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F16C/D. FLIGHT MANUAL (2002) - page 11

T.O. GR1F16CJ1

1146

CAUTION.

BINGO.

DATA.

IFF.

The VMS does not function with WOW. However, it

can be tested by pressing the MAL & IND LTS test

button on the TEST switch panel. During test, each

word is heard one time. The VMS is powered by

battery bus No. 1.

VOICE MESSAGE Switch

Refer to figure 13. The VOICE MESSAGE switch,

located aft of the stick, is a twoposition switch.

Positions are marked VOICE MESSAGE and

INHIBIT. During normal operation, the switch is

safetywired in VOICE MESSAGE. Placing the

switch to INHIBIT disables all voice messages.

INHIBIT should only be used to clear a voice message

which repeats abnormally. Placing the switch back to

VOICE MESSAGE enables normal operation.

MASTER CAUTION LIGHT

The MASTER CAUTION light, located on the

left upper edge,

center of the glareshield,

illuminates shortly after an individual light on the

caution light panel illuminates (except the IFF

caution light) to indicate a malfunction or specific

condition exists.

The MASTER CAUTION light does not illuminate in

conjunction with the warning lights. The MASTER

CAUTION light may be reset by depressing the face

of the light unless it is illuminated by the ELEC SYS

caution light. For FLCS FAULT, ENGINE FAULT,

and AVIONICS FAULT caution lights, the MASTER

CAUTION light may also be reset by depressing the

FACK,

FAULT ACK button. The light

should be reset as soon as feasible so that other

caution lights can be monitored should additional

malfunctions or specific conditions occur. Unless it is

reset, the MASTER CAUTION light remains

illuminated as long as the individual caution light is

illuminated.

The MASTER CAUTION light is a

repeater and cannot be reset individually.

PILOT FAULT LIST DISPLAY (PFLD)

Refer to figure 156. The PFLD, located on the

right auxiliary console,

instrument panel,

displays engine, avionics, and FLCS PFL's. In

addition, a status line displays a system code to

identify the system associated with an active fault(s).
Two types of PFL's are displayed: warning level and

caution level. Warning level PFL's are associated with

the FLCS (TFR system PFL's are considered to be

associated with the FLCS) and are distinguished

from caution level PFL's by a warning indicator which

brackets the PFL message. When an FLCS warning

level PFL occurs, the PFL message and FLCS code

are displayed on the PFLD, the FLCS warning light

illuminates, a flashing WARN is displayed in the

HUD, and the voice warning message is activated.

Caution level PFL's are associated with the FLCS,

engine, and avionic system. When a caution level PFL

occurs, the PFL message and system code are

displayed on the PFLD, the appropriate system fault

caution panel light illuminates, the MASTER

CAUTION light illuminates, and the voice caution

message is activated.
If multiple PFL's occur, they are displayed in the

following priority order:

FLCS warning level PFL's.

FLCS caution level PFL's.

Engine PFL's.

Avionic PFL's.

Each page of the PFLD displays up to three PFL's.

Additional pages are indicated by an arrow at each

end of the bottom PFL and are accessed by depressing

the

FACK,

FAULT ACK button. Page

numbers are also displayed when more than three

PFL's are listed.
PFL's are acknowledged and recalled by depressing

the

FACK,

FAULT ACK button.

Acknowledging a caution level PFL clears it from the

PFLD and extinguishes the associated caution panel

light and MASTER CAUTION light (if not previously

reset). Acknowledging an FLCS warning level PFL

clears it from the PFLD; however, the FLCS warning

light remains on. Subsequent depressions of the

FACK,

FAULT ACK button perform fault

recalls. At the time of a fault recall, PFL's that are no

longer being reported as a failure within the

originating system are not displayed and are cleared

from memory. The system code (FLCS, ENG, and/or

AV) provides a real time indication of the presence of

active fault(s). If the code is displayed, there is at least

one active PFL within the reported category. If no

system codes are displayed, there are no active PFL's.

T.O. GR1F16CJ1

1147

FLCS

ENG

FLCS

ENG

LEF

AOA

A/I

LOCK

FAIL

GR1F-16CJ-1-0058X37

2. Warning Indicator

3. Page Number

4. PFL Message(s)

5. Additional Page Indicator

6. Severity Indication

7. LRU or Function

8. Subsystem

Pilot Fault List Display (Typical)

1. System Codes

Figure 156.

Eliminating a FLCS failure condition by corrective

action (e.g., FLCS reset) prior to fault acknowledg

ment removes all FLCS failure indications. For

engine and avionic failure conditions and for FLCS

failure conditions after fault acknowledgment,

elimination of the failure condition will automatically

remove/clear the system codes but not the PFL

messages. Fault acknowledgment (if not previously

accomplished) and fault recall are required to remove

the PFL message(s).

The PFLD blanks if the upfront controls fail. Refer to

T.O. GR1F16CJ3411 for additional PFLD infor

mation. The PFLD is powered by the nacelle essential

ac bus.

CAUTION LIGHT PANEL

The caution light panel is located on the right

auxiliary console.

The ELEC SYS caution light must be reset at the

ELEC control panel with the ELEC CAUTION

RESET button. The light may appear nonresettable

in situations where the ELEC SYS caution light is

rapidly flashing or cycling on and off.

The following caution lights may be reset with the

FACK

FAULT ACK button:

FLCS FAULT.

ENGINE FAULT.

AVIONICS FAULT.

MAL & IND LTS Test Button

The MAL & IND LTS test button, located on the TEST

switch panel, operates relays which test the

illumination of all warning, caution, and indicator

lights, the LG warning horn, and voice messages.

T.O. GR1F16CJ1

1148

LIGHTING SYSTEM

EXTERIOR LIGHTING

Refer to figure 157, 158, and 159. All of the exterior

lights except the landing/taxi lights are controlled

from the EXT LIGHTING control panel.

Anticollision Strobe Light

The anticollision strobe light is masked to minimize

projections in the cockpit.

PX III

The anticollision light has a strobe (visible to

the unaided eye) as well as an infrared emitter

(covert, visible to night vision devices but invisible to

the unaided eye). The strobe is disabled and the IR

emitter enabled with the MASTER knob in COVERT

ALL or COVERT AC. The anticollision light can

flash seven selectable patterns in each of four power

supply switch settings (figure 159).

Position/Formation Lights

Refer to figure 160.

PX III

The position/formation lights have NVIS

friendly visible color lights as well as covert IR

emitters. The visible lights are disabled and the

covert lights enabled with the MASTER knob in

COVERT ALL or COVERT FORM. The lower

formation light and the lower wingtip lights do not

have IR emitters and are disabled with the MASTER

knob in COVERT ALL or COVERT FORM.

Air Refueling Lights

The AR floodlight shares the housing of the top

fuselage formation light. The light is directed aft to

flood the receptacle, fuselage, wing, and empennage.

The AR floodlight is not NVIS friendly. The AR

slipway contains embedded lights on each side of the

slipway. These lights are enabled when the AIR

REFUEL switch is in OPEN. The intensity of these

lights is controlled by the AERIAL REFUELING

knob. These lights are not NVIS friendly.

GR1F-16CJ-1-0059A37

1 2

EXT LIGHTING Control Panel

1. ANTICOLLISION Switch

2. FLASH STEADY Switch

3. WING/TAIL Switch

4. FUSELAGE Switch

5. AERIAL REFUELING Knob

6. MASTER Switch

7. FORM Knob

C DF

(Typical)

PX II

Figure 157.(Sheet 1)

T.O. GR1F16CJ1

1149

EXT LIGHTING Control Panel

(Typical)

PX II

CONTROL

POSITION

FUNCTION

1. ANTICOLLISION Switch

ANTICOLLISION

Turns on the white anticollision strobe (flash)

light on top of vertical tail

OFF

Turns off the anticollision strobe light

2. FLASH STEADY Switch

FLASH

Causes the lights controlled by WING/TAIL

switch to flash when turned on

STEADY

Causes the lights controlled by WING/TAIL

switch to light steady when turned on

3. WING/TAIL Switch

BRT

Turns on the red and green wingtip and inlet

lights and white light at trailing edge of verti

cal tail bright

OFF

Turns off the white light at trailing edge of ver

tical tail and the inlet lights. Allows the red

and green wingtip lights to be controlled by the

FORM knob

DIM

Turns on the red and green wingtip lights dim.

Turns on the red and green inlet lights and the

white light at the trailing edge of the vertical

tail dim

4. FUSELAGE Switch

BRT

Turns on the white floodlights at the base of

the vertical tail bright

OFF

Turns off the white floodlights

DIM

Turns on the white floodlights dim

5. AERIAL REFUELING

Knob

Variable from off to

BRT

Varies the AR slipway lights from off to bright

if AIR REFUEL switch is in OPEN

6. MASTER Switch

NORM

Enables all exterior lights except landing and

taxi lights

OFF

Disables all exterior lights except landing and

taxi lights

7. FORM Knob

Variable from off to

BRT

Varies the white formation lights on top and

bottom of fuselage and, when the WING/TAIL

switch is OFF, varies the red and green wing

tip lights from off to bright

Figure 157.(Sheet 2)

T.O. GR1F16CJ1

1150

GR1F-16CJ-1-1059X37

1 2

EXT LIGHTING Control Panel

1. ANTI-COLLISION Knob

2. FLASH STEADY Switch

3. WING/TAIL Switch

4. FUSELAGE Switch

5. AERIAL REFUELING Knob

6. MASTER Knob

7. FORM Knob

C DF

(Typical)

PX III

CONTROL

POSITION

6. MASTER Knob

CONTROL

POSITION

COVERT ALL

COVERT AC

COVERT FORM

NORM

1. ANTI

COLLISION

K b

1, 2, 3, 4,

A, B, & C

Flashes set pattern

(covert strobe)

Flashes set pattern

(covert strobe)

Flashes set pattern

(visible strobe)

Flashes set pattern

(visible strobe)

Knob

OFF

Off

2. FLASH

STEADY

Switch

FLASH

All lights flash co

vert

All lights except

the fuselage lights

flash

All lights flash co

vert

All lights except

the fuselage lights

flash

STEADY

All lights are covert

steady

All lights steady

All lights are covert

steady

All lights steady

3. WING/

TAIL

Switch

BRT

Upper wingtip, in

take, upper forma

tion, and tail lights

on covert bright

(lower wingtip and

lower formation

lights off)

Wing tip, intake,

and tail lights on

visible bright

Upper wingtip, in

take, upper forma

tion, and tail lights

on covert bright

(lower wingtip and

lower formation

lights off)

Wing tip, intake,

and tail lights on

visible bright

Figure 158.(Sheet 1)

T.O. GR1F16CJ1

1151

EXT LIGHTING Control Panel

(Typical)

PX III

CONTROL

POSITION

6. MASTER Knob

CONTROL

POSITION

COVERT ALL

COVERT AC

COVERT FORM

NORM

3. WING/

TAIL

Switch

(Cont)

OFF

Wing tip, intake

and tail lights off.

Upper formation

light covert bright

Intake and tail

lights off. Wingtip

lights controlled

by FORM knob

Wing tip, intake

and tail lights off.

Upper formation

light covert bright

Intake and tail

lights off. Wingtip

lights controlled

by FORM knob

DIM

Upper wingtip, in

take, tail lights on

covert dim. Upper

formation light co

vert bright. (lower

wingtip and forma

tion lights off)

Wingtip, intake,

and tail lights on

visible dim

Upper wingtip, in

take, tail lights on

covert dim. Upper

formation light co

vert bright. (lower

wingtip and forma

tion lights off)

Wingtip, intake,

and tail lights on

visible dim

4. FUSE

LAGE

S it h

BRT

Fuselage lights co

vert bright

Fuselage lights

visible bright

Fuselage lights co

vert bright

Fuselage lights

visible bright

Switch

OFF

Fuselage lights off Fuselage lights off Fuselage lights off Fuselage lights off

DIM

Fuselage lights co

vert dim

Fuselage lights

visible dim

Fuselage lights co

vert dim

Fuselage lights

visible dim

5. AERIAL

REFUEL

ING Knob

Variable from off to

bright

Variable from off to

bright

Variable from off to

bright

Variable from off to

bright

7. FORM

Knob

No effect

Controls forma

tion lights (and

wingtip lights

when WING/TAIL

switch is in OFF)

variable from off

to bright

No effect

Controls forma

tion lights (and

wingtip lights

when WING/TAIL

switch is in OFF)

variable from off

to bright

Figure 158.(Sheet 2)

T.O. GR1F16CJ1

1152

GR1F-16CJ-2066X37

POWER SUPPLY SETTING 1

Description

OFF

POWER SUPPLY SETTING 2

Description

NOTE:

Power supply settings are preset by maintenance personnel.

Anticollision Light Flash Patterns

ANTI-COLLISION

Knob

ANTI-COLLISION

Knob

Setting

1 Flash

2 Flash

3 Flash

4 Flash

1-2 Flash

1-3 Flash

6 Flash

OFF

1 Flash

2 Flash

3 Flash

4 Flash

2-1 Flash

3-1 Flash

6 Flash

PX III

Figure 159.(Sheet 1)

T.O. GR1F16CJ1

1153

GR1F-16CJ-1-2067X37

POWER SUPPLY SETTING 3

Description

OFF

POWER SUPPLY SETTING 4

Description

NOTE:

Power supply settings are preset by maintenance personnel.

Anticollision Light Flash Patterns

ANTI-COLLISION

Knob

ANTI-COLLISION

Knob

Setting

1 Flash

2 Flash

3 Flash

4 Flash

2-2 Flash

2-4 Flash

6 Flash

OFF

1 Flash

2 Flash

3 Flash

4 Flash

3-2 Flash

4-2 Flash

6 Flash

PX III

Figure 159.(Sheet 2)

T.O. GR1F16CJ1

1154

GR1F-16CJ-1-0060A37

POSITION LIGHT

(R-GREEN)

(L-RED)

FORMATION LIGHT

(WHITE)

TAXI LIGHT

LANDING LIGHT

POSITION/FORMATION

LIGHT (RED)

(TOP AND BOTTOM)

(BOTH SIDES)

FORMATION

LIGHT (FUSE-

LAGE LABEL ON

CONTROL PANEL)

(FLOOD) (WHITE)

POSITION

LIGHT (WHITE)

ANTICOLLISION STROBE

VERTICAL TAIL-MOUNTED

FLOODLIGHT (WHITE)

AR SLIPWAY LIGHT

(INTERIOR LIGHT)

POSITION/FORMATION

LIGHT (GREEN)

(TOP AND BOTTOM)

(AFT SIDE)

AR (FLOOD)

(WHITE)

(FORWARD SIDE)

FORMATION LIGHT

(WHITE)

Exterior Lighting (Typical)

(

TOP WITH IR)

WITH IR)

(WHITE) (

WITH IR)

(

WITH IR)

TOP WITH IR)

PX III

(

PX III

(

PX III

(

PX III

(

PX III

Figure 160.

Vertical TailMounted Floodlight

A white light is mounted on the upper leading edge of

the vertical tail and is directed forward to flood the AR

receptacle and upper fuselage. The light illuminates

by the OPEN position of the AIR REFUEL switch.

The floodlight is not NVIS friendly.

Landing and Taxi Lights

A white landing and taxi light assembly is located on

the NLG door. The landing light is angled to

illuminate the landing area. The lights are turned on

by the threeposition LANDING TAXI lights switch

located on the LG control panel. The switch has

positions of LANDING, OFF, and TAXI. The light

goes off during LG retraction if the switch is left in

either the LANDING or TAXI position. The landing

and taxi lights are not NVIS friendly.

INTERIOR LIGHTING

Refer to figure 161. The interior LIGHTING control

panel, located on the right console, contains the power

and intensity controls for the primary (console and

instrument) and secondary (flood) lighting systems

for the cockpit,

PX III

and NVIS (night vision imaging

system). The HIGH INT position of the FLOOD

CONSOLES knob provides thunderstorm lighting.

PX III

In addition, NVIS operation is provided which

turns off most primary and secondary lights and sets

the warning, caution, and advisory lights to dim.

PX III

The interior lighting system, with the

exception of the utility light, functions normally

except all lighting is NVIS green. Internal instru

ment lighting has been disabled and replaced with

post and bezel NVIS friendly lighting. Secondary

lighting has been equipped with NVIS green filters to

eliminate IR light. Caution and warning lights have

filters which limit IR emissions to be compatible with

night vision goggles. All interior lighting (except for

one position on the utility light) is NVIS friendly and

invisible through the night vision goggles. Cockpit

instruments must be viewed beneath the goggles.

T.O. GR1F16CJ1

1155

PX III

When NVIS operation is deselected, all light

control panel functions are returned to normal

operation. All console, instrument, and flood lights

are illuminated to current settings. All warning,

caution, and advisory lights return to bright only if

the PRIMARY INST knob is in HIGH INT or OFF.

PRIMARY CONSOLES Knob

The PRIMARY CONSOLES knob has a cw arrow

pointing toward BRT. Rotating the knob cw varies the

intensity of the primary console and left auxiliary

console lighting from dim to bright.

PX III

During

NVIS operation, this lighting is off and rotating the

knob has no effect on lighting intensity.

PRIMARY INST PNL Knob

The PRIMARY INST PNL knob has a cw arrow

pointing toward BRT. Rotating the knob cw varies the

intensity of the forward instrument panel and right

auxiliary console lighting from off to bright.

PX III

During NVIS operation, rotating the knob cw varies

the intensity of the

ICP,

IKP.

DATA ENTRY DISPLAY Knob

The DATA ENTRY DISPLAY knob has a cw arrow

pointing toward BRT. The knob controls the lighting

of the DED and PFLD from dim to bright.

MAL & IND LTS Switch

The MAL & IND LTS switch has positions of BRT and

DIM and a springloaded unmarked center position.

If the PRIMARY INST PNL knob is on, momentary

activation of the switch to DIM places the lighting

system to the dim condition. The system automatical

ly returns to the BRT condition if the FLOOD

CONSOLES knob is turned past the detent to HIGH

INT, if the PRIMARY INST PNL knob is turned off,

or if emergency dc power is lost. The BRT condition

can be manually selected anytime. The switch

controls the light intensity of all the warning, caution,

and indicator lights except the following individually

dimmed lights:

AOA indexer.

AR/NWS indexer.

DED.

ECM control panel.

MFD's.

PFLD.

TWS indicators.

PX III

When the NVIS switch is in ARM, all lights

controlled by the MAL & IND LTS switch are

automatically set and locked to the dim setting and

the MAL & IND LTS switch is inoperative.

FLOOD INST PNL Knob

The FLOOD INST PNL knob has a cw arrow pointing

toward BRT. Rotating the knob cw varies the

floodlights intensity from off to bright.

PX III

During

NVIS operation, the floodlights are off and rotating

the knob has no effect on lighting intensity.

FLOOD CONSOLES Knob

The FLOOD CONSOLES knob rotates from OFF to

HIGH INT. Rotating the knob cw varies the console

floodlights intensity from off to bright. If rotated to

HIGH INT, the MAL & IND LTS and instrument

panel floodlights automatically go to bright and the

alphanumeric displays controlled by the DATA

ENTRY DISPLAY knob go to the highest intensity

level. CCW rotation past a certain point restores the

alphanumeric displays to the intensity level set by

the DATA ENTRY DISPLAY knob, but the MAL &

IND LTS switch must be manually reset to DIM, if

dim is desired.

PX III

During NVIS operation, the

console floodlights are off and rotating the knob has

no effect on lighting intensity.

NVIS Switch

PX III

The NVIS switch has three positions: NORM LTG,

ARM, and NVIS. The ARM position is a lever locked

position. The NVIS position is spring loaded and the

switch returns to the ARM position when released.
Functions are:

NORM LTG:

All cockpit lighting functions normally.

Blackout function disabled.

ARM:

Blackout function enabled (not activated).

Caution/warning/advisory lights function in the

dim mode.

High intensity flood lighting disabled.

Reduces the MFD brightness level when above a

preset level.

Deenergizes the MFD nonNVIS compatible

backlighting.

NVIS:

Activates/deactivates blackout function.

T.O. GR1F16CJ1

1156

GR1F-16CJ-1-0061A37

Interior LIGHTING Control Panel (Typical)

PRIMARY CONSOLES Knob

PRIMARY INST PNL Knob

DATA ENTRY DISPLAY Knob

MAL & IND LTS Intensity Switch

FLOOD INST PNL Knob

FLOOD CONSOLES Knob

Hands-on Blackout (HOBO) Paddle Switch

NVIS Switch

PX II

PX III

Figure 161.

T.O. GR1F16CJ1

1157

When the blackout function is activated, most of the

nonNVIS compatible light sources in the cockpit are

turned off. These include primary flight instruments,

engine instruments, and hydraulic gauges. For a

complete list of the nonNVIS compatible lights which

are not turned off by the blackout function, refer to

GR1F16CJ3411.

HandsOn Blackout (HOBO) Switch

PX III

The HOBO paddle switch, located on the throttle,

activates/deactivates the blackout function when the

NVIS switch is in ARM.

Utility Light

Refer to figure 162. The utility light, located on the

right console, includes

PX II

three,

PX III

four

controls:a pushbutton switch to allow momentary

operation at the highest intensity level, an OFF DIM

BRT rotary knob to allow continuous operation at any

desired intensity level,

PX III

an NVIS WHITE

selector for NVIS (green) or normal (white) operation,

and a lens housing which, when rotated, adjusts the

beam from flood to spot. To release the light from its

stowed position, lower the knurled collar at the base

of the light and it will pop free. The light can be locked

back into position by placing the body of the light

parallel to the sidewall fairing and pushing down

firmly on the light assembly. With the canopy closed,

the utility light may be attached to an adjustable

sliding holder located on the right body positioning

handle (towel rack). The light is powered by battery

bus No. 1.

Cockpit Spotlights

Refer to figure 162.

The cockpit spotlights are located

under the upper left and right glareshields. In the

stowed position (horizontal, facing forward), the

spotlight is off. The spotlight is turned on by pulling

the spotlight barrel downward. Illumination intensity

is controlled by turning the knurled barrel (dimmer).

To turn the spotlight off, return it to the stowed

position. Overrotation of the knurled barrel may

cause breakage of the bulb or rheostat. The lights are

ESCAPE SYSTEM

CANOPY

The canopy is a twopiece, plastic, bubbletype,

transparent enclosure. The forward part is a single

piece windshieldcanopy transparency, which is

hinged at the aft end and is unlatched, opened, or

closed/latched by an electrically operated actuator

with a manual backup.

A smaller fixed

transparency fairs to the fuselage aft of the seat. The

canopy may be jettisoned by internal controls for

inflight or ground escape and by external controls

for ground rescue. An inflatable pressurization seal

on the cockpit sill mates with the edge of the movable

canopy. A noninflatable rubber seal on the canopy

prevents the entry of water when the cockpit is not

pressurized.

The canopy provides some bird strike protection. Bird

strikes on centerline at approximately eye level may

produce enough canopy deflection to shatter the HUD

combiner glass and cause rearward propagation of a

deflection wave. Deflection of the canopy in the area

of the pilot's helmet has been observed to be 1 to 2

inches during bird strike tests that were considered

successful. Successful completion of canopy bird

strike testing (4 pound bird at 350 or 550 knots,

depending on canopy) requires that the canopy not

deflect more than 2 1/4 inches in the area of the pilot's

helmet. This may be a consideration for adjusting

seat height, especially while flying at lower altitudes

with helmetmounted equipment. Impacts off center

may not shatter the HUD glass. High energy bird

strikes may cause canopy penetration or larger

deflection waves.

CANOPY CONTROLS AND INDICATORS

Refer to figure 163.

MANUAL CANOPY CONTROL Handcrank

An internal MANUAL CANOPY CONTROL

handcrank manually performs the same function as

the canopy switch. Due to the strength required to

open the canopy with the handcrank, the method

should be considered a last resort.

An external flushmounted CANOPY handcrank

receptacle just opposite the inside manual drive is

used for ground crew manual operation of the canopy.

Canopy Handle

The canopy handle, located on the canopy sill just

forward of the throttle, hinges down to cover and

protect the internal canopy switch. The handle also

functions to inflate/deflate the canopy pressure seal,

to turn the CANOPY warning light off/on, and to

mechanically prevent the canopy actuator from

unlatching. The canopy handle should be in the up

(unlock) position prior to lowering the canopy.

T.O. GR1F16CJ1

1158

GR1F-16CJ-1-0062A37

LENS HOUSING

ROTARY KNOB

PUSHBUTTON SWITCH

QUICK-

DISCONNECT

PLUG

COLLAR

Utility Light and Spotlights (Typical)

FLOOD SPOT

QUICK-

DISCONNECT

PLUG

RIGHT BODY

POSITIONING

HANDLE

(TOWEL RACK)

COLLAR

NVIS WHITE

SELECTOR

LENS HOUSING

PUSHBUTTON

SWITCH

ROTARY KNOB

RIGHT BODY

POSITIONING

HANDLE

(TOWEL RACK)

C DF

COCKPIT SPOTLIGHTS

UTILITY LIGHT

PX III

PX II

Figure

162.

T.O. GR1F16CJ1

1159

If the internal canopy switch is in the up position,

the canopy cannot be closed using the external

canopy switch.

Canopy Handle (shown in unlocked position)

Canopy Switch (internal) (spring-loaded

to center from down position)

CANOPY Warning Light (Red)

Ejection Handle (PULL TO EJECT)

MANUAL CANOPY CONTROL Handcrank

CANOPY JETTISON T-Handle

Canopy Jettison D-Handle (each side of fuselage)

Canopy Lock Access Plug (external)

CANOPY Handcrank Receptacle (external)

Canopy Switch (external) (spring-loaded to center)

C DF

NOTE:

GR1F-16CJ-1-0063A37

(Left side panel,

forward cockpit)

Canopy Controls and Indicators (Typical)

10.

CANOPY

7 8 9 10

CANOPY

PX III

PX II

PX III

Figure 163.(Sheet 1)

T.O. GR1F16CJ1

1160

Canopy Controls and Indicators (Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

1. Canopy Switch (inter

nal) (spring loaded to center

C DF

Opens canopy

nal) (springloaded to center

from down position)

Center

Stops canopy motion

Down

Closes and latches canopy

2. Canopy Handle

C DF

Unlocks canopy

Down

Locks canopy

3. CANOPY Warning Light

(red)

Off

Canopy locked

(red)

Canopy unlocked

4. Ejection Handle (PULL TO

EJECT)

Pull

Jettisons canopy and ejects seat

5. MANUAL CANOPY

CONTROL Handcrank

C DF

Rotate ccw

Opens canopy

CONTROL Handcrank

Rotate cw

Closes and latches canopy

6. CANOPY JETTISON

THandle

Pull (depress either but

ton)

Jettisons canopy independent of seat ejection

7. Canopy Jettison DHandle

(each side of fuselage)

Pull (approximately 6

feet) (either handle)

Jettisons canopy independent of seat ejection

8. Canopy Lock Access Plug

(external)

Remove access plug

Access to unlock internal canopy handle

(external)

Refer to EMERGENCY ENTRANCE AND

CREW RESCUE, Section III

9. CANOPY Handcrank

Receptacle (external)

Rotate cw

Opens canopy

Receptacle (external)

Rotate ccw

Closes and latches canopy

10. Canopy Switch (external)

(spring loaded to center

Opens canopy

(springloaded to center

position)

Aft

Center

Stops canopy motion

Down

Closes and latches canopy

Fwd

Figure 163.(Sheet 2)

T.O. GR1F16CJ1

1161

CANOPY JETTISON

Pulling the external canopy jettison Dhandle,

located on either side of the fuselage, initiates the

canopy jettison sequence independent of seat

ejection.

Depressing the button, located on either side of the

internal

CANOPY JETTISON Thandle, and pulling

the Thandle initiates the canopy jettison sequence

independent of seat ejection.

Pulling the ejection handle (PULL TO EJECT),

located on the front of the ejection seat, initiates the

canopy jettison sequence followed by the

seat ejection

sequence.

EJECTION SEAT

Refer to figure 164.

The ACES II ejection seat is a

fully automatic emergency escape system. One of

three ejection modes is automatically selected. Mode

1 is a low airspeed, low altitude mode during which

the recovery parachute assembly is deployed almost

immediately after the ejection seat departs the

aircraft. Mode 2 is an intermediate airspeed, low

altitude mode during which a drogue chute is first

deployed to slow the ejection seat followed by the

deployment of the recovery parachute assembly.

Mode 3 is a high airspeed/high altitude mode in which

the sequence of events is the same as mode 2, except

that automatic pilot/seat separation and deployment

of the recovery parachute assembly are delayed until

safe airspeed and altitude are reached. Controls are

provided to adjust seat height and lock shoulder

harness.

Ejection Handle

The ejection handle (PULL TO EJECT) is sized for

onehanded or twohanded operation and requires a

pull of 4050 pounds to activate. The handle remains

attached to the seat by a wire cable after activation.

SHOULDER HARNESS Knob

The SHOULDER HARNESS knob unlocks the

inertia reel when in the aft position and locks it when

in the forward position. If high longitudinal

deceleration force or high shoulder harness strap

playout velocities are encountered, the inertia reel

automatically locks.

EMERGENCY MANUAL CHUTE Handle

The EMERGENCY MANUAL CHUTE handle is

locked while the ejection seat is in the aircraft. After

ejection, the handle provides a backup to the

automatic pilot/seat separation and recovery para

chute deployment system. The handle must be pulled

approximately 6 inches. The first 2 inches of pull

ballistically deploys the recovery parachute assem

bly; however, the seat will still be attached by the

lapbelt and the inertia reel straps, and the survival

kit under the latched seat pan lid. Continued pull

releases the lapbelt and inertia reel straps and

unlatches the seat pan lid.

Ejection Safety Lever

The ejection safety lever mechanically safeties (in the

up/vertical position) or arms (in the down/horizontal

position) the seat ejection handle.

SEAT NOT ARMED Caution Light

The SEAT NOT ARMED caution light, located on the

caution light panel, illuminates when the ejection

safety lever is in the up (vertical) position.

The

caution lights illuminate independently of each

other.

SEAT ADJ Switch

Refer to figure 13. The SEAT ADJ switch is located

on the right cockpit sidewall outboard of the stick.

Center position is springloaded off. The up position

raises the seat, while the down position lowers the

seat. The seat adjustment motor is protected by a

thermal relay which interrupts electrical power when

overheated. After a 1minute cooling period, the

motor should operate normally. The motor is powered

by nonessential ac bus No. 1.

Shoulder Harness Straps/Parachute Risers

The upper torso restraints consist of shoulder

harness straps which also act as parachute risers.

The inertia reel straps are attached to the parachute

risers.

Inertia Reel Straps

The inertia reel straps may be manually released

after ejection by pulling the EMERGENCY MANU

AL CHUTE handle approximately 6 inches.

Lapbelt

The lower torso restraint is the lapbelt. The lapbelt

may be released after ejection by pulling the

EMERGENCY MANUAL CHUTE handle approxi

mately 6 inches.

Content .. 9 10 11 12 ..

F16C/D. FLIGHT MANUAL (2002) - page 11

F16C/D. FLIGHT MANUAL (2002) - page 11