survival KIT DEPLOYMENT switch-As

desired.

A Parachute Landing Fall (PLF) with

the survival kit not deployed may result

in injury.

RADIO BEACON-As desired.

Emergency oxygen bottle-1800 psi mini

mum.

Quickdisconnect (left side)-Connected.

Recovery parachute-Free from damage and

grease.

Inertia reel straps retaining pin (yel

low)-Visible in circular inspection hole.

Parachute risers and SEAWARS -Free from

damage and grease.

T.O. GR1F16CJ1

Rapidly pulling on the shoulder

harness to check the locking mecha

nism may cause damage to the locking

mechanism.

Lanyards from canopy to seat-Check.

Emergency oxygen hose quickdiscon

nect-Connected.

Environmental sensor pitot tubes-Clear of

obstructions and if flipup pitot tubes are

installed, safety pins (2) removed.

Quickdisconnect (right side)-Connected.

Electronic recovery sequencer battery indi

cator-White indication.

CANOPY JETTISON Thandle-Secure,

safety pin removed.

Lapbelt retaining pins (yellow)-Protrud

ing, both sides.

Lapbelts-Secure. (Pull up and forward,

both sides.)

Survival kit straps-Secure. (Pull up and

aft, both sides.)

2. MAIN PWR switch-OFF.

For solo flight:

3. Ejection seat-Safe, straps secure, pins

removed.

4. CANOPY JETTISON Thandle-Secure,

safety pin removed.

5. SPD BRK switch-Center.

6. FUEL MASTER switch-MASTER (guard

down).

7. ENG CONT switch-NORM (guard down).

8. Audio panels-Set:

COMM 1 mode knob-SQL.

COMM 2 mode knob-SQL.

All other knobs-CCW.

9. ALT GEAR handle-In.

10. ALT FLAPS switch-NORM.

11. GND JETT ENABLE switch-OFF.

12. DRAG CHUTE Switch-NORM.

13. HOOK switch-UP.

14. ARMT CONSENT switch-ARMT CON

SENT (guard down).

15. EJECTION MODE SEL handle-SOLO.

16. Interior LIGHTING control panel-All

knobs off.

17. OXYGEN REGULATOR-OFF and 100%.

18. Utility light-OFF and secured.

COCKPIT INTERIOR CHECK

The checklist steps are not arranged in a mandatory

order.

*1. Loose or foreign objects-Check.

A thorough cockpit interior preflight check

shall be accomplished prior to each flight

with emphasis on loose or foreign objects

that might cause injury to personnel or

damage to the aircraft.

*2. Harness and personal equipment-Fasten.

Attach the parachute risers to the harness.

Attach and adjust survival kit straps.

Secure and adjust the lapbelt. After

fastening lapbelt, hold right side of lapbelt

buckle stationary and shake and push left

side. Also insure that latching mechanism

has reset back to its original position and is

flush with buckle to insure a positive lock.

Connect oxygen hose, gsuit hose, vest hose,

and communication leads. Check operation

of the shoulder harness locking mechanism.

T.O. GR1F16CJ1

A partially locked lapbelt may open

during maneuvering flight or ejection

sequence.

Unobserved gsuit hose or vest hose

disconnects can contribute to gray/

blackout or loss of consciousness.

Failure to adjust survival kit straps to

achieve a snug fit between the pilot

and seat pan lid may result in injury

during ejection.

Failure to adequately secure and

tighten lapbelt may result in inability

to reach and operate the MPO switch

during outofcontrol situations.

Do not adjust seat height with survival

kit straps or lapbelt disconnected as

damage to the ejection seat or stick

may occur.

NOTE

Refer to figure 211. The recommended

routing of the gsuit hose is directly

under the torso harness and aft of the

survival kit strap to reduce the

possibility of a gsuit hose disconnect.

Gsuit hose routing must provide

sufficient slack to allow for maximum

mobility since inflight reconnect is

extremely difficult.

Excess gsuit hose must be properly

routed to prevent MANUAL TRIM

panel interference during flight.

Incorrectly routed or unsecured

gsuit hose may result in throttle

interference or disconnected gsuit hose.

*3. Rudder pedals-Adjust.

Adjust rudder pedals so that legs are flat on

the seat cushion to prevent the right leg

from hitting stick or injury during ejection.

Left Console

1. PROBE HEAT switch-OFF.

STICK CONTROL switch-As briefed

when

occupied; FWD for solo flight.

3. FLCS PWR TEST switch-NORM.

4. DEFOG lever-Midrange.

5. DIGITAL BACKUP switch-OFF.

*6. ALT FLAPS switch-NORM.

7. MANUAL TF FLY UP switch - ENABLE.

8. LE FLAPS switch-AUTO.

9. BIT switch-OFF.

10. TRIM/AP DISC switch-NORM.

11. ROLL, YAW, and PITCH TRIM-Center.

*12. FUEL MASTER switch-MASTER (guard

down and

safetywired).

13. TANK INERTING switch-OFF.

14. ENG FEED knob-NORM.

15. AIR REFUEL switch-CLOSE.

16. IFF MASTER knob-STBY.

17.

PX II

CNI,

PX III

C & I knob-BACKUP.

*18. TACAN-As desired.

19. EXT LIGHTING control panel-As required.

PX III

If ground operation of the

anticollision strobe light is anticipated

to be longer than 2 hours, the

ANTICOLLISION knob should be set

in position 1 to avoid overheating the

power supply and strobe.

20. MASTER light switch-NORM.

21. EPU switch-NORM (guard down).

22. MAIN PWR switch-OFF.

23. AVTR power switch-OFF.

24. AVTR

PX II

DISPLAY,

PX III

VIDEO SELECT

knob-HUD.

25. ECM power-Off.

*26. COMM 1 power knob-CW.

*27. COMM 1 mode knob-SQL.

T.O. GR1F16CJ1

Change 125

*28. COMM 2 power knob-CW.

*29. COMM 2 mode knob-SQL.

*30. TACAN power knob-CW.

31.

AB RESET switch-NORM.

32.

ENG CONT switch-PRI (guard down).

33.

ENG CONT switch-NORM (guard down).

34. JFS switch-OFF.

35. UHF radio backup control panel:

a. Function knob-BOTH.

b. Frequency-As desired.

36. Throttle-Verify freedom of motion, then OFF.

*37. SPD BRK switch-Forward.

*38. DOG FIGHT switch-Center.

Left Auxiliary Console

*1. ALT GEAR handle-In.

2. CMDS switches (9)-OFF.

3. RF switch-NORM.

PX III

SYMBOLOGY power knob-Off.

5. STORES CONFIG switch-As required.

6. LANDING TAXI LIGHTS switch-OFF.

*7. LG handle-DN.

*8. GND JETT ENABLE switch-OFF.

9. BRAKES channel switch-CHAN 1.

10. ANTISKID switch-ANTISKID.

*11. EMER STORES JETTISON button-Cover

intact.

*12. HOOK switch-UP.

Instrument Panel

1. ROLL switch-ATT HOLD.

2. PITCH switch-A/P OFF.

3. MASTER ARM switch-OFF.

ARMT CONSENT switch-ARMT CON

SENT (guard down).

5. LASER ARM switch-OFF.

*6. DRAG CHUTE switch-NORM.

*7. HUD/ASHM-Set.

*8. Altimeter-Set.

9. FUEL QTY SEL knob-NORM.

10. EXT FUEL TRANS switch-NORM.

NOTE

If a wing transfer valve fails and WING

FIRST is selected, fuel flows onto the

ground from the overboard vent line

under the left wing (outboard of the

fuel pylon). Selecting NORM should

stop the fuel spillage.

PX III

If CFT's are installed and an

external tank transfer valve fails to

close when the tank is empty and

WING FIRST or NORM is selected,

fuel is trapped in the CFT and some

trapped fuel may vent overboard.

Selecting CFT FIRST/NO FILL should

prevent trapped/vented CFT fuel.

*11. INSTR MODE knob-As desired.

Right Auxiliary Console

*1. Clock-Set.

EJECTION MODE SEL handle-

b2p

NORM or AFT (as briefed),

LESS

b2p

AFT.

SOLO position should not be selected

with the rear seat occupied.

Ejection initiated with the EJEC

TION MODE SEL handle in NORM

may incapacitate the

pilot at

airspeeds greater than 180 knots. Use

of the NORM position is therefore not

recommended.

T.O. GR1F16CJ1

Right Console

NOTE

PX III

Oxygen regulator pressure de

creases slowly when OBOGS is not

operating and may indicate low prior

to engine start.

1. SNSR PWR switches (4)-OFF.

2. HUD control panel-Set.

3. NUCLEAR CONSENT switch-OFF (guard

down).

4. ZEROIZE switch-OFF.

*5. Wristrest and armrest-As desired.

*6. Interior LIGHTING control panel-As

desired.

VOICE MESSAGE switch-VOICE

MESSAGE.

If safety wire is broken, notify maintenance.

8. TEMP knob-AUTO.

9. AIR SOURCE knob-NORM.

If AIR SOURCE knob is in OFF or

RAM, electronic equipment may be

damaged.

10. AVIONICS POWER switches (8)-OFF.

11. ANTI ICE switch-AUTO/ON.

If engine antiice is on or has been on,

heat in the inlet strut may be sufficient

to cause injury if touched.

If there is visible moisture and

ambient temperature is 45

F (7

C) or

less, place the ANTI ICE switch to ON.

12. IFF ANT SEL switch-NORM.

13. UHF ANT SEL switch-NORM.

*14.

PX II

Oxygen system-Check:

Pressure-Check 50120 psi.

Mode lever-PBG/ON (as required).

Diluter lever-NORM.

EMER lever-NORM.

FLOW indicator-Check.

EMER lever-EMER.

Check for positive oxygen pressure and

mask and hose/connector leakage.

EMER lever-NORM.

AFTER COCKPIT CHECK IS COMPLETE-VERIFY

The following items are those important switches

that, if not correctly positioned, could cause a safety

hazard and/or improperly operated systems during

engine start.

*1. FUEL MASTER switch-MASTER (guard

down and

safetywired).

2. ENG FEED knob-NORM.
3. EPU switch-NORM (guard down).

ENG CONT switch-PRI (guard down).

ENG CONT switch-NORM (guard down).

*6. Throttle-OFF.
*7. LG handle-DN.

Insure that the LG handle is confirmed

fully down. The LG handle can be in an

intermediate position allowing LG

extension and/or safe indications;

however, the LG handle is not locked

and LG retraction could occur during

subsequent ground operations.

*8. HOOK switch-UP.

If either HOOK switch is in DN, the

hook extends when aircraft battery

power is applied.

9. MASTER ARM switch-OFF.

T.O. GR1F16CJ1

10. AIR SOURCE knob-NORM.

*11. Loose or foreign objects-Check.

Loose or foreign objects in the cockpit

can cause entanglement or obstruction

with critical controls (e.g., ejection

handle, stick, rudder pedals, throttle,

canopy handle, etc.).

BEFORE STARTING ENGINE

1. MAIN PWR switch-BATT.

To prevent possible depletion of bat

tery power, do not allow MAIN PWR

switch to remain in BATT or MAIN

PWR for more than 5 minutes without

engine running or external power

applied.

NOTE

A JFS RUN light flashing once per

second indicates a noncritical failure

in the JFS system. If the JFS operates

normally for engine start, the mission

may be continued. Notify maintenance

after flight.

A JFS RUN light flashing twice per

second indicates a critical failure in

the JFS system. The JFS will not

operate. Place the MAIN PWR switch

to OFF and notify maintenance.

Verify FLCS RLY light on.

NOTE

Toe brakes are not available when the

FLCS RLY light is on and the aircraft

battery is the only operating power

source.

PX III

Labored breathing through the

oxygen mask before engine start is

possible with the diluter lever in

NORM. It is not possible to to breath

through the oxygen mask before

engine start with the diluter lever in

100%.

2. FLCS PWR TEST switch-TEST and hold.

Activation of the FLCS PWR TEST switch

with the MAIN PWR switch in BATT closes

FLCS relays and allows verification of

power output of the FLCC with the aircraft

battery as the power source.

Verify lights on:

ACFT BATT TO FLCS.

FLCS PMG.

FLCS PWR (4).

Verify FLCS RLY light off.

3. FLCS PWR TEST switch-Release.

4. MAIN PWR switch-MAIN PWR.

Verify lights on:

ELEC SYS.

HYD/OIL PRESS.

FLCS RLY.

SEC.

ENGINE.

Do not apply external electrical power

for more than 30 minutes without

cooling air; longer operation may

damage electronic components which

cannot be turned off. Prior to applying

external power without cooling air,

insure that all avionic equipment is

off; UHF radio operation on backup

control is permissible.

T.O. GR1F16CJ1

NOTE

If FLCS RLY light is off, cycle MAIN

PWR switch to BATT and back to

MAIN PWR to open FLCS relays.

5. EPU GEN and EPU PMG lights-Confirm

off.

If either light is illuminated, turn the

MAIN PWR switch to OFF. Insure that

the EPU safety pin remains installed

and notify maintenance. (The EPU

will activate using hydrazine if the

EPU safety pin is removed.)

6. Communications-Established.

7. Canopy-As desired.

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.

To prevent possible engine damage,

stow or secure loose cockpit items prior

to engine start with the canopy not

closed.

When lowering or raising the

canopy handle, insure that the canopy

switch is not bumped to the up (open)

position before handle is completely

locked or unlocked. If this occurs, hold

the switch in the down (close) position

as soon as possible to relieve the

jammed condition and prevent canopy

actuator motor burnout. If required,

manually crank canopy toward the

closed position to relieve the jammed

condition. If possible, place MAIN

PWR switch to OFF and have the

aircraft battery disconnected by the

ground crew. This action removes

power from the canopy actuator.

8. Chocks in place, fireguard posted, and intake

and other danger areas clear (ground crew).

STARTING ENGINE

PW 229

Refer to figure 28 for danger areas. Moving the JFS

switch to either start position closes the FLCS

relays. The FLCS RLY light goes off; the FLCS PMG

light (and ACFT BATT TO FLCS light if engine is

started on battery power) illuminates. Toe brakes

also become functional (if engine is started on

battery power).

The JFS RUN light comes on within 30 seconds; after

the JFS RUN light illuminates, engine rpm starts to

increase smoothly. At approximately 15 percent

rpm, the hydraulic and fuel pressures increase. The

SEC caution light goes off by approximately 18

percent rpm. The throttle should be advanced to

IDLE after engine rpm reaches 20 percent.

Immediately after advancing the throttle to IDLE,

the SEC caution light illuminates for about 3

seconds to indicate automatic DEEC/SEC ground

selftest. Engine lightoff occurs within 20 seconds

after throttle advance and is indicated by airframe

vibration and an increase in rpm followed by an

increase in FTIT. Without external power connected,

only the RPM and FTIT indicators function until the

standby generator is on line.

At approximately 50 percent rpm, the JFS automati

cally shuts down. At approximately 55 percent rpm,

the standby generator comes on line, the ENGINE

warning light goes off, and the OXY LOW warning

light illuminates for approximately one second. To

insure the emergency buses are being powered by the

standby generator, check for illumination of the

SEAT NOT ARMED caution light and three green

WHEELS down lights prior to the main generator

coming on line. Five to ten seconds after the the

standby generator comes on line, the main generator

comes on line, and the standby generator goes off line.

FTIT increases smoothly at a moderate rate and

normally peaks at less than 625

1. JFS switch-START 2.

2. SEC caution light-Check off.

T.O. GR1F16CJ1

3. Throttle-Advance to IDLE at 20 percent

rpm minimum.

If the FUEL MASTER switch is

discovered in OFF during start (i.e.,

after the throttle is moved to IDLE),

discontinue the start. Positioning the

FUEL MASTER switch to MASTER

with the throttle out of OFF may cause

a hot start or tailpipe fire.

NOTE

If the HYD/OIL PRESS warning light

goes off and stays off prior to

approximately 25 percent rpm, sus

pect failure of the engine oil pressure

sensor and abort the aircraft. This

check is not valid if less than 30

seconds elapse from movement of the

MAIN PWR switch out of OFF until

both hydraulic pressures are above

1000 psi (i.e., low oil pressure time

delay has not expired; in which case,

the HYD/OIL PRESS warning light

goes off when hydraulic pressures

exceed 1000 psi, but may reilluminate

if the 30second time delay expires

while oil pressure is still low.

If the main and/or standby generator

fails to come on, do not attempt reset.

Although the generator(s) may reset, a

problem may still exist. Notify

maintenance.

The SEC caution light illuminates

immediately after throttle advance for

about 3 seconds indicating automatic

DEEC/SEC ground selftest.

If the FLCS RLY light remains on with

the JFS switch in either start position,

one or more FLCS relays did not latch

closed. Latching may occur when the

standby or main generator comes on

line. If the FLCS RLY light goes off

when either generator comes on line,

notify maintenance of the occurrence

after flight. If the FLCS RLY light

remains on after the main generator is

on line, notify maintenance.

If an engine restart is desired shortly

after engine shutdown, motor the

engine with the JFS for a minimum of

1 minute or a maximum of 4 minutes

before throttle advancement to insure

the FTIT drops below 200

C. Initiat

ing a start with the FTIT above 200

may result in a DEEC FTIT limited

hung start.

4. ENGINE warning light-Off (approxi

mately 55 percent rpm).

*Engine at idle and check:

5. JFS switch-Confirm OFF.

If JFS switch does not automatically

return to OFF, turn JFS off. Notify

maintenance after flight.

6. HYD/OIL PRESS warning light-Off.

The HYD/OIL PRESS warning light may

not go off until rpm is increased to 70

percent. If the warning light comes on again

at idle, notify maintenance.

7. FUEL FLOW - 5001500 pph.

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.

NOTE

FFP light may blink at idle rpm.

T.O. GR1F16CJ1

210

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

Do not make stick inputs while ground

crew is in proximity of control surface.

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

16. Throttle cutoff release-Check.

Verify that the cutoff release does not

remain in the actuated position by attempt

ing to retard the throttle to OFF without

depressing the cutoff release. If throttle

moves to OFF, remain in OFF and notify

maintenance.

NOTE

Failure to perform this check after

engine start can result in an unde

tected stuck throttle cutoff release,

which may lead to an unintentional

engine shutdown.

STARTING ENGINE

129

Refer to figure 28 for danger areas. Moving the JFS

switch to either start position closes the FLCS

relays. The FLCS RLY light goes off; the FLCS PMG

light (and ACFT BATT TO FLCS light if engine is

started on battery power) illuminates. Toe brakes

also become functional (if engine is started on

battery power).

The JFS RUN light comes on within 30 seconds; after

the JFS RUN light illuminates, engine rpm starts to

increase smoothly. The throttle should be advanced

to IDLE after engine rpm reaches either 20 percent

rpm (ambient temperature less than 90

F) or

maximum motoring rpm (ambient temperature

F or greater). Engine lightoff occurs within 10

seconds after throttle advance and is indicated by an

airframe vibration and an increase in rpm followed

by an increase in FTIT. Without external power

connected, only the RPM and FTIT indicators

function until the standby generator is on line.

The SEC caution light goes off at 20 percent rpm. At

approximately 55 percent rpm, the JFS automati

cally shuts down. At approximately 60 percent rpm,

the standby generator comes on line and the

ENGINE warning light goes off. To insure the

emergency buses are being powered by the standby

generator, check for illumination of the SEAT NOT

ARMED caution light and three green WHEELS

down lights prior to the main generator coming on

line. Five to ten seconds after the standby generator

comes on line, the main generator comes on line and

the standby generator goes off line.

FTIT increases smoothly at a rapid rate.

1. JFS switch-START 2.

NOTE

Abnormal rpm indications (i.e. instan

taneous jumps) may indicate alterna

tor failure and not rpm indicator

malfunction. Abort the aircraft and

notify maintenance.

2. Throttle-Advance to IDLE at either 20

percent rpm minimum (ambient tempera

ture less than 90

F) or maximum motoring

rpm (ambient temperature 90

F or greater).

If the FUEL MASTER switch is

discovered in OFF during engine start

(i.e., after the throttle is moved to

IDLE), discontinue the start. Position

ing the FUEL MASTER switch to

MASTER with the throttle out of OFF

may cause a hot start or tailpipe fire.

NOTE

If the HYD/OIL PRESS warning light

goes off and stays off prior to

approximately 15 percent rpm, sus

pect failure of the engine oil pressure

sensor and abort the aircraft. This

check is not valid if less than 30

seconds elapse from movement of the

MAIN PWR switch out of OFF until

both hydraulic pressures are above

1000 psi (i.e., low oil pressure time

delay has not expired; in which case,

the HYD/OIL PRESS warning light

goes off when hydraulic pressures

exceed 1000 psi, but may reilluminate

if the 30second time delay expires

while oil pressure is still low).

If the main and/or standby generator

fails to come on, do not attempt reset.

Although the generator(s) may reset, a

problem may still exist. Notify mainte

nance.

T.O. GR1F16CJ1

211

NOTE

If the FLCS RLY light remains on with

the JFS switch in either start position,

one or more FLCS relays did not latch

closed. Latching may occur when the

standby or main generator comes on

line. If the FLCS RLY light goes off

when either generator comes on line,

notify maintenance of the occurrence

after flight. If the FLCS RLY light

remains on after the main generator is

on line, notify maintenance.

3. SEC caution light-Off.

4. ENGINE warning light-Off (approximately

60 percent rpm).

NOTE

In hot day conditions (temperature

greater than 90

F (32

C)) the EN

GINE warning light may not go off

until idle speed is obtained (greater

than 70 percent rpm).

*Engine at idle and check:

5. JFS switch-Confirm OFF.

If JFS switch does not automatically

return to OFF, turn JFS off. Notify

maintenance after flight.

6. HYD/OIL PRESS warning light-Off.

The HYD/OIL PRESS warning light may

not go off until rpm is increased to 70

percent. If the warning light comes on again

at idle, notify maintenance.

7. FUEL FLOW- 7001700 pph.

8. OIL pressure-15 psi (minimum).

9. NOZ POS-Greater than 94 percent.

10. RPM-6280 percent.

11. FTIT-650

C or less.

12. HYD PRESS A & B-28503250 psi.

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

NOTE

FFP light may blink at idle rpm.

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

Do not make stick inputs while ground

crew is in proximity of control surface.

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

16. Throttle cutoff release-Check.

Verify that the cutoff release does not

remain in the actuated position by attempt

ing to retard the throttle to OFF without

depressing the cutoff release. If throttle

moves to OFF, remain in OFF and notify

maintenance.

NOTE

Failure to perform this check after

engine start can result in an unde

tected stuck throttle cutoff release,

which may lead to an unintentional

engine shutdown.

Engine vibration/rumble may be

sensed on the ground while accelerat

ing or decelerating the engine, when

transferring to SEC, or when stabi

lized at idle in either PRI or SEC. This

vibration/rumble has no adverse effect

on the engine or aircraft structure. The

vibration/rumble should disappear

when the throttle is advanced slightly

(approximately 5 percent rpm increase).

AFTER ENGINE START

1. TEST switch panel-Check:

a. PROBE HEAT switch - PROBE HEAT.

PROBE HEAT caution light off. If the

caution light illuminates, one or more

probe heaters are inoperative or a

monitoring system failure has occurred.

b. PROBE HEAT switch - TEST.

PROBE HEAT caution light flashes 35

times per second. If the caution light

does not illuminate or if it illuminates

but does not flash, the probe heat

monitoring system is inoperative.

c. PROBE HEAT switch - OFF.

d. FIRE & OHEAT DETECT button-Test.

T.O. GR1F16CJ1

212Change 1

PX II

OXY QTY test switch-Test and

check.

f. MAL & IND LTS button-Test.

NOTE

Proper VMS operation is verified by

the presence of each word in priority

sequence (i.e., PULLUP, ALTITUDE,

WARNING, etc.). A brief LG warning

horn is also heard prior to the

WARNING and CAUTION words.

Only the LG warning horn and the

warning and caution voice messages

are heard when MAL & IND LTS test

is initiated from the rear cockpit.

LESS

b7n

PX III

The circuitry

powering the AVIONICS FAULT cau

tion lights and ECM lights is not

capable of turning on both the

and

the

lights except during MAL &

IND LTS test. As a result, the only time

these lights illuminate in either

cockpit is during MAL & IND LTS test.

For avionics faults, failure of the

AVIONICS FAULT caution lights to

come on also prevents illumination of

the MASTER CAUTION light and

operation of the voice caution message.

Faults will still be displayed on the

PFLD. The interim solution is removal

of the light bulbs from the

AVIONICS FAULT caution light and

ECM light. This solution enables

operation of the

AVIONICS FAULT

caution light,

ECM light, both

MASTER CAUTION lights, and the

voice caution message after a fault

occurs. The

AVIONICS FAULT

caution light and

ECM light should

not illuminate during MAL & IND LTS

test if the bulbs have been removed. If

the

AVIONICS FAULT caution

light or

ECM light illuminates

during MAL & IND LTS test, contact

maintenance.

PX II

AVIONICS POWER panel-Set:

a. FCC switch-FCC.

b. SMS switch-SMS.

c. MFD switch-MFD.

d. UFC switch-UFC.

e. GPS switch-GPS.

PX III

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.

4. EGI/INS-Align (

PX III

after display visible

on the DED).

NOTE

PX III

If GPS is unavailable, failure to

enter alignment coordinates flags the

alignment as degraded (NAV RDY

light does not flash).

PX II

Entry of alignment coordinates is

required even if internal coordinates

are exactly equal to parking spot

location.

Failure to enter alignment coordinates

flags the alignment as degraded (NAV

RDY light does not flash).

5. SNSR PWR panel:

a. LEFT HDPT switch-OFF, unless

required.

Select OFF unless TFR/FLIR opera

tion is planned. With LEFT HDPT

power on and the TFR in OFF/STBY, a

failure in the WX mode circuitry can

cause the TFR to operate in the WX

mode. An unexpected flyup may

subsequently occur.

b. RIGHT HDPT switch-As required.

c. FCR switch-FCR.

In environments of high humidity,

delay turning the FCR on for approxi

mately 4 minutes. This action pre

cludes damage to FCR caused by

moisture in the ECS immediately after

engine start.

d. RDR ALT switch-RDR ALT.

T.O. GR1F16CJ1

Change 1213

*6. HUD/ASHM-As desired.

PX II

CNI,

PX III

C & I knob-UFC.

NOTE

If UFC battery failure occurs, UHF/

VHF preset frequencies in the UFC

revert to default values until entered

manually or by the DTC.

8. MFL-Clear.

NOTE

Multiple nonresettable FLCS MFL's

may occur during engine start and may

be accompanied by a lack of control

surface response to stick/rudder com

mands. These MFL's can occur if

aircraft battery voltage is low or if a

switching problem occurs when the JFS

switch is moved out of OFF. If multiple

FLCS MFL's remain after a FLCS reset:

b1q

Perform the following:

DBU switch-BACKUP, then OFF.

Cycling the DBU switch with

WOW reinitializes the FLCC and

inhibits FLCS MFL reporting for

20 seconds.

If FLCS MFL's clear and do not recur

after 20 seconds, maintenance action

is not required.

LESS

b1q

Perform the following:

DBU switch - BACKUP, then OFF.

FLCS RESET switch - RESET.

If FLCS MFL's clear, maintenance

action is not required.
If FLCS MFL's remain:

FLCS BIT - Initiate and monitor.

If FLCS MFL's remain:

Engine - Shut down, then restart to

cycle power to the FLCC.

If FLCS MFL's clear following FLCS BIT

or engine restart, notify maintenance of

the occurrence after flight.

PW 229

SEC-Check after the engine has

run at idle for at least 30 seconds. May be

delayed until the BEFORE TAKEOFF check.

Throttle-IDLE.

ENG CONT switch-SEC.

NOZ POS - Less than 5 percent.

SEC caution light-On.

Throttle - Verify engine response to

throttle movement, then IDLE.

ENG CONT switch-

PRI,

NORM.

NOZ POS - Greater than 80 percent.

SEC caution light-Off.

10.

129

SEC-Check. May be delayed until

the BEFORE TAKEOFF check.

ENG CONT switch-SEC.

SEC caution light-On.

RPM-Stabilized.

RPM may drop up to 10 percent from PRI

value before stabilizing. Stabilized SEC

idle rpm may be up to 5 percent lower

than that in PRI.

Throttle-Snap to MIL and then snap to

IDLE when rpm reaches 85 percent. Check

for normal indications and smooth operation.

NOZ POS-10 percent or less within 30

seconds after selecting SEC.

ENG CONT switch-

PRI,

NORM.

SEC caution light-Off.

NOZ POS-Greater than 94 percent.

11. Flight controls-Cycle.

NOTE

To assist in warming the hydraulic

fluid and removing air from the

hydraulic system, maximum stick and

rudder pedal inputs should be made

prior to running FLCS BIT.

12. FLCS BIT-Initiate and monitor.

Position BIT switch to BIT. The RUN light

on FLCP illuminates. At successful comple

tion of BIT (approximately 45 seconds), the

RUN light goes off, the BIT switch returns

to OFF, and the FAIL light and FLCS

warning light remain off. A BIT pass

message appears on the FLCS MFD page.

T.O. GR1F16CJ1

214

NOTE

If the FLCS BIT reports a failure

through the FLCS warning light and

the FAIL light on the FLCP, the failure

cannot be reset. The BIT must be

reinitiated. In this case, the RUN light

and the FAIL light are simultaneously

illuminated for the first steps of the BIT,

after which the FAIL light goes off

unless BIT detects a subsequent failure.

If the

PX II

FCC,

PX III

MMC is not

turned on prior to FLCS BIT, an FLCS

MUX DEGR message appears on the

PFLD.

Entering system altitude during FLCS

BIT results in an incorrect system

altitude.

During FLCS BIT, the ECS air ejectors

are turned off. This results in higher

ECS component temperatures and

may cause fumes in the cockpit that

could be described as metallic odors.

This situation is normal and does not

require maintenance action.

PW 229

During FLCS BIT, the CADC

provides a mach signal to the engine

that results in an rpm increase of

approximately 2 percent.

13. ECM panel-As required.

14. SPD BRK switch-Cycle.

*15. WHEELS down lights-Three green.

*16. SAI-Set.

17. FUEL QTY SEL knob-Check.

The following values are based on JP4 or JP5/8:

TEST-FR, AL pointers indicate 2000

(

100) pounds and totalizer indicates 6000

(

100) pounds. FWD and AFT FUEL LOW

caution lights illuminate.

PX III

If CFT's are

installed, CFT pumps operate and shut down

30 seconds after switch is moved out of TEST

(if INT WING & CFT fuel quantity is less

than 1425/1500 pounds).

NORM-AL pointer indicates approxi

mately 2675/2810 pounds. FR pointer

indicates approximately 3100/3250 (

1800/

1890) pounds.

RSVR-Each reservoir indicates approxi

mately 460/480 pounds.

PX II

INT WING-Each wing indicates

approximately 525/550 pounds.

PX III

INT WING & CFT - If CFT's are not

installed (or installed and not filled), each

wing indicates approximately 525/550

pounds. If CFT's are filled, each pointer

indicates approximately 2000/2100 pounds.

EXT WING - Each external wing tank

indicates approximately 2300/2420 pounds

(370gallon fuel tank) or 3750/3925 pounds

(600gallon tank) (for full tanks).

EXT CTR-FR pointer indicates approxi

mately 1800/1890 pounds (for full tank). AL

pointer drops to zero.

NOTE

The sum of the individual fuel tanks

and the totalizer should agree within

100 pounds with only internal fuel or

300 pounds with external fuel.

FUEL QTY SEL knob-As desired.

18. EPU FUEL quantity-95102 percent.

19. Avionics-Program as required and verify

(manual or data transfer cartridge).

SMS.

When AIM9's are loaded, the

PX II

SMS,

PX III

ST STA switch must be

maintained in the

PX II

SMS,

PX III

STA position while taxiing or airborne.

If recycling of the

PX II

SMS,

PX III

STA switch is required, power should

not be off longer than 8 seconds at any

one time.

Communications.

Steerpoints.

Profile data (including bingo fuel).

MFD master mode data.

T.O. GR1F16CJ1

215

*20. MFD's-As desired.

21. VHF radio-As desired.

After FLCS BIT completed:

*22. DBU-Check.

a. DIGITAL BACKUP switch-BACKUP.

Verify that DBU ON warning light

illuminates.

NOTE

The AOA indicator displays the middle

AOA value selected. The indication

may change in gusty wind conditions.

b. Operate controls-All surfaces respond

normally.

c. DIGITAL BACKUP switch-OFF.

Verify that DBU ON warning light goes

off.

23. Trim-Check.

TRIM/AP DISC switch-DISC.

Stick TRIM button-Activate in roll and

pitch.

No control surface motion.

No TRIM wheel or indicator motion.

TRIM/AP DISC switch-NORM.

Stick TRIM button-Check and center.

Control surface motion.

TRIM wheel and indicator motion.

Rudder trim check.

YAW TRIM knob - Check and center.

*24.

FLCS override - Check.

STICK CONTROL - Selected cockpit.

Stick indicator - As selected.

Selected cockpit paddle switch - Depress.

OVRD lights - On (both cockpits).

Selected cockpit stick - Operative.

Other cockpit stick - Inoperative.

*25. MPO - Check.

Stick - Full forward and hold; note

horizontal tail deflection.

MPO switch - OVRD and hold.

Confirm that horizontal tail trailing edges

move farther down.

Stick and MPO switch - Release.

Confirm that the horizontal tail returns to

its original position.

*26. Operate controls - All surfaces respond

normally; no FLCS lights on.

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

AIR REFUEL switch - OPEN, RDY light on,

DISC light off.

NOTE

If both the RDY and DISC lights are on,

then one or more relays are failed. This

condition must be corrected prior to

AR.

A/R DISC button - Depressed. DISC light

on, RDY light off; 3 seconds later, RDY light

on, DISC light off.

AIR REFUEL switch - CLOSE, RDY light

off.

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

CHAN 1.

One brake pedal - Depress.

Confirm (ground crew) - Brake activates.

Opposite brake pedal - Depress.

Confirm (ground crew) - Initial brake does

not activate.

Repeat above steps for opposite brake.

Content .. 14 15 16 17 ..

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

F16C/D. FLIGHT MANUAL (2002) - page 16