F16C/D. FLIGHT MANUAL (2002)

T.O. GR1F16CJ1

GR1F-16CJ-1-1107X37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

Is EPU

run light

on?

Is ELEC

SYS caution

light on?

Low pressure in one or both hydraulic

systems, low engine oil pressure, or low

oil pressure switch failure

Check pressure indicators to determine sys-

tem and condition

Refer to:

OIL SYSTEM MALFUNCTION

HYDRAULIC MALFUNCTIONS

CHECK OIL AND

HYD PRESS

INDICATORS

OIL PRESSURE

NORMAL

OIL PRESSURE

SWITCH FAILURE

MONITOR

OIL PRESSURE

INDICATOR

REFER TO

SYSTEM A

FAILURE

REFER TO

SYSTEM B

FAILURE

REFER TO DUAL

HYDRAULIC

FAILURE

PTO SHAFT

FAILURE

DUAL HYDRAULIC

FAILURE

SYSTEM A

HYDRAULIC

FAILURE

SYSTEM A

HYD PRESS

INDICATOR ONLY

BELOW 1000 PSI

ENGINE OIL

SYSTEM MAL-

FUNCTION, MINI-

MIZE THROTTLE

MOVEMENT.

LAND AS SOON

AS POSSIBLE

OIL PRESSURE

BELOW 15 PSI

SYSTEM B

HYD PRESS

INDICATOR ONLY

BELOW 1000 PSI

SYSTEM B

HYDRAULIC

FAILURE

REFER TO SYSTEM B

AND MAIN GENERATOR

FAILURE (PTO SHAFT)

YES

OIL

HYD

EJECT

BOTH HYD PRESS

INDICATORS BE-

LOW 1000 PSI

WITH EPU SWITCH

IN NORM OR ON

TOTAL HYDRAULIC FAILURE

(EPU MAY STILL RUN AND

POWER THE EPU GENERATOR,

BUT EPU RUN LIGHT DOES

NOT ILLUMINATE UNLESS

SYSTEM A IS RESTORED)

PRESS

HYD/OIL

PRESS

HYD/OIL

REFER TO OIL

SYSTEM

MALFUNCTION

PW229

Figure 31.(Sheet 2)

T.O. GR1F16CJ1

GR1F16CJ10107A37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

Is EPU

run light

on?

Is ELEC

SYS caution

light on?

Low pressure in one or both hydraulic

systems, low engine oil pressure, or low

oil pressure switch failure

Check pressure indicators to determine sys-

tem and condition

Refer to:

OIL SYSTEM MALFUNCTION

HYDRAULIC MALFUNCTIONS

CHECK OIL AND

HYD PRESS

INDICATORS

OIL PRESSURE

NORMAL

LOW OIL

PRESSURE

SWITCH

FAILURE

REFER TO

SYSTEM B

FAILURE

REFER TO DUAL

HYDRAULIC

FAILURE

PTO SHAFT

FAILURE

DUAL HYDRAULIC

FAILURE

SYSTEM A

HYDRAULIC

FAILURE

SYSTEM A

HYD PRESS

INDICATOR ONLY

BELOW 1000 PSI

ENGINE OIL

SYSTEM MAL-

FUNCTION, MINI-

MIZE THROTTLE

MOVEMENT.

LAND AS SOON

AS POSSIBLE

OIL PRESSURE

BELOW 15 PSI

SYSTEM B

HYD PRESS

INDICATOR ONLY

BELOW 1000 PSI

SYSTEM B

HYDRAULIC

FAILURE

REFER TO SYSTEM B

AND GENERATOR

FAILURE (PTO SHAFT)

YES

OIL

HYD

MONITOR OIL

PRESSURE

INDICATOR

REFER TO

SYSTEM A

FAILURE

MONITOR NOZ

POS INDICATOR

EJECT

BOTH HYD PRESS

INDICATORS BE-

LOW 1000 PSI

WITH EPU SWITCH

IN NORM OR ON

TOTAL HYDRAULIC FAILURE

(EPU MAY STILL RUN AND

POWER THE EPU GENERATOR,

BUT EPU RUN LIGHT DOES

NOT ILLUMINATE UNLESS

SYSTEM A IS RESTORED)

PRESS

HYD/OIL

PRESS

HYD/OIL

REFER TO OIL

SYSTEM

MALFUNCTION

GE129

Figure 31.(Sheet 3)

T.O. GR1F16CJ1

GR1F-16CJ-1-0108X37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

DOWN

SEE A

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

CHECK

WHEELS

DOWN

LIGHTS

SEE B

SEE A

Is canopy

handle up

or down?

CANOPY

NOT

SECURE

POSITION HANDLE

DOWN

CANOPY HOOKS

NOT FULLY

ENGAGED

ANY/ALL LG OR

LG DOORS NOT

FULLY UP AND

LOCKED

IN FLIGHT

Canopy hooks or lock not secure

Push handle down farther into

locked (outboard) position or if

on the ground, inform maintenance
Refer to CANOPY LOSS/PENE-

TRATION IN FLIGHT

Refer to LG FAILS TO RETRACT

Refer to LG FAILS TO EXTEND

LG or LG door not in position

commanded by LG handle

LG handle warning

light illuminated

NONILLUMINATED LIGHT INDICATES

ASSOCIATED LG IS NOT DOWN AND

LOCKED (MAY ALSO HAVE LG WARN-

ING HORN AND TO/LDG CONFIG

WARNING LIGHT)

CANOPY

Figure 31.(Sheet 4)

T.O. GR1F16CJ1

Change 139

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

TF FAIL

TF system failure

Climb to a safe altitude. Refer to TF FAIL WARN

ING LIGHT

FLCS

One or more malfunctions

Note PFL(s) displayed and refer to PILOT

FAULT LIST - FLCS

DBU ON

FLCC operating with backup software

program

Refer to DBU ON WARNING LIGHT

CANOPY

Partial pressure oxygen low

Refer to OBOGS MALFUNCTION

, this

section

III

CANOPY

OXY LOW

III

BIT has detected a fault

section

OXY LOW

Regulator pressure below 5 psi

Flashing WARN symbol

WARN

One or more red glareshield warning

lights illuminated

Check for specific illuminated warning light

WARN

Reset by toggling WARN RESET switch on ICP

Flashing TRP FUEL and FUEL warning

symbols

A trapped

external fuel condition is de

tected

Reset FUEL by toggling WARN RESET

switch on ICP

FUEL

TRP FUEL

Check fuel tank quantities and refer to

TRAPPED EXTERNAL FUEL

Figure 31.(Sheet 5)

T.O. GR1F16CJ1

310

GR1F-16CJ-1-1109X37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

ENGINE

ALTERNATOR

FAILURE

CHECK RPM AND

FTIT INDICATIONS

RPM

abnormally

low?

RPM

erroneously

zero?

FTIT

abnormally

high?

ENGINE

FLAMEOUT

YES

SEE A

SEE B

Check rpm and FTIT indications

Engine flameout

Engine alternator failure

Engine warning system failure or

RPM/FTIT indicator failure

Engine overtemperature

Place throttle to OFF and initiate airstart.

Refer to AIRSTARTS

Refer to ZERO RPM

Land as soon as possible

Land as soon as practical

ENGINE OVERTEMPERATURE

SEE C

SEE D

ENGINE WARNING SYSTEM

FAILURE OR RPM/FTIT

INDICATOR FAILURE

PW229

Figure 31.(Sheet 6)

T.O. GR1F16CJ1

311

GR1F-16CJ-1-0109A37

Warning Light Analysis

WARNING LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

ENGINE

ALTERNATOR

FAILURE

CHECK RPM AND

FTIT INDICATIONS

ENGINE OVERTEMPERATURE

RPM

abnormally

low?

RPM

erroneously

zero?

FTIT

abnormally

high?

ENGINE

FLAMEOUT

YES

SEE A

SEE B

Check rpm and FTIT indications

Engine flameout

Engine alternator failure

Engine overtemperature

Place throttle to OFF and initiate airstart.

Refer to AIRSTARTS

Refer to ZERO RPM

Land as soon as possible

SEE C

Land as soon as practical

SEE D

ENGINE

Engine warning system failure or

RPM/FTIT indicator failure

ENGINE WARNING SYSTEM

FAILURE OR RPM/FTIT

INDICATOR FAILURE

GE129

Figure 31.(Sheet 7)

T.O. GR1F16CJ1

312

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

One or more caution lights on

NOTE

Check for specific caution light on caution light

panel

The MASTER CAUTION light does not

illuminate for the IFF caution light.

Reset MASTER CAUTION light

NOTE

The MASTER CAUTION light does not reset when

the ELEC SYS caution light is illuminated. The

ELEC CAUTION RESET button must be depressed

or the electrical malfunction cleared to extin

guish ELEC SYS and MASTER CAUTION lights.

FLCS

FAULT

ENGINE

FAULT

AVIONICS

FAULT

SEAT NOT

ARMED

ELEC

SYS

SEC

EQUIP

HOT

NWS

FAIL

PROBE HEAT

FUEL/OIL

HOT

RADAR

ALT

ANTI

SKID

CADC

INLET

ICING

IFF

HOOK

STORES

CONFIG

OVERHEAT

NUCLEAR

OXY

LOW

ATF NOT

ENGAGED

EEC

________

CABIN

PRESS

FWD

FUEL LOW

BUC

_________

AFT

FUEL LOW

________

_________

PX II

FLCS

FAULT

ENGINE

FAULT

AVIONICS

FAULT

SEAT NOT

ARMED

ELEC

SYS

SEC

EQUIP

HOT

NWS

FAIL

PROBE HEAT

FUEL/OIL

HOT

RADAR

ALT

ANTI

SKID

CADC

INLET

ICING

IFF

HOOK

STORES

CONFIG

OVERHEAT

NUCLEAR

OBOGS

ATF NOT

ENGAGED

EEC

________

CABIN

PRESS

FWD

FUEL LOW

BUC

_________

AFT

FUEL LOW

________

_________

PX III

Figure 32.(Sheet 1)

T.O. GR1F16CJ1

313

Caution Light Analysis

CAUSE

CORRECTIVE ACTION/REMARKS

CAUTION LIGHT

Refer to CADC MALFUNCTION

Loss of valid mach data to engine

Refer to CADC MALFUNCTION

ENGINE FAULT caution

light on?

LOSS OF VALID

MACH NUMBER

DATA TO ENGINE

SEE A

SEE B

YES

GR1F-16CJ-1-0110X37

MALFUNCTION OF

CADC OR INPUT(S)

TO IT

Malfunction of CADC or input(s) to it

CADC

ENGINE

FAULT

Figure 32.(Sheet 2)

T.O. GR1F16CJ1

314

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

ELEC

SYS

Failure(s) of electrical system

*Check ELEC control panel for illuminated

light(s) and depress ELEC CAUTION RESET

button

FLCS PMG light (in flight)

Failure of FLCS PMG

A. Refer to FLCS PMG FAILURE

STBY GEN light

Failure of standby generator

Refer to SINGLE GENERATOR FAILURES

MAIN GEN light

Failure of main generator

C. Refer to SINGLE GENERATOR FAILURES

STBY GEN and FLCS PMG lights

Failure of standby generator and FLCS

PMG

D. Refer to SINGLE GENERATOR FAILURES

MAIN GEN, STBY GEN, EPU run, EPU

AIR, and (possibly) EPU HYDRAZN lights

Failure of main and standby generators

Refer to MAIN AND STANDBY GENERATOR

FAILURE

MAIN GEN, STBY GEN, EPU GEN, and

EPU PMG lights on. EPU run light off

Failure of main, standby, and EPU

generators

Refer to MAIN, STANDBY, AND EPU

GENERATOR FAILURE

MAIN GEN, STBY GEN, EPU GEN, EPU

PMG, FLCS PMG, and ACFT BATT TO

FLCS and/or FLCS BATT lights on. EPU

run light off

Failure of all generators

G. Refer to MAIN, STANDBY, AND EPU

GENERATOR FAILURE

*ACFT BATT FAIL light or ACFT BATT FAIL

and FLCS RLY lights

Failure of aircraft battery or battery

charging system

H. Refer to AIRCRAFT BATTERY FAILURE

FLCS RLY light

Voltage on one or more of the four FLCC

branches connected to the aircraft battery

is inadequate (below 20V)

Refer to FLCS RLY LIGHT

NOTE:

*During ground operations after engine start, the ACFT BATT FAIL light (and possibly ELEC SYS caution light) may flicker on then off (duration

of illumination is not long enough to activate the MASTER CAUTION light). This flickering is the result of a nuisance problem that does
not require corrective action by maintenance and it should not occur in flight.

Figure32. (Sheet 3)

T.O. GR1F16CJ1

315

GR1F-16CJ-1-0111X37

Caution Light Analysis

SEE A

FLCS PMG LIGHT

(IN FLIGHT)

STBY GEN LIGHT

MAIN GEN LIGHT

STBY GEN AND

FLCS PMG LIGHTS

MAIN GEN, STBY

GEN, EPU RUN,

AND EPU AIR

(AND POSSIBLY

MAIN GEN, STBY

GEN, EPU GEN,

AND EPU PMG

LIGHTS ON. EPU

RUN LIGHT OFF

MAIN GEN, STBY

GEN, EPU GEN,

EPU PMG, FLCS

PMG, AND ACFT

BATT TO FLCS

LIGHTS ON. EPU

RUN LIGHT OFF

ACFT BATT FAIL

LIGHT OR ACFT

BATT FAIL AND

FLCS RLY LIGHTS

FLCS RLY LIGHT

NONE OF THE FLCS BRANCHES ARE RE-

CEIVING POWER FROM THE FLCS PMG

STANDBY GENERATOR FAILURE

MAIN GENERATOR FAILURE

STANDBY GENERATOR ON LINE

FLCS PMG OPERATING

STANDBY GENERATOR AND FLCS PMG

FAILURE

EPU IS OPERATING AT PROPER SPEED

FLCS PMG IS OPERATING

MAIN GEN FAILURE

STBY GEN FAILURE

EPU FAILED OR UNDERSPEED

FLCS PMG OPERATING

AIRCRAFT BATTERY POWERING BATTERY

BUSES

MAIN GEN FAILURE

STBY GEN FAILURE

EPU FAILED OR UNDERSPEED

FLCS PMG FAILURE

AIRCRAFT BATTERY POWERING FLCS

AIRCRAFT BATTERY POWERING BATTERY

BUSES

AIRCRAFT BATTERY SYSTEM FAILURE

CHECK ELEC CONTROL

PANEL FOR ILLUMINATED

LIGHT(S) AND DEPRESS

ELEC CAUTION RESET

BUTTON

SEE B

SEE C

SEE D

SEE E

SEE F

SEE G

SEE H

SEE I

MAIN AND STBY GENERATORS FAILURE

ELEC

SYS

HYDRAZN) LIGHTS

VOLTAGE ON ONE OR MORE OF THE

FOUR FLCC BRANCHES CONNECTED TO

THE AIRCRAFT BATTERY IS INADEQUATE

(BELOW 20V)

NOTE:

During ground operations

after engine start, the ACFT

BATT FAIL light (and possibly

ELEC SYS caution light) may

flicker on then off (duration

of illumination is not long

enough to activate the MAS

TER CAUTION light). This

flickering is the result of a

nuisance problem that does

not require corrective action

by maintenance and it

should not occur in flight.

Figure32. (Sheet 4)

T.O. GR1F16CJ1

316

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

AVIONICS

FAULT

Avionic fault(s) detected or MUX commu

nication with FLCS or engine lost

Note PFL(s) displayed on PFLD. Depress

FACK, FAULT ACK button to acknowledge

fault(s) and reset AVIONICS FAULT caution light.

Perform fault recall(s) to determine if the failure

condition still exists

C DF

SEAT NOT

ARMED

Ejection safety lever up (system safe)

When desired, rotate ejection safety lever down

(armed)

HOOK

Hook not up and locked

Normal landing, touchdown beyond approach

end arresting gear

NWS

FAIL

NWS system

failure or loss of NWS electri

cal power

Normal landing, NWS is not available. Refer to

NWS FAILURE/HARDOVER
NOTES:

Does not illuminate for NWS failure due
to hydraulic system B failure or NLG
strut overextension.

Possible indication that AR door cannot
be opened or closed.

EEC

Not used

None

BUC

Not used

None

FLCS

FAULT

FLCS fault(s) detected

Note PFL(s) displayed and refer to PILOT FAULT

LIST - FLCS

FUEL/OIL

HOT

229

Temperature of fuel to engine excessive.

Oil hot function is inoperative

Refer to HOT FUEL/OIL OR GRAVITY FEED

FUEL/OIL

HOT

129

Temperature of fuel to engine excessive or

engine oil temperature excessive

Refer to HOT FUEL/OIL OR GRAVITY FEED

FWD

FUEL LOW

Forward reservoir contains:

Less than 400 pounds fuel

Less than 250 pounds fuel

Refer to FUEL LOW

AFT

FUEL LOW

Aft reservoir contains:

Less than 250 pounds fuel

Less than 400 pounds fuel

Refer to FUEL LOW

IFF

MODE 4 REPLY sw in OUT (backup mode

only); zeroized or not coded; correct code

not selected (A or B); code does not match

code interrogation; or mode 4 inopera

tive; or RF sw in QUIET or SILENT

Advisory

Figure 32.(Sheet 5)

T.O. GR1F16CJ1

317

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

INLET

ICING

Ice accumulation detected or system mal

function

If in area of known or suspected icing conditions,

position engine ANTI ICE switch to ON

NUCLEAR

Malfunction in nuclear control circuitry

Advisory

SEC

Engine operating in SEC or

main fuel pump pressure is low

229

Refer to SEC CAUTION LIGHT

Engine operating in SEC

129

Refer to SEC CAUTION LIGHT

ENGINE

FAULT

Engine fault(s) detected

Refer to ENGINE FAULT CAUTION LIGHT

STORES

CONFIG

STORES CONFIG switch is in incorrect

position or loading category in SMS soft

ware disagrees with actual GP/STORE/

LINE loading category

Verify STORES CONFIG switch is in proper posi

tion for aircraft loading category. Refer to T.O.

GR1F16CJ12

PROBE HEAT

Ground:Probe heater failure, monitor

ing system failure, or one/both AOA

probe heaters have shut off to prevent

overheat

Ground:Place PROBE HEAT switch to OFF for

1 minute (caution light goes off when OFF is

selected); then reselect PROBE HEAT. If caution

light comes on simultaneously with reselection

of PROBE HEAT, a probe heater or monitoring

system failure has occurred. If caution light does

not come on when PROBE HEAT is reselected,

one/both AOA probe heaters were shut off to

prevent overheat

In flight:Probe heater(s) or monitoring

system failure

In flight:Place PROBE HEAT switch to PROBE

HEAT, if required, and avoid areas of known or

suspected icing conditions

Figure 32.(Sheet 6)

T.O. GR1F16CJ1

318

GR1F-16CJ-1-0112X37

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

Cockpit pressure altitude above 27,000

feet

Refer to COCKPIT PRESSURE/TEMPER-

ATURE MALFUNCTION

CHECK COCKPIT

PRESSURE

ALTITUDE

BELOW 27,000

FEET

MALFUNCTION

IN INDICATOR

SYSTEM

CONTINUE

COCKPIT PRESSURE

EXCEEDS 27,000

FEET BECAUSE OF

PRESSURIZATION

FAILURE

YES

AIR SOURCE

KNOB NORM

ABOVE 27,000

FEET

SEE A

ILLUMINATES WHEN

AVIONIC EQUIPMENT

COOLING AIR TEMP-

ERATURE/PRESSURE

IS INSUFFICIENT

AIR SOURCE

KNOB NORM

DEGRADED EQUIP-

MENT PERFORMANCE

AND/OR DAMAGE

CAN RESULT

YES

AIR SOURCE knob

in NORM?

FLIGHT

AIR SOURCE knob

in NORM?

SEE A

Avionic equipment cooling air temper-

ature/pressure insufficient

Refer to EQUIP HOT CAUTION LIGHT

CABIN

PRESS

CABIN

PRESS

EQUIP

HOT

EQUIP

HOT

Figure 32.(Sheet 7)

T.O. GR1F16CJ1

319

GR1F-16CJ-1-0113X37

Caution Light Analysis

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

Overheat condition in engine compart-

ment, ECS or EPU bays, or MLG wheel

Refer to OVERHEAT CAUTION LIGHT

SEE A

OVERHEAT

THROTTLE TO

MINIMUM PRAC-

TICAL THRUST

CHECK FIRE

DETECT CIRCUIT

overheat

detect circuit

check good?

OVERHEAT

IN ENGINE

COMPARTMENT

TURN EPU OFF

IF IT WAS MANU-

ALLY ACTIVATED

SEE A

CONDITION

IN EPU BAY

REACTIVATE

EPU

OXYGEN 100%

Did

OVERHEAT

caution light

go off?

Did

OVERHEAT

caution light

go off?

Did

overheat

detect circuit

check good?

Did

EPU

running?

CONT

YES

OVERHEAT

CONDITION

wells

Figure 32.(Sheet 8)

T.O. GR1F16CJ1

320

GR1F-16CJ-1-0114A37

Caution Light Analysis

OVERHEAT

caution light

go off?

Did

overheat

detect circuit

check good?

Did

YES

CONT

AIR SOURCE

KNOB OFF

SEE A

overheat

detect circuit

check good?

CONDITION

IN ECS BAY

Did

OVERHEAT

caution light

go off?

Did

YES

LG DN

OVERHEAT CONDITION

IN MLG WHEEL

LAND AS SOON

AS POSSIBLE

WELLS

YES

SEE A

OVERHEAT

OVERHEAT CONDITION IN ENGINE COM-

PARTMENT, ECS OR EPU BAYS, OR MLG

WHEEL WELLS STILL PRESENT

OVERHEAT CONDITION IN ENGINE COM-

PARTMENT, ECS OR EPU BAYS, OR MLG

WHEEL WELLS STILL PRESENT

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

ANTI

SKID

ANTI-SKID switch OFF or system

malfunction

Refer to ANTISKID MALFUNCTION

ANTI

SKID

Is switch

in ANTI-SKID

position?

ANTISKID

MALFUNCTION

POSITION TO

ANTI-SKID

SEE A

YES

Figure 32.(Sheet 9)

T.O. GR1F16CJ1

321

GR1F-16CJ-1-0115A37

Caution Light Analysis

OXY

LOW

Is oxygen

quantity below

0.5 liter?

QUANTITY

INDICATION

Is oxygen

pressure below

42 psi?

SEE A

YES

MALFUNCTION

ATF NOT

ENGAGED

RADAR

ALT

OXY

LOW

Malfunction of radar altimeter

Oxygen pressure is below 42 psi or

quantity is below 0.5 liter

Move RDR ALT switch to OFF

Descend to 10,000 feet cockpit pres-

sure altitude. Activate emergency

oxygen if required

NVP or FLCS cannot support ATF

CAUTION LIGHT

CAUSE

CORRECTIVE ACTION/REMARKS

If in ATF, climb to a safe altitude and

AIR REFUEL switch CLOSE

ALT FLAPS switch NORM

TRIM/AP DISC switch NORM

No CADC failures

NOTE

Deselect ATF until the cause of the

caution light illumination can be

determined.

verify:

PX II

PX III

OBOGS

The ECS air supply for OBOGS has

dropped below 10 psi

Oxygen production stops. BOS provides

oxygen for 35 minutes. Expect OXY LOW

warning light if regulator pressure drops

below 5 psi. Attempt to increase ECS air

pressure by increasing throttle setting,

increasing airspeed, and/or decreasing

altitude

NOTE

The OBOGS caution light may illuminate as

a result of ECS cycling or temporary ECS

shutdown. This is normal as long as the

OXY LOW warning light does not illuminate.

Figure 32.(Sheet 10)

F16C/D. FLIGHT MANUAL (2002) - page 19

F16C/D. FLIGHT MANUAL (2002) - page 19