F16C/D. FLIGHT MANUAL (2002)

T.O. GR1F16CJ1CL2

A10

OTHER CONSIDERATIONS:

Illumination of the MAIN GEN light after a 23 second loss

of power to the HUD, MFD's, and other cockpit instruments

indicates shorting failure of an OCSC or other wiring/equip

ment.

With standby generator failure and the MAL & IND LTS sw

in DIM, the ELEC SYS caution light may not appear to illuminate

when the MASTER CAUTION and STBY GEN lights illuminate.

This action may reset the main or standby generator. Cycling

the MAIN PWR sw may also reset the main generator; however,

this action momentarily removes standby generator power and

activates the EPU.

The nonessential dc buses and essential dc bus lose

power. This results in loss of power to fuel boost and transfer

pumps, CARA, ECM, and FCR and power for normal weapon

arming/release including selective jettison.

If the affected systems are required for the safe recovery of

the aircraft, consider delaying/terminating EPU operation until

the systems are no longer required.

A10

7 3/4 " Page

T.O. GR1F16CJ1CL2

A11

SINGLE GENERATOR FAILURES (IN FLIGHT)

If MAIN GEN light illu

minated after a 23 sec

ond loss of the HUD and

MFD's was observed:

1. Land as soon as

practical.

If MAIN GEN light illu

minated and a 23 second

loss of the HUD and

MFD's was not observed,

or if STBY GEN or STBY

GEN and FLCS PMG

lights illuminate:

1. ELEC CAUTION

RESET button -

Depress.

2. Land as soon as

practical.

FLCS RLY Light

1. FLCS PWR TEST sw - TEST, momentarily.

If FLCS RLY light goes off:

2. Land as soon as practical.

If FLCS RLY light remains on:

2. EPU sw - ON.

3. Land as soon as practical.

4. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

If EPU runs abnormally:

3. EPU sw - OFF, then NORM.

4. Land as soon as possible.

END

A11

SGL GEN FAIL (IN FLT)/FLCS RLY LIGHT

" Page

A11

SGL GEN FAIL (IN FLT)/FLCS RLY LIGHT

" Page

T.O. GR1F16CJ1CL2

A12

OTHER INDICATIONS:

Main, standby, and EPU generators inoperative:

Avionics inoperative.

Uncontrollable cold airflow into the cockpit or reduced airflow

to the cockpit if the water separator coalescer freezes up.

ADI AUX warning flag.

ADI OFF warning flag.

MAJOR INOPERATIVE EQUIPMENT:

Main, standby, and EPU generators inoperative:

Normal LG extension.

LEF's, speedbrakes, stick trim.

FUEL quantity/FUEL FLOW indicators.

Fuel boost and transfer pumps.

Stores jettison (SEL and EMER).

ADI, AOA, IFF, INS, TACAN, and VHF.

Go to EMERGENCY POWER DISTRIBUTION, page A19, for

other systems lost.

OTHER CONSIDERATIONS:

With a main, standby, and EPU generator failure, OBOGS

and the OXY LOW warning light are inoperative. Activate EOS

if above 10,000 ft cockpit altitude.

LEF's are inoperative and departure susceptibility may be

increased. Near 1g flight, 200 kts should keep AOA less than

. Limit rolling maneuvers to a max bank angle change of

and avoid rapid roll rates.

This action may reset the main and/or standby generator.

This action may reset the main generator.

A12

8 " Page

T.O. GR1F16CJ1CL2

A13

MAIN, STANDBY, AND EPU GENERATOR FAILURE

If MAIN GEN, STBY GEN, and EPU GEN lights illu

minate:

1. AOA - 12

max (200 kts min).

2. EPU sw - ON (if EPU run light is off).

3. Climb if necessary.

4. Throttle - As required to extinguish the

HYDRAZN light.

If EPU GEN light goes off:

5. Go to MAIN AND STANDBY GENERATOR

FAILURE (IN FLIGHT), page A15.

If EPU GEN light is still on:

6. ELEC CAUTION RESET button - Depress.

If both MAIN GEN and STBY GEN lights remain on:

7. MAIN PWR sw - BATT, then MAIN PWR.

(Cont)

A13

8 1/4

MAIN, STANDBY, AND EPU GEN FAILURE

" Page

T.O. GR1F16CJ1CL2

A14

OTHER CONSIDERATIONS:

Plan to land within 30 minutes to insure adequate

electrical power for communications, brakes, hook, and drag

chute.

If the FLCS PMG and EPU PMG lights are on in combination

with the ACFT BATT TO FLCS light, the aircraft battery is

powering the FLCS. With the aircraft battery powering the FLCS

in addition to the battery buses, approx 314 minutes flight time

is available.

When the FLCS is powered by aircraft battery, remain alert

for degraded flight controls. At the first indication of degraded

response, reduce airspeed and climb to safe ejection altitude.

Eject prior to complete loss of control.

Fly airspeed for 11

AOA approach using fuel state when

power was lost.

If LG handle does not lower, select BRAKES CHAN 2 and

position ALT FLAPS sw to EXTEND. Nozzle remains closed,

resulting in higher than normal landing thrust.

Alternate LG extension can be used up to 300 kts;

however, the NLG may not fully extend until 190 kts. Time

above 190 kts should be minimized in case there is a leak in the

pneumatic lines.

WHEELS down lights and TO/LDG CONFIG warning light

function are inoperative. Monitor LG handle warning light to

verify that LG is down.

NWS is not available following alternate LG extension.

Do not depress the ALT GEAR reset button while pulling the

ALT GEAR handle. This action may preclude successful LG

extension.

Pulling the ALT GEAR handle with normal system B hydraulic

pressure may result in system B hydraulic failure within 15

minutes.

A14

8 1/4 " Page

T.O. GR1F16CJ1CL2

A14.1

If either MAIN GEN or

STBY GEN light goes off:

8. EPU sw - OFF, then

NORM.

9. Land as soon as

possible.

10. Refer to ACTIVATED

EPU/HYDRAZINE

LEAK, page F13.

END

If MAIN GEN, STBY

GEN, and EPU GEN

lights all remain on or all

come on again:

8. HOOK sw - DN.

9. C&I knob - BACK

UP.

10. Minimize UHF

transmissions.

If conditions permit:

11. Land as soon as

possible.

12. LG handle - DN.

(Use DN LOCK REL

button.)

13. ALT GEAR handle -

Pull (190 kts max).

14. Consider an approach

end arrestment, if

conditions permit.

Refer to CABLE

ARRESTMENT, page

F11.

15. Refer to ACTIVATED

EPU/HYDRAZINE

LEAK, page F13.

After landing:

16. Stop straight ahead

and have chocks

installed (or engage

parking brake).

17. MAIN PWR sw -

MAIN PWR (until

chocks are installed).

END

A14.1

8 1/8 " Page

T.O. GR1F16CJ1CL2

A14.2

MAJOR INOPERATIVE EQUIPMENT:

Fuel boost and transfer pumps.

Go to EMERGENCY POWER DISTRIBUTION, page A19, for

other systems lost.

OTHER INDICATIONS:

Numerous caution lights.

Caution lights come on bright, if dimmed.

OTHER CONSIDERATIONS:

This action may reset the main and/or standby generator.

The MAIN PWR sw may also be cycled to reset the main

generator.

If warning flag(s) is in view, refer to EGI FAILURE, page F29.

If chocks are not installed, be prepared to immediately

engage the parking brake if it disengages when the EPU is shut

off.

A14.2

8 1/8 " Page

T.O. GR1F16CJ1CL2

A15

MAIN AND STANDBY GENERATOR FAILURE (IN

FLIGHT)

If MAIN GEN and STBY GEN lights illuminate:

1. EPU sw - ON (if EPU run light is off).

2. ELEC CAUTION RESET button - Depress.

If MAIN GEN or STBY

GEN light goes off:

3. EPU sw - OFF, then

NORM.

4. ADI - Check for

presence of OFF

and/or AUX warn

ing flags.

5. Land as soon as

practical.

6. Refer to ACTIVATED

EPU/HYDRAZINE

LEAK, page F13.

END

If MAIN GEN and STBY

GEN lights remain on:

3. ADI - Check for

presence of OFF

and/or AUX warn

ing flags.

4. Land as soon as

possible.

5. Refer to ACTIVATED

EPU/HYDRAZINE

LEAK, page F13.

6. If hydrazine depletes

or EPU run light

goes off at low thrust

- Go to ABNORMAL

EPU OPERATION,

page A17.

After landing and air

craft is stopped:

7. Chocks - Installed

(or parking brake

engaged).

8. EPU sw - OFF.

9. MAIN PWR sw -

MAIN PWR (until

chocks are installed).

END

A15

8 1/2

MAIN AND STANDBY GEN FAIL (IN FLIGHT)

" Page

T.O. GR1F16CJ1CL2

A16

OTHER CONSIDERATIONS:

The nonessential dc buses and essential dc bus may lose

power. If so, this results in loss of power to fuel boost and

transfer pumps, CARA, ECM, and FCR and power for normal

weapon arming/release including selective jettison.

Only if required to maintain low thrust.

The nonessential dc buses and essential dc bus lose

power. This results in loss of power to fuel boost and transfer

pumps, CARA, ECM, and FCR and power for normal weapon

arming/release including selective jettison.

If the affected systems are required for the safe recovery of

the aircraft, consider delaying/terminating EPU operation until

the systems are no longer required.

Keep thrust high enough to assure adequate bleed air if EPU

fuel usage continues above 80 percent rpm or if EPU run light

is flashing. If EPU fuel is depleted or if EPU run light goes off at

low thrust, set throttle to keep EPU run light on.

Make an approachend arrestment, if practical, if EPU fuel

depletes before landing or if EPU run light goes off at low thrust

settings. Refer to CABLE ARRESTMENT, page F11.

If PTO shaft or both hydraulic systems are failed,

underspeed of the EPU results in loss of control. Do not retard

throttle completely to IDLE until after touchdown.

If EPU underspeeds, electrical bus cycling may affect

brake operation. For a missed engagement, attempt CHAN 1

then CHAN 2 brakes. If no braking is available, consider going

around for another engagement or making a departureend

arrestment. The parking brake still operates.

A16

8 1/2 " Page

T.O. GR1F16CJ1CL2

A17

EPU MALFUNCTIONS

Uncommanded EPU Operation

If uncommanded EPU operation on bleed air is sus

pected:

1. Throttle - Min practical thrust.

2. Stores - Jettison (if required).

3. Land as soon as possible.

If EPU is running with normal indications:

4. EPU - Leave running.

5. Land as soon as possible.

6. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

Abnormal EPU Operation

If EPU was turned on for an ACFT BATT FAIL or an

FLCS RLY light:

1. EPU sw - OFF, then NORM.

2. Land as soon as possible.

3. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

If EPU was activated for other reasons:

1. Throttle - As required ( 7580 percent rpm).

2. EPU FUEL quantity - Monitor.

3. Land as soon as possible.

4. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

END

A17

8 3/4

EPU MALFUNCTIONS

" Page

T.O. GR1F16CJ1CL2

A19

Emergency Power Distribution

MAIN GENERATOR FAILED

BUS ASSIGNMENT

SYSTEM

INOPERATIVE

EQUIPMENT

NONESS AC

NACELLE

NONESS DC

EQUIPMENT

NO. 1 NO. 2 NO. 1 NO. 2

FUEL

Pumps 1,2,4 & 5

*ą

CFT Pumps

STORES MGT

AIMĆ120

***ą

STORES MGT

Stations 3, 5 & 7 - EO,

RadarĆGuided Weapons,

ECM Pods

**ą

Stations 4 & 6 - EO,

RadarĆGuided Weapons

AVIONICS

DTU

AVIONICS

FCR

Radarą

*ą

TWS

LIGHTS

Flood Console

LIGHTS

Flood Instrument

Formation

Taxi

Other

ąąASIU

*ą

ECM Control

*ą

Halon Heater

HMCS

Inlet Strut Heater

Nacelle Ejector Shutoff

Seat Adjustment

Total Temperature Probe

Heater

NOTE

Equipment on nonessential ac bus No. 1 or nonessential ac bus No. 2 may

be functional with the MAIN GEN light on (bus contactor failure).

*Aft equipment bay nonessential dc bus.

**Overcurrent sensing contactors.

***Nacelle nonessential ac bus.

A19

EMERGENCY POWER DISTRIBUTION

T.O. GR1F16CJ1CL2

A20

Emergency Power Distribution

MAIN AND STANDBY GENERATORS FAILED

(All equipment from page A19 plus the following:)

SYSTEM

INOPERATIVE

BUS ASSIGNMENT

SYSTEM

INOPERATIVE

EQUIPMENT

ESS AC

ESS DC

FUEL

Pump 3

Xą

Tank Inerting

Xą

STORES MGT

AIMĆ9

*ą

STORES MGT

Arm and Release

Power - Stations 1 Thru 9

Xą

AVIONICS

Radar Altimeter

Xą

AVIONICS

MFD's

Xą

PFLD

*ą

OTHER

Air Data Probe Heater

(fuselage)

*ą

ąąASHM

Xą

Battery Charger

Xą

Data Link

Xą

NOTE

Equipment on this sheet may operate if MAIN GEN light was caused by bus

contactor failure at nonessential bus No. 1.

*Nacelle essential ac bus.

A20

T.O. GR1F16CJ1CL2

A20.1

Emergency Power Distribution

MAIN, STANDBY, AND EPU GENERATORS FAILED

(All equipment from pages A19 and A20 plus the

following:)

INOPERATIVE

BUS ASSIGNMENT

SYSTEM

INOPERATIVE

EQUIPMENT

EMER AC

EMER DC

SYSTEM

EQUIPMENT

NO. 1 NO. 2 NO. 1 NO. 2

ENGINE

Engine ANTI ICE Sw

ENGINE

ENGINE FAULT Caution Light

Engine Ice Detector

Fire/Overheat Detect and Test

HYD PRESS Indicators

NOZ POS Indicator

OIL Pressure Indicator

FLIGHT

INSTRUMENT

ADI

FLIGHT

INSTRUMENT

Altimeter (ELECT)

AOA Indexer

AOA Indicator

HSI

Turn Needle

INSTR MODE Select Sw

VVI

FUEL

Automatic Forward Fuel

Transfer

FUEL FLOW Indicator

FUEL LOW Caution Lights

FUEL Quantity Indicator

FLT CONT

Autopilot

FLT CONT

DBU ON Warning Light

(branches A & B)

DBU ON Warning Light

(branches C & D)

FLCS FAULT Caution

Light (branches A & B)

C DF

FLCS FAULT Caution

Light (branches C & D)

FLCS RESET Switch

(branches A & B)

FLCS RESET Switch

(branches C & D)

FLCS Power Source

(branches A & B)

FLCS Power Source

(branches C & D)

FLCS Warning Light

(branches A & B)

A20.1

8 7/8 " Page

T.O. GR1F16CJ1CL2

A20.2

Emergency Power Distribution

MAIN, STANDBY, AND EPU GENERATORS FAILED - CONT

(All equipment from pages A19, A20, and A20.1 plus

the following:)

INOPERATIVE

BUS ASSIGNMENT

SYSTEM

INOPERATIVE

EQUIPMENT

EMER AC

EMER DC

SYSTEM

EQUIPMENT

NO. 1 NO. 2 NO. 1 NO. 2

FLT CONT

(Cont)

FLCS Warning Light

(branches C & D)

(Cont)

LEF's

Speedbrakes

Stick Trim

NAV/COMM

EGI

IFF

ILS

TACAN

VHF Radio

STORES MGT

ALT REL Button

CIU*

Chaff Dispenser

Gun

EMER JETT Button*

MASTER ARM Sw

MSL STEP Sw

NUCLEAR CONSENT Sw

STORES CONFIG Caution

Light

WPN REL Button

C DF

WPN REL Button

AVIONICS

CADC

AVIONICS

CADC Caution Light

HUD

HUD/CTVS

ICP/IKP

MFD Video Control

MMC*

Upfront Controls

LIGHTS

ANTICOLLISION Strobe

AR (flood)

AR (slipway)

*Indicates redundancy.

A20.2

8 7/8 " Page

T.O. GR1F16CJ1CL2

A20.3

Emergency Power Distribution

MAIN, STANDBY, AND EPU GENERATORS FAILED - CONT

(All equipment from pages A19, A20, A20.1, and

A20.2 plus the following:)

INOPERATIVE

BUS ASSIGNMENT

SYSTEM

INOPERATIVE

EQUIPMENT

EMER AC

EMER DC

SYSTEM

EQUIPMENT

NO. 1 NO. 2 NO. 1 NO. 2

LIGHTS

(Cont)

Landing

LANDING/TAXI/External Sw

MAL & IND LTS TEST/

BRT DIM

POSITION

PRIMARY CONSOLES

PRIMARY INST PNL

LG/NWS/

LG Hydraulic Isolation

BRAKES

LG Sequence (doors)

LG UPDN Command

NWS

WHEELS Down Lights

OTHER

Air Data Probe Heater

(nose)

AOA Probe Heaters

AR System

AVTR/CTVS

CABIN PRESS Caution Light

CAMERA/GUN Trigger

Cockpit Pressure Dump

Capability

Cockpit Temperature Control

Engine Bleed Air Valves

(close capacity)

EQUIP HOT Caution Light

INLET ICING Caution Light

OXY LOW Warning Light

OBOGS Caution Light

OBOGS Concentrator

OBOGS Monitor

Probe Heat Monitor

PROBE HEAT Sw

SEAT NOT ARMED

Caution Light

A20.3

8 3/4 " Page

F16C/D. FLIGHT MANUAL (2002) - page 41

F16C/D. FLIGHT MANUAL (2002) - page 41