Content .. 10 11 12 13 ..

F16C/D. FLIGHT MANUAL (2002) - page 12

T.O. GR1F16CJ1

1162

GR1F-16CJ-1-0064X37

PARACHUTE

ASSEMBLY

FLCS DATA

RECORDER

EMERGENCY OXYGEN

BOTTLE

LAPBELT AND SURVIVAL

KIT STRAPS

Emergency Oxygen Green Ring

SHOULDER HARNESS Knob

Ejection Safety Lever

RADIO BEACON Switch

Survival KIT DEPLOYMENT Switch

Ejection Handle (PULL TO EJECT)

EMERGENCY MANUAL CHUTE Handle

Survival Kit Ripcord

Electronic Recovery Sequencer Battery Indicator

EJECTION MODE SEL Handle

Ejection Seat Controls and Indicators

(Typical)

11.

RED PIN PROTRUSION

INDICATES EXPENDED

SEQUENCER

SEAT/HOSE

DISCONNECT

C DF

EMERGENCY OXYGEN HOSE

QUICK-DISCONNECT

SHOULDER HARNESS STRAPS/

RECOVERY PARACHUTE RISERS

ENVIRONMENTAL SENSOR

PITOT (STOWED)

(ROTATED 180 )

SEAT NOT

ARMED

SURVIVAL KIT

(UNDER SEAT

PAN LID)

(FLIP-UP PITOTS)

EMERGENCY OXYGEN

PRESSURE INDICATOR

INERTIA REEL STRAPS

RETAINING PIN

LAPBELT

RETAINING PIN

(BOTH SIDES)

(YELLOW)

SIDE VIEW

INSPECTION HOLE

ENVIRONMENTAL

SENSOR PITOTS

DURING EJECTION

SAFETY PIN

HOLE

ALTERNATE

CONFIGURATION

(EXTENDED PITOTS)

(FIXED PITOTS)

SEAT NOT ARMED Caution Light

10.

RECOVERY

INERTIA REEL

STRAPS

Figure 164.(Sheet 1)

T.O. GR1F16CJ1

1163

Ejection Seat Controls and Indicators

(Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

1. Emergency Oxygen Green

Ring

Pull

Activates emergency oxygen

2. SHOULDER HARNESS

Knob

UNLOCKED (aft)

Unlocks inertia reel and allows free move

ment of shoulder harness

LOCKED (forward)

Locks inertia reel and prevents forward

movement of shoulder harness

3. Ejection Safety Lever

Prevents pulling of ejection handle

Down

Allows ejection handle to be pulled

4. RADIO BEACON Switch

MAN (green dot visible)

Selects manual mode

AUTO (red dot visible)

Selects automatic mode

5. Survival KIT DEPLOY

MENT Switch

A (forward)

Selects automatic mode

MENT Switch

M (aft)

Selects manual mode

6. Ejection Handle (PULL TO

EJECT)

Pull

Jettisons canopy and ejects seat

7. EMERGENCY MANUAL

CHUTE Handle

Pull

After ejection-ballistically deploys the

recovery parachute assembly and releases

lapbelt and inertia reel straps and unlatches

the seat pan lid

8. Survival Kit Ripcord

Pull

Deploys survival kit

9. Electronic Recovery Se

quencer Battery Indicator

White

Sequencer thermal batteries not acti

vated-operational

Red

Sequencer thermal batteries activated-not

operational

10. SEAT NOT ARMED Cau

tion Light (amber)

Ejection safety lever up

tion Light (amber)

Off

Ejection safety lever down

11. EJECTION MODE SEL

Handle (LIFT TURN)

AFT/NORM/SOLO

Selects ejection mode

Handle (LIFT TURN)

Refer to F16D AIRCRAFT, this section

Figure 164.(Sheet 2)

T.O. GR1F16CJ1

1164

Survival Kit

The survival kit is stowed under the seat pan lid. The

KIT DEPLOYMENT switch has a manual (aft) or

automatic (forward) position which selects the mode

of postejection survival kit deployment. Pulling the

kit ripcord handle deploys the kit which remains

attached by a 25foot lanyard.

RADIO BEACON Switch

The RADIO BEACON switch allows the pilot to select

AUTO or MAN. In AUTO (red dot visible), the beacon

activates after pilot/seat separation. In MAN (green

dot visible), the beacon does not activate. The beacon

may be activated when on the ground if the RADIO

BEACON switch is placed to AUTO or it can be

removed and manually operated as desired. The

beacon transmits on 243.0 MHz.

Emergency Oxygen

Emergency oxygen supply is automatically activated

during ejection or may be manually activated by

pulling the emergency oxygen green ring.

EJECTION SEAT OPERATION

Seat ejection is initiated by pulling the ejection

handle (PULL TO EJECT). This action retracts the

shoulder harness straps and locks the inertia reel,

fires the initiators for canopy jettison, and ignites two

canopy removal rockets. As the canopy leaves the

aircraft, lanyards fire two seat ejection initiators.

A rocket catapult propels the seat from the cockpit

exposing the seat environmental sensor pitots and

activating the emergency oxygen. The recovery

sequencer selects the correct ejection mode, ignites

the stabilization package (STAPAC) rocket and the

trajectory divergence rocket, and (if in mode 2 or 3)

initiates the drogue gun.

If the automatic pilot/seat separation and recovery

parachute deployment system fails, pulling the

EMERGENCY MANUAL CHUTE handle approxi

mately 6 inches ballistically deploys the recovery

parachute assembly and releases the lapbelt and

inertia reel straps and unlatches the seat pan lid.

The liferaft, survival kit, and radio beacon antenna

are deployed following pilot/seat separation when the

survival KIT DEPLOYMENT switch is in AUTO. If

the parachute is equipped with SEAWARS, the

parachute risers are automatically released within 2

seconds after entering saltwater.

Seat ejection also automatically performs an escape

zeroize operation by purging coded electronic

information associated with the following equipment:

DTC.

PX II

FCC.

PX III

MMC.

PX III

EGI.

PX II

GPS.

AIFF mode 4.

PX III

IDM.

MFDS.

TWS.

EJECTION MODE ENVELOPES

Refer to figure 165.

EJECTION SEQUENCE TIMES

Refer to figure 166.

CANOPY JETTISON/SEAT EJECTION

Refer to figure 167.

EJECTION SEAT PERFORMANCE

Refer to figure 168.

T.O. GR1F16CJ1

1165

100

200

300

400

500

600

700

AIRSPEED KIAS

PRESSURE AL

TITUDE 1000 FEET

MODE 1

MODE 2

MODE 3

1F-16X-1-0011X

Ejection Mode Envelopes

Figure 165.

Ejection Sequence Times

NOTE:

TIME (SECONDS)

EVENT

Mode 1

Mode 2

In mode 3, events after drogue deployment

are delayed until within mode 2 envelope.

Recovery parachute deploys 1 second after

entering mode 2 envelope.

Times in the aft/forward sequence

increase to include a 0.33second delay for

the rear seat and a 0.73second delay for

the forward seat. In SOLO, the forward seat

is delayed 0.33 second.

Canopy jettison time varies from 0.75

second at 0 KIAS to 0.13 second at 600 KIAS.

Ejection begins when canopy jettison initi

ates seat lanyards.

Catapult Initiation

Drogue Gun Fired

Drogue Chute Inflated

Parachute Fired

Seat/Drogue Separation

Pilot/Seat Separation

Recovery Parachute Inflated

Survival Kit Deployed

0.0

0.20

0.45

1.80

5.50

0.0

0.17

0.38

1.17

1.32

1.42

2.80

6.30

Figure 166.

. GR1F

16CJ

1166

1F-16X-1-0012X

T = 5.5

T = 0

T = 0.20

T = 0.45

T = 1.8

T = 6.3

T = 0

T = 0.17

T = 0.38

T = 1.17

T = 1.32

T = 1.42

T = 2.8

MODE 1

MODE 2

Canopy Jettison/Seat Ejection

Figure 167.

T.O. GR1F16CJ1

1167

1F-16X-1-2002X

Ejection Seat Performance

MINIMUM EJECTION ALTITUDE vs DIVE ANGLE AND SPEED

NOTES:

ZERO PILOT REACTION TIME

WINGS LEVEL

SEA LEVEL

95th PERCENTILE PILOT

1600

1400

1200

1000

800

600

400

200

MINIMUM EJECTION AL

TITUDE AGL FEET

1600

1400

1200

1000

800

600

400

200

MINIMUM EJECTION AL

TITUDE AGL FEET

DIVE ANGLE DEGREES

MODE 1

MODE 2

MODE 1

MODE 2

UPRIGHT

INVERTED

Figure

168.(Sheet 1)

T.O. GR1F16CJ1

1168

1F-16X-1-2003X

Ejection Seat Performance

MINIMUM EJECTION ALTITUDE vs SINK RATE AND SPEED

NOTES:

ZERO PILOT REACTION TIME

WINGS LEVEL

SEA LEVEL

95th PERCENTILE PILOT

MINIMUM EJECTION AL

TITUDE AGL FEET

SINK RATE FEET PER MINUTE

MODE 1

MODE 2

600

500

400

300

200

100

2000

4000

6000

8000

10,000

INVERTED

UPRIGHT

Figure

168.(Sheet 2)

T.O. GR1F16CJ1

1169

1F-16X-1-2004X

Ejection Seat Performance

NOTES:

ZERO PILOT REACTION TIME

SEA LEVEL

MINIMUM EJECTION AL

TITUDE AGL FEET

DIVE ANGLE DEGREES

MODE 1

MODE 2

1600

1400

1200

1000

800

600

400

200

95th PERCENTILE PILOT

MINIMUM EJECTION ALTITUDE vs SPEED, DIVE ANGLE,

AND BANK ANGLE

Figure

168.(Sheet 3)

T.O. GR1F16CJ1

1170

1F-16X-1-2005X

Ejection Seat Performance

MINIMUM EJECTION ALTITUDE vs DIVE ANGLE AND SPEED

NOTES:

ZERO PILOT REACTION TIME

WINGS LEVEL

FORWARD SEAT DURING DUAL,

95th PERCENTILE PILOT

2800

2400

2000

1600

1200

800

400

2800

2400

2000

1600

1200

800

400

DIVE ANGLE DEGREES

MODE 1

MODE 2

MODE 1

MODE 2

UPRIGHT

INVERTED

SEA LEVEL

MINIMUM EJECTION

TITUDE AGL FEET

MINIMUM EJECTION

TITUDE AGL FEET

SEQUENCED EJECTION

Figure

168.(Sheet 4)

T.O. GR1F16CJ1

1171

1F-16X-1-2006X

Ejection Seat Performance

MINIMUM EJECTION ALTITUDE vs SINK RATE AND SPEED

NOTES:

ZERO PILOT REACTION TIME

WINGS LEVEL

FORWARD SEAT DURING DUAL,

SEQUENCED EJECTION

1000

800

600

400

200

2000

4000

6000

8000

10,000

SINK RATE FEET PER MINUTE

MODE 1

MODE 2

UPRIGHT

INVERTED

SEA LEVEL

MINIMUM EJECTION AL

TITUDE AGL FEET

1200

95th PERCENTILE PILOT

Figure

168.(Sheet 5)

T.O. GR1F16CJ1

1172

1F-16X-1-2007X

Ejection Seat Performance

NOTES:

ZERO PILOT REACTION TIME

SEA LEVEL

MINIMUM EJECTION AL

TITUDE AGL FEET

DIVE ANGLE DEGREES

MODE 1

MODE 2

2800

2400

2000

1600

1200

800

400

MINIMUM EJECTION ALTITUDE vs SPEED, DIVE ANGLE,

AND BANK ANGLE

FORWARD SEAT DURING DUAL,

SEQUENCED EJECTION

95th PERCENTILE PILOT

Figure

168.(Sheet 6)

T.O. GR1F16CJ1

1173

OXYGEN SYSTEM

PX III

The oxygen system consists of an onboard oxygen

generating system (OBOGS), a backup oxygen supply

(BOS), and a regulated 50 cubic inch emergency

oxygen supply (EOS) bottle.

ONBOARD OXYGEN GENERATING SYSTEM

(OBOGS)

The OBOGS is a molecular sieve/concentrator that

uses an adsorption filtering process to remove

nitrogen from the ECS supplied bleed air and provide

oxygen rich breathing gas. The system is capable of

producing 95 percent oxygen with the balance being

argon and other inert gases. For normal operation the

concentrator provides oxygen to a compatible diluter

demand breathing regulator. The system pressure to

the regulator can be read on a pressure gage located

on the face of the regulator. The normal operating

pressure range is 2540 psi.

OBOGS BACKUP OXYGEN SUPPLY (BOS)

If the OBOGS is not producing oxygen due to loss of

ECS input air to the concentrator, concentrator

failure, or loss of power to the concentrator, the

system will revert to stored oxygen in the sieve filled

plenum, called the backup oxygen supply (BOS). The

BOS will last for a period of 3 to 5 minutes depending

on altitude and breathing rate. Resupplying a

depleted BOS requires up to 10 minutes. After the

BOS has been expended and system pressure falls

below 5 psi, the OXY LOW warning light, located on

the right glare shield, illuminates.

OBOGS MONITOR

The OBOGS is monitored by an oxygen monitor with

builtintest (BIT) circuitry. The oxygen monitor

samples oxygen for the correct oxygen concentration

at a particular altitude from 10,000 to 50,000 feet.

The OBOGS monitor provides a signal to turn on the

OXY LOW warning light if the partial pressure of

oxygen (PPO

) from the concentrator drops below a

preset alarm range or if BIT detects an internal

monitor fault. The monitor provides low oxygen

partial pressure warning at either of two thresholds

based on the position of the diluter lever located on

the regulator. Low PPO

can be caused by a

concentrator malfunction or a clogged input filter on

the concentrator.

EMERGENCY OXYGEN SUPPLY (EOS)

The emergency oxygen supply (EOS) consists of a

highpressure bottle mounted on the left side of the

ejection seat. The EOS is a regulated oxygen supply

that will last for 8 to 12 minutes depending on

altitude and breathing rate. The hose is routed to the

right side of the seat. The system is activated:

Automatically upon ejection.

Manually by pulling the emergency oxygen green

ring located on the left aft side of the seat.

A gauge on the EOS indicates the stored oxygen

pressure.

OBOGS BUILTINTESTS (BIT's)

The OBOGS monitor has four BIT programs:

powerup BIT, periodic BIT, manual BIT, and

pneumatic BIT. All BIT programs are for testing the

monitor's circuitry only.

OBOGS PowerUp BIT

Powerup BIT is performed automatically upon

powerup during engine start. The powerup BIT

includes a two minute warmup period during which

the OXY LOW warning light is inhibited. The OXY

LOW warning light illuminates at the end of the

powerup BIT if a monitor failure is detected.

OBOGS Periodic BIT

Periodic BIT is performed automatically during

normal operations. If a monitor fault is detected, the

OXY LOW warning light will illuminate.

OBOGS Manual BIT

Manual BIT is activated by momentarily positioning

the OBOGS BIT switch, located on the TEST panel,

to BIT. This can be accomplished to perform a monitor

check or to determine the cause of an OXY LOW

warning light.

Selecting BIT causes the OXY LOW warning light to

illuminate for ten seconds. If no faults are detected,

the warning light will go off. If a monitor fault is

detected, the OXY LOW warning light will remain on

with a continuous indication as long as the fault

condition exists.

T.O. GR1F16CJ1

1174

If the OBOGS BIT switch is positioned to BIT while

the OXY LOW warning light is on, the warning light

will remain on steady if the problem is due to a low

PPO

condition or low regulator pressure. It will flash

one second on and one second off if a monitor fault was

detected. If a monitor fault exists, subsequent

positioning of the OBOGS BIT switch to BIT will

toggle the warning light from flashing to continuous.

OBOGS Pneumatic BIT

Pneumatic bit is a maintenance function.

PRESSURE BREATHING FOR G (PBG)

The PBG mode of the oxygen regulator provides

pressure breathing above 4g's to enhance g tolerance

and reduce fatigue. Air pressure from the antig valve

is used by the oxygen regulator to control the amount

of pressurization supplied to the oxygen mask,

helmet, and vest. A malfunction in the OBOGS

system can result in a degradation in PBG system

performance.

OXYGEN SYSTEM CONTROLS AND INDICATORS

Refer to figure 169 for a description of the oxygen

system controls and indicators.

OXYGEN SYSTEM SCHEMATIC

Refer to figure 170.

GR1F-16CJ-1-1073X37

Oxygen System Controls and Indicators

(Typical)

OXYGEN REGULATOR FLOW Indicator

OXYGEN SUPPLY Indicator

OBOGS BIT Switch

OXY LOW Warning Light

Supply (Mode) Lever (PBG Lever Lock)

C DF

7. Diluter Lever

8. EMERGENCY Lever

OBOGS Caution Light

CABIN PRESS ALT

PX III

Figure 169.(Sheet 1)

T.O. GR1F16CJ1

1175

Oxygen System Controls and Indicators

PX III

(Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

1. CABIN PRESS ALT

C DF

050,000 feet

Indicates cockpit altitude

2. OXYGEN Regulator FLOW

Indicator

White

Indicates oxygen flow

Indicator

Black

Indicates no oxygen flow

3. OXYGEN SUPPLY Indica

tor

Oxygen pressure (psi)

Indicates gaseous oxygen pressure at regula

tor in psi

4. OBOGS BIT Switch

BIT

Initiates OBOGS manual BIT

5. OBOGS Caution Light (am

ber)

Indicates that ECS air pressure has dropped

below 10 psi

6. SUPPLY (Mode) Lever

PBG (lever lock)

Provides oxygen supply to mask, helmet

bladder, and vest. Pressure breathing as a

function of g is available

Provides oxygen supply to mask, helmet

bladder, and vest. Pressure breathing as a

function of g is not available

OFF

Turns off oxygen supply

7. Diluter Lever

NORM

Provides regulated mixture of cockpit air and

oxygen as determined by cockpit altitude

100%

Provides maximum amount of oxygen

8. EMERGENCY Lever

NORM

Provides normal operation. Positive pressure

is provided if cockpit altitude exceeds

28,00032,000 feet

EMERGENCY

Provides maximum amount of oxygen under

positive pressure. This position is used by the

pilot to test for leaks

TEST MASK

Provides maximum amount of oxygen under

positive pressure. This position is used for

testing by life support maintenance

9. OXY LOW Warning Light

(red)

Indicates that partial pressure of oxygen

(PPO

) is low, the presence of a BIT detected

monitor fault, or that regulator pressure has

dropped below 5 psi

Figure 169.(Sheet 2)

T.O. GR1F16CJ1

1176

PRESSURE

SWITCH

OXYGEN MASK

HARNESS-

MOUNTED

CONNECTOR

EMERGENCY OXYGEN SUPPLY

PILOT TO SEAT

LEGEND:

CHECK VALVE

QUICK DISCONNECT

FILL CONNECTOR

ECS AIR

GASEOUS OXYGEN

WARNING

LIGHT

Oxygen System Schematic (Typical)

OXYGEN REGULATOR PANEL

GR1F-16CJ-1-1074X37

ELECTRICAL

ON VALVE WITH

EMERGENCY OXYGEN

GREEN RING

EMERGENCY OXYGEN

PRESSURE INDICATOR

VEST FILL/DUMP

VALVE

VEST

CONNECTOR

HELMET

BLADDER

CONNECTOR

PRESSURE SIGNAL

FROM ANTI-G VALVE

PRESSURE RELIEF VALVE

(FUNCTIONAL WHEN VEST

IS NOT CONNECTED)

SEAT TO

AIRCRAFT

CAUTION

LIGHT

OXY LOW

OBOGS

BACK-UP OXYGEN

SUPPLY (BOS) PLENUM

PUMP MOTOR

FILTER ASSY

CONCENTRATOR

ECS LOW PRESSURE

SWITCH

ECS AIR SUPPLY

OBOGS

MONITOR

EOS REGULATOR

(EOS) BOTTLE

PX III

Figure 170.

T.O. GR1F16CJ1

1177

OXYGEN SYSTEM

PX II

The oxygen system consists of a liquid system and an

emergency gaseous system.

LIQUID OXYGEN SYSTEM

A 5liter liquid oxygen system provides breathing

oxygen to a diluter demand oxygen regulator. The

regulator provides for selection of normal diluted

oxygen and 100 percent oxygen and selection of PBG.

Quickdisconnects are used to expedite egressing the

aircraft on the ground. Oxygen duration varies

depending upon altitude, regulator settings, and

usage.

Pressure Breathing for G (PBG)

The PBG mode of the oxygen regulator provides

pressure breathing above 4g's to enhance g tolerance

and reduce pilot fatigue. ECS air used to inflate the

gsuit is also used by the oxygen regulator to control

the amount of pressurization supplied to the oxygen

mask, helmet, and vest.

Oxygen System Controls and Indicators

Refer to figure 171 for description of the oxygen

system controls and indicators.

Oxygen Duration

Refer to figure 172.

EMERGENCY OXYGEN SYSTEM

The emergency oxygen system consists of a high

pressure bottle with a flow controller mounted on the

left side of the ejection seat. The hose is routed to the

right side of the seat. The system is activated:

Automatically upon ejection.

Manually by pulling the emergency oxygen green

ring located on the left aft side of the seat.

OXYGEN SYSTEM SCHEMATIC

Refer to figure 173.

GR1F-16CJ-1-0073A37

C DF

Oxygen System Controls and Indicators

(Typical)

OXYGEN REGULATOR FLOW Indicator

OXYGEN SUPPLY Indicator

Mode Lever (PBG Lever Lock)

Diluter Lever

EMER Lever

LIQUID OXYGEN Quantity Indicator

OXY QTY Indicator Test Switch

OXY LOW Caution Light

CABIN PRESS ALT

C DF

PX II

Figure 171.(Sheet 1)

Content .. 10 11 12 13 ..

F16C/D. FLIGHT MANUAL (2002) - page 12

F16C/D. FLIGHT MANUAL (2002) - page 12