F16C/D. FLIGHT MANUAL (2002) - page 7

T.O. GR1F16CJ1

182

Under extremely humid conditions or after initial

engine start, fog may form at the cockpit air outlets as

the cold air mixes with the moist cockpit atmosphere.

This condition can be eliminated by selecting MAN

and moving the TEMP knob toward WARM until the

fog stops forming. In flight, while operating in AUTO,

the most rapid method of eliminating air outlet

fogging is by selecting the MAX position with the

DEFOG lever. Fog may form on the interior surface of

the canopy as a result of moisture in the cockpit air

condensing on the cold surface. To warm the canopy

surface above the dewpoint and permit the cockpit air

to retain more moisture during cold weather

operation, the DEFOG lever should be placed in a

forward position and the TEMP knob positioned to

MAN WARM.

EQUIP HOT Caution Light

The EQUIP HOT caution light, located on the caution

light panel, illuminates when the avionic equipment

cooling air temperature/pressure is insufficient.

Degraded equipment performance and/or damage

can result from overheating. Therefore, when the

EQUIP HOT caution light illuminates, the electronic

equipment should be turned off unless it is essential

for flight. Illumination of the EQUIP HOT caution

light automatically interrupts electrical power to the

radar. Turning the radar to OFF in flight does not

close the radar cooling air shutoff valve.

A short duration or intermittent EQUIP HOT caution

light may occur when ground cooling air is

disconnected.

Cockpit Pressure Altimeter 

C

 

DF

The cockpit pressure altimeter, located on the right

auxiliary console outboard of the stick, is labeled

CABIN PRESS ALT.

CABIN PRESS Caution Light

The CABIN PRESS caution light, located on the

caution light panel, illuminates when the cockpit

pressure altitude is above 27,000 feet.

ANTIG SYSTEM

The antig system includes the ANTIG panel/valve,

the gsuit, and PBG equipment.

GR1F-16CJ-1-0033X37

1

1. DEFOG Lever

Defog Control Panel

(Typical)

C DF

Figure 128.

The gsuit connector and TEST button are located on

the ANTIG panel at the aft end of the left console.

The ECS delivers cooled bleed air to the gsuit and to

the oxygen regulator as a control pressure for PBG.

Airflow is proportional to the positive g forces

sensed. If an ECS shutdown occurs, gsuit and PBG

protection are not available.

The system can be manually tested by depressing

the antig TEST button to inflate the gsuit and to

check the PBG function. The system incorporates an

automatic pressure relief valve.

ELECTRICAL SYSTEM

Refer to figure 129. The electrical system consists of

a main ac power system, a standby ac power system,

an emergency ac power system, a dc power system,

an FLCS power supply, and provisions for external

ac power.

MAIN AC POWER SYSTEM

AC power is normally supplied by a 60 kva main

generator located on and driven by the ADG. The

main generator supplies power to the overcurrent

sensing contactors and nonessential, essential, and

emergency ac buses.

T.O. GR1F16CJ1

183

Overcurrent Sensing Contactors

The eight overcurrent sensing contactors protect

certain ac buses; stations 3, 5, and 7; and inlet

stations from overcurrent. The ELEC CAUTION

RESET button on the ELEC control panel is used to

reset a tripped overcurrent sensing contactor on

nonessential ac bus No. 1 and the nacelle

nonessential ac bus. The overcurrent sensing

contactor may not remain reset if the fault persists.

The items with a nonresettable overcurrent sensing

contactor are the radar ac bus; stations 3, 5, and 7;

and left and right inlet stations.

STANDBY AC POWER SYSTEM

The standby ac power system consists of the

essential and emergency ac buses and is powered (if

the main generator is inoperative) by a 10 kva

standby generator which is located on and driven by

the ADG. The standby generator has power

available whenever the ADG is rotating and comes

on line when the main generator is not supplying

power, as long as the MAIN PWR switch is in MAIN

PWR. The standby generator has an integral FLCS

PMG which supplies power to the four FLCS

branches. Refer to FLCS POWER SUPPLY, this

section, for further discussion of the FLCS PMG.

EMERGENCY AC POWER SYSTEM

If the main and standby generators fail, emergency ac

power is supplied automatically by a 

PX II

 5  kva,

PX III

 7 kva EPU generator driven by the EPU. The

system supplies power to the emergency ac buses.

The EPU generator has a PMG which supplies dc

power through an ac to dc converter to the four FLCS

branches. Refer to EMERGENCY POWER UNIT,

this section, for further discussion of the EPU.

DC POWER SYSTEM

DC power is supplied by ac to dc converters or by the

aircraft battery. With the main generator operating,

the ac to dc converters power emergency dc bus No.

1, battery bus No. 1, nonessential dc bus, nacelle dc

bus, emergency dc bus No. 2, essential dc bus, and

battery bus No. 2. With the standby generator

operating, the ac to dc converters power emergency

dc bus No. 1, battery bus No. 1, emergency dc bus No.

2, essential dc bus, and battery bus No. 2. With the

EPU generator operating, the ac to dc converters

power emergency dc bus No. 1, battery bus No. 1,

emergency dc bus No. 2, and battery bus No. 2. With

the main, standby, or EPU generator operating, the

aircraft battery is disconnected and charged by the

battery charger/control assembly. If all generators

fail, the aircraft battery is connected and powers

battery bus No. 1 and battery bus No. 2. The battery

buses are powered in all cases to provide a source of

power to the FLCS power supply (if needed) and start

power to the EPU.

FLCS POWER SUPPLY

The primary FLCS power supply includes a

dedicated FLCS PMG and two dualchannel

converter regulators and four branch power supplies

within the FLCC.

The FLCS PMG is the primary power source for the

FLCS during normal operations. The FLCS PMG is

integral with the standby generator and generates

power whenever the ADG is rotating. The PMG has

four outputs, one for each branch of the FLCS, and

generates sufficient power to operate the FLCS at 40

percent rpm or greater.

Other FLCS power sources are the main generator,

the standby generator, the EPU generator, the EPU

PMG, and the aircraft battery.

Two converter/regulators, having two channels

each, provide a separate channel for each branch of

the FLCS. Both converter/regulators receive power

from the FLCS PMG, the aircraft battery, and if the

EPU is running, the EPU PMG. The branch A and B

converter/regulator also receives power from emer

gency dc bus No. 1, and the branch C and D

converter/regulator also receives power from emer

gency dc bus No. 2. Each converter/regulator

channel converts ac power from the FLCS PMG to dc,

selects the power source with the highest voltage

(within limits), and provides dc power to the

respective FLCC branch. Converter/regulator out

put voltages are regulated to prevent overvoltage to

the FLCS. The converter/regulators also provide

fault indications for display on the ELEC control

panel and provide test indications to the TEST

switch panel.

The aircraft battery can provide temporary emer

gency power to the FLCS. The length of time that the

aircraft battery is able to power the FLCS is a

function of the state of charge. The FLCS

incorporates four latching relays which function to

prevent depletion of the aircraft battery during

ground maintenance. The relays prevent the FLCC

from being connected to the aircraft battery until a

JFS start is initiated.

T.O. GR1F16CJ1

184

F

W

D

A

C

P

W

R

P

N

L

A

F

T

E

Q

U

I

P

B

A

Y

D

C

P

W

R

P

N

L

EXTERNAL PWR

CABLE RECEPTACLE

STANDBY GENERATOR

FLCS PMG

EPU CONTROLLER

EPU GENERATOR

PMG

AC TO DC CONVERTER

A

B

CONVERTER/

REGULATOR

FLCC

AIRCRAFT BATTERY

C

D

CONVERTER/

REGULATOR

EPU

ON

STBY

ON

ADG

CSD

MAIN GENERATOR

PMG

BATTERY CHARGER, CONTROL

ASSEMBLY, AND FLCS RELAYS

MONITOR UNIT

MAIN POWER

CONTACTORS

Electrical Power Distribution Diagram

EPU ON

(EXCEPT

DURING GND

TEST) OR

STBY ON

GR1F-16CJ-1-0034-1B37

OVERCURRENT

SENSING

CONTACTORS

LEFT

INLET

RIGHT

INLET

NONESS DC

BUS

EMERGENCY

DC BUS NO. 1

NONESS AC

BUS NO. 1

EMERGENCY

AC BUS NO. 1

RADAR

AC BUS

AC TO DC CONVERTER

BATT BUS

NO. 1

Figure 129.(Sheet 1)

T.O. GR1F16CJ1

185

R

I

G

H

T

S

T

R

A

K

E

A

C

P

W

R

P

N

L

NONESS AC

BUS NO. 2

EMERGENCY

AC BUS NO. 2

ESS AC

BUS

EPU

ON

STBY

ON

R

I

G

H

T

S

T

R

A

K

E

D

C

P

W

R

P

N

L

EMERGENCY

DC BUS NO. 2

ESS DC

BUS

MAIN POWER

CONTACTORS

AC TO DC CONVERTER

BATT BUS

NO. 2

EPU ON

(EXCEPT

DURING GND

TEST)

GR1F-16CJ-1-0034-2A37

*OVERCURRENT SENSING CONTACTORS

R

I

G

H

T

N

A

C

E

L

L

E

E

Q

U

I

P

A

C

/

D

C

P

W

R

P

N

L

NACELLE NON

ESS AC BUS

NACELLE ESS

AC BUS

NACELLE

NONESS DC

BUS NO. 1

STBY

ON

NACELLE

NONESS

DC BUS

NO. 2

OVERCURRENT

SENSING

STATIONS 3, 5 & 7

B

A

Y

ELECTRICAL

MECHANICAL

RESETTABLE*
NONRESETTABLE*

LEGEND:

Can be powered by EPU

Powered thru NONESS AC

Bus No. 2
Powered thru Nacelle OCSC

Powered thru Fwd OCSC

CONTACTORS

Figure 129.(Sheet 2)

T.O. GR1F16CJ1

186

EXTERNAL POWER PROVISIONS

The external power provisions include a standard

external power cable receptacle and a monitor unit

which is part of the airframe. The monitor unit

allows external power to be connected to the aircraft

buses if the phasing, voltage, and frequency of the

external power are correct. When connected, the

external power provides the same power as the main

generator.

ELECTRICAL SYSTEM CONTROLS AND INDICA

TORS

Refer to figure 130.

ELECTRICAL POWER DISTRIBUTION

Refer to figures 131 and 132.

ELECTRICAL SYSTEM NORMAL OPERATION

Prior to engine start, the MAIN PWR switch is

placed to BATT to permit a check of the aircraft

battery. The ELEC SYS, MAIN GEN, STBY GEN,

and FLCS RLY lights come on. The FLCS RLY light

illuminates because the four FLCS relays are open

and the FLCC is not connected to the aircraft battery.

The FLCS PMG light is not illuminated since it

requires FLCS power. The ACFT BATT TO FLCS

light does not illuminate since the FLCS relays are

open. With the FLCS PWR TEST switch held in

TEST, the FLCS relays close but do not latch. The

FLCS PMG and the ACFT BATT TO FLCS lights

illuminate and the FLCS RLY light goes off. The

FLCS PWR lights on the TEST switch panel

illuminate, indicating that the power output of the

FLCC is good.

With the FLCS PWR TEST switch in NORM and the

MAIN PWR switch positioned from BATT to MAIN

PWR, the lights do not change. If external power is

connected, the MAIN GEN light goes off.

If the FLCS PWR TEST switch is placed to TEST

with the MAIN PWR switch in MAIN PWR, the

FLCS relays are latched closed. The FLCS RLY light

remains off when the FLCS PWR TEST switch is

returned to NORM. The aircraft battery is now

powering the FLCC and depletes more rapidly. To

eliminate the increased battery load, cycle the MAIN

PWR switch to BATT and back to MAIN PWR to open

the FLCS relays (FLCS RLY light illuminates).

When the JFS switch is moved to either start

position, the FLCS PMG light (and ACFT BATT TO

FLCS light if engine is started on battery power)

illuminates and the FLCS RLY light goes off,

indicating that the FLCS relays have closed.

During engine start, the FLCS PMG light (and

ACFT BATT TO FLCS light if engine is started on

battery power) goes off at approximately 

PW 229

 40,

129

GE

 44 percent engine rpm. The STBY GEN light

goes off at approximately 

PW 229

 55, 

129

GE

 60

percent engine rpm; the MAIN GEN light goes off

approximately 10 seconds later if both generators

are operating normally. External power, if used, is

disconnected from the aircraft buses when the main

generator comes on line.

Anytime after selecting MAIN PWR, including in

flight, the FLCS PWR TEST switch may be held

momentarily in TEST to check FLCC power output.

During the EPU test, the FLCS PWR lights come on

to indicate that EPU PMG power is available to the

FLCS.

During engine shutdown, the ELEC SYS caution

light and FLCS PMG, MAIN GEN, and STBY GEN

lights come on as the engine spools down. The ACFT

BATT TO FLCS light also illuminates.

T.O. GR1F16CJ1

187

GR1F-16CJ-1-0035X37

10

7

8

MAIN PWR Switch

FLCS PMG Indicator Light

MAIN GEN Indicator Light

STBY GEN Indicator Light

EPU GEN Indicator Light

EPU PMG Indicator Light

ACFT BATT Indicator Lights

ELEC SYS Caution Light

ELEC CAUTION RESET Button

FLCS PWR TEST Switch

FLCS PWR Indicator Lights

9

Electrical System Controls and Indicators

(Typical)

C DF

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

11

2

1

3
4

5
6

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

1. MAIN PWR Switch

NOTE:

During ground operation, if

the MAIN PWR switch is

d f

MAIN PWR t

MAIN PWR

Connects external power or the main genera

tor to the electrical system and enables

standby generator. Determines function of

FLCS PWR TEST switch. If ac power is not

available, connects aircraft battery to the

battery buses

moved from MAIN PWR to

OFF without a delay of 1 se

cond in BATT, the EPU does

not activate and electrical

power for braking, NWS,

hook, and radios is lost.

BATT

Connects aircraft battery to the battery

buses, disconnects main generator or exter

nal power, resets main generator, disables

standby generator, and determines function

of FLCS PWR TEST switch

,

OFF

In flight-disconnects main generator from

electrical system and disables standby gener

ator

On ground-disconnects main generator or

external power from aircraft electrical sys

tem and disables standby generator. Discon

nects the aircraft battery from the battery

buses. Canopy operation is available after

engine shutdown

Figure 130.(Sheet 1)

T.O. GR1F16CJ1

188

Electrical System Controls and Indicators

C

 

DF

 (Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

2. FLCS PMG Indicator Light

FLCS PMG (amber)

In flight-None of the FLCS branches are

receiving power from the FLCS PMG

On ground-FLCS PMG power is not avail

able at one or more FLCS branches. Light is

delayed 60 seconds after initial NLG WOW

3. MAIN GEN Indicator Light

MAIN GEN (amber)

Indicates external power or main generator

not connected to one or both nonessential ac

buses

4. STBY GEN Indicator Light

STBY GEN (amber)

Indicates standby generator power is not

available

5. EPU GEN Indicator Light

EPU GEN (amber)

Indicates the EPU has been commanded on

but the EPU generator is not providing power

to both emergency ac buses. The light does

not function with the EPU switch in OFF

(WOW) and the engine running

6. EPU PMG Indicator Light

EPU PMG (amber)

Indicates the EPU has been commanded on

but EPU PMG power is not available to all

branches of the FLCS

7. ACFT BATT Indicator

Lights

FAIL (amber)

In flight-indicates aircraft battery failure

(20V or less)

On ground-indicates aircraft battery or bat

tery charger failure. Light is delayed 60

seconds after MLG WOW

TO FLCS (amber)

In flight-indicates battery bus power is

going to one or more FLCS branches and volt

age is 25V or less

On ground-indicates battery bus power is

going to one or more FLCS branches

FLCS RLY (amber)

Indicates that voltage on one or more of the

four FLCC branches connected to the aircraft

battery is inadequate (below 20V) or that one

or more FLCC branches are not connected to

the battery

Figure 130.(Sheet 2)

T.O. GR1F16CJ1

189

Electrical System Controls and Indicators

C

 

DF

 (Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

8. ELEC SYS Caution Light

ELEC SYS (amber)

Illuminates in conjunction with any of the

above lights

9. ELEC CAUTION RESET

Button

Push

Resets resettable overcurrent protection

units and ELEC SYS caution light and clears

MASTER CAUTION light for future indica

tions. Resets main and standby generators

10. FLCS PWR TEST Switch

TEST

When MAIN PWR switch is in:

MAIN PWR

BATT

Tests FLCC power

output

Tests FLCC power

output on aircraft

battery

NORM

Normal position.

Tests EPU PMG

power availability

during EPU/GEN

test on ground

NA

MAINT

For maintenance use on the ground. Inopera

tive in flight

11. FLCS PWR Indicator Lights

A, B, C, and D (green)

Illuminate to indicate proper power output of

FLCC during FLCS power tests

Figure 130.(Sheet 3)

T.O. GR1F16CJ1

190

AC Power Distribution Diagram

EPU

ON

MAIN GENERATOR

ESSENTIAL AC BUS

EPU GENERATOR

EMERGENCY AC BUS NO. 2

GR1F-16CJ-1-1154-1A37

Battery Charger Power

ADI

Anticollision Light

AR Light (flood)

Fuel Quantity Indicator

Gun

HSI

LIQUID OXYGEN

 Quantity Indicator

NOZ POS Indicator

Oil Pressure Indicator

Position Lights

HUD/CTVS

Data Transfer Unit

Flood Console Lights

Flood Instrument Lights

Formation Lights

Sta 4 & 6 - EO &

Taxi Light

 Radar-Guided Weapons

NONESSENTIAL AC BUS NO. 2

Halon Heater

Engine Ice Detector

Fire/Overheat Detect & Test

Landing Light

TACAN

DF

C

Fuel Pumps 1, 2, 4 & 5

Inlet Strut Heater

Fuel Pump No. 3

MFD's

HYD PRESS Indicators

STBY

ON

STBY GENERATOR

PX II

Upfront Controls

Figure 131.(Sheet 1)

T.O. GR1F16CJ1

191

EMERGENCY AC BUS NO. 1

ELECTRICAL

MECHANICAL

RESETTABLE
NONRESETTABLE

LEGEND:

Can be powered by EPU
Powered thru NONESS AC Bus No. 2
Powered thru Nacelle OCSC
Powered thru Fwd OCSC

GR1F-16CJ-1-1154-2A37

Air Data Probe Heater

 (nose)

Altimeter (ELECT)

AOA Indicator

AOA Probe Heaters

DED

FUEL FLOW Indicator

INS

LEF's

Low Energy Ignition

 System

Primary Console Lights

Primary Instrument Lights

VVI

CADC

NACELLE NONESSENTIAL AC BUS

NACELLE ESSENTIAL AC BUS

Sta 3

Sta 5

Sta 7

FCR BUS

Sta 3, 5, & 7 - ECM, EO &

 Radar-Guided Weapons

FCR

LEFT

RIGHT

INLET

INLET

OVERCURRENT SENSING CONTACTORS

EPU

ON

NONESSENTIAL AC BUS NO. 1

AIM-9/AIM-120

STBY

ON

ECM Aft Xmit

GPS

Seat Adjustment

Air Data Probe Heater

 (fuselage)

PFLD

AIM-9/AIM-120

Sta 3

Sta 5

Sta 7

Nacelle

OVERCURRENT SENSING CONTACTORS

FCR

Fwd

Left

Right

Total Temperature

 Probe Heater

TWS

STBY

ON

ECM Prcs

FCC

STBY

ON

Figure 131.(Sheet 2)

T.O. GR1F16CJ1

192

DC Power Distribution Diagram

EMERGENCY AC BUS NO. 1

EMERGENCY DC BUS NO. 1

GR1F-16CJ-1-1155-1A37

ALT REL Button

AOA Indexer

CIU

ECM Control

 (branches A & B)

FUEL LOW Caution Lights

FLCS Power Source

CADC Caution Light

Cockpit Temp Control

C

DBU ON Warning Light

IFF

INSTR MODE Select

AC TO DC CONVERTER

MSL Step Switch

INS

ECM Fwd Xmit

Antiskid/Chan 1

 Brakes

CANOPY Warning

 Light

Cockpit Spotlights

MLG WOW

 (branches A & B)

NLG WOW

 (branches A & B)

RPM Indicator

BATTERY BUS NO. 1

Drag Chute

UHF Radio

Utility Light

VMS

NONESSENTIAL DC BUS

NACELLE NONESS DC BUS NO. 1

EPU ON

(EXCEPT

DURING GND

TEST) OR

STBY ON

BATTERY

 (branches A & B)

EMER JETT Button

 (branches A & B)

FLCS Reset Switches

 (branches A & B)

FLCS Warning Light

 Light (branches A & B)

FLCS FAULT Caution

DF

C

LG DOWN Permission Button

LG WHEELS Down Lights

MAL & IND LTS Test/BRT/

MASTER ARM Switch

 DIM Feature

NWS/AR System

Probe Heat Monitor

PROBE HEAT Switch

Speedbrakes

Stick Trim

WPN REL Button

DR

Turn Needle

TACAN

OCSC Trip

NACELLE NONESSENTIAL DC BUS NO. 2

FUEL/OIL HOT Caution

 Light (oil hot signal)

Nacelle Ejector Shutoff

AIBU

ECM Aft Xmit

EMSC

ECM TBRF

ECM Prcs

FCR

Fuel Pumps 1, 2 & 4

VHF Radio

ENGINE Warning Light

EPU

HYD/OIL PRESS

 Warning Light

Intercom

JFS

LG Downlock Relays

 (WHEELS down lights)

LG Uplock/Downlock

Master Caution

FTIT Indicator

FLCS (branches A & B)

TWS

PX II

Figure 131.(Sheet 3)

T.O. GR1F16CJ1

193

EMERGENCY AC BUS NO. 2

EMERGENCY DC BUS NO. 2

GR1F-16CJ-1-1155-2A37

FLCS Power Source

 (branches C & D)

FLCS Reset Switch

FLCS Warning Light

 (branches C & D)

 (branches C & D)

AC TO DC CONVERTER

 Light

FUEL/OIL HOT Caution

EPU FUEL Quantity

 Indicator

ENGINE FIRE Warning

 Light

BATTERY BUS NO. 2

FLCS (branches C & D)

Electrical Throttle

 Position

ELEC SYS Caution Light

OVERHEAT Caution

 Light

ESSENTIAL DC BUS

EPU ON

(EXCEPT

DURING

GND TEST)

LEGEND:

Can be powered by EPU

Powered thru NONESS AC Bus No. 2

EPU

Parking Brake

SAI

HUD

Gun

* Power available from the battery bus box with MAIN PWR switch OFF.

ANTI ICE Switch

AR System Lights

Auto Fwd Fuel Trans

Autopilot

AVTR

 Light

CABIN PRESS Caution

CAMERA/GUN Trigger

Chaff/Flare Dispensers

*Canopy Actuator

DBU ON Warning Light

 (branches C & D)

EMER JETT Button

Engine Bleed Air Valves

ENGINE FAULT Caution Light

FLCS FAULT Caution

EQUIP HOT Caution Light

 Light (branches C & D)

DR

Altimeter (PNEU)

Antiskid/Chan 2 Brakes

DEC

SEC Caution Light

OCSC Trip

Data Link

CIU

Cockpit Pressure Dump

NLG WOW (branches

 C & D)

Powered thru Fwd OCSC

ELECTRICAL

MECHANICAL

 (close capability)

ILS

LANDING/TAXI/EXT

 Light Switches

INLET ICING Caution

 Light

ICP/IKP

WPN REL Button

DF

C

LG Door Close

LG Hyd Isolation

LG UP-DN Command

NUCLEAR CONSENT Switch

MASTER ARM Switch

OXY LOW Caution Light

MFD Video Control

STORES CONFIG Caution

SEAT NOT ARMED

 Light

 Caution Light

LEF Asymmetry Brake

FUEL MASTER Switch

GCU's (main/standby)

Hook

LG Warning Light (handle)

MLG WOW (branches

 C & D)

ZEROIZE Switch

Fuel Pumps 3 & 5

Radar Altimeter

 ARM/Release

Stations 1, 2, 3, 3A, 4,

 5, 6, 7, 7A, 8 & 9

Tank Inerting

Upfront Controls

Figure 131.(Sheet 4)

T.O. GR1F16CJ1

194

AC Power Distribution Diagram

EPU

ON

MAIN GENERATOR

ESSENTIAL AC BUS

EPU GENERATOR

EMERGENCY AC BUS NO. 2

GR1F-16CJ-1-2154-1X37

Battery Charger Power

ADI

Anticollision Light

AR Light (flood)

Fuel Quantity Indicator

Gun

HSI

NOZ POS Indicator

OBOGS Concentrator

HUD/CTVS

ECM Aft Transmitter

Flood Console Lights

Flood Instrument Lights

Formation Lights

Sta 4 & 6 - EO &

Taxi Light

 Radar-Guided Weapons

NONESSENTIAL AC BUS NO. 2

Halon Heater

Engine Ice Detector

Fire/Overheat Detect & Test

Landing Light

Fuel Pumps 2 & 4

Inlet Strut Heater

Fuel Pump No. 3

MFD's

HYD PRESS Indicators

STBY

ON

STBY GENERATOR

PX III

Data Transfer Unit

CFT Fuel Transfer Pumps

DTC

EGI

Oil Pressure Indicator

NAV/Position Lights

TISL

Figure 132.(Sheet 1)

T.O. GR1F16CJ1

195

EMERGENCY AC BUS NO. 1

ELECTRICAL

MECHANICAL

RESETTABLE
NONRESETTABLE

LEGEND:

Can be powered by EPU
Powered thru NONESS AC Bus No. 2
Powered thru Nacelle OCSC
Powered thru Fwd OCSC

GR1F-16CJ-1-2154-2X37

Altimeter (ELECT)

AOA Indicator

AOA Probe Heaters

FUEL FLOW Indicator

LEF's

Pitot Static Probe Heater

Primary Console Lights

Primary Instrument Lights

Upfront Controls

CADC

NACELLE NONESSENTIAL AC BUS

NACELLE ESSENTIAL AC BUS

Sta 3

Sta 5

Sta 7

FCR BUS

Sta 3, 5, & 7 - ECM, EO &

 Radar-Guided Weapons

FCR

LEFT

RIGHT

INLET

INLET

OVERCURRENT SENSING CONTACTORS

EPU

ON

NONESSENTIAL AC BUS NO. 1

AIM-9/AIM-120

STBY

ON

ECM Fwd Transmitter

Seat Adjustment

Air Data Probe Heater

 (fuselage)

PFLD

AIM-9/AIM-120

Sta 3

Sta 5

Sta 7

Nacelle

OVERCURRENT SENSING CONTACTORS

FCR

Fwd

Left

Right

Total Temperature

 Probe Heater

TWS

STBY

ON

ECM Processor

STBY

ON

EGI (GPS)

VVI

HMCS

MMC (Side A)

Figure 132.(Sheet 2)

T.O. GR1F16CJ1

196

DC Power Distribution Diagram

EMERGENCY AC BUS NO. 1

EMERGENCY DC BUS NO. 1

GR1F-16CJ-1-2155-1X37

ALT REL Button

AVTR Switch

 (branches A & B)

FUEL LOW Caution Lights

FLCS Power Source

CADC Caution Light

Cockpit Temp Control

C

DBU ON Warning Light

IFF

AC TO DC CONVERTER

OBOGS Monitor

Antiskid/Chan 1

 Brakes

CANOPY Warning

 Light

MLG WOW

 (branches A & B)

NLG WOW

 (branches A & B)

RPM Indicator

BATTERY BUS NO. 1

Drag Chute

UHF Radio

Utility Light

VMS

NONESSENTIAL DC BUS

NACELLE NONESS DC BUS NO. 1

EPU ON

(EXCEPT

DURING GND

TEST) OR

STBY ON

BATTERY

 (branches A & B)

EGI

 (branches A & B)

FLCS Reset Switches

 (branches A & B)

FLCS Warning Light

 Light (branches A & B)

FLCS FAULT Caution

DF

C

LG DOWN Permission Button

LG WHEELS Down Lights

MAL & IND LTS Test/BRT/

MASTER ARM Switch

 DIM Feature

NWS/AR System

Probe Heat Monitor

PROBE HEAT Switch

Speedbrakes

Stick Trim

WPN REL Button

DR

VHF Radio

TACAN

OCSC Trip

NACELLE NONESSENTIAL DC BUS NO. 2

MFD Heater

ENGINE Warning Light

EPU

HYD/OIL PRESS

 Warning Light

Intercom

JFS

LG Downlock Relays

 (WHEELS down lights)

LG Uplock/Downlock

Master Caution

FTIT Indicator

TWS

PX III

AOA Indexer

MMC (Side A)

ASIU

AVTR Heater

ECM Control

ECM Fwd Transmitter

ECM Processor

FCR

Fuel Pumps 1, 2 & 4

ECM Aft Transmitter

MAX POWER Switch

Nacelle Ejector Shutoff

TGP (right inlet power and control)

TISL

D

EMER JETT Button

MSL Step Switch

Figure 132.(Sheet 3)

T.O. GR1F16CJ1

Change 1197

EMERGENCY AC BUS NO. 2

EMERGENCY DC BUS NO. 2

GR1F-16CJ-1-2155-2X37

FLCS Power Source

 (branches C & D)

FLCS Reset Switch

FLCS Warning Light

 (branches C & D)

 (branches C & D)

AC TO DC CONVERTER

EPU FUEL Quantity

 Indicator

ENGINE FIRE Warning

 Light

BATTERY BUS NO. 2

CSFDR

EDU

ELEC SYS Caution Light

OVERHEAT Caution

 Light

ESSENTIAL DC BUS

EPU ON

(EXCEPT

DURING

GND TEST)

LEGEND:

Can be powered by EPU

Powered thru NONESS AC Bus No. 2

EPU

Parking Brake

SAI

HUD

Gun

* Power available from the battery bus box with MAIN PWR switch OFF.

ANTI ICE Switch

AR System Lights

Auto Fwd Fuel Trans

Autopilot

AVTR

 Light

CABIN PRESS Caution

CAMERA/GUN Trigger

Chaff/Flare Dispensers

*Canopy Actuator

DBU ON Warning Light

 (branches C & D)

EMER JETT Button

Engine Bleed Air Valves

ENGINE FAULT Caution Light

FLCS FAULT Caution

EQUIP HOT Caution Light

 Light (branches C & D)

DR

Altimeter (PNEU)

Antiskid/Chan 2 Brakes

OCSC Trip

Aft Seat Hud Monitor

Data Transfer Unit

NLG WOW (branches

 C & D)

Powered thru Fwd OCSC

ELECTRICAL

MECHANICAL

 (close capability)

ILS

LANDING/TAXI/EXT

 Light Switches

INLET ICING Caution

 Light

ICP/IKP

WPN REL Button

DF

C

LG Door Close

LG Hyd Isolation

LG UP-DN Command

NUCLEAR CONSENT Switch

MASTER ARM Switch

OXY LOW Warning Light

MFD Video Control

STORES CONFIG Caution

SEAT NOT ARMED

 Light

 Caution Light

LEF Asymmetry Brake

FUEL MASTER Switch

GCU's (main/standby)

Hook

LG Warning Light (handle)

MLG WOW (branches

 C & D)

ZEROIZE Switch

Fuel Pumps 3 & 5

NVP (left inlet

 ARM/Release

Stations 1, 2, 3, 3A, 4,

 5, 6, 7, 7A, 8 & 9

Tank Inerting

Cockpit Pressure Dump

MMC (side B)

OBOGS Caution Light

Upfront Controls

Data Link

power and control)

Radar Altimeter

D

Antiskid/Chan 2 Brakes

Figure 132.(Sheet 4)