F16C/D. FLIGHT MANUAL (2002) - page 40

T.O. GR1F16CJ1CL2

EP8

Pilot Fault List FLCS

(FLCS warning light illuminated)

FAULT

CAUSE

CORRECTIVE

ACTION/REMARKS

FLCS AOA WARN

Dual AOA failure

Refer to AOA 

MALFUNCTION,

page B5

FLCS DUAL FAIL

Dual electronic,

sensor, or power

failure in one or

more axes

Refer to FLCS DUAL

ELECTRONIC FAILURE,

page B15

FLCS LEF LOCK

LEF's are locked

due to multiple

failures, LE FLAPS

switch position, or

asymmetry

Refer to LEF MAL

FUNCTION, page

B11 and B13

STBY GAIN

Dual air data 

failure

Refer to AIR DATA

MALFUNCTIONS,

page B9

FLCS BIT FAIL

FLCS BIT has

detected a failure

Perform a second

FLCS BIT. If fault does

not clear, notify main

tenance. Fault only

occurs on ground

T.O. GR1F16CJ1CL2

EP9

Pilot Fault List   FLCS

(TF FAIL warning light illuminated)

FAULT

CAUSE

CORRECTIVE

ACTION/REMARKS

SWIM NVP FAIL

NVP data bad,

AMUX wraparound

failure, NVP self

mode failure, or

cyclic test problem

monitor failure

Refer to TF FAIL

WARNING LIGHT,

Page B21

SWIM RALT FAIL

SDC monitor fail

ure or CARA data

bad

SWIM SCP FAIL

Below set clear

ance failure

SWIM ATTD FAIL

INS attitude esti

mator failure

SWIM ATF FAIL

NVP ATF select

failure

SWIM VEL FAIL

GPS/INS failure

T.O. GR1F16CJ1CL2

EP10

Pilot Fault List   FLCS

(FLCS FAULT caution light illuminated for all)

FAULT

CAUSE

CORRECTIVE

ACTION/REMARKS

FLCS ADC FAIL

First failure of tri

plex air data input

signal

Refer to AIR DATA

MALFUNCTIONS,

page B9

FLCS AOA FAIL

First failure of tri

plex AOA input

signal

Refer to AOA 

MALFUNCTION,

page B5

FLCS AOS FAIL

AOS feedback

function is inop

erative due to 

failure

Perform FLCS reset to

attempt to clear fault;

fault cannot be reset

if INS or CADC is

failed
If fault does not clear,

the autopilot cannot

be engaged. Position

the STORES CONFIG

sw to CAT III if the

aircraft is configured

with a      GP/STORE/

LINE loading*

33

FLCS FLUP OFF

MANUAL TF FLYUP

sw moved to DIS

ABLE

FLCS BIT detects

MANUAL TF FLYUP

sw in  DISABLE

Position the MANUAL

TF FLYUP sw as re

quired. A FLCS reset

extinguishes FLCS

FAULT caution  light

Position MANUAL TF

FLYUP sw to ENABLE.

Rerun FLCS BIT

FLCS A/P DEGR

Autopilot operat

ing outside of atti

tude limits or

unable to hold

commanded mode

Autopilot is 

inoperative

NOTE:

*The potential for a departure from controlled flight is signifi

cantly increased if the AOS feedback function is inoperative and

maneuvering with     GP/STORE/LINE loadings occurs with the

STORES CONFIG sw in CAT I.

33

T.O. GR1F16CJ1CL2

EP11

Pilot Fault List   FLCS

(FLCS FAULT caution light illuminated for all except FLCS BUS

FAIL)

FAULT

CAUSE

CORRECTIVE

ACTION/REMARKS

FLCS A/P FAIL

Autopilot has dis

connected or can

not be engaged

due to loss of

needed data

Autopilot is 

inoperative

FLCS BUS FAIL

Communication

lost between FLCC

and MUX bus

Illuminates AVIONICS

FAULT caution light.

Other FLCS PFL's may

not be displayed on

the PFLD. Refer to

FLCS page on MFD for

FLCS PFL's

BRK PWR DEGR

Power supply 

failure detected 

in one or more

branches

Refer to FLCS SINGLE

ELECTRONIC FAILURE,

page B15

FLCS CCM FAIL

Erroneous output

command detected

by CCM

Refer to FLCS SINGLE

ELECTRONIC FAILURE,

page B15

FLCS HOT TEMP

FLCC sensors

detect two

branches in excess

of 75

°

C

Refer to FLCS

TEMPERATURE

MALFUNCTIONS,

page B13

ISA ALL FAIL

Two or more ISA's

have reported a

first servo valve

failure

Refer to SERVO MAL

FUNCTION, page

B17

T.O. GR1F16CJ1CL2

EP12

Pilot Fault List   FLCS

(FLCS FAULT caution light illuminated for all)

FAULT

CAUSE

CORRECTIVE

ACTION/REMARKS

ISA LHT FAIL

ISA RHT FAIL

ISA LF FAIL

ISA RF FAIL

ISA RUD FAIL

Indicated ISA has

reported a first

servo valve failure

Refer to SERVO

MALFUNCTION,

page B17

FLCS SNGL FAIL

Indicates single

electronic or sen

sor failure in one

or more axes

Notify maintenance.

Fault only occurs on

ground

FLCS MUX DEGR

BIT detected deg

radation of FLCC

MUX interface

FLCS reset will not

clear fault. Perform a

second FLCS BIT. If

fault does not clear

and no other faults

are reported, the sys

tem redundancy is

adequate for flight.

Notify maintenance

after flight. Fault only

occurs on ground

ELEC

A

T.O. GR1F16CJ1CL2

A1

GLOSSARY

Dash line indicates light may be

on or off

GEN

MAIN

PMG

FLCS

ELEC

A

T.O. GR1F16CJ1CL2

A2

Electrical System Failures

PARTIAL ELECTRICAL POWER LOSS

A7

. . . . . . . . . . . . . . . . . . 

Refer to ELEC control panel.

ACFT BATTERY FAILURE

A9

. . . . . . . . . . . . 

FLCS  RLY LIGHT

A11

. . . . . . . . . . . . . . . . 

EPU MALFUNCTIONS

A17

. . . . . . . . . . . . 

AND 

EPU RUN LIGHT 

OFF OR FLASHING

FLCS PMG FAILURE

A9

. . . . . . . . . . . . . . . . 

MAIN AND STANDBY 

                             GENERATOR FAILURE

AND

(GROUND)

A5

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

(IN FLIGHT)

A15

. . . . . . . . . . . . . . . . . . 

ELEC

SYS

ACFT BATT

FAIL

RLY

FLCS

AIR

HYDRAZN

PMG

FLCS

GEN

MAIN

GEN

STBY

T.O. GR1F16CJ1CL2

A3

AND EPU RUN LIGHT OFF

MAIN, STANDBY, AND EPU 

GENERATOR FAILURE

A13

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

PTO SHAFT FAILURE

GO TO TAB D

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

GEN

MAIN

OR

GEN

STBY

OR

PMG

FLCS

AND

GEN

STBY

SINGLE GENERATOR FAILURE (IN FLIGHT)

A11

. . . . . . . . . 

EMERGENCY POWER DISTRIBUTION

A19

. . . . . . . . . . . . . . . 

GEN

MAIN

PMG

FLCS

GEN

STBY

EPU PMG

EPU GEN

FAIL

TO FLCS

ACFT BATT

A3

7 " Page

T.O. GR1F16CJ1CL2

A4

OTHER CONSIDERATIONS:

1

 Turn EPU on, if required, to obtain NWS.

2

C

 If chocks are not installed, be prepared to immediately

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

off.

3

 Toe brakes and parking brake are available with or without

the EPU as long as the MAIN PWR sw is not moved to OFF.

4

C

 If main or standby generator cannot be reset, NWS is

inoperative unless the EPU is activated.

A4

7 " Page

T.O. GR1F16CJ1CL2

A5

MAIN AND STANDBY GENERATOR FAILURE

(GROUND)

If MAIN GEN and STBY GEN lights illuminate:

1. Stop the aircraft. 

1

2. ANTISKID sw - PARKING BRAKE.

3. OXYGEN - 100%.

4. EPU sw - OFF. 

2

C

If further taxiing is required:

5. ELEC CAUTION RESET button - Depress. 

3

4

C

6. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

END

A5

7 1/4

MAIN AND STANDBY GEN FAIL (GROUND)

" Page

T.O. GR1F16CJ1CL2

A6

OTHER CONSIDERATIONS:

1

 The failed open OCSC may reset.

2

Refer to the following diagram to determine the power

status of individual buses. If one item on a bus is powered, then

that bus should be considered powered.

EMER AC BUS NO. 1

NONESS AC BUS NO.1

EMER DC BUS NO. 1

BATTERY

AIRCRAFT

EMER DC BUS NO. 2

EMER AC BUS NO. 2

MAIN

GEN

EPU

GEN

STBY

GEN

NONESS AC BUS NO.2

ESS AC BUS

TWS

Seat Adjustment

FLOOD Instrument/

 Console Lights

MFD's (off)

AOA Indicator (off)

FUEL FLOW (frozen)

VVI (off)

HSI (off flag)

HYD PRESS (frozen)

OIL Pressure (frozen)

Critical items lost:

D

CADC

Critical items lost:

D

ADI, HSI, Fuel

Quantity

AOA Indexer

Speedbrakes

D

LG WHEELS

Critical items lost:

D

LG DOWN

BATT BUS NO. 1

BATT BUS NO. 2

Permission Button

button required)

Down Lights

D

TACAN

Autopilot

HUD

D

ILS

Critical items lost:

D

LG UPDN

Command (ALT

GEAR extension

SEAT NOT ARMED

 Caution Light

Intercom*

UHF Radio

RPM (indicates < zero)

D

LG WHEELS

Critical items lost:

D

Channel 1 Brakes

EPU Fuel (indicates

 < zero)

SAI (off flag)

D

HOOK

Critical items lost:

FTIT (indicates < 200)

Down Lights

D

LGWarning Light

(handle)

*VHF radio is also inoperative because

required)

(DN LOCK REL

the ability to key either radio is lost.

D

Drag Chute

HMCS

D

EGI

D

TACAN

VHF Radio

D

Parking Brake

3

Determining the status of the battery buses is critical for a

safe recovery of the aircraft.

A6

7 1/4 " Page

T.O. GR1F16CJ1CL2

A7

PARTIAL ELECTRICAL POWER LOSS

1. ELEC CAUTION RESET button-Depress.

1

If power is restored:

2. Land as soon as practical.

If power is not restored:

2. Determine the power status of electrical buses. 

2

3

(Cont)

A7

7 1/2

PARTIAL ELECTRICAL POWER LOSS

" Page

T.O. GR1F16CJ1CL2

A8

OTHER CONSIDERATIONS:

4

 

F

 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.

F

 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.

5

 If power to the battery buses is lost after the landing gear has

been extended, the landing gear cannot be raised.

A8

7 1/2 " Page

T.O. GR1F16CJ1CL2

A8.1

If one or both emergency ac buses are not powered: 

3. EPU sw - ON. 

4

If the battery buses and emergency dc bus No. 2 are not

powered:

4. Consider a net arrestment, refer to NET

ARRESTMENT, page F11.

If net arrestment is not available:

5. Consider a gear up landing, refer to LANDING

WITH LG UNSAFE/UP, page E15. 

5

6. Refer to EMERGENCY POWER DISTRIBUTION,

page A19.

7. Land as soon as possible.

If EPU was activated:

8. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

END

A8.1

7 3/8 " Page

T.O. GR1F16CJ1CL2

A8.2

OTHER CONSIDERATIONS:

1

C

 If the aircraft battery fails (and EPU is off), do not taxi

except to clear runway. Subsequent loss of the main and

standby generators results in loss of all braking, NWS, hook,

and radios.

2

F

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.

F

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.

F

 If both radios become inoperative after an aircraft battery

failure indication, refer to PARTIAL ELECTRICAL POWER LOSS,

page A7.

F

The ACFT BATT FAIL light may subsequently extinguish. This

should not be interpreted to mean that the battery has

recharged. It may indicate that the battery voltage is so low that

the light cannot remain illuminated.

A8.2

7 3/8 " Page

T.O. GR1F16CJ1CL2

A9

AIRCRAFT BATTERY FAILURE

1

C

1. EPU sw - ON.

2

2. Land as soon as practical.

3. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

If EPU runs abnormally:

4. EPU sw - OFF, then NORM.

5. Land as soon as possible.

6. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

Prior to shutdown:

7. Loose items - Secure.

8. Canopy - Open.

FLCS PMG FAILURE

If FLCS PMG light illuminates:

1. Land as soon as practical.

END

A9

7 3/4

ACFT BATT FAIL/FLCS PMG FAIL

" Page