Content .. 16 17 18 19 ..

F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002) - page 18

T.O. GR1F16CJ1

1128

Stick (Typical)

NWS

A/R DISC

MSL STEP

CAMERA/

GUN

WPN

REL

TRIM

GR1F-16CJ-1-0047X37

NWS A/R DISC MSL STEP Button

TRIM Button (4-Way, Momentary)

Display Management Switch

(4-Way, Momentary)

Countermeasures Management

Target Management Switch

(4-Way, Momentary)

WPN REL Button

Expand/FOV Button

Paddle Switch

CAMERA/GUN Trigger (2-Position)

Switch (4-Way, Momentary)

CONTROL

POSITION

FUNCTION

1. NWS A/R DISC MSL

(NWS)

STEP Button

Depress (on ground)

Activates NWS

STEP Button

Depress (2nd time)

Deactivates NWS

(A/R DISC)

Depress (in flight)

Disconnects boom latching. AIR REFUEL

switch must be in OPEN position

(MSL STEP)

Depress (in flight)

Activates missile step function. Refer to

T.O. GR1F16CJ3411

2. TRIM Button (NOSE DOWN)

Fwd

Trims nosedown

(4way, momentary) (NOSE UP)

Aft

Trims noseup

(LWD)

Left

Trims left wing down

(RWD)

Right

Trims right wing down

Figure

146.(Sheet 1)

T.O. GR1F16CJ1

1129

Stick (Typical)

CONTROL

POSITION

FUNCTION

3. Display Management Switch

(4 way momentary)

Refer to T.O. GR1F16CJ3411 for a de

tailed description of switch functions

(4way, momentary)

Down

tailed description of switch functions

Left

Right

4. Target Management Switch

(4 way momentary)

(4way, momentary)

Down

Left

Right

5. Countermeasures Manage

ment Switch (4 way momen

Fwd

ment Switch (4way, momen

tary)

Aft

Left

Right

6. Expand/FOV Button

Depress

Successive depressions sequence through

the available fieldofview (FOV) selections

for the sensor/system mode being displayed

on the DOI

7. Paddle Switch

Depress

Interrupts the autopilot while switch is de

pressed. Terminates ATF flyup. If in ATF,

reverts to manual TF while depressed.

Resets SWIM monitors when released

For stick override function, refer to

F16D AIRCRAFT, this section

8. CAMERA/GUN Trigger

(2position)

Squeeze trigger to

detent

Starts operation of AVTR/CTVS with AUTO

selected on AVTR power switch and pro

vides consent for laser fire (if selected and

armed)

Squeeze trigger past

detent

Fires gun (if selected and armed), AVTR/

CTVS operation continues, and consent for

laser fire continues (camera operation con

tinues for 30 seconds after trigger is

released)

9. WPN REL Button

Depress

Signals consent to FCC or SMS,

MMC to initiate weapon release and

operates HUD camera for 30 seconds when

in AUTO

III

Figure

146.(Sheet 2)

T.O. GR1F16CJ1

1130

Maximum noseup and nosedown pitch commands are

generated by 25 and 16 pounds of input, respectively.

Roll commands are generated by a maximum of 17

pounds in cruise gains and by 12 pounds in takeoff

and landing gains. When using the switches/buttons

on the stick, inadvertent commands to the FLCS are

possible.

The wristrest and armrest assemblies which may be

used in conjunction with the stick are located on the

right side wall aft of the stick.

Rudder Pedals

The rudder pedals are forcesensing units containing

transducers. Force on the applicable rudder pedal

produces electrical yaw command signals.

The rudder pedals are also used to generate brake

and NWS signals. Rudder pedal feel is provided by

mechanical springs.

MANUAL TRIM Panel

Refer to figure 147. The MANUAL TRIM panel,

located on the left console, contains trim controls and

indicators.

MANUAL PITCH Override (MPO) Switch

Refer to figure 148. The MPO switch, located on the

left console, has two positions, NORM and OVRD,

and is springloaded to the NORM position. This

switch is used during a deep stall condition to enable

manual control of the horizontal tails. Positioning

and holding the switch to OVRD overrides the

negative g limiter. If AOA exceeds 35 degrees, the

OVRD position overrides the AOA/g limiter and

allows pitch commands.

STORES CONFIG Switch

Refer to figure 149. The STORES CONFIG switch,

located on the LG control panel, has two positions,

CAT I and CAT III. The CAT III position shall be

selected when the aircraft is configured with a

category III loading.

AOA limiting is provided. Refer to FLCS LIMITERS,

this section, for a description of categories I and III

AOA limiter.

Low Speed Warning Tone

Refer to figure 150. A low speed warning tone

(steady) sounds in the headset when one of the

following conditions exists:

AOA is 15 degrees or greater with LG handle down

or ALT FLAPS switch in EXTEND.

Combined airspeed and pitch angle fall on a point

within the tone on area with LG handle up and ALT

FLAPS switch in NORM.

When the TFR is operating and airspeed drops

below 300 knots (KCAS or groundspeed).

The low speed warning tone has priority over the LG

warning horn. Depressing the HORN SILENCER

button silences the low speed warning tone.

The low speed warning tone is reactivated only after

the original warning condition is eliminated. The

MAL & IND LTS test button does not test the low

speed warning tone.

FLT CONTROL Panel (FLCP)

Refer to figure 151. The FLCP, located on the left

console, contains indicators and controls related to

flight control functions.

FLCS WARNING, CAUTION, AND INDICATOR

LIGHTS

The instrument panel, caution panel, PFLD, FLCP,

ELEC control panel, TEST switch panel, and avionic

system contain warning, caution, and indicator lights

related to the FLCS. The FLCS is interfaced to the

avionic system via the multiplex (MUX) bus to

provide PFL and MFL reporting.

FLCS Warning Light

The FLCS warning light, located on the right

glareshield, illuminates to indicate a dual malfunc

tion in the FLCC electronics, including the

processors, power supplies, input commands or

sensors, AOA, or air data inputs. The FLCS warning

light also illuminates if the LEF's are locked or BIT

fails. The FLCS warning light remains illuminated

until FLCS reset action is successful in clearing the

failure. If an active warning fault exists and a

subsequent warning level malfunction occurs, the

FLCS warning light goes off momentarily to retrigger

HUD WARN and voice warning.

More specific system failure information can be

obtained from the PFLD.

T.O. GR1F16CJ1

1131

GR1F-16CJ-1-0048X37

1. ROLL TRIM Wheel

2. ROLL TRIM Indicator

3. TRIM/AP DISC Switch

4. PITCH TRIM Indicator

5. PITCH TRIM Wheel

6. YAW TRIM Knob

MANUAL TRIM Panel

(Typical)

C DF

CONTROL

POSITION

FUNCTION

1. ROLL TRIM Wheel

L WING DN rotation

Trims left wing down

R WING DN rotation

Trims right wing down

2. ROLL TRIM Indicator

Visual

Indicates roll trim

3. TRIM/AP DISC Switch

NORM

Energizes stick TRIM button. Permits autopi

lot engagement

DISC

Deenergizes stick TRIM button, prevents

autopilot engagement and ATF/autopilot

blending, and deactivates trim motors

(manual trim wheels still operative)

4. PITCH TRIM Indicator

Visual

Indicates pitch trim

5. PITCH TRIM Wheel

NOSE UP rotation

Trims noseup

NOSE DN rotation

Trims nosedown

6. YAW TRIM Knob

CCW rotation

Trims nose left

CW rotation

Trims nose right

Figure 147.

T.O. GR1F16CJ1

1132

GR1F-16CJ-1-0049X37

1. MPO Switch

Manual Pitch Over-

ride Switch (Typical)

C DF

Figure 148.

GR1F-16CJ-1-0050X37

1. STORES CONFIG Switch

STORES CONFIG

Switch

(Typical)

C DF

Figure 149.

PITCH ATTITUDE DEGREES

KIAS

30 45 60 75 90 105 120 135 150

100

125

150

175

200

225

250

TONE ON

1F-16X-1-0022X

Low Speed Warning

Tone Schedule

NOTES:

Dashed lines indicate airspeed tolerances for low

speed warning tone activation.

LG handle in UP and ALT FLAPS switch in NORM.

Figure150.

DBU ON Warning Light

The DBU ON warning light, located on the right

glareshield, illuminates to indicate the FLCC has

automatically switched to DBU or if the DIGITAL

BACKUP switch is manually positioned to DIGITAL

BACKUP.

TO/LDG CONFIG Warning Light

Refer to LANDING GEAR SYSTEM, this section.

FLCS FAULT Caution Light

The FLCS FAULT caution light, located on the

caution light panel, illuminates when the FLCC

reports a caution level PFL item which requires pilot

action. The caution light goes off either when the fault

is acknowledged or when FLCS reset action is

successful in clearing the failure.

If the FLCS FAULT caution light is illuminated and

a subsequent malfunction occurs, the caution light

goes off momentarily to activate the MASTER

CAUTION light and retrigger voice caution.

More specific system failure information can be

obtained from the PFLD.

T.O. GR1F16CJ1

1133

GR1F16CJ10052X37

1. MANUAL TF FLYUP Switch

2. DIGITAL BACKUP Switch

3. ALT FLAPS Switch

4. RUN FAIL Light

5. BIT Switch

6. FLCS RESET Switch

7. LE FLAPS Switch

8. ADV MODE Switch

9. Autopilot PITCH Switch

FLT CONTROL Panel

10. Autopilot ROLL Switch

MISC Panel

(Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

1. MANUAL TF FLYUP

Switch (lever lock)

DISABLE

Flyup protection not available in manual TF

Switch (lever lock)

ENABLE

Flyup protection available in manual TF for

TF or SWIM detected failure

2. DIGITAL BACKUP Switch

(lever lock)

BACKUP

Selects backup software program within the

FLCC

OFF

Normal position

3. ALT FLAPS Switch

(lever lock)

NORM

TEF operation controlled by LG handle

(lever lock)

EXTEND

TEF's extend regardless of LG handle posi

tions

4. RUN/FAIL Lights

RUN (green)

Indicates FLCS BIT is running

FAIL (red)

Indicates a failure during the FLCS BIT

5. BIT Switch (solenoid

held in BIT and

OFF

Normal position

held in BIT and

leverlocked to OFF)

BIT

Commands BIT if weight is on main LG and

wheel speed is less than 28 knots

groundspeed

Figure

151.(Sheet 1)

T.O. GR1F16CJ1

1134

FLT CONTROL Panel

(Typical)

CONTROL/INDICATOR

POSITION/INDICATION

FUNCTION

6. FLCS RESET Switch

(spring loaded to OFF)

OFF

Normal position

(springloaded to OFF)

RESET

Momentary position which performs servo or

electronic reset of FLCS system failures.

Resets FLCS warning light, CADC, FLCS

FAULT, and MASTER CAUTION lights and

clears PFL's if fault is cleared

7. LE FLAPS Switch

(lever lock)

AUTO

LEF's are automatically controlled as a func

tion of mach, altitude, and AOA

LOCK

Manually locks the LEF's in position and illu

minates the FLCS warning light and FLCS

LEF LOCK PFL

8. ADV MODE Switch

Depressing switch illuminates ATF NOT

ENGAGED caution light if NVP or FLCS

cannot support ATF

ACTIVE (green)

Depressing switch illuminates ACTIVE light

and selects ATF if TFR is in operate mode

STBY (amber)

Illuminates when ATF/autopilot blended

mode is in use or the paddle switch is de

pressed in ATF. STBY light indicates that

ATF is ready to take over if the paddle switch

is released or if higher terrain requires it

9. Autopilot PITCH Switch

ALT HOLD

Engages pitch and roll axes of autopilot.

Autopilot maintains constant altitude as

determined by CADC; roll mode is deter

mined by ROLL switch

A/P OFF

Disengages pitch and roll axes of autopilot

ATT HOLD

Engages pitch and roll axes of autopilot.

Autopilot maintains constant pitch attitude

as determined by INS; roll mode is deter

mined by ROLL switch

10. Autopilot ROLL Switch

NOTE:

HDG SEL

Autopilot turns the aircraft to capture and

maintain the heading selected by the head

ing reference marker on the HSI

Autopilot roll modes

are functional when

th PITCH

it h i

ATT HOLD

Autopilot maintains roll attitude as deter

mined by the INS

the PITCH switch is

out of A/P OFF.

STRG SEL

Autopilot steers aircraft to the selected steer

point

Figure 151.(Sheet 2)

T.O. GR1F16CJ1

1135

BuiltIn Test (BIT)

The BIT switch, located on the FLCP, is a twoposition

switch which is leverlocked in OFF and solenoid held

in BIT. When engaged (green RUN light illuminates),

the BIT runs for approximately 45 seconds. A failure

during the BIT sequence or a BIT interlock failure

terminates BIT, returns the switch to OFF,

illuminates the red FAIL light and the FLCS warning

light, and sends an FLCS BIT FAIL PFL message.

BIT failures are nonresettable and the red FAIL light

does not go off until a subsequent BIT is successfully

completed. A BIT detected bus communication failure

results in illumination of the FLCS FAULT caution

light and an FLCS MUX DEGR PFL. An FLCS reset

extinguishes the caution light but the PFL remains.

Successful completion of BIT is indicated by the BIT

switch automatically returning to OFF, the green

RUN light going off, no FLCS BIT FAIL PFL, and a

BIT PASS message on the FLCS page of the MFD.

Pilot Fault List Display (PFLD)

The PFLD, located on the

right auxiliary

console,

instrument panel, displays FLCS PFL's.

Refer to WARNING, CAUTION, AND INDICATOR

LIGHTS, this section, for a description of the PFLD.

Refer to PILOT FAULT LIST - FLCS, Section III, for

a description of FLCS PFL's.

TRIM

Pitch trim inputs may be initiated from either the

TRIM button on the stick or the PITCH TRIM wheel

on the MANUAL TRIM panel. In cruise gains, pitch

trim inputs are g command signals identical in

function to normal stick pitch commands. In takeoff

and landing gains, the FLCS operates as a pitch rate

command system until 10 degrees AOA and a pitch

rate and AOA command system above 10 degrees

AOA.

With both main wheel speeds at 60 knots

groundspeed or greater, pitch trim automatically

centers.

Roll trim inputs can be initiated from either the TRIM

button on the stick or the ROLL TRIM wheel on the

MANUAL TRIM panel. For asymmetric configura

tions or rudder mistrim, roll retrimming may be

required as flight conditions change. Roll trim inputs

also command proportional rudder deflection

through the ARI function.

Rudder trim is initiated from the YAW TRIM knob on

the MANUAL TRIM panel only. For asymmetric

configurations or roll mistrim, rudder retrimming

may be required as flight conditions change.

AUTOPILOT

The autopilot provides attitude hold, heading select,

and steering select in the roll axis and attitude hold

and altitude hold in the pitch axis. These modes are

controlled by PITCH and ROLL switches on the MISC

panel. The TRIM/AP DISC switch on the MANUAL

TRIM panel disengages the autopilot. The paddle

switch on the stick interrupts autopilot operation

while the switch is held depressed.

The PITCH switch is a threeposition switch which is

solenoid held in an engaged position and goes to the

A/P OFF position if any of the following conditions

exist.

Conditions are:

AIR REFUEL switch - OPEN.

ALT FLAPS switch - EXTEND (below 400 knots).

A/P FAIL PFL occurs.

AOA greater than 15 degrees.

DBU - Engaged.

LG handle - DN.

Low speed warning tone sounds.

MPO switch - OVRD.

STBY GAIN PFL occurs.

TRIM/AP DISC switch - DISC.

Movement of the PITCH switch out of A/P OFF

engages both the pitch and roll autopilot modes

selected.

The ROLL switch is a threeposition switch which

enables one of the three roll autopilot modes

whenever a pitch autopilot mode is selected.

Content .. 16 17 18 19 ..

F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002) - page 18

F16C/D (BLOCKS 50 AND 52+). FLIGHT MANUAL (15 OCTOBER 2002) - page 18