F16C/D. FLIGHT MANUAL (2002) - page 46

T.O. GR1F16CJ1CL2

C32/PW

OTHER CONSIDERATIONS:

9

C

 Do not turn JFS or EPU off if indicated rpm is below 60

percent with adequate thrust (e.g., tower shaft failure).

10

 Verify MAIN GEN and STBY GEN lights are off.

11

 If warning flag(s) is in view, refer to EGI FAILURE, page

F29.

12

 If the SEC caution light is on, refer to SEC CAUTION LIGHT,

page C29.

C32/PW

8 3/4 " Page

T.O. GR1F16CJ1CL2

C32.1/PW

If engine does not respond normally after airstart is

completed:

12. Refer to FLAMEOUT LANDING, page C33.

If engine responds normally: 

9

C

12. JFS sw - OFF.

13. ELEC CAUTION RESET button - Depress. 

10

14. EPU sw - OFF, then NORM.

15. ADI - Check for presence of OFF and/or AUX

warning flags. 

11

16. Throttle - As required. 

12

17. Land as soon as possible.

18. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

END

C32.1/PW

8 5/8 " Page

T.O. GR1F16CJ1CL2

C32.2/PW

OTHER CONSIDERATIONS:

1

Altitudes (overhead approach):

D

High key - 700010,000 ft AGL.

Recommended altitude is  

C

 7000, 

D

 7500 ft AGL plus

500 ft per1000 lb of fuel/store weights and plus 500 ft if

CFT's are installed.

D

Low key - 30005000 ft AGL.

Recommended altitude is 

C

 3000, 

D

 3250 ft AGL plus

250 ft per1000 lb of fuel/store weights and plus 250 ft if

CFT's are installed.

D

Base key - 2000 ft AGL min.

Altitudes (straightin approach):

D

Clean glide - 7000 ft AGL min at 8 nm.

D

Lower LG - 40008000 ft AGL at 4 nm.

Delay lowering LG until initial aimpoint is 11

_

17

_

 below

the horizon.

2

W

 Eject if a safe landing cannot be made. Ejection can be

accomplished at any point in the pattern but do not delay

ejection below 2000 ft AGL in an attempt to salvage a

questionable approach.

3

 Increase airspeed by 5 kts per 1000 lb of fuel/store weights

and plus 5 kts if CFT's are installed. This airspeed equates to

approx  7

_

AOA.

4

 During an airstart attempt, do not slow below the min

airstart airspeed.

C32.2/PW

8 5/8 " Page

T.O. GR1F16CJ1CL2

C33/PW

FLAMEOUT LANDING 

1

 

2

W

1. Stores - Jettison (if required).

2. Airspeed - 

C

 200, 

D

 205 kts. 

3

 

4

3. EPU sw - ON.

(Cont)

C

FUEL/

STORE

ALTITUDEĂ-ĂFEET AGL

KIAS

WT

HI

LOW

LGĆUP

LGĆDN

MIN

1000

7000

3000

200

190

180

2000

7500

3250

205

195

185

3000

8000

3500

210

200

190

4000

8500

3750

215

205

195

5000

9000

4000

220

210

200

6000

9500

4250

225

215

205

7000

10,000

4500

230

220

210

8000

10,500

4750

235

225

215

D

FUEL/

STORE

ALTITUDEĂ-ĂFEET AGL*

KIAS**

WT

HI

LOW

LGĆUP

LGĆDN

MIN

0000

7500

3250

205

195

185

1000

8000

3500

210

200

190

2000

8500

3750

215

205

195

3000

9000

4000

220

210

200

4000

9500

4250

225

215

205

5000

10,000

4500

230

220

210

6000

10,500

4750

235

225

215

7000

11,000

5000

240

230

220

8000

11,500

5250

245

235

225

*Add 500 ft (HI) or 250 ft (LOW) if CFT's are installed.

**Add 5 kts if CFT's are installed.

C33/PW

FLAMEOUT LANDING

T.O. GR1F16CJ1CL2

C34/PW

OTHER CONSIDERATIONS:

5

W

F

Min EPU fuel quantity without (with) JFS running:

D

Overhead approach at high key - 25 (20) percent.

D

Straightin approach:

S

8 nm - 45 (40) percent.

S

4 nm - 25 (20) percent.

F

The JFS alone does not provide adequate hydraulic pressure

to land the aircraft.

F

Do not start the JFS if engine seizure has occurred or is

anticipated or if engine failure is a result of fuel starvation.

Starting the JFS may result in no brake/JFS accumulator

pressure for the brakes.

6

F

If engine is not operating, consider placing the FUEL

MASTER sw to OFF if a fuel leak exists. This action may conserve

fuel for the JFS.

F

If the JFS is erroneously placed to START 1, leave it there.

F

If the JFS RUN light does not illuminate or goes off once

illuminated, place the JFS sw to OFF and reattempt START 2 when

the brake/JFS accumulators are recharged. The JFS sw does not

relatch in either start position while the JFS is spooling down.

7

W

F

Do not delay lowering LG below 2000 ft AGL.

F

If LG handle does not lower, select BRAKES CHAN 2 and

position ALT FLAPS sw to EXTEND. Nozzle remains closed,

resulting in higher than normal landing thrust.

8

Alternate LG extension can be used up to 300 ks; however, the

NLG may not fully extend until 190 ks. Time above 190 kts should

be minimized in case there is a leak in the pneumatic lines.

9

C

F

NWS is not available following alternate LG extension.

F

Do not depress the ALT GEAR reset button while pulling the

ALT GEAR handle. This action may preclude successful LG

extension.

10

 Increase airspeed by 5 kts per 1000 lb of fuel/store weights

and plus 5 kts if CFT's are installed.

11

W

 Do not allow airspeed to decrease below 

C

 180, 

D

 185

kts, plus 5 kts per 1000 lb of fuel/store weights and plus 5 kts

if CFT's are installed.

12

C

F

Brakes should be applied in a single, moderate, and

steady application without cycling the antiskid.

F

Brake pedal deflection of 1/16 inch activates the brakes and

bleeds the brake/JFS accumulators. To avoid brake activation and

loss of accumulator fluid, do not rest feet on the brake pedals.

F

Do not attempt to taxi clear of the runway. Loss of brake/JFS

accumulator pressure results in the inability to stop or steer the

aircraft.

C34/PW

T.O. GR1F16CJ1CL2

C34.1/PW

4. JFS sw - START 2 below 20,000 feet MSL and

below 400 knots. 

5

W

 

6

5. AIR SOURCE knob - RAM (below 25,000 ft

MSL).

6. DEFOG lever - Forward.

7. LG handle - DN. (Use DN LOCK REL button if

required.) 

7

W

8. ALT GEAR handle - Pull (if required) (190 kts

max, if practical). 

8

 

9

C

9. Airspeed - 

C

 190, 

D

 195 kts optimum in pattern.

10

 

11

W

After touchdown:

10. DRAG CHUTE sw - DEPLOY (if required).

11. HOOK sw - DN (if required).

If brake/JFS accumulator braking is used:

12. Stop straight ahead and engage parking brake.

12

C

13. Refer to ACTIVATED EPU/HYDRAZINE LEAK,

page F13.

END

C34.1/PW

8 7/8 " Page

T.O. GR1F16CJ1CL2

C34.2/PW

NOTES:

C34.2/PW

8 7/8 " Page

FUEL/HYD

D

T.O. GR1F16CJ1CL2

D1

NOTES:

FUEL/HYD D

RED ZONE ON

AL POINTER

AND/OR

TOTALIZER

AND

POINTERS DO

NOT AGREE

BELOW 5700

(  4500) LB

D

INT WING &

CFT QUANTITY

GREATER

THAN 700 LB

AND 

FUSELAGE

FUEL 

DECREASING

AND 

EXTERNAL

TANK EMPTY

ABNORMALLY

DECREASING

TOTALIZER

T.O. GR1F16CJ1CL2

D2

Fuel/Hydraulic Malfunctions

FUEL IMBALANCE

D5

. . . . . . . . . . . . . 

FUEL LOW

D7

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

TRAPPED EXTERNAL FUEL

D9

. . . . . . 

TRAPPED CFT FUEL

D21

. . . . . . . . . . . 

FUEL LEAK

D11

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

HOT FUEL/OIL OR

GRAVITY FEED

D13

. . . . . . . . . . . . . . . 

FLAMEOUT LANDING

GO TO C33

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

FWD

FUEL LOW

AFT

FUEL LOW

FUEL/OIL

HOT

T.O. GR1F16CJ1CL2

D3

SINGLE HYDRAULIC

FAILURE

D15

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

ONE HYD PRESS INDICATOR LOW

EPU RUN LIGHT OFF

ISA ALL FAIL PFL

DUAL HYDRAULIC

FAILURE

D17

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

B HYD PRESS INDICATOR LOW

EPU RUN LIGHT ON

ISA ALL FAIL PFL

SYSTEM B AND 

GENERATOR FAILURE 

(PTO SHAFT)

D19

. . . . . . . . . . . . . . . . . 

B HYD PRESS INDICATOR LOW

EPU RUN LIGHT ON

ISA ALL FAIL PFL

PRESS

HYD/OIL

FLCS

FAULT

PRESS

HYD/OIL

FLCS

FAULT

PRESS

HYD/OIL

ELEC

SYS

FLCS

FAULT

GEN

MAIN

PMG

FLCS

D3

6 3/4 " Page

GEN

STBY

T.O. GR1F16CJ1CL2

D4

OTHER CONSIDERATIONS:

1

 A fuel imbalance when not carrying an external fuel tank(s)

indicates a system malfunction. A fuel imbalance when

carrying an

 

external fuel tank(s) may be the result of normal

system operating tolerances.

2

F

A

ny correction required per total fuel quantity usage

with internal fuel only indicates a system malfunction.

F

More than one correction per total fuel quantity usage with

either a 300gallon fuel tank or two 370gallon fuel tanks

indicates a system malfunction.

F

More than two corrections per total fuel quantity usage with

either a 300gallon fuel tank and two 370gallon fuel tanks or

two 600gallon fuel tanks indicate a system malfunction.

F

More than three corrections per total fuel quantity usage with

a 300gallon fuel tank and two 600gallon fuel tanks indicate a

system malfunction.

F

Placing the ENG FEED knob to either FWD or AFT during

external tank fuel transfer may cause some fuel to enter empty

CFT's.

3

W

 Limit fuel flow to the min required to sustain flight while

the cause is determined. Avoid negative g flight when either

reservoir is not full.

4

W

 Aft fuel heavy (red portion of AL pointer showing) results

in increased susceptibility to departure and deep stall

conditions. Limit AOA and avoid max command rolling

maneuvers.

5

 Indicated by abnormally high fuel flow, by totalizer

decreasing at abnormal rate, or by visual means.

6

 Use the FUEL QTY SEL knob to determine if a trapped fuel

condition exists. Refer to TRAPPED EXTERNAL FUEL, page D9,

if required.

D4

6 3/4 " Page

T.O. GR1F16CJ1CL2

D5

FUEL IMBALANCE

1

2

If fuel imbalance is indicated by AL and FR pointers

with FUEL QTY SEL knob in NORM:

1. Fuel flow - Reduce to the min required to sustain

flight below 6000 pph.

3

W

If aft fuel imbalance exists (aft CG):

2. AOA - 15

_

 max.

4

W

If a fuel leak is suspected:

5

3. Go to FUEL LEAK, page D11.

If a fuel leak is not suspected:

4. Fuel quantities - Check.

6

(Cont)

D5

7

FUEL IMBALANCE

" Page

T.O. GR1F16CJ1CL2

D6

OTHER INDICATIONS:

7

 Use only to correct a forward and aft fuselage fuel

imbalance and not to correct imbalances between reservoirs.

Do not exceed 25,000 pph fuel flow while balancing fuel.

8

C

 If twopoint aerodynamic braking is used with an aft CG,

pitch overshoots may occur and the nozzle, speedbrakes, and

ventral fins may contact the runway.

9

 A NVP TFR FAIL PFL and a flyup can occur when NORM is

reselected while operating in TFR.

D6

7 " Page

T.O. GR1F16CJ1CL2

D6.1

5. ENG FEED knob - FWD or AFT.

7

If imbalance is not cor

rected:

6. Land as soon as

practical.

8

C

END

If proper distribution is

attained:

6. ENG FEED knob -

NORM.

9

7. Fuel balance - Moni

tor.

END

D6.1

6 7/8 " Page

T.O. GR1F16CJ1CL2

D6.2

OTHER INDICATIONS:

D

A fuel low caution light may be caused by a fuel leak, trapped

external fuel, trapped CFT fuel, a fuel imbalance between the

forward and aft systems, prolonged AB operation, or a fuel

sensing problem.

D

The FWD FUEL LOW and AFT FUEL LOW caution lights

indicate reservoir tank quantities are less than:

C

D

FWD

400 pounds

FWD

250 pounds

AFT

250 pounds

AFT

400 pounds

OTHER CONSIDERATIONS:

1

W

 Limit fuel flow to the min required to sustain flight while

the cause of the fuel low light(s) is determined. Avoid negative

g flight when either reservoir is not full.

2

 A NVP TFR FAIL PFL and a flyup can occur when NORM is

reselected while operating in TFR.

3

 Leave FUEL QTY SEL knob out of NORM if FUEL quantity

indicator displays erroneous information.

4

 Fuel flow indications may fluctuate with either reservoir

empty.

5

 Consider an SFO. Refer to FLAMEOUT LANDING, page

C33.

6

 Indicated by abnormally high fuel flow, by totalizer

decreasing at abnormal rate, or by visual means.

D6.2

6 7/8 " Page

T.O. GR1F16CJ1CL2

D7

FUEL LOW

If FWD FUEL LOW and/or AFT FUEL LOW caution

light illuminates:

1. Fuel flow - Reduce to the min required to sustain

flight below 6000 pph.

1

W

2. ENG FEED knob - NORM.

2

3. FUEL QTY SEL knob - RSVR.

3

If either or both reservoir

tanks are low:

4

4. Land as soon as

possible.

5

If a fuel leak is suspected:

6

5. Go to FUEL LEAK,

page D11.

(Cont)

If reservoir tanks indi

cate full:

4. FUEL QTY SEL

knob - TEST.

If AL and/or FR pointers

test bad, or FUEL quan

tity indicator is inopera

tive:

5. Land as soon as

possible.

5

(Cont)

D7

7 1/4

FUEL LOW

" Page