F16C/D. FLIGHT MANUAL (2002) - page 43

T.O. GR1F16CJ1CL2

B12

OTHER CONSIDERATIONS:

1

W

 

F

 Exceeding 10

_

 AOA may result in insufficient roll

authority. Limit rolling maneuvers to gentle roll in with a max

bank angle of 30

_

.

F

 Flying a fast approach (lower than 6

_

 AOA) presents

additional control difficulties caused by a change in the path of

the disturbed airflow coming off the failed LEF.

2

W

 Minimize rudder inputs. Use rudder as required to reduce

sideslip when jettisoning stores or to aid in maintaining desired

ground track during the final part of landing approach. Do not

use rudder trim.

3

 Lock operating LEF as near symmetrical as possible.

4

 Consider selective jettison of stores from the heavy wing as

a means to reduce roll control requirements. Refer to

SELECTIVE JETTISON, page F27.

5

C

 Reduce fuel weight if pilot arm fatigue is not a factor. Fuel

flow is significantly higher with an LEF failed full up or down and

must be considered during recovery.

6

 Lower LG at a safe altitude and check handling qualities at

6

_

8

_

 AOA.

7

W

 

F

 Prior to landing with a significant asymmetric LEF

condition, consider aircraft configuration, pilot experience

level, pilot arm fatigue, airfield facilities, weather, winds, and

light conditions (day/night). If conditions are not favorable, a

controlled ejection is recommended.

F

 If crosswind component is greater than 10 kts, choose a

runway, if possible, which allows landing with the heavy wing

upwind. Fly a shallow, straightin approach at approx 8

_

 AOA

(fly no lower than 6

_

 AOA) with min roundout for touchdown.

Use rudder, as required, to align aircraft with the runway

immediately prior to touchdown.

8

C

Until WOW, forward stick pressure in excess of approx 2

lbs results in full trailing edge down deflection of the horizontal

tails with reduced directional control and wheel braking

effectiveness.

B12

7 3/4 " Page

T.O. GR1F16CJ1CL2

B13

LEF MALFUNCTION (ASYMMETRIC)

If LEF asymmetry occurs:

1. AOA - 6

_

10

_

.

1

W

2. Lateral stick/roll trim - As required.

2

W

3. LE FLAPS sw - LOCK.

3

4. Stores - Jettison (if required).

4

5. Fuel weight - Reduce (if feasible/required).

5

C

6. Controllability - Check.

6

7. Land as soon as practical.

7

W

8. Stick - Lower the nose immediately after

touchdown.

8

C

If departureend arrestment is required:

9. HOOK sw - DN.

FLCS TEMPERATURE MALFUNCTION

If an FLCS HOT TEMP PFL occurs:

1. Airspeed - 400 kts max (subsonic).

(Cont)

B13

8

LEF MALF (ASY)/FLCS TEMP MALF

" Page

T.O. GR1F16CJ1CL2

B14

OTHER CONSIDERATIONS:

9

 If possible, descend below 15,000 ft MSL.

10

W

F

With the ECS shut down or the AIR SOURCE knob in

OFF or RAM, the gsuit does not inflate and PBG is disabled.

F

 If AIR SOURCE knob is placed to OFF or RAM, OBOGS is

inoperative. Activate EOS if OXY LOW warning light illuminates

above 10,000 ft cockpit altitude.

11

 External fuel cannot be transferred in OFF or RAM.

Consider jettisoning tanks to decrease drag if range is critical

and the ECS cannot be turned on for short periods of time to

transfer fuel.

12

 It may take up to 15 minutes for ramair cooling to

extinguish the light.

B14

8 " Page

T.O. GR1F16CJ1CL2

B14.1

2.Altitude - 25,000 ft MSL max.

9

3.AIR SOURCE knob - RAM.

10

W

11

If failure indications go off:

12

4.Land as soon as practical.

If failure indications remain on:

5.Land as soon as possible.

END

B14.1

7 7/8 " Page

T.O. GR1F16CJ1CL2

B14.2

OTHER INDICATIONS:

Single Failures:

D

FLCS FAULT caution light.

D

FLCS AOA FAIL and FLCS ADC FAIL PFL's may accompany a

BRK PWR DEGR PFL.

Dual Failures:

D

FLCS warning light.

OTHER CONSIDERATIONS:

1

 Observe FLCS PWR lights and determine brake and brake

channel affected. If branch A, B, or C FLCS PWR light fails to

illuminate, use a max of 11

_

 AOA for approach, landing, and

twopoint aerodynamic braking.

2

The ATF NOT ENGAGED caution light may illuminate shortly

after depressing the ADV MODE sw.

3

Reset may clear the FLCS warning light; however, the single

failure is still present.

4

F

No significant flying qualities degradation should occur;

however, with an FLCS dual failure, the FLCS has no

redundancy.

F

Two minutes after WOW, the FLCS FAULT caution light

illuminates and an FLCS SNGL FAIL PFL occurs.

B14.2

7 7/8 " Page

T.O. GR1F16CJ1CL2

B15

FLCS SINGLE ELECTRONIC FAILURE

If BRK PWR DEGR or FLCS CCM FAIL PFL occurs:

1. Establish 1g flight and airspeed less than 400 kts

(subsonic).

2. FLCS RESET sw-RESET.

If failure indications go

off:

3. Continue normal op

eration.

If failure indications

remain on:

3. FLCS PWR TEST

sw - TEST.

1

4. BRAKESchannel

sw-Change channels

(if required).

5. Land as soon as

practical.

FLCS DUAL ELECTRONIC FAILURE

If FLCS DUAL FAIL PFL occurs:

1. Establish 1g flight and airspeed less than 400 kts

(subsonic).

2. ADV MODE sw - Depress. 

2

3. FLCS RESET sw - RESET. 

3

If FLCS warning light goes off and no FLCS PFL's are

present:

4. Continue normal operation, but do not use ADV

MODE sw.

If FLCS warning light

goes off and an FLCS PFL

is still present:

4. FLCS PWR TEST

sw-TEST.

1

5. BRAKES channel

sw - Change chan

nels (if required).

6. Land as soon as

practical.

END

If FLCS warning light re

mains on:

4. FLCS PWR TEST

sw-TEST.

1

5. BRAKESchannel

sw-Change channels

(if required).

6. Land as soon as

possible.

4

END

B15

8 1/4

FLCS SINGLE/DUAL ELECT FAILURE

" Page

T.O. GR1F16CJ1CL2

B16

OTHER CONSIDERATIONS:

1

 Below 15 degrees AOA.

2

 Hydraulic failures or momentary drops in hydraulic pressure

(e.g., wake turbulence encounter, air in hydraulic system) also

illuminate the FLCS FAULT caution light and cause an ISA ALL

FAIL PFL.

B16

8 1/4 " Page

T.O. GR1F16CJ1CL2

B17

AUTOPILOT MALFUNCTIONS 

If FLCS A/P FAIL PFL occurs:

1. Establish 1g flight. 

1

2. FLCS RESET switch-RESET.

If PFL clears:

3. Continue normal operation.

If PFL remains, autopilot cannot be engaged.

If FLCS A/P DEGR PFL occurs:

1. Maneuver aircraft into autopilot envelope.

2. FLCS RESET switch-RESET.

If PFL clears:

3. Continue normal operation.

If PFL remains:

3. Disengage autopilot.

SERVO MALFUNCTION

2

1. Airspeed - 400 kts max (subsonic).

If a hydraulic failure is confirmed:

2. Go to SINGLE (page D15)/DUAL (page D17)

HYDRAULIC FAILURE.

If hydraulic pressures are normal:

3. FLCS RESET sw - RESET.

If failure indications go

off:

4. Continue normal op

eration.

END

If failure indications

remain on:

4. Land as soon as prac

tical.

END

B17

8 1/2

AUTOPILOT/SERVO MALFUNCTION

" Page

T.O. GR1F16CJ1CL2

B18

OTHER CONSIDERATIONS:

1

W

F

Recovery from a deep stall condition will present a

low airspeed situation in which the aircraft may require more

than 6000 ft of altitude to attain level flight.

F

If recovery (pitch rate stopped, AOA within -5 to +25

_

,

and airspeed 200 kts or greater) is not apparent by 6000 ft

AGL, eject.

2

 Engine may stall when out of control.

3

 If other than AB, do not move the throttle.

4

 Positive g, AOA indicator pegged at 32

_

 (upright deep stall)

or negative g, AOA indicator pegged at -5

_

 (inverted deep

stall).

5

 Maintain firm pressure.

6

W

F

The MPO sw must be held in the OVRD position until

the deep stall is positively broken as evidenced by the pitch rate

stopping, AOA in the normal range (-5 to +25

_

), and airspeed

increasing above 200 kts. Early release of the MPO sw may

delay recovery.

F

Failure to adequately secure and tighten lapbelt may

result in inability to reach and operate the MPO sw during

outofcontrol situations.

7

W

 Pitch rocking with a high sustained yaw rate may prevent

recovery. Delay stick inputs until yaw rotation stops or is

minimized. Pitch, roll, and yaw oscillations associated with a

deep stall should not be confused with the continuous yaw

rotation associated with a spin.

B18

8 1/2 " Page

T.O. GR1F16CJ1CL2

B19

OUTOFCONTROL RECOVERY

1

W

2

In the event of a departure from controlled flight,

accomplish as much of the following as required to

effect a recovery:

1. Controls - Release.

2. Throttle - MIL if in AB. 

3

If still out of control:

4

3. MPO sw - OVRD and hold.

5

6

W

4. Stick - Cycle inphase. 

7

W

END

B19

8 3/4

OUTOFCONTROL RECOVERY

" Page

T.O. GR1F16CJ1CL2

B20

OTHER CONSIDERATIONS:

1

 In the event that structural damage of unknown extent is

encountered or if continued control of the aircraft is in doubt,

consider accomplishing applicable steps of EJECTION (TIME

PERMITTING), page F23, prior to proceeding with CON

TROLLABILITY CHECK.

2

 If LEF damage is observed, consider locking LEF's.

3

W

 If a condition which might cause asymmetric TEF

extension exists, consider alternate LG extension with the LG

handle in UP to preclude TEF extension.

If the LG handle remains up:

D

Final approach airspeed is 20 kts higher than normal.

D

The TO/LDG CONFIG warning light may illuminate.

D

Nozzle remains closed, resulting in higher than normal

landing thrust.

D

NWS is inoperative.

D

BRAKES CHAN 2 must be selected.

D

FLCS remains in cruise gains. Consider positioning AIR

REFUEL sw to OPEN to obtain takeoff and landing gains.

D

The LG handle warning light remains on to indicate the

position of the gear handle is not in agreement with the actual

gear position.

4

W

 If the aircraft is not controllable down to a reasonable

landing speed (given consideration to weather, runway

condition, facilities, pilot experience, pilot arm fatigue, etc.), an

ejection is recommended.

5

 Climb to min enroute altitude (MEA) or depart low altitude

environment, if required.

6

 This action interrupts the flyup in ATF or manual TF (if

enabled).

7

 If a SWIM PFL is displayed, the TF malfunction was detected

by one or more SWIM monitors.

8

 If the malfunction was detected by SWIM and this

malfunction is no longer present, releasing the paddle sw

resets the SWIM monitors, cancels the flyup, and extinguishes

the TF FAIL warning light.

9

W

 Further TF operations should not be attempted after the

occurrence of a SWIM ATTD FAIL or SWIM VEL FAIL PFL.

B20

8 3/4 " Page

T.O. GR1F16CJ1CL2

B21

CONTROLLABILITY CHECK

The following items should be accomplished:

1. Attain safe altitude.

1

2. GW - Reduce (as required).

3. LE FLAPS sw-LOCK (if required). 

2

4. Determine optimum configuration available for

landing.

3

W

5. Stores - Selectively jettison (if required). Refer to

SELECTIVE JETTISON, page F27.

6. Slow only to that AOA/airspeed which allows

acceptable handling qualities.

4

W

TF FAIL WARNING LIGHT

If TF FAIL warning light illuminates:

1. Altitude - As required.

5

2. Paddle sw - Depress (if required).

6

3. PFLD - Check.

7

4. CARA, EGI, MMC - Check for proper operation.

If SWIM ATF FAIL, SWIM NVP FAIL, SWIM RALT

FAIL,  or SWIM SCP FAIL PFL is displayed:

5. Paddle sw - Release.

8

If SWIM ATF FAIL, SWIM NVP FAIL, SWIM RALT

FAIL, or SWIM SCP FAIL PFL does not clear or recurs:

6. Discontinue TF operations.

If SWIM ATTD FAIL or SWIM VEL FAIL PFL is dis

played:

5. Paddle sw - Release.

6. Discontinue TF operations.

9

W

If no SWIM PFL was present (NVP malfunction):

5. Paddle sw - Release.

6. Perform TFR BIT.

If NVP malfunction still exists:

7. Discontinue TF operations.

END

B21

CONT CHECK/TF FAIL WARN LIGHT

T.O. GR1F16CJ1CL2

B22

NOTES:

B22

ENG

PW

/C

T.O. GR1F16CJ1CL2

C1/PW

NOTES:

This section contains F100PW229 engine data.

ENG PW

/C

T.O. GR1F16CJ1CL2

C2/PW

Engine Malfunctions

1.If

is on, check RPM and FTIT

. . . . . . . . . . 

indications. If RPM and FTIT

. . . . . . . . . . . 

indications are normal, land as

. . . . . . . . . . . 

soon as practical.

. . . . . . . . . . . 

HOT START (GROUND)

C5/PW

. . . . . . . . . . . . . . . . . . . . . . . . . 

HUNG START/NO START

C7/PW

. . . . . . . . . . . . . . . . . . . . . . . . 

ENGINE AUTOACCELERATION (GROUND)

C7/PW

. . . . . . . 

FIRE/OVERHEAT/FUEL LEAK (GROUND)

C9/PW

. . . . . . . . . . 

ENGINE FAILURE ON TAKEOFF

C11/PW

. . . . . . . . . . . . . . . . 

AB MALFUNCTION ON TAKEOFF

C13/PW

. . . . . . . . . . . . . . 

LOW THRUST ON TAKEOFF OR AT 

LOW ALTITUDE (NONAB)

C13/PW

. . . . . . . . . . . . . . . . . . 

ENGINE FIRE

C15/PW

. . . . . . . . . . . . . . . . . . . . 

OVERHEAT CAUTION LIGHT

C17/PW

. . . . . . 

ENGINE VIBRATIONS

C19/PW

. . . . . . . . . . . . . . . . . . . . . . . . . 

OIL SYSTEM MALFUNCTION

C19/PW

. . . . . . 

ZERO RPM/ERRONEOUS RPM INDICATION

C21/PW

. . . . 

ENGINE STALL RECOVERY

C21/PW

. . . . . . . . . . . . . . . . . . . . 

ABNORMAL ENGINE RESPONSE

C23/PW

. . . . . . . . . . . . . . 

NOZZLE FAILURE

C25/PW

. . . . . . . . . . . . . . . . . . . . . . . . . . . . 

LOW ALTITUDE ENGINE FAILURE OR

FLAMEOUT

C27/PW

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

SEC CAUTION LIGHT

C29/PW

. . . . . . . . . . . . . 

ENGINE FAULT CAUTION LIGHT

C29/PW

. . 

AIRSTART PROCEDURES

C31/PW

. . . . . . . . . . . . . . . . . . . . . . . 

FLAMEOUT LANDING

C33/PW

. . . . . . . . . . . . . . . . . . . . . . . . 

ENG FIRE

OVERHEAT

PRESS

HYD/OIL

SEC

ENGINE

FAULT

ENGINE

T.O. GR1F16CJ1CL2

C3/PW

NOTES:

C3/PW

5 1/4 " Page