A4 NATOPS PocketCheckList

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NAVAIR 01-40AVD-1B

NATOPS PILOT'S

POCKET CHECKLIST

TA-4F/J

AIRCRAFT

ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS

AND UNDER THE DIRECTION OF THE COMMANDER,

NAVAL AIR SYSTEMS COMMAND

1 APRIL 1972

Changed 1May 1978



NAVAIR 01·40AVD·1B

Reproduction for nonmilitary use of the information or illustration. ron·tained in this publication is not permitted without specific approval of the

Commander, Naval Air Systems Command.

r----------LlST Of EFFECTIVE PAGES---------.

Note: Text affected by current change indicated by vertical line in outer margin.

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 145,

CONSISTING OF THE FOLLOWING:

Page No. Issue

°Cover .......... 1 May 1978

OTitIc Page ....... 1 May 1978° A - D .......... I May 1978

I - 2 .......... I May 1976

2A/(2B blank) '" I May 1976

3-4 ........•. 1MayI976

5 ................. Original

°6 ...........•.. I May 1978

7 ...........•.. 1 May 1976

8 .............. 1 Apr 1974

9 .....•.•...... I May 1976

10 .......•.....•.. Original

°11 ............. I May 1978

12 ............. 1 May 1976

°12A ........... I May 1978

12B - 12C ......... Original

12D ........... 1 May 1976

°12£ - 12 F ...... 1 May 1978

°13/(14 blank) .... I May 1978

15 ...........•• 1 Apr 1974

16 ...••........ 1 May 1976

17 ............. 1 Apr 1974

18 ............. I May 1976

°18A ........... 1 May 1978

18B ....•....... 1 May 1976

18C/(180 blank) .. I May 1976

°19 ......•...... 1 May 1978

20 ................ Original

°21 -24 ........ 1MayI978

°24A - 24 0 ...... I May 1978

°24E/(24F blank) .. 1 May 1978

25 ••........•.. I May 1976

°26....•........

1 May 1978°26A - 26B ...... I May 1978

°27 ...........•. 1 May 1978

28 - 30 .....•..... Original

31 ............. 1 Apr 1974

32 ...••........... Original

33 .••.•........ 1 Apr 1974

° 34 - 36 ........ 1 May 1978

°36A - 36 0 ...•.. 1 May 1978

Page No. Issue

°37 -38 I May 1978

• 38A - 38D deleted 1 May 1978

° 39 - 40 ........ 1 May 1978

°40A - 40B deleted I May 1978

·41 - 42 ........ I May 1978

°42A1(42B hlank) .. I May 1978

43 ................ Original

44 - 45 ........ 1 Apr 1974

46 - 49 ........... Original

50 ............. I Apr 1974

5 I ................ Original

52 ............. I Apr 1974

53 •............... Origi nal

54 ............. I May 1976

55 ............ IS Nov 1976

56 ............. I May 1976

57................

Original· 5 8 - 60 ........ 1I11ayI978

61 ................ Original

62 ............. 1 Apr 1974

63 - 64 ........... Original65 ............. IAprI974

66 - 79 ........... Original80 ............. 1 Apr 1974

81 ............. I May 1976

82 - 87 ........... Original

°88 .......•..... I May 1978

89 ................ Original90 ............. I May 1976

90Al(90B blank) .. I Apr 1974

°91 ....•........ 1 May 1978

92 - 95 ......•.... Original

96 ............. 1 May 197697/(98 blank) .... I May 1976

99 •.•............. Original

100 ............ 1 May 1976

101 - lOS •.......• Original

106 ............ 1 May 1976

107/(108 blank) .. 1 Apr 1974

°109/(110 blank) .. 1 May 1978

Inside Back Cover ..... Original

°Asterbk I n d l c a l e ~ pages changed, added, or deleted hy the current change.

ADDITIONAL COPIES:

Additional caples of Ihis manual and changes thereto ma)' be procured hysUhmittlng Form DO • 348 to NI'FC I'hilade'phia in accordance withIntroduction to Navy Stocklist of I'uhlicatlons and Forms NAVSUI'I'uhllcation 2002 (SIN 0535·U'·004·001J1).

1 APRil 1972

Changed 1 May 1978A



NAVAIR Ol-40AVD-18

\II INTERIM CHANGE SUMMARY III

The following Inlerim Changel have been canceled or previoullyincorporated in thb manual;

INTERIMCHANGE NUMBER(SI

I thru18

REMARKS/PURPOSE

Previoully Incorporated

The following Interim Changel have been incorparated in thil Change/Revilion:

INTERIMREMARKS/PURPOSE

CHANGE NUMBER

_ .

Interim Chang.s Outstanding - To be maIntained by the custodian of thll manual.

INTERIM ORIGINATOR/DATE PAGESREMARKS/PURPOSE

CHANGE NUMBER (or DATE/TIME GROUPI AFfeCTED

B Changed 1 May 1978

TAKEOFF PRESSURE/FUEL CONTROL CHART

J52-P·8A ENGINE

J52-P-6A ENGINE FUEL CONTROL (JFC-25-3)

FUEL CONTROL P&W PIN 571058 HAM. STO.

(JFC·25-3) PIL 706644 & SUBS.

AMBEPR'

AMB MAXA AMBEPR'

AMB MAXA

TEMPoC TEMP OF RPM DROP TEMP 0C TEMpoF RPM DROP@l8S%"

50@8S%

120-2.0 -3.0

110 110-3.5-2.5

40100 100 -4.0

-3.0

90 -3.5 90 -4.530

80 -4.0 80 -5.0

-4.5 -5.570 70

2 20 -6.0-5.0

60 60-5.5 -6.5

50 10 50 -7.0-6.0

40 40 -7.5

-6.5

30 -7.0 30 -8.0

-7.5 -8.5

20 20-8.0 -9.0

10-8.5

10 -9.5

0 -9.0 0 -10.0

-10 -9.5 -10 -10.5

2.60 -20-10.0

-11.0

-30 30

TA-4F/TA-4J TA-4F

• PROVIDES A MINIMUM OF 97% INSTALLED MILITARY THRUSTTA'9-4CA

•• DURING MANUAL FUEL CHECK NS/1'

Changed 1 May 1978 c



TAKEOFF PRESSURE/FUEl CONTROL CHART

MODEL: TA-4F FUEL CONTROL IJFC·26·3)ENGINE: J62·P·88

P & W PIN 671058 HAM STD

PIN 706644 AND SUBS.

AMBEPR'

AMB MAX A

TEMP oc TEMPOf RPM OROP

50@85%

2.20 120

45-3.0

110-3.5

40100 -4.0

35 2.3590 -4.5

30 2.4080 -5.0

25

2.45 -5.520 70-6.0

15 2.50 60-6.5

10 50

2.55 -7.05 40 -7.5

02.60 30 -8.0

-5 -8.520

-10 -9.02.65

10-9.5

-150 -10.0

-202.70

-10-10.5

-25-11.0

-30-20 -11.5

2.75

• PROVIDES A MINIMUM OF 97% INSTALLED MILITARY THRUST

" DURING MANUAL FUEL CHECKTA,a...uANsna

o Changed 1 May 1918

AIRCRAFT DRAG INDEX - 61

WEIGHT (LESS FUEl) -12,816 POUNDSAll PYlONS, GUNS (NO AMMO), AND

TWO 300·GAllON EXTERNAL TANKSRESERVE FUEL FOR LANDING - 800 POUNDS

MODEL: TA-4F DATA AS OF: 1 MAY 1972ENGINE: JSZ·P-8A/B DATA BASIS; FLIGHT TEST (NAVY)

InQZ

0A-

IQa.:<0CD

Z0

...

&II

...

2700

2500

2300

2100

1900

1700

1500

1300

1100

2700

2500

2300

2100

1900

1700

1500

1300

1100

PRESSUREALTITUDE

FEET

SEA LEVEL

5000

10,000

15,000

20.000

25,000

30000

35,000

40,000

IF YOU ARE ATSEA LEVEL

RAIIGE AT: OPTIMUMSEA OPTIMUM CRUISE

LEVEL ALTITUDE AlTITUDE

11M 11M fEET

208 402 35,000

186 358 35,000

165 313 35000

143 268 35,000

121 223 35,000

99 177 35,000

77 130 35,000

55 83 30000

33 44 15,000

IF YOU ARE AT20,000 FEET

RAIIGE AT: OPTIMUM20,000 OPTIMUM CRUISEfEET ALTITUDE ALTITUDE

11M 11M FEET

372 448 35.000

335 403 35000

299 359 35,000

262 314 35,000

226 269 35,000

189 222 35,000

151 176 35,000

114 129 35,000

76 81 35,000

CLIMB SPEED CRUISEMILITARY THRUST SPEED

IICAS MaCH liD. KCAS

310 270

310 265

310 260

310 260

310 260

0.71 255

0.71 240

0.71 225

0.71 215

IF YOU ARE AT10,000 FEET

RAIIGE AT: OPTIMUM10,000 OPTIMUM CRUISEfEET ALTITUDE ALTITUDE

11M 11M FEET

281 425 35,000

253 381 35,000

225 337 35,000

197 292 35.000

168 246 35000

140 200 35.000

111 153 35,000

83 106 35,000

54 61 25000

If YOU ARE AT35,000 FEET

RAIIGE AT: OPTIMUM35,000 OPTIMUM CRUISE

FEET ALTITUDE ALTITUDE

11M 11M FEET

473 473 35.000

429 429 35,000

385 385 35,000

340 340 35000

294 294 35,000

248 248 35,000

201 201 35,000

154 154 35,000

106 106 35,000

DESCEIIT SPEED START LETDOWIIEIIGIIIE IDlE- fROM AlTITUDESPEEDBRAKES WITH FUEL/OISTANC!

ClOSiO REMAINING

lIeAS POUNOS/NM

190 800/0

190 823/7

190 839/1 5

190 853/23

190 867/32

190 880/40

190 892/49

190 904/59

190 916/69

Bingo Range fP·8AIBI

Changed 1 May 1976



..""" 'N: : :R ~ O A ~ 8 " " '" ,

AIRCRAFT DRAG INDEX-SOWEIGHT (LESS fUEl) -12,345 POUNDS

fiVE PYlONS, GUNS, AND TWO 300-GALLON EXTERNAL TANKSINCLUDES 800 POUNDS RESERVE FUEl FOR LANDING

MODEL: TA-4F/TA-4J

ENGINE: J52·P·6A

\I )

QZ

0A-

IQIII:

<0=Z0......::;)II .

2

RANGEAT

SEALEVEL

NMI

2700 201

2500 180

2300 159

2100 138

1900 117

1700 96

1500 7S

1300 54

1100 32

RANGEAT

20.000fEET

NMI

2700 360

2500 326

2300 290

2100 255

1900 219

1700 184

1500 147

1300 111

1100 7S

PRESSUREALTITUDE

FEET

SEA LEVEL

10,000

20000

30.000

35000

40,000

IF YOU ARE AT If YOU ARE AT

SEA LEVEL 10,000 FEET

RANGE KCAS RANGE RANGE KCASOPTIMUM AT AT AT OPTIMUM AT ATALTITUDE OPTIMUM OPTIMUM 10.000 ALTITUDE OPTIMUM O P T l M ~ ~

ALTITUDE ALTITUDE fEET ALTITUDE ALliTUD

FEET HMI KNOTS HMI FEEl HMI KNOTS

40,000 402 220 278 40000 428 220

40,000 357 220 250 40,000 383 220

40,000 312 220 222 40,000 338 220

40,000 265 220 195 40,000 291 220

40,000 218 220 167 40,000 244 220

40,000 171 220 139 40,000 196 220

35,000 122 230 111 40,000 147 220

25000 79 235 83 35,000 99 230

15,000 4S 240 5S 20,000 60 235


20,000 FEET 35,000 FEET

RANGE KCAS RANGE RANGE KCASOPTIMUM AT AT AT OPTIMUM AT ATAlTITUDE OPTIMUM OPTIMUM 35.000 AlTITUDE ~ m r u U D ~ ~ m r U ~ ~ ALTITUDE ALTITUDE fEU

fEET NMI KNOTS NMI FEET NMI KNOTS

40.000 453 220 480 40.000 484 220

40,000 409 220 435 40,000 438 220

40,000 363 220 389 40,000 394 220

40.000 316 220 344 40000 348 220

40000 270 220 298 40000 302 220

40,000 222 220 251 40000 254 220

40000 173 220 204 40,000 206 220

40000 124 220 156 40 DOO 158 220

25,000 77 230 107 40,000 108 220

CLIMB SPEED

M I ~ I T A R Y THRUST

DESCENT SPUDENGINE IDLE -

SPEEDBRAKES C ~ O S E D START LETDOWN fROM

ALTlTUOE WITH fUElDISTANCE REMAINING

KCAS MACH NO. KCAS POUNDS/NM,

315 18S 800/0

300 185 835/15

285 185 865/32

265 185 895/49

0.72 185 910/59

0.72 185 925/69

Bingo Range (P·6A)

Changed 1 May 1976


WEIGHT (LESS FUEL) - 12,816 POUNDSALL PYlONS, GUNS (NO AMMO), ANDTWO 300-GALLON EXTERNAL TANKS

RESERVE FUEL FOR LANDING - 800 POUNDS

MODEL: TA·4F

ENGINE: J52-P·SA/B

DATA AS OF: 1 MAY 1972

DATA BASIS: FLIGHT TEST (NAVY)If YOU ARE AT " YOU ARE AT

SEA LEVEL 10,000 FEETENDURANCE AT: OPTIMUM ENDURANCE AT: OPTIMUM

SEA OPTIMUM ENDURANCE 10,000 OPTIMUM ENDURANCELEVEL ALTITUDE ALTITUDE fEET ALTITUDE ALTITUDE

MINUTES MIfIUTES fEET MINUTES MINUTES fEET

2700 56 72 30,000 68 75 30,000

2500 50 64 30,000 61 6.8 30,000\I )

2300 30,000 61 30,000Q 45 57 55Z 2100 39 49 30,000 48 5;1 30,000

1900 33 42 30,000 41 45 30,0000A- 1700 27 34 30,000 35 38 30,000

I 1500 21 26 30,000 28 30 30,000

Q 1300 15 18 20,000 21 22 20,000I¥

1100 9 11 15,000 14 14 13,000""0 IF YOU ARE AT If YOU ARE ATra 20,000 FEET 35,000 fEETZ ENDURANCE AT: OPTIMUM ENDURANCE AT: OPTIMUM

0 20,000 OPTIMUM ENDURANCE 35.000 OPTIMUM ENDURANCEFEET ALTITUDE ALTITUDE FEET ALTITUDE ALtITUDE

... IIIIIUTES MIIIUTES fEET MINUTES MINUTES FEETw

2700 78 79 30,000 83 84 30,000:;:)...2500 71 72 30,000 76 77 30,000

2300 64 65 30,000 69 69 30,000

2100 56 57 30,000 61 62 30,000

1900 49 49 30,000 54 54 30,000

1700 41 42 30000 46 46 35,000

1500 34 34 30,000 38 38 35.000

1300 26 26 20,000 30 30 35,000

1100 18 18 20,000 22 22 35.000

PRESSURE CLIMB SPEED "!DURANCE"LTITUDE MILITARY THRUST SPEED SPEEDBRAIIES AlmUDE WITH fUElI

CLOSED TIME REMAINING

FEET IICAS MACH NO. IICAS IICAS POUNDS MIN

SEA lEVEL 310 19S 190 800/0

5000 310 195 190 823/2

10000 310 195 190 839 / 4 . _

IS 000 310 195 190 853/6

20,000 310 195 190 867/8

25,000 0.71 195 190 880/10

30,000 0.71 195 190 892/12

35000 0.71 195 190 904/14

40.000 0.71 195 190 916/16

Bingo Endurance IP-8A/BI

Changed 1 May 1976

[iel¢III§lili••2A/12B Blank!




WEIGHT (LESS FUEL) - 12,345 POUNDS

FIVE PYLONS, GUNS, AND TWO 300·GALLON EXTERNAL TANKSINCLUDES 800 POUNDS RESERVE FUEl FOR LANDING

MODEL: TA·4F/TA·4J

ENGINE: J52·P·6A

DATA AS OF: 1 JANUARY 1967

DATA BASIS: ESTIMATED

VIQ

Z: )

0a.IQ

III:

III:0a:a

Z0.I I1M:)

...


SEA LEVEl 10,000 FEET

ENDUR. ENOUR· IICAS ENDUR· ENDUR· IICAS

~ i l C E AT OPTIMUM ANCE AT AT ANtE AT OPTIMUM ANtE AT AT

SEA ALTITUDE OPTIMUM OPTIMUM 10,000 ALTITUDE OPTIMUM OPTIMUM

LEVEl ALTITUDE ALTITUDE fEET ALTITUDE ALTITUDE

MINUTES fEET MINUTES IINOTS MINUTES fEET MINUTES IINOTS

2700 56 30000 72 195 68 30,000 76 195

2500 51 30,000 65 195 61 30,000 68 195

2300 45 30,000 57 190 55 30,000 61 195

2100 39 30000 49 190 48 30,000 53 195

1900 33 30,000 42 190 42 30,000 45 190

1700 27 25000 34 190 35 30000 38 190

1500 21 20000 26 190 28 25,000 30 19 0

1300 15 20000 18 190 21 20000 22 190

1100 9 15000 11 190 14 20000 14 190

IF YOU ARI AT IF YOU ARE AT

20,000 FEET 35,000 FEET

ENDUR· ENDUR· IItAS ENDUR· ENDUR· IICAS

ANCE AT OPTIMUM ANCE AT ATA!lCE AT OPTIMUM ANCE AT AT

2 ~ 0 0 0 ALTITUDE OPTIMUM OPTIMUM 35,000 AlTITUDE OPTIMUM O P T I M U , ~ f ET AlTITUDE ALTITUDE fEET ALTITUDE ALTITUD

MINUTES FEET MINUTES IINDTS M INUTES fEET

2700 77

2500 70

2300 63

2100 56

1900 48

1700 41

1500 34

1300 26

1100 18

PRESSURE

ALTITUDE

fEET

SEA LEVEL

10000

20000

30000

35000

40,000

30,000 80

30000 73

30,000 65

30000 58

30000 50

30000 42

25000 34

25,000 26

20,000 18

ClIMI SPEEDMILITARY THRUST

IICAS MACH NO.

315

30 0

285

265

0.72

0.72

195 84 30,000

195 77 30000

195 69 30,000

195 62 30,000

195 54 30000

190 46 30,000

190 39 30000

190 31 30000

190 23 30,000

DESCENT SPEED

ENGINE ID lE-SPE£D8RAKES CLOSED

IICAS

185

185

185

185

185

185

MINUTES IINOTS

85 195

78 195

75 195

63 195

55 195

47 195

39 190

31 190

23 190

STm l£T1l0WII fROM

AlmUDE WIlli fUEUTIME iltMAlftlNG

POUNDS/MIN

800/0

835/4

867/9

896/13

910115

923/17

8ingo Endurance (P·6A)

Changed 1 May 1916

l i . I , I I I , I I I It>

3



AIRCRAFT DRAG INDEX - 391AIRCRAFT WEIGHT (LESS FUEL) - 12,816 POUNDS

ALL PYLONS, GUNS (NO AMMO), ANDTWO 300·GALLON EXTERNAL TANKS

RESERVE FUEL FOR LANDING - 800 POUNDS

MODEL: TA·4F

ENGINE: J52·P·8A/BDATA AS OF: 1 MAY 1972DATA BASIS: FLIGHT TEST (NAVY)

If YOU ARE AT

SEA LEVEL

RANGE AT: OPTIMUMSEA OPTIMUM CRUISE

LEVEL ALTITUDE ALTITUDE

NM NM FEET

2700 131 206 25,000

2500 117 184 25,000

2300 104 161 25,000Q

Z 2100 90 139 25,000

!:) 1900 76 116 25,0000

1700 63 92 25,000A-

I 1500 49 69 25,000

Q 1300 35 46 20,000

D: 1100 21 2S 15,000

0 If YOU ARE ATCIQ

20,000 FEETZ

RANGE AT: OPTIMUM0 20,000 OPTIMUM CRUISE... FEET ALTITUDE ALTITUDE...

NM NM fEET::»110 2700 225 234 25,000

2500 204 212 25,000

2300 182 190 25,000

2100 160 167 25,000

1900 138 144 25,000

1700 116 120 25,000

1500 94 97 25,000

1300 71 73 25,000

1100 49 49 25,000

PRESSURE CLlM8 SPEED CRUISEALTITUDE MILITARY THRUST SPEED

fEET KCAS KCAS

SEA LEVEL 190 215

5000 190 210

10 00 0 190 210

15,000 190 205

20,000 190 200

25,000 190 195

30,000 190 185

If YOU ARE AT

10,000 FEET

RANGE AT: OPTIMUM10,000 OPTIMUM CRUISEFEET ALTITUDE ALTlTUOE

NM NM FEET

176 221 25000

158 199 25,000

141 176 25,000

123 153 25,000

106 131 25,000

88 107 25.000

70 84 25,000

52 60 25,000

34 37 20,000

If YOU ARE AT

30,000 FEET

RANGE AT: OPTIMUM30,000 OPTIMUM CRUISEFEET ALTITUDE ALTITUDE

NM NM FEET

246 246 30,000

223 223 30,000

201 201 30,000

178 178 30,000

155 155 30,000

132 132 30000

108 108 30,000

84 84 30,000

60 60 30,000

DESCENT SPEED SURT lETDOWN fROMENGINE IDLE- ISPEEDBRAKES AlmUDE WITH fUEl

DISTANCE REMAININGCLOSED

KCAS POUNDS/NM

165 800/0

165 817/5

165 830/10

165 84D/15

165 850/20

165 860{25

165 869/31

Bingo Range - Gear Down Ip·8AIB'

4 Changed 1 Ma y 1976

AIRCRAFT DRAG INDEX - 390 (GEAR DOWN)

WEIGHT (LESS FUEL) - 12,561 POUNDSFIVE PYlONS, GUNS, AND TWO 300·GALLON EXTERNAL TANKS

INCLUDES 800 POUNDS RESERVE FUEL FOR LANDING

MODEL: TA·4F/TA·4J

ENGINE: J52,P·6A

DATA AS OF: 1 SEPT 1968

DATA BASIS: ESTIMATED

'"QZ!:)

0A.

IQD:

0CIQ

Z0......::»...

RANGEAT

SEALEVEL

NMI

2700 130

2500 116

2300 103

2100 89

1900 76

1700 62

1500 49

1300 35

1100 21

RANGEAT

15,000FEET

NMI

2100 189

2500 170

2300 151

2100 133

1900 114

1700 96

1500 77

1300 57

1100 3S

PRESSUREALTITUDE

FEET

SEA lEVEl

10000

15,000

20000

25,000

IF YOU ARE AT IF YOU ARE AT

SEA LEVEL 10,000 FEET

RANGE KCAS RANGE RANGE KCASOPTIMUM AT AT AT OPTIMUM AT ATALTITUDE OPTIMUM OPTIMUM 10,000 ALTITUDE OPTIMUM OPTIMUM

AlTITUDE alTITUDE FEET ALTITUDE ~ L T l T U D E FEET NMI KNOTS NMI FEET NMI KNOTS

25,000 189 195 168 25,000 204 195

25,000 168 195 152 25000 183 195

25000 146 190 135 25,000 162 195

25000 125 190 118 25 000 140 190

25000 103 190 101 25000 119 190

25,000 81 190 84 25,000 96 190

20000 60 190 67 25,000 74 190

15000 40 195 50 20,000 53 190

10000 22 195 32 15,000 33 195

IF YOU ARE AT IF YOU ARE AT

15,000 FEET 20,000 FEET

RANGE KCAS RANGE RANGE KCASOPTIMUM AT AT AT OPTIMUM AT ATALTITUDE OPTIMUM OPTIMUM 20,000 ALTITUDE OPTIMUM OPTIMUM

ALTITUDE ALTITUDE FEET ALTITUDE ALTITUDE

fEET NMI KNOTS NMI fEET NMI KNOTS

25,000 212 195 208 25,000 219 195

25000 191 195 188 25000 198 195

25,000 169 195 168 25,000 176 195

25000 T47 190 148 25000 155 195

25000 126 190 127 25,000 133 190

25,000 104 190 lOT 25000 111 190

25.000 81 190 86 25,000 88 190

20,000 59 190 65 25,000 68 190

20,000 39 190 44 20,000 44 190

CLIMB SPEEDMILITARY THRUST

DESCENT SPEEDENGINE lDLE-

SPEEDBRAKES CLOSED

START LETDOWNfROM AlTITUDE

WITH FUEL REMAINING

KCAS MACH NO. KCAS

205 0.310 156

205 0 ,37 ]_ 156

205 0.409 156

205 0.451 156

205 0.588 156

Bingo Range-Gear Down (P·6A)

POUNDS

800

! I ~ O 866

878

888

.eUlmm,,,S



HIGH KEY

7500 FEET ACl, 2500FEET DOWN THE RUNWAY,

~ g ~ ~ : : - ~ ~ : ~ t l o ~ ~ ~ S

FlARE

C O " ' M E ~ C £ O AT )00 fEE' Ael.. 200KIA5, FLARE TO A POINT 500 TO 1000FEET fROM TI1RE5t40I.D. AT 50 FEET,180 I(IA5 ...RR.ES T RATE Of OE 5C ENTTO A MINIMUM OElAVl/rIC TOUCHDOWN.

' , ,/

, k , , - ,

lCNi KEY

------

PATTERN HOTES:

1. OPTIMUM APPROACH CONfiGURATION:

t . . ~ ~ C ~ H ~ ~ A M ~ ~ M ~ ~ ~ ~ IB IN.2, ...AXIMUM CROSS WEICHT -10,000 LB_

" AIRSPEED RAHCE -IQO TO 220 KIASUNTIL INITIAL FLARE; 180.IAS"'INIMUM U FINAL FLARE.

4. ALTITUDE ;MINUSSOOFEETIS ACCEPT FOR PATTERN CHECKPOINTS UP TO LARE.

MINIMUM FLARE At..TITUOE :250HET ACl.

5, WIND CORRECTION :OISPlACE HIGHKEY INTO THE WINO 1000 FEfT ANDTHE AIM POINT ON FINAl 250 FEElFOR EVERY 5 KTS OF HEADWIND.

/ "

FINAL

IIII

,/

'\ 9(1' POS IliON'- 3000 FEET ACL. 8000

FEET SHon OF RUNWAY.200 KIAS.

N5178TAtB·,·Q

Flameout Approach

6 Changed 1 May 1978

MOTE:

sn GUHSICHT 110 MILS. wHEfrt

~ : ~ ~ ~ R U ~ H ~ l ' t o : i ~ ~ Y t t U ~ ' ; f O E O W H POIHT UHTlL FLARE. USE SPEED-8.. .ES FOR SPEED CONTROL.

-- ."". --------

N O T E ~ THE STRAICHJ.lN flIGHT ' ' 'TH IMY BE INTEACEPT£O

LANDING CONFIGURmON

HAVE AIRCRAFT OIRrY PRIORTO THIS POINT, 1·112 NUt

1000 Fl AtL. SPOILERsARI,!EO. lBO 1C'45 MfNIMUM,

200 FT A(;I.,1000 FT FROMEND OF RU"'WAY·"'AH04TORYI.IINIMUM. 180 1C14S MINIMUM.

AT THE MOST CONVlNlEJH POINT PftIDR TO THE FIN"LCHEel'; POINT. THt CHECK POfNTS ARt GUIDEliNES ONLY,

TA111-.,.,.

Precautionary Approach

Changed 1 May 1976 7


http://slidepdf.com/reader/full/a4-natops-pocketchecklist 10/74B

INlIlAl3 liM, ~ O O FH l ACL

• DRAG CONFICURATION WHICH R[SUl TS INTHE LOWEST APPROACH AIRSPEED ABOVEA MINIMUM VALUE OF 180 KIAS,

.B ~ : : g ~ ~ ~ Y FUEL SHUTOFF LEvER

PUSHOVER

INT£RCEPT 3 1/2 0 CllOE SLOPE,500 FEET ACL

• LOWER LANDING CEAR IF NOT DOWN,

eLIDE SLOPE

TARCET Al TlTUDE

• SHutDOWN ALTITUOE PREDICATED ONIt. UlO KT APPROACH SPEED A N ~ A 150 FTAl TITUDE. FOR EVER'( 10 KT INCREASE IN

~ ~ ~ n ~ ~ ~ ~ I ~ ; I ~ ~ ~ ~ ' ADO 25 FEET TO

SHUTDCIIINAf TARCET ALT IT UD [

• [MERCENCY FUlL. SHuTOFF L.EVER OFF.

• ENSURESPHOBUKES

OuT.

COND ITiONS

• GROSS WEIGHT UMIT 1&,000 L.8S.

• WINO CORRECTION, 10 KTS HEADWINDCQ,I.IPQNENT DECREASE SHUTDOWNALTITUDE BV 25 FElT,

• PATTeRN IS FOR STOPPINC ON AN

~ ~ ~ g ~ e 2 I T L : ~ ~ r ~ Y WItH ARRESTINC

• ~ ~ I ~ J ~ 1 1 ~ t ~ ! ~ ~ \ ~ ~ ~ ~ e O C E l ~ O D 1 5}OPEOEC£L [RATING A P P R O A C ~ TO HARE.

FLARE

•![2RKiAlo ~ N : R ~ ~ l ~ A 4 l E f O ~ £ b t S l l ~ ~ ¥ D E

[ lbO KIAS !.4INUMUM TO FlARE),

RUNWAV

/

TOUCHOCIIIN

• 140 I(IA5 AHO 1500 F en FROM MIRROR.

• HOOK DOWN PRlOR TO ARRESTINC CEAR.

TAlB-54

Stuck Throl//e Approach (Power lor Level Flight)

Changed 1 April 1974

FIRE

1. Throttle • OFF

2. Manual FUEL shutoff control - EMER OFF

3. Use Starter - CONTINUE CRANKING ENGINE

4. If fire continues - ABANDON AIRCRAFT

5. If fire continues • Use CO 2 AT INTAKE

ENGINE FIRE (IN FLIGHT)

WITH OTHER INDICATIONS

1. Throttle • OFF

2. Manual FUEL shutoff control - EMER OFF

3. Emergency generator • EXTEND

4. DO NOT RESt ART ENGINE

5. If conditions warrant • EJECT

ENGINE FIRE (IN FLIGHT)

WARNING LIGHT ONLY

1. Throttle. MIN FOR FLIGHT

2. Land as soon as possible.

WING FIRE UN FLIGHT)

1. Combustible stores • JETTISON

2. Fire continues. EJECT

ELECTRICAL FIRE (IN FLIGHT)

1. Electrical equipment • OFF

2. If fire persists • EXTEND EMER GEN

3. Fire out • NECESSARY elECTRICAL EQUIPMENT ON,ONE AT A TIME

4. If fire continues. LAND OR EJECT

5. If landing made. USE SHORT FIELD ARRESTING GEAR,

SECURE ENGINE WHEN STOPPED

Changed 1 May 1976ca·mmliU.•

9



lOl"L DISI"NCE 10 CLEAR" SO Ft OaSl"ClI- 1000 ,EIT

TakeoH Distance IP·8AI B}

10

FUEL CONTROL

1. Throttle • MATCH WITH RPM2. Fuel control switch • MANUAL3. Slowly advance throttle to desired setting.

THROTTLE LINKAGE FAILURE

1. Do not manipulate throttle.

2. Determine thrust available; be alert for slow rpm decay.

3. Fly PA or STA, maintain 180 KIAS minimum.

LOW ALTITUDE AIRSTART

1. Commence zoom climb.

2. Retard throttle.3. Switch fuel cont rol to MANUAl.

4. Extend emergency generator.

If thrust is not regained immediately, proceed as follows:

5. Throttle to IGN, then to IDLE.6. Cautiously advance throttle and ascertain restoration of

thrust.

7. If engine fails to respond adequately and peak altitude at

zoom apex is less than 5000 feet, EJECT. If time andaltitude permit, establish 250·KIAS glide and commenceAI RST ART procedure s.

i 3 f J ~ B ' 1 ' i _ ENGINE FAILURE

1. Throttle • OFF (Fwd cockpit!

2. EMER GEN handle • PULL

3. Evidence of fire • MANUAL FUel SHUTOFFEMER OFF

4. Fire exists or existed • NO ENGINE RESTART

5. No fire • SEE AIRSTART

CONIINUED




170

I

•

i:t: 110

12

HAL' .LArs

MCDILl ' A ~ ' IIENGINE, JS2-'-6A11

TAKEOff DISTANCE

O'UATIONAL II ' NOSEU' TlIMI

3 4 5

NO IATO

DATA AI 01. I MAY " 7 2

DATA IASIS •• UGHT TlST IKAVYI

GIOUND IUN DISTAHCI - 1000 un•TAI1-6'(;

Takeoff Distance (P-6AI BJ

Changed 1 May 1976

(AIRSTART

1. Throttle. RETARD2. Fuel control. MANUAL3. If loss of thrust cannot be corrected:

a. Throttle. 0 F F

b. Emergency generator. EXTENDc. Check for fire.d. If fire persists or existed prior to shutdown, do not

attempt restart.

If no fire exists, proceed as follows:

4, If practicable, descend to 30,000 feet or below at bestglide speed.

5. Establish 25 0 KIAS glide.

6. Throttle. IGN, THEN IDLE7. RPM and EGT. MONITOR

8.If

relight does not occur within 30 seconds (JP·4) or 45seconds (JP·5), retard throttle to IGN, then return to

IDLE .

Changed 1 May 1978 12A



MODEll TA..'ENGINE: H2-P- 'AI '

TAkEOff REfUSAL SPEEDSPUD.IAKES AND SPOILERS OPEN

HALF FLAPS

1';1. :-11:: r:: !.'::

; l l ~

DATA AS 0 ', I MAY 1972DATA IASIS. ESnMATED

,"+--t-.......{ 2 ~ . . " . . . ~ _ I - l - - , t . I , . , . . . . . . . . . { f + ' - t - H .....::.,..j

; . l , . . ~ ~ . : - ~ ; . . . . ; . ; . . ; . . ! I . . : T ; . . i - I .

b - n ~ ~ ~ ~ . ~ ~ ; o ; ; : j : ; i : ; ; ; ; ; j . . i ... ~ i # a ; i ~ ~ ~ ~ ....

o ~ · ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ -2 0 -1 0 0 10 20 30 40

r---,,......--,,......--.r--+._ ........_ ........ _ 4 l ~ ~ ~ ~ ~ E , . . ; T ; . : E ; ; . ; : . M P E ~ : T U U - D E G . E E S CENTIGUDE

i.-i,.

!

ii

I r!"

OIOSS WEIOHT-1000 POUNDS

. ...,.' "t..:..:..,... ,

-! !.. ti I

f~ R i . : - . ; . . ' 4 ~ - + . . . . ; . . # ~ + + - - " 1 - t - H . . , . f ~ r + .......rl-.,.,...., 20 NOTE:

.. !;1

... .,. IIAKE A"LlCATION SPEED

L : : : ' ~ L . : . . ; . : ; u = . . : . . L : . : . . . - l J . ~ . w L . ; . . . . . : . . . . , l . ; . , ; . . . . . . . . 1 . . : . . : . . . ; ~ L ; ; ' ; ' ; ' O > J . . : . ~ , . ~ p i ~ : . I T : : F : ~ I W E TI.E

SPEED WILL NOT IE

o EXCEEDED IT ANYTAKEOff SPUD COMPUTEDF.OM THIS CHAIT.

10

~ ~ h - ~ ~ o . ; J . ; . ; . . : . + . ; . - . . ; ~ ~ ' k : - ~ ~ ~ ~ " d ' ~ - : ; ! - ~ ~ 20 HEADWIND

50 60 70 .0 90 100 110

REFUSAL SPEED - KIA!

o

+2130 140 150 160

Tokeo" Refusal Speed IPSA/B)

12B

-KNOTS

IUNWAY OIADIENT- PEiCENT SLOPE

TAII-!

MODILI fA ....,

PlGINI, 15t-P-IAII

TAKEOff RE'USAL SPIEDsrnDUAKE! O'fN-SPOlllU ClonD

HAl' RAPS

DATA AS Of, I MAT 1972DATA IASIS, ISTlMATlD

-2 0 -1 0 0 10 20 30 40 50

_ ......- ...... . . - . . . . . J _ ~ ~ ! ! ! . , ! ! ; : ! = : ; . . _ . . . - _ , . TEMPIIATUII-DIOIISS CINTIO.ADI

so 10

"'USAL SPIID-IC1AS

GlOSS WIIGHT- 1000 POUNDS

0

I10

20HIADWIND

-KNOTS

30

40

:-,IUNWAY

0GRADIENT

- ' I ICINT$10'1

+'140

Talceoff Refusal Speed IP8A/BI

TAli_52

12C



TAKEOFF REFUSAL SPEED

S'IEDIlAKES AND SPOILIIS 0 ' IN

HALf fLA'S

DATA AI Of. 1 MAY . ,72DATA IASIS, ISTiMATID

~ 2 0 -1 0 0 10 20 30 40 SO

TEM'IIATUII- DIOIEIS CENTIGIADE~ ~ ~ ~ ~ ~ ~ ~ ~ r . T r . T ~ T 7 ~ ~ T . ' ~ 2 .

to 60 70

12D

11

0

10

20

30

40

- 2

0

IUUSAL S'EED - KIAS

OIOSS WEIOHT

- 1000 POUNDS

HIADWIND

- KNOTS

IUNWAY

O....DIENT

- 'IICENTSlO'E

Takeoff Refusal Speed IP-6AIBJ

'AII.SO·A

Changed 1 May 1976

MODn, TA.4./JINOINI, JI2· '·6A'1

TAKIOFF REFUSAL SPEED

I 'UDUAKIS O'IN - 1'011111 CIOIID

HALF FIA'I

DATA AS 0" I MAY '972

DA'A IASIS UTiMATED

-2 0 -1 0 0 to 20 30 40

W ~ I I ~ O ~ H ~ ' J I ~ A ~ S I ~ U ~ H [ I J - ~ ~ ~ __ __ -r__' -___ 24 T(M . . . . . . 'U U _ DIOIUS CINIlGIADI

50 60 70 90 100 110 120

".USAI SOUD - KIAS

140

20

11

01051 WIIOHT

- 1000 'OUNDS

0

10

20 HEADWIND

- K N o n

30

40

-2IU_AT

0O....DIINT

- 'IICEHTSlOPE

+2

ISO 160

Takeoff Refusal Speed (P-6AIB)

TAIt·51.A

Changed 1 May 1978 12E



0

! i : ~ .,

" .. %- ""'0 ., J5};II

cS... i J2l Q-

" : : : ~ "' z !L-"' Q

ex )( ....... t: c ...2l _L

tJ ... '"

;:)

~ . : 2:::

cz

Maximum Takeoff Weigh' IP-8AIB)

12F Changed 1 May 1978

SMOKE

1. Possible fog • CABIN TEMP-MAN. HOT

2. Possible air conditioning • CABIN PRESS-RAM3. Possible electrical. SEE ELECTRICAL FIRE

4. Vision affected. SLOW AIRCRAFT-RAM AIR

(IF NECESSARY-JETTISON CANOPY.)

5. Land as soon as possible.

EJECTION

1. Lower ejection hand le • PULL

EJECTION

1. Throttle • IDLE

2. Speed • SLOW AS POSSIBLE

3. Seats. OPTIMUM POSITION

4.EMER GEN handle. AS REQUIRED

5. IFF. EMERGENCY

6. Transmit • MAYDAY POSITION REPORT

7. Visor. DOWN8. Shoulder harness lock lever • LOCKED

9. CABIN Pressure switch. RAM10. Sit erect, spine straight, head firmly against head

rest, feet on rudder pedals.11. Face Curtain • PULL TO FULL EXTENT

(Rear seat pilot shall initiate own ejection first, followed by the front seat pilot).If canopy fails to jettison,

12. Either ejection handle • GRASP (WITH LEFT HAND)13. Canopy jettison handle • PULL

14. Either ejection handle • PULL

If canopy still fails to jettison,15. Either ejection handle. GRASP (WITH RIGHT HAND)

'6 . Canopy control handle. MOVE to OPEN (RETURN TO

CLOSED AFTER JEniSON)(Canopy should Jettison aerodynamically if speed isabove 240 KIAS. However, canopy hand pump maybe used to raise canopy if cockpit is not pressurizedand utility hydraulic pressure is not avaifable,)

17. Either ejection handle • PULL

Changed 1 May 1978(i.',II""" ...

13/14(blank)



BAILOUT

1. Emergency oxygen. PULL GREEN RING

2. Oxygen/antiblackout hoses. DISCONNECT FROM

CONSOLE

3. Cockpit pressurization' RAM4. Canopy. JETTISON

5. Emergency restraint release handle • PULL

6. Lean forward for chute-headrest clearance.

7. Trim nosedown.

8. Arms against body, let stick snap forward.

9. When clear an d below 14,000 f t . PULL O-RING

DITCHING

1. Review UNDERWATER ESCAPE procedure.

2. Shoulder harness lock lever • LOCKED I3. Gear . UP

4. Stores • JETTISON

5. Flaps • DOWN

6. IFF • EMERGENCY

7. Transmit. MAYDAY POSITION REPORT

8. Visor • DOWN

9. Armament switches • SAFE

10. Hook. DOWN

1. Cockpit pressurization. RAM

12. Prior to touchdown:

Emergency oxygen • PULL

Canopy. JETTISON

13. Remain braced until shocks stop,

Changed 1 April 1974 lS



16

:. ::

a fi 0 i I

laYlOIIN.;) snlOla - l in lYII.WUf iT ' ~ ' 1 i r i T j i r i i l , - - . , - , . " . . , - " t - r - n ~ 7 ~ : 7 r . : : : : : : T . " : " : : ' I s .. - l l iHNIIH" SlIlOla - JlRlYII4WI1

; . . . . : . . : . l J . + t t ~ ~ + + + f f ! t ! f i + I i! §I~ ~ ~ ~ ~ ~ ~ ~ i l i a ~ al

~ : . t : - \ - ~ ~ t - : - l ~ ~ ~ m 2!2 !2:; s-

~ ~ ~ ~ I . M - + - I h l - : t r r t t l 2 ~ ~ = i l;A; i

: =II ~ ~ ~ " : ' : " ¥ . . : . . l M - - l t ' ; - l \ - H - A t r l ± t t i RiI

Maximum Takeoff Weight CP-6AIBJ

Changed 1 MaV 1976

UNDERWATER ESCAPE

1. Emergency oxygen • PULL

2. Oxygen hose • DISCONNECT FROM CONSOLE

3. Canopy • JETTISON

4. Emergency restraint release hand le • PULL

5. Lean forward for chute-headrest clearance

6. Grab cockpit structure and PULL • PUSH WITH FEET

7. When clear. PULL INflATION GEAR TOGGLES

If canopy fails to iettison, hold manual canopy control handle in OPEN position an d actuate hand pump

(R console-fwd cockpitl. If this should fail, userevolver or service knife to break plexiglas.

HYDRAULIC FAILURE

FLIGHT CONTROL HYDRAULIC SYSTEM FAILURE

Avoid maneuvers requiring high control forces.

UTILITY HYDRAULIC SYSTEM FAILURE

Result-Pressure loss for SPEEDBRAKES, FLAPS, GEAR,

HOOK (UP), CANOPY, SPOILERS, AFCS, and NOSEWHEEL

STEERING

DUAL FAILURE (FLIGHT AND UTILITY)

1. Accelerated maneuvers. TERMINATE

2. Airspeed • REDUCE BELOW 200 KIAS

3. TRIM AIRCRAFT FOR 200 KIAS OR BELOW

4. MAN. FLT CO NT handle . PULL FULLY WITH RAPIDPOSITIVE MOTION

5. Retrim aircraft.

6. Land as soon as possible with straight-in approach.

7. Make arrested landing if crosswind is IN EXCESS OF

8 knots.






UNSAFE MAIN LANDING GEAR-DOWN

INDICA nO N

1. Airspeed· 225 KIAS OR LESS

2. Gear · CYCLE

3. Apply positive g to correct possible microswitch mal·

function

4. Visual check • OBTAIN AND PERFORM APPROPRIATE

ACTION

Note

With gear still UNSAFE an d no visual checkavailable, perform steps (5), (6), (7), or (9) as

required.

5. Ooor(s) open but hung in well: Raise gear, apply ant

maintain negative-g, extend speedbrakesan d lower

gear.

6. Ooor(s) not open • EMERGENCY GEAR EXTEND

7. Gear still not down an d locked • ACCEL 35 0 KIAS

APPLY POSITIVE G

8. Gear still indicates UNSAFE bu t visually down an d

locked: Arrested landing; if unavailable, normal

landing. Pin gear ASAP.

9. Gear not down an d locked: Attempt to raise gear.

Refer to Gear Malfunction Landing Guide.

18B Changed 1 May 1976

UNSAFE NOSE GEAR-UP INDICATION

1. Airspeed' 22 5 KIAS OR LESS.

2. Obtain visual check. If gear up an d door is flush,Icycle gear in an attempt to obtain up indication.

Continue mission.

3. If gear is not up or door is not closed, lower gear

when practicable, dump excess fuel an d land. Do not

recycle.

4. If visual check ca n not be obtained, lower gear when

practicable, dump excess fuel an d land. Do not

recycle.

UNSAFE NOSE GEAR-DOWN INDICATION

1. Airspeed' 22 5 KIAS OR LESS

2. GEAR' CYCLE

3. Apply positive g to correct possible microswitch malfunction

4. Visual Check • OBTAIN AND PERFORM APPROPRI

ATE ACTION

Note

With gear still UNSAFE an d no visual check

available, perform steps IS', (6', (7', or (9', as

required.

5. Door Open and gear Hung in well: Raise gear, apply

an d maintain positive-g an d lower gear.

6. Doorls' nof open • EMER GEAR EXTEND

7. Gear still not down an d locked • ACCEL 35 0 KIAS

APPLY POSITIVE G

8. Gear still indicates UNSAFE bu t visually down an d

locked: Arrested Landing; if unavailable, normal

landing. Pin Gear ASAP.

9. Gear not down an d locked: Attempt to raise gear.

Refer to Gear Malfunction landing Guide.

Changed 1 May 1976 18C/I180 Blank)



, ",' N 1 ! R 1 r : o A ~ 8 ' " hI BASIS: NADC

GEAR MALFUNCTION LANDING GUIDE

fiNAL fIELDFIELD

CONFIGURATION CARRIER Arresting GearAvailable

No Arresting Gear

MALFUNCTIONING = Nose gear)

Action Notes ActionA/G Notes Action Notes

(MG =Main gearl Used

All gear up LAND 1 LAND ND 3,4 lAND 3NG up LAND 1,2 LAND YES 5 LAND 7

Stub NG LAND 1 LAND YES 5 EJECTOne MG up LAND 1 EJECT NO 6 EJECTStub MG LAND I ElECT NO ElECTI MG & NG up ElECT EJECT NO mCTBoth MG up EJECT LAND YES 8 ! LAND 8

GENERAL

Whenever any landing gear is damaged or not down and locked. but all gear can still beretracted, retract the gear and divert ashore if feasible. Retain and land on empty tankltanks, empty rocket packs, or other light weight inert stores, with exception of the airrefueling store. Jettison the drop tanks, if they cannot be emptied. Prior to landing withany of the above malfunctions, burn down to 600 pounds or less fuel remaining to ensurethat the wing fuel is expended and the fire hazard minimized. LSD control is advisableon any normal approach.

NOTES:

1. Crossdeck pendant configuration shall be per current recovery bulletins.

2. If lime considerations preclude removal of crossdeck pendants, land with hook up toprevent severe nosedown rotation, should arrestment occur prior to barricade engage·ment.

3. Ensure crossdeck p e n d . ~ t s are removed from runway. Make flat approach at normalapproach speed. Touch down lightly, with low sink rate. If 10 knots or more of cross·wind component exists It may be desirable to use arresting gear where available.

4. Alternate method: Use arresting gear. Wave off if wire is missed.

5. Make short field arrestment from flat approach at normal approach speed. Trim fullNOSEUP approaching touchdown. At touchdown, do not retard throttle. Hold nose upuntil arrestment. Wave off if wires are missed.

6. An alternative to ejection for this condition is to land in approach similar to that inNote 5, except slightly fast and with touchdown point Immediately prior to arrestinggear. Grease this one on holding w i n ~ s level with lateral stick as long as possible.An lSO is probably a necessity for thIS situation unless gear location is prominentlymarked.

7. Make flat approach al normal approach speed. Trim fuJi NOSEUP approaching touch·down. At touchdown, secure engine. Lower nose slowly before elevator effectivenessis lost.

8. Ejection mandatory without two drop tanks Installed.




LANDING DISTANCEHAIIl SUIFACE IUNWAY

DIYSPEEIlIIAKES AND SPOILUS OPEN

ICI=23

MODILI TA··" DATA AI 0 ', I MAY 1972

ENGINE: J52,P"A/1 DATA 11.515, FLIGHT TEST !NAVY AND CONUACTOII

20 -1 0 0 10 20 30 40

TEMPEIATUU FULL- IlEGUES CENTIGIADE

APPROACH HAL.FLAP

IlEFLECTlON UP

HEAIlWIND 20 0-': . . : . . : . . j ~ # 4 · : " ; " ; 4 - ; : i R 7 f + t T . f t f ~ H t r . - ; : ; t 1 -KNOTS I.

RUNWAY •.

GRAIlIENT 0 ~ ~ ~ J . . . . ; . . ; + A : ; : ; " : " ' . : { - . . : r - I : ~ h t t ~ r . " - PERCENTSLOPE

Landing Distance

20

WHEN LANDING WITHOUT FLAPS

1. Dump to landing weight.

2. Fly slightly wider pattern.

3. Fly optimum angle of attack. 9 KIASIAOA donut-approach speed is about 16 to 1

above normal.!

LANDING WITH STUCK SLAT

1. Normal approach speed • INCREASE 10 KNOTS)

2. Trim ou t adverse lateral control pressures.

3. Be alert for prompt correction if slat extends.

4. Carrier • OBSERVE MAXIMUM ENGAGING SPEED

SPOILERS

11.2.

3.

If feasible, go around.If unable, control swerving with correctivebrakes and aileron as required.When ~ o n t r o l is regained, spoiler switch. OFF

rudder,

SPOILERS

1. Ensure power is above 70 percent.2. Spoiler switch • OFF.

3. Deploy emergency generator. ..

4. If none of the above proceduresfsucc5eOeOdOlfn ctloAslGnlg

the spoilers, slow flight the aircra t a ~ . ee ,or above, to check landing charactenstlcs.

5. Use full flaps with gear down.

6. Keep speedbrakesclosed.

7. Expect excessive approach speed.

8. Use arresting gear where practical.




RUNAWAY NOSEUP TRIM

DURING TAKEOFF

1. Flaps· FULL DOWN

2. Maintain safe airspeed and attitude.

3. Use manual trim override to reposition trim.

If trim continues to runaway:

• EMER GEN • DEPLOY4. External stores • JETTISON (IF REQUIRED)

5. Burn down and land.

RUNAWAY NOSEDOWN TRIM

DURING TAKEOFF

Below refusal speed:

1. ABORT

Above refusal speed:

1. Flaps. UP2. Horizontal stab override • UP3. External stores. JETTISON (IF REQUIRED)

RUNAWAY STABILIZER TRIM DURING FLIGHT

1. Trim· CHECK INDICATOR

2. Manual override • ACTUATE OPPOSITE TORUNAWAY

3. If runaway continues:

• EMER GEN • DEPLOY

4. Remain on hydraulic power control.

5. If unable to retrim and trim is stuck at or near fullnoseup position:

• Reduce speed• lower flaps


LANDING WITH RUNAWAY NOSEUP TRIM

1. Flaps· FULL DOWN

2. Light weight • FWD CG

3. Straight in approach recommended.

LANDING WITH INSUFFICIENT NOSEUP TRIM1. Flaps. UP

2. Max allowable landing weight (AFT CGI.

3. Fly airspeed that ensures additional back stickmovement of at least 2 inches.

4. Straight-in appro ach.

Note

A carrier landing with nosedown trim is not recommended. If possible divert to a shore station.If a divert is not feasible, a barricade engagement

is recommended since aircraft bolter capability isextremely margina l.

AILERON OR RUDDER TRIM RUNAWAY


• Remain on hydraulic power control.• DO NOT APPLY OPPOSITE TRIM.

2. Reduce speed.

M f u i ~ C d @ H l 4 ( . ) i i t i i i ' W _ ELECTRICAL1. Airspeed • BELOW 500 KIAS or 0.91 IMN

2. Above 25,000 feet • THROTTLE 90 PERCENT or LESS


• EMER GEN bypass switch • NORMAL




EQUIPMENT AVAILABLE TO PILOT ON

EMERGENCY GENERATOR

PRIMARY AC BUS

1. Air conditioning

2. AJB-3A attitude system

3. Cabin temperature control(Fwd & Aftl

4. Cabin pressure (Normal-

Ram)

5. Console lights (Fwd & Afll

6. Fuel flow

7. Horizontal stabilizer trim

8. Ignition (20 louie)

9. Instrument lightsIFwd &Aft)

26 VAC BUS

1. Angle of attack

2. BOHI (Fwd & Aft)

3. Compass

4. Emergency bomb release

28 VOC PRIMARY BUS

1. Air refueling ITA-4F)

2. AJB-3A attitude system

3. Audio isolation amplifier

. 4. Cabin pressure (Normal-

Ram)

5. Fuel quantity (Wing & Ext)

6. Fuel transfer bypass

7. Hook bypass8. ICS

MONITORED PRIMARY AC BUS

1. Fire warning

2. Fuel quantity (fuselage)

3. IFF

4. LOX quantity

S. Pltot heat

10. Oil level

11. Standby attitude indicator

12. Test panel

13. tWindshield heat (Center)

14. Engine control

15. tAngle-of-attack heat

16. Approach lights & AOAindexer

17. Fuel dump

18. Red floodlights

19. Warning lights relays

5. Hose lettison ITA-4F)

6. Oil pressure

7. 10-249 ITA-4J)

9. Ignition timer

10. Oil level

11. Radio control

12. Trim position

13. UHFI ADFI AUX receiver

14. Wheels &flaps position

indicator

15. Altimeter (MC-31AAU-19A)

16. Retraction release solenoid

17. Emergency fuel transfer I(AFC586)

6. Radio

7. tTACAN

8. UHF-ADF

9. Anti-icing regulator

tlnoperative with landing gear handle down


The following is a partial list of equipment that will be lost

while operating on emergency generator:

'I. All normal trim

2. All normal weapon delivery capability

3. All external lights except approach light (with hook

down)

4. AFCS5. Radar altimeter

6. Rain removal

7. Seat actuetor

8. Instrument panel vibrator

'3. Side panel windscreen heat

10. White floodlights

11. Normal drop tank transfer (drop tanks go to automatic

transfer)

12. Normal speedbrake control

13. Fuel boost pump

14. Nosewheel steer ing (on landing)

15. Spoilers (on landing)

DC CONVERTER FAILURE

The following items will be inoperative on the main generator:

1. ICS and radio transmission and reception

2. Control and utility hydraulic warning lights

3. Fuel boost lights and transfer warning lights

4. Approach lights

5. Fuel low warning lights

6. Hook bypass

7. AJB·38. Standby attitud e system disable

9. Trim position indicato rs

10. ADF

11. All armament circuits (except emergency jettison)

12. Spoilers

13. Nosewheel steeri ng

14. Speed brakes (manual override available)

15. Aileron and rudder trim

16. AFCS

17. APC

18. Counting accelerometer

Changed 1 May 1978 24A



19. Rain repellant

20. LAWS

21. Test circuit for all warning lights

22. Wheel and flap indicators

23. JATO jettison

24. Landing gear solenoid

25. Emergency wing fuel transfer

26. Air conditi oning

a. Canno t be turn ed off

b. Relief valve cannot be opened

c. Ram air valve can be opened

27. Ignition

a. 4 joule only on P6 engine

b. None on PS engine

2S. TACAN

29. Oil level

30. IFF

If the emergency generator is deployed, the following additional items

will be inoperative:

1. Radar altimete r

2. Fuel boos t

3. Engine pressure ratio indicat or

4. Aileron bungee heater blanket

5. Anti·exposure suit ventilation blower

6. Side panel windshield heate r

7. Seat actuator

S. Instrument panel vibrators

9. Rain removal

10. Exterio r lights

11. White floodlights

The following items will remain operative on either main or emergency

generator:

1. EGT

2. Tach

3. Oil pressure

4. Fuel flow indicator

5. Fire warning (minus test circuit)

6. Center panel windshield heater

7. Fuel contr ol

8. Stabilizer trim (with override only)248 Changed 1 May 1978

9. Fuel quantity indicator (fuselage fuel only)

10. Instrument lights

11. Emergency jettison

12. Anti·icing and pitot heat

13. LOX quantity gage

14. Servoed altimeter

If the emergency generator is deployed, the main generator can be

Iregained by placing the switch in the forward cockpit in BYPASS. Thiscannot be accomplished in the aft cockpit, as this switch requires dc

power to hold it in BYPASS.

LIMITATIONS"M'ltj"' · '4F_-----------------1. AIRCRAFT

a. Gear and flaps down •

b. Negative normal accelerations.

c. Normal accelerations between

plus 0.5g and minus 0.5g •

d. Maximum asymmetrical load for

225 KIAS

10 SECONDS

TRANSITORYONLY

field takeoff an d carrier landing. 7500 FT-lB

e. Maximum asymmetrical load forfield landings • 12,500 FT-lB

f. Maximum asymmetrical load forcatapult • 5120 FT-lB(See wing moment (loading' nomogram'

g. Emergency generator extension. 500 KIAS or

0.91 IMNh. 300-gal tanks (carriage) • 575 KIAS or 0.90 IMN

i. External baggage container (carriage) • 525 KIASor 0.80 IMN

Changed 1 May 1978 24C



"-'"'"~ N ~ R ~ ~ B ~ '-'"'-'"2. ENGINE

Operating Max EGTMax RPM

LimitCondition C Time

Idle* 34 0 Idle

AcceleratonJ52-P-6A 650 Military S minJ52-P-68

66 0 Military S minJ52-P-SA/B 6S0 Military S min

NormalJ52-P-6A 59 0 Mil Minus 3%J52-P-6B 60 2 Mil Minus 3%J52-P-SA/B 59 5 Mil Minus 3%

MilitaryJ52-P-6A 610 Military 30minJ52-P-6B 621 Military 30 minJ52-P-SA/B 65 0 Military 30 min

*Idle temperature of 34 0 C is not a limit bu t is given asa guide to indicate temperature which, if exceeded, ma y

signify engine malfunction.

Oil Pressure • 40 to 50 psi in flight35 to 50 psi on deck (IDLE)

For aircraft with reduced smoke engines installed IJ52-P-S8 engines Or J52-P-8A engines

with PPC 185 incorporated), a minimum inflight engine rpm of 70 percent should be

maintained to preclude possible flameout. I3. GROSS WEIGHT (POUNDS)

Field takeoH • 24,500

Field landing. 16,000

Catapulting • 24,500

(C-11 / C-11-1 catapult). 23,500

240

" , . , .I N 1 ! R ~ A ~ B ' " ' ' hWARNING I

Shipboard catapult shots with partial fuelloading in external drop tanks is prohibited,

Arrested, T&G, and FClP . . . . . . , ............ 14,500

Barricade engagement ................ , , .. 14,500

Changed 1 May 1978 24E/(24F blank





DROP TANK TRANSFER FAILURE

If fuel transfer from all drop tanks is abnormally slow or

fails during flight, proceed as follows:

1. Drop tank transfer switch • PRESS

2. Emergency transfer/fuel transfer bypass (AFC 317) •

OFF/NORMAL

If drop tank transfer still does not occur:

3. Emergency generator • DEPLOY

When drop tank transfer is complete, place emergency

generator bypass switch in BYPASS. If deploying emer

gency generator does not accomplish transfer:

4. Ashore: Ensure aircraft weight for landing does not

exceed maximum limits. Effect minimum descent

landing.

S. Ship: Jettison drop tanks prior to landing.

INADVERTENT FUEL DUMPING

1. Proceed to nearest suitable field at highest feasiblespeed.

2. If fuel in drop tank, drop tank transfer switch. OFF3. If wing fuel depleted, continue at MAX RANGE

CRUISE.

Drop tank fuel remaining, proceed as follows:

4. Drop tank transfer switch. PRESSURIZE

5. Fuel transfer bypass. ACTIVATE

26 Chanflp.rl1 May 197R

ABNORMAL Oil PRESSURE

Less than 40 ps i . 1 MINUTE MAXIMUM

Zero pressure. 10 SECONDS MAXIMUM

If oil pressure remains out of limits (high or low), M A I N ~ TAIN (86 to 88%) UNTIL LANDING ASSURED OR DECI-SION TO EJECT IS MADE.

USE PRECAUTIONARY APPROACH.

Oil lOW LIGHT ON

1. Set engine RPM 86-88 % an d

land as soon as possible • USE PRECAUTIONARYAPPROACH

Changed 1 Ma y 1978 26A



ASYMMnRIC WING SfAliON LOAD LIMITATION NOMOGRAM

20,000 20,000

19,0000- 1000·11,000 0

2000..

g 15,00017,000 3000

16,000 i 12,5004000

0:I 70015,000 0 to,OOO 5000

\ :I100

\14,000

75006000 0 6DO2000, 13,000 I;; 7000

200 , :I 5000 5120500

SOO

\ 150012,000 :I 1000

.. (300 \ . 11,000 ' 9 0 0 0 . ~ 400

\ / 1900400 1000 to,OOO

" / 10,000 300\..

\ 9000 3 / It,OOO ASOO / 1500 200

SOO •1000 • t2,OOO

6DO5120 SOoo

1007000 \),000, g G 2000

700, 6000 7500/ 14,000 LOAD AT

0LOAD AT \ / STATION 4!LOAD Al STATION 2 {OOO:I /

10,000 15,000 IPOUNDSI LO"D ATST"TlON I IPOUNDSI

0 / SI .. TION SIPOUNDS! 4090

:I/12,Soo

16,000

IPOUNDSI\

3000, !:! 17,000IS.OOO

2000 '" 11,000f :I

1000 :I19.000..

0 20.000 20,000

MOMINT TO TOT .. L MOMINt 10pon .. SYMMEI." st . . . .OA.D

DUI TO LOADS MOMINT DUI TO LO .. DSAT ITA liONS 1f00T -POUNDII AT ST .. TlONS

I AND 2 4 "NO S1f00T-POUNDSI IFOOt·POUNDSI

to USI tHI NOMOG.. .M (ONNlct tHI KNOWN LOADS ON stATIONS I AND 2 IFO. MODILSA-41/C STAIION SAND , LOADS Al l ZUO' WIIH .. N IXIINDID SIIAIGHt LlNI. lEAD tHIMOMINI TO '011 DUI TO LOADS AT stATIONS I "NO 2. IIPlAT tHIS .10CIDUIl fOI StAIIONS4 .. NO S to fiND stAI.OAID MOMINT. CONNIC! THI 5TAIlOA.D MOMINI AND ,on MOMINIWIIH A SIIAIGHI LlNI. lEAD tOTAL AlYMMItIiC MOMINT AI THI 'OjTElSICTlON Of IHICONNICTING UNI AND THE 10TAL ASYMMIIIIC MOMENT SCALI. If THI TOTAL ASYMMIIIICMOMINI IS IllS THAN IHAT AILOWID fOI A GIVEN OPIIATION IHI LOADING IS SATlSfAClon.

UMIlATlONS,

fiELD LANDINOS . _ ...... , . . . . . I2,SOO fI-IIFIE,D TAKIOfFSO. CAIIIII LANDINGS .

CAIIIEI CA TA'U" .

.. 1100'1-1.

.. 5120 FT-I.

EXAMPlE,A lOAD AT ST AlION S .......... 2S0 II

I LOAD AT STATION 4 ......... 1000 LI( MOMIN I It) UAlIOA.D .. . 1620 FT-LIo LOAD Al STATION I ............0 III LOAD AI SIATION 2 " ........300 IIF MOM IN I TO .on •.......1I7S fI-IIo TOTAL ASYMMEl.ICAI

MOMINI ................ 6745 n· la

TAlI-9 '"

Asymmetric Wing Station Load Limitation Nomogram

26B Chan!led 1 May 1978

SECTION II

NORMAL PROCEDURES

TABLE OF CONTENTS

Subject Page

Briefing Guide ......... , ...................... 28

Preflight Checklist ............................. 31

Exterior Inspection ....... , ...... , . . . , ......... 31

Interior Inspection Before Entering Cockpit ......... 36

Interior Inspection After Entering Cockpit. , .......36A

Starting Engine ..............................36 0

Pilot-Controlled Start. . . . . . . . . . . . ...........36 0

Ground-Controlled Start . . . . . . . . . ...........36 0

Modified Pilot-Controlled Start ............ , . . , , . . 37

Engine Idle Check Curves , . . , ....... " . . . . , ..... 38

Abnormal Starts . . . , . . , . . , . . . . , . , ..... , . . . , . . . 39

Hung Start ..... , . , . . . , . , . . , , . , ....... , , , , . . , . 39

Hot Start ..................................... 39

False Start ............... , ....... , . . . . . , ..... 39

Wet Start ............................... , . . . . 39

Clearing Engine ............................... 39

Poststart Checklist ............ , ................ 40

Pretakeoff Checklist ............................ 41

Jet Penetrations ....... , . . . . , .......... , . . . , . . . 42

Securing Engine . . . . , .......... , . . . . , .......... 42




NAVAIR OI·40AVD·16

BRIEFING GUIDE

The briefing guide will include the following items. when

applicable.

General

I. Aircraft assigned, call signs. event number, and deck

spot

2. Succession [() lead

. ~ . Fuel load. stores, and aircraft gross weight

4. Engine start, taxi, and takeoff times

5. Rendezvous instructions. takeoff distance, speed, and

line speed

Mission

I. Primary

2. Secondary

3. Operating area/rargct

4. Control agency

;. Time on station or over mrget

Navigation an d Flight Planning

1. Duty runway/predicted Foxtrot eorpen for launch

and recovery. and position in the force

2. Climbout

.1. Operating area procedures and rcstrictcd areas

4. Mission plan. inc.:luding fuel/oxygen management

and PIM

; . Bingo/low state fuel

6. Marshal/holding (normal and emergency)

'28


7. Penetration R[ocedurcs an d minimums

8. Ship/field approach and runway lighting

9. GCA/CCA procedures and minimums. missed

approach

10. Recovery: course rules, patterns, breakup, landing,

waveolTI I. Divert and emergency fields/ready deck

Communications

J. Frequencies

2. Controlling agencies

3. Radio procedure and discipline

4. ADIZ procedures

5. IFF

6. Navigational aids

7. Hand/light signals

8. Shift of aircra ft control will be accomplished with posi.

tive ICS call

Weapons

I. Loading

2. Arming

3. Special routes because of ordnance aboard

4. Pattern

5. Armament switches

6. Aiming point/sector setting

7. Run.in/entryairspeed

8. Minimum release/pullout altitudes

9. Duds, hung ordnance procedures, dearming, jettison

area

10. Safety

11. "G" vs gross weight

29



NAVA•• O\-40AVD-1I

Weather

I. Local area, en route, and destination (existing and

forecast)

2. Weather at airerna ce/divert fields

. Winds, jct stream, temperature, and conrrail band

width

Emergencies

I. Takcoff aborts

2. Radio failure

3. Loss of N AV AIDS

4. Loss of visual contact with flight

5. Lost plane procedures

6. Downed pilot and SAR

7. Aircraft emergency procedures and system failures

8. Ejection procedures

Air Intelligence an d Special Instructions

1. Friendly/enemy force disposition

2. Current situation

. ~ . Targets4. Safety precau tions

5. R ~ p o r t s and authentication6. Esbpc and evasion

30

NAVA•• O\-40AVD-1I

PREFLIGHT CHECKLIST

Consult Naval Aircraft Flight Record (yellow sheet) to

determine status of aircraft, and that the aircraft has beenfully serviced with fuel, oil, liquid oxygen, compressed air,and hydraulic fluid .

EXTERIOR INSPECTION

Forward Fuselage

I. External canopy control handle . . . . . . . . STOWED,

ACCESS DOOR CLOSED

2. Static pressure vent (2 vents left side) . . . . CLEAR3. Engine bleed static port (left side) . . . . . . . . CLEAR4. Angle-of-attack vane ..............CONDITION

5. Air-conditioning intake and exhaust ducts .. . CLEAR

6. Nose compartment panels .........CONDITION,

SECURITY7. Nose compartment cooling air inlet . . . . . . . CLEAR8. Air refueling probe cover ...........REMOVED9. Static pressu re vent (right side) .......... CLEAR10. Controls access panel (right side) . . . . . . . SECURE

11. Nosewheel well door .. CONDITION, SECURITY

IIA. Air·conditioningground test plug I(nosewheel well) .................SECURITY

12. Nose gear shock strut . . . . . . , . . . . . EXTENSION,

NO LEAKAGE

12A. Nosewheel spindle nut ............SECURITYI13. Nosewheel steering wire

bundle/lines . . . . . , . . . . CONDITION, LEAKAGE

14. Nosewheel tire ...................CONDITION

IS. Nose gear downlock pin ............. INSERTED

16. Nosegear actuator ................CONDITION

17. Emergency generator . . . . RETRACTED, SECURE

18. Externa l canopy jettison hand le(both sides) .. STOWED, ACCESS DOOR CLOSED

19. Gun flash suppressors and guns .........SECURE

20. Engine forward compartment . . . . . . CONDITION,

SECURITY

Changed 1 April 1974 31



NAVAIR O\·40AVD·1B

21. Guncharger pneumatic pressure gage . . . . . . . CHECK

22. Gearcase oil drain line cap . . . . . . . . . . . LOCKWIRED

23. Aileron power package . . . . . . . . . . . . . . . . . . . . CHECK

ALIGNING MARKS

f

24. AJB-3A GN D TEST switch . . . . . . . . . . . . ,NORMAL

25. Fuel boost curout switch . . . . . ' . . . . . . . . . . NORMAL

Right Wheel Well

1. Well doors '" , . . . . . . . . . . . . . . . . . . . ,CONDITION,SECURITY

2. Taxilight , , . , . , . , . . . . . . . . . . . . . . . . . . . . .SECURITY

3. Gun pneumatic pressure gage, .. , , . . . . . . . , .. CHECK

4. Armament safety disable switch. , . . . . . . , . . . . . . SAFE

5. Catapult hook . . , . . . . . . . . . . . . . . . . , . . . . PRELOAD,SECURITY

6. Main gear downlock pin . . . . . . . . . , . . . . . INSERTED

7. ShlH.'k strut .. ' . . . . ', . . . . " . , . . . . . . . EXTENSION,

NO LEAKAGE

8. Tire , . . . . , . . . . . . . . . . . . . . . . . . . . . . . . .CONDITION

9. Brakes . . . . , .. , . . . . . . . . . . . . , . . . . . . . CONDITION,

NO LEAKAGE

10. Main landing gear actuator , . . . . , ' . . . CONDITION

11. Fuel system vent , . , . ' . . . . ' . . . . . , ' . . . . . . . . CLEAR

Right Wing

1. General condition . . . . . . . . . . WRINKLES, CRACKS,LOOSE RIVETS,

FUEL DEPOSITS

2. Wing rack/stores . . . , . . . . . . . . . . . . . . . . . . . . . SECURE

3. Drop rank filler cap .. , . . . . . . . . . . . . . . . . . . . SECURE

4. Slar . . . . . . . . . . . , . . . . . . . , . , . , ' FREE MOVEMENT

5. Navigation and fuselage (wing)

lights " , .. , . . . , .. , . , . . , .. , ' , . . . . . . CONDITION

6. Aileron and flap . . . . . . . . . . , . , . . . . . . CONDITION,

BONDING

32

NAVAIR O\.40AVD·1B

7. Spoiler . . . . . . , . . . , ' , . . " . . . , . ," CONDITION

8. Wink tank filler cap . . , . , . , . . . . . , . . . , , ,SECURE

Aft Fuselage an d Tail Section

1. All fuselage access doors . . . . . . . , . . . . . . . CLOSED

2. Speed brak e .......... CONDITION, SECURITY

3. LOX compartment . . . . CONDITION, SECURITY4 T '1 .. al pIpe cover ..................... REMOVED

5. Tailpipe ........ , . . . . . . CRACKS, WRINKLES,

BURNS, FUEL DEPOSITS

6. Taillight ........................ CONDITION

7. Rudder, elevator and horizontalstabilizer ............CONDITION, BONDING

8. Speedbrakes .......... CONDITION, SECURITY

9. Arresting hook . . . . . LOCKED UP, CONDITION10. Tension bar retainer ..............CONDITION

11. Arresting hook holddown cylinderpressure gage .................... 900 + 50 PSI

12. Engine aft compartment . . . . . . , . . . CONDITION,

SECURITY

13. Flap actuator .................... CONDITION

14. Drop tank pressure fueling switch ........... OFF

15. Engine fuel drain lines ...........CONNECTED

(aft engine compartment)

! WARNING IDo not pull any cable in the aft engine compart.ment. Inadvertent full or partial elevator disconnect or lowering of the arresting hook may result.

16. Elevator power disconnecthook and power hook drivepin (aircraft reworked perA·4 AFC 530) . . " . . . . , . . . . . . , . , . . . ENGAGED





Left Wing

1. General condition ........ WRINKLES, CRACKS,LOOSE RIVETS

FUEL DEPOSITS

2. Wing flap and aileron .......... CONDITION,

BONDING

3. Aileron tab ....................CONDITION

4. Spoiler ........................ CONDITION

5. Navigation and fuselage (wing)lights ......................... CONDITION

6. Slat ...................... FREE MOVEMENT

7. Wing rack/stores ....................SECURE8. Drop tank filler cap .................. SECURE9. Approach lights and cover ....... CONDITION

Left Wheelwell

1. Well door ........... CONDITION, SECURITY2. Capture hook ........... PRELOAD, SECURITY3. Main gear down lock pin ........... INSERTED

4. Shock strut ....... EXTENSION, NO LEAKAGE

5. Tire ..........................CONDITION

6. Brakes ......... CONDITION, NO LEAKAGE7. Main landing gear actuator ...... CONDITION8. Retraction release switch .........CONDITION

Center Fuselage, Underside

1. Fuselage rack store ................... SECURE2. Centerline fuel tank cap ...............SECURE3. Centerline external baggage container .. SECUREj

(If installed) CHECK BAGGAGETIEDOWNj DOORS

SECURED

14. Forward engine and accessories

section access doors ................... CLOSED

S. Link and case ejection chutes ............. CLEAR


NAVAIR OI·40AVD.\8

Cockpit Area, External

l. External canopy jettison handle . . . . . . . . . STOWED;

ACCESS

DOORCLOSED

2. Controls access panel..................

SECURE3. Angle·of-attack vane .............. CONDITION,

FREEMOVEMENT

4. Engine intake plugs. . . . . . . . . . . . . . . . REMOVED

S. Intake ducts ........................FREE OF

FOREIGNOBJECTS

6. Canopy cover. . . . . . . . . . . . . . . . . . . . . REMOVED

7. Fuselage tank fillercap ................. SECURE

8. Pitot tube cover ....................REMOVED

9. Total temperature sensor cover . . . . . . . . REMOVED10. Canopy surface and seal ............CONDITION

Changed 1 May 1978 3S



NAVAIR 01·40AVD·18

INTERIOR INSPECTION BEFOREENTERING COCKPIT

FWD COCKPIT

1. Ejection seat control safety handle(headknocker) ..................... DOWN

2. Ej ection seat control safety handle

safety pin (1) •.•.....••....•.•. REMOVED

3. Seat firing control mechanism

initiator safety pins (2) •••....•.. REMOVED

4. CanopY-5eat interlock initiator

safety pins (2) ....••.•••..•.••• REMOVED

5. Canopy interlock (observe through

sight in control box housing) •..... ENGAGED

6. Face curtain and lower ejection

handle firing control cables •....•.. ENGAGED

7. Ejection seat firing control release

fitting an d firing control housing

surfaces .........•..•.....•......MATED

8. Face curtain ......••....•........ STOWED

9. Shoulder harness lockpin •.......••• SECURE

10. Shoulder harness inertia reel ..... OPERABLE

11. Parachute ripcord handle .•......... SECURE

12. Parachute pack ....... CLOSED/CONDITION

13. Spreader gun safety pin .....••..... STOWED

IWARNING'

If ballistic spreader gun safety pin has not

been removed. main parachute canopy will

no t deploy.

14. Delay initiator quick

disconnect .............•........ SECURE

15. Ejection seat control selector

lever ....................... AS DESIRED

16. Lapbelt and lapbe1t lockpins (2) • • • . . SECURE

17. Emergency oxygen lanyard ..... CONNECTED

18. Dart system lanyard •.......... CONNECTED

19. Emergency beacon lanyard ..... CONNECTED

20. Lower ejection handle ............. STOWED

21. Emergency oxygen bottle ............ 170o F)

1800 PSI

22. Seat kit release handles .....•.•..•. STOWED

36

AFT COCKPIT

DUAL SOLO

•

Changed 1 May 1978

NAVAl. 01·iOAVD-18

INTERIOR INSPECTION BEFORE

ENTERING COCKPIT (CONT.)

FWD COCKPIT

23. Emergency restraint release

handle/parachute arming

cable •....•••......••• CONNECTED AND

STOWED

24. External pilot chute static

line ..•..•.•...•.•..••• ROUTED UNDER

ARMING CABLE

25. Power inertia reel hose quick

disconnect .....•.......•••.•..•. SECURE

INTERIOR INSPECTIONAFTER ENTERING COCKPIT

FWD COCKPIT

1. Emergency speedbrake knob • • . • • . • NORMAL

2. Suit blower/exposure suit vent . . • • . • • . • OFF

3. Antiblackout (ANTI·G) suit, oxygen

an d radio communications

connections . • • . • • . . • • . . . . • • . CONNECTED

4. Oxygen switch • • . • • • • • . . ON, CHECK FLOW,

THEN OFF

5. AFCS standby switch . . • • • • • . • • . . • . . • OF F

6. AFCS aileron trim switch ...•.••..•.. NORM

7. Radar function selector switch • . • . • . • • • OF F

(I f installed)8. Manual fuel shutoff control

lever . • . • • • . . • • • • • . . . • . • CYCLE/NORMAL

(GUARD DOWN)

9. Smoke abatement switch • . . • • . • • . • • • • . OF F

10. Emergency fuel trensfer switch ••.•..... OFF

11. Drop tenks switch • . • . . • . • • • . . . . • . • • • OFF

12. Engine start swi tch .................... UP

13. Fuel control switch ••....•.•..•.. PRIMARY

14. Rudder trim control switch • • • . . • . NEUTRAL

15. Horizontal stabilizer manual

override • . • • . • • • . . • • • . . • • • • . • • NEUTRAL

16. Throttle • • • • • . • • . • • • • . . • • • . • • . • . . . . OF F

Changed 1 May 1978

AFT COCKPIT

DUAL SOLO

AFT COCKPIT

DUAL SOLO

OFF

36A



NAVAIR O\-40AVD·\B

INTERIOR INSPECTION AFTERENTERING COCKPIT (CONT.)

FWD COCKPIT

17. Speedbrake switch .........•...... CLOSED18. Master exterior lights switch . . . . . . • • . • • OFF

19. Throttle friction .................... OFF

20. JATO jettison switch . • • . . • • • • • . . . . • . SAFE

21. Flap handle • . . . . . . . • • • . . . • . . • • • . . . • . • UP

22. Spoiler switch ...•...••......•.•.... OFF

23. Nose'fVheel steering switch • . . • . . . • • • • . NORM

24. JATO arming switch ....•........•.•. OF F

26. Catapult handgrip ....•.•......... STOWED

26. Landing gear handle . . . . • . • . . . • • • • • • . DOWN

27. Emergency landing gear handle • . • . . . STOWED

28. Emergency bomb release ha ndle ..... STOWED

29. Vertical velocity indicator . . . . . . . . . . • • • • . . 0

30. Altimeter •........••................ SET

31. AJB-3 all-attitude indicator pitchtrim adjustment knob . , _• . . . . . • . . . . . • • SET

32. Airspeed indicator .....•.......•••.. 0, SET

33. Gunsight brightness control ............ OFF

34. Accelerometer . . . . . . . • • • • . PUSH TO RESET

35. APC standby switch . . . • • . • . . . . . • . • . . . OFF

36. APC temperature switch • . . . • . . . . . . • • . . STD

37. Data link power switch . . • . • . • . • . • . . . . OFF

38. Gunsight ......•..•..•..•..... SET, LOCK

39. Standby attitude indicator . . . UNLOCKED/SET

40. BDHI function selector

switch ...........•.•.•..... AS DESIRED

41. Stores emergency jettison select

switch • . . • . . . . . . . • • • • • . • • • • AS DESIRED

42. All arm amen t switChes . . . • . • . • . . . . . • . . OFF43. Radar altimeter .............•....•.. OFF

44. Manual flight control ha ndle ........ STOWED

46. ICS radio control panel

switches •..•.•.............. AS DESIRED

46. Emergency generator release

handle . . . . . • • . • . • . . . . • . • . . . . . •STOWED

47. Arresting hook handle ....•.•.....••.... UP

48. Canopy jettison handle ...•.... STOWED/PIN

REMOVED

49. Fuel transfer bypass switch . • . • • • . . • • . NORM

50. White floodlight control • . . . . • • AS DESIRED

51. Doppler radar function selector

switch ( T A - 4 F ~ ..................... OFF

368

AFT COCKPIT

DUAL SOLO

UNLOCKED

OFF

Changed 1 May 1978

NAVAIR O\-40AVD.\B

INTERIOR INSPECTION AFTERENTERING COCKPIT (CONT.)

FWD COCKPIT

52. Navigation computer (TA-4F) . . . . SET UP/OFF

53. UHF function selector switch . • • . . . . . . . OFF

54. IFF master switch ...••.............. OFF

55. TACAN function selector switch

(If installed) •.•...•.......•......... OFF

56. Radar function selector switch

(If installed) • . • • • • • . • • . • . . • • . • . . •• OF F

57. Compass control panel •• SLAVED, LATITUDE

SET

58. UHF auxiliary receiver functional

selector switch . • • . • . • • • • • • • . • • • • . . • . OFF

59. Interior light switches • • • • • • • . • AS DESIRED

60. Spare lamps container •• • ADEQUATE SUP PL Y

AND LID CLOSED61. UHF antenna switch ITA-4F) . . . • . • • . • . . . UP

62. TACAN antenna switch . • • . • • . . . . . . • • AUTO

63. Rain removal switch • • • • . . . • . • . . • . . . . OFF

64. Anti·icing switch • • • • . • • • • • . . • • • • . • • • OFF

65. Emergency generator bypass

switch • • . . . • • • • • . . . • • • • . . . • • . • NORMAL

66. Air distribution control

lever . • . • • . • • • . . • . . • . . . . . • . . AS DESIRED

67. Temperature control knob . • . . . • AS DESIRED

68. Cabin pressurization switch . • • • • . . . NORMAL

69. Air conditioning OFF/ON

switches • . • • • • . • . . . • • • • . • • . . AS DESIRED

70. External light switches • . • • . • • • • AS DESIRED71. Anticollision light . • . . . . . . . • • . AS DESIRED

Changed 1 May 1978

AFT COCKPIT

DUAL SOLO

OFF

HEAD

MEDIUM

RANGE

36C



NAVAIR 01-40AVD-l B

STARTING ENGINE

PILOT-CONTROLLED START

After application of air/external power,

1. Throttle ................................OFF

2. Engine starter switch . . . . . . DEPRESS TO START

3. 5% rpm, throttlE: ......................... IGN

4. 15 % rpm, throttle ....................... IDLE

5. Stabilized idle rpm ........ (SEE ENGINE IDLE

CHECK CURVES FORMINIMUM IDLE RPM)

6. Disconnect power.

GROUND-CONTROLLED START

1. Pilot holds one finger vertically . . PiC CONNECTSEXTERNAL POWER

AND STARTS GTC

2. ICS ................................. CHECK

3. Master press-to-test .................... CHECK

4. Throttle ................................ OFF

After plane captain signals that GTC is up to speed,

5. Tw o fingers held vertically . . . . . PiC OPEN GTC

AIR VALVE

6. 5% rpm, throttle ......................... IGN

7. 15 % rpm, throttle ....................... IDLE

8. 45% rpm, three fingers held

vertically ............... PiC CLOSE GTC AIR

VAL VE AN D REMOVESTARTER AIR HOSE

9. Stabilized idle rpm, pilot holds

360

four fingers vertically . . Pic SELECTS INTERNAL

ELECTRICAL POWER,

SECURES POWER UNIT,

REMOVES ELECTRICALCABLE, SECURES ACCESS

PANEL (SEE ENGINE IDLE

CHECK CURVE FOR MINIMUMIDLE RPM)

Changed 1 May 1978

NAVAIR OI-40AVD-l.

MODIFIED PILOT-CONTROLLED START

After application of air / ignitor power,

1. Throttle ................................ OFF

2. Engine starter switch . . . . . . DEPRESS TO START

3. 5% rpm, throttle ......................... 1GN4. 15 % rpm, throttle ...................... IDLE

5. Stabilized idle rpm ........ (SEE ENGINE IDLECHECK CURVES FOR

MINIMUM IDLE RPM)

Note

No aircraft instrument except the tachometer andthe EGT indicator are operable during the start

cycle until the generator comes on the line.

6. Disconnect power.


NAVAIR 01-40AVO-18



ENGINE IDLE CHECK CURVE - J52-P-6A/B

UODEL: TA- 4F/TA- 4J

DATA AS OF: 9 S'pi."" ., 1966DATA BASIS: ContriQOrS 1.lm CUI....

62 m : : ; : q : + + + + ~ m

6°Bffffl

-20 0 20 40 60 100

AMBIENT AIR TEMPERATURE IDEGREES FAHRENHEITI

ENGINE I DLE CHECK CURVE - J52-P-SAiB

MODEL: TA-4FDATA AS OF. 9 S.piomber 1966

DATA BASIS: ConlraciOls Trim Co",.

62 r-7'r':""""''''''''''

54

52

·20 0 20 40 60 so 100 120

AMBIENT AIR TEMPERATURE IDEGREES FAHRENHEITlTA1B-49

Engine Idle Check Curves


NAVAIR 01-40AVO-18

ABNORMAL STARTS

HUNG START

When engine lights off normally, rpm stabilizes below idle(usually 40 to 45 percent), and EGT continues to rise towardmaximum temperature limits:

1. Throttle (FWD COCKPIT) . . . . . . . . . . . . . . . . . . OFF

2. Engine starte r . . . . . . . . . . . CONTINUE CRANKING

HOT START

Any start during which EGT momentarily exceeds 455°C isa hot start. I f lightoff occurs and starting EGT limits may be

exceeded, retard throttle toward OFF and monitor EGT. I fEGT limits cannot be maintained:

1. Throttle (FWD COCKPIT) . . . . . . . . . . . . . . . . . .OFF

2. Engine starte r . . . . . . . . . . . CONTINUE CRANKING

FALSE START

If engine lights off normally, but rpm does not increase toidle (50 to 60 percent) and EGT remains within limits, thestart is false. When false start occurs:


2. Engine starter . . . . . . . . . . . . . . . . . . . . . . . . . .PULL UP

WET START

When engine Iightoff is not obtained within 20 seconds of Ithrottle IGN, no EGT, and fuel vapor is emitting from the

tailpipe:


Do not actuate igniters.2. Engine starter . . . . . . . . . . . CONTINUE CRANKING

3. Proceed with dear engine procedure.

CLEARING ENGINE

To dear engine of excess fuel after abnormal starts:


2. Engine starter button . . . . . . . . . . . . . . . . . . . . DEPRESS

3. Allow starter to crank engine . . . . . . . . . . 15 to 20 SEC

4. Engine starter button . . . . . . . . . . . . . . . . . . . . PULL UP


NAVAIR 01-40AVO-18



NAVAIR 01-40AVO-18

POSTSTART CHECKLIST30. Drop tank pressure ...................... OFF

1. ICS ................................ CHECK 31. Pins ................. PLANE CAPTAIN PULL

2. Headknocker(s) ................. AS DESIRED AND STOW

3. Rain removal ........................ CHECK 32. AlB-3 .............................. ERECT

4. Canopy ........................ AS DESIRED

5. Master press-to-test...................... TEST

6. Anti-g suit vent ....................... CHECK

7. AFCS ............................... STBY

33. Oil quantity ......................... CHECK

34. Standby gyro........................

ERECT35. Altimeter ................ CHECKED AND SET

36. EPR .................................. SET

8. Drop tanks ........................... PRESS9. Fuel quantity ................ CHECK INT/EXT

10. Lox quantity ......................... NOTEII. Radar altimeter ..................... ON/SET PRETAKEOFF CHECKLIST12. Doppler ............................. STBY

13. Nav computer ......................... STBY I. Trim14. UHF .............................. T/ R & G Rudder ............................... 00

IS. IFF ................................. STBY Horizonta l Stabilizer . . . . . . . . . . . . . . . . . . . . 80 UP16. TACAN .............................. REC Aileron ................... SYMMETRICAL17. Auxiliary receiver ....................... ADF18. Compass controller ....................... SET19. Seat(s) ............................. CHECK20. AFCS (i f applicable) .............. CHECKS/OFF

2. Harness ............................ LOCKED3. Canopy .............. DOWN. LUGS LATCHED,

BOLT LOCKED, LIGHT OUT

4. Flaps ......................... SET AT 1/2

Perform with plane captain signals:5. Speedbrakes ........................ CLOSED

6. Armament ................... OFF/SAFE/SET

21. All flight controls ...................... FREE7. Spoilers .................... ARMED (FIELD)

22. Flaps ......................... FULL DOWNSpeedbrakes .......................... OPEN Prior to taking runway:Hook ............................... DOWN

Spoilers ............ ARM/CHECK OPERATION 8. Ejection selector ............ VERIFY POSITION

23. Flaps .............................. UP/l/2 9. AFCS ................................ OF F

Speedbrakes ........................ CLOSED 10. Emergency transfer .. . ,................. OFF

Hook .................................. UP I I. Nosewheel steering .................. NORMAL

Spoilers ........................... DEARM 12. Oil quantity ......................... CHECK

24. E)nergency transfer ...................... ON

25. Rudder trim ..................... CHECK/SET

13. Cabin temperature ................ 12 O'CLOCK

14. Anti-ice ........................... AS REQ

26. Horizontal stab trim and override ......... CHECK 15. Headknocker ............................ UP27. Horizontal stab .......................... SET 16. Controls ............................. FREE

28. Aileron .................. SET SYMMETRICAL

CHECK TRIM TAB29. Emergency transfer ..................... OF F

40 Changed 1 May 1978Changed 1 May 1978 41




Before takeoff:

17. Throttle ................... 85 PERCENT RPM

18. Fuel control ....................... MANUAL19. Fuel control light ........................ ON

20. Fuel flow/EPR ................ FLUCTUATION

21. RPM .................. DROP WITHIN LIMITS

22. Fuel control.......................

PRIMARY23. Fuel control light ....................... OFF

24. All caution lights ....................... OFF

25. Engine instruments ............... NORMAL

26. ICS .......................... AS REQUIRED

JET PENETRATIONS

I. Navaids ................. TUNED/IDENTIFIED

2. Compass ........................... ALIGNED

3. Weather field conditions .. . . . . . . . . . . . . CHECKED

4. Fuel ............................. CHECKED5. Air conditioning ......................... HOT

6. Anti-ice ....................... AS REQUIRED

7. Pressure altimeter . . . . . . . . . .. CHECKED AND SET

8. Radar altimeter ........................... SET

SECURING ENGINE

The following steps will be performed prior to shutdown:

1. Flaps .......................................UP

2. Speedbrakes ..................................IN

3. Spoilers ................................CLOSED

4. Deleted

5. Horizontal stabilizer trim ...................ZERO

6. Drop tank switch ...........................OFF

7. Radios and all electrical equipment . . . . . . . . . . . OFF

8. Gear pins, ordnance pins, and chocks . . . . . IN PLACE

9. Headknockers ............................DOWN

10. Check oil level by depressing OIL LOW indicator

switch if installed. If light comes on, oil level is below

80 percent and must be serviced.


NAVAIR 01.40A'ID·18

Note

For engine cooling purposes, whenever the enginehas been operated above approximately 85 percentfor a period exceeding one minute, the engine

should be operated at idle for a period of at least

three minutes, just prior to shutdown.

11. Clear air-conditioning system of condensation after

each flight by turning temperature control to full

ho t and depressing anti-g suit valve until warm

ai r is expelled.

12. Internal/external power switch . . . . . . . . . EXTERNAL

(Plane Captain)

Note

With A·4 AFC 338 over/under freC)uency protector

installed, step 12 need not be performed.

13. With engine stabilized at IDLE, throttle . . . . . . . . OFF

14. Oxygen ....................................OFF

15. Canopy .................... , . . . . . . . . . . . . . . OPEN

Do not commence opening canopy (ambient cock

pi t temp permitting) until engine is below 40 per

cent rpm. Above 40 percent, loose equipment lost

inadvertently from the cockpit area will likely beingested into the engine.

t 6. Canopy jettison initiator

safety pin( s) .................... INSTALLED

Changed 1 May 19 78 42A!(42B BlonlrJ



N A " A I ~ OI·40AVD.IB

SECTION IIISPECIAL PROCEDURES

TABLE OF CONTENTS

AFCS Preflight Checklist . . . . . . . . . . . . . . . . . . . .. . . . . .. 44

ASN·41 Preflight Checklist .. , . . . . . . . . . . . . . . . . . . . . . . 45

APN·153 Preflight Checklist . . . . . . . . . . . . . . . . . . . . . . . , 46

Operation of APG·53A (Airborne Tuning) . . . . . . . . . . . 46

Air Refueling Store . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

Time to EACjRAMP After Transfer . . . . . . . . . . . . . . . .. 50

Angle of Attack-Cruise Control ..... , . . . . . . . . . . . . . 51

MACH vs Temperature. . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

JATO Firing Delay . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53·54

JATO Takeoff Distance . . . . . . . . . . . . . . . . . . . . . . . . . . 55·56

Crosswind Component . . . . . . . . . . . . . . . . Inside Back Cover

43

NAVAl. OI-40AVD-18



AFCS PREFLIGHT CHECKLIST1. Turn AFCS power to STANDBY.

2. After 90 seconds place in position 1 on preflight panel.

a. Indicators should deflect upward.

b.Push right rudder pedal: yaw indicator swings down.

c. Engage STAB AUG: should hold.

d. Engage AFCS: should not hold.

*3. Place in position 2 for at least 30 seconds.

*a. Indicators should deflect upward.

*b. Engage AFCS: should hold.

*c. All indicators should null.

*d. Depress AP switch on stick grip, AFCS should nothold.

*e. Engage AFCSj move stick trim button to right.AFCS should not hold.

*f. Engage AFCSj move stick trim button to left. AFCSshould not hold.

*g. Engage AFCSj move stick fully right . AFCS shouldnot hold.

*h. Engage AFCSj move stick fully left. AFCS shouldnot hold.

*i. Engage AFCSj tur n TRIM switch on AFCS panelto EMERG position. AFCS should not hold.

*j. Engage AFCSj go to CSS. Move stick af t and trim

stabilizer nose up. AFCS should not hold.*k. Engage AFCSj move stick forward and trim sta-

bilizer nose up. AFCS should not hold.

1. Engage AFCS. Engage altitude hold: should hold.

m. Move stick inca CSS. Altitude hold should drop out.

n. Set preselect heading knob to that of ID-250. En

gage heading hold: should hold.

o. Decrease heading and note stick move to left.

p. Increase heading and note stick move to right.

*Indicates mandato ry check.

44 Changed 1 April 1974

NAVAIR OI-40AVD-IB

4. Place test switch in position N: AFCS and STAB

AUG disengage.

5. Place standby switch OFF.6. Recheck takeoff trim settings.

ASN·41 PREFLIGHT CHECKLIST nA·4F)

1. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

2. BDHI Switch . . . . . . . . . . . . . . . . . . . . . . NAV CMPTR

Check the following readings:

WIND SPEED . . . . . . . . . . . . . . . . . . . 223.6 -+-2.5 knots

WIND DIRECTION . . . . . . . . . . . . . 091 ±1.5 degrees

LATITUDE PRESENT POSITION . . . . . . . . . .South

integration

LONGITUDE PRESENT POSITION . . . . . . . . . . East

integrationBDHI . . . . . . . . . . . . . . . . . . . . . . . . . . Smooth change in

distance indication

BDHI NO.1 Pointer.·. . . . . . . . . . .\ Depends on present

position and destinationdata set in.

BDHI NO.2 Pointer . . . . . . . . . . . 30 ±1 degrees right

3. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY

4. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .D2

5. Latitude/Longitude Destination . . . .SET (Coordinates

of point of returnor present position)

6. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY

7. Latitude/Longitude Destination .. SET (Coordinates of

primary target)

8. Latitude/Longitude Present Position . . . . . . . . . . . . SET

(Coordinates of

present positi on)

9. Magnetic Variation . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

10. Wind Direction/Velocity . . . . . . . . . . . . . . . . . . . . . SET


NAVAIR 01-40AVD-18 NAVAIR 01-40AVD-IB



ANIAPN-153 PREFLIGHT CHECKLIST (TA-4F)

1. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . .TEST

NoteAllow equipment to warm up for approximately

5 minutes and check:Memory Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OutGroundspeed . . . . . . . . . . . . . . . . . . . . . . . . 121 ±5 knotsDrift Angle . . . . . . . . . . . . . . . . . . . . . . . . . 0 ±2 degrees

2. Function Switch . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY

OPERATION OF APG-53A (TA-4F)(AIRBORNE TUNING)

1. Mode switch .. , .STBY. Allow 3 minutes for warmup.

2. BRIL, STOR, RET knobs . . . . . . . . . . . . Fully clockwise

3. GAIN, DETAIL knobs. . . . . . .

Fully counterclockwise4. Range switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LONG

5. Terrain switch . . . . . . . . . . . . . . . . . . . . . . . . . .PROFILEANGLE OF ATTACK COMP switch . . . . . . . . . . .ON

6. Mode switch . . . . TC. Note that 1000·foot clearance lineintersects proper indices on face of scope.

7. In level flight at 3000 to 5000 feet, advance GAIN

until return covers width of scope and is approximately5 degrees wide (between any two horizontal scribed

lines On scope).

8. Advance DETAILto

narrow returnto

approximately1 degree.

9. Adjust BRIL and RET to suit pilot.Set is now tuned and will remain tuned when switched

to any plan mode of operation.

46

NoteWhen switching from TC to OFF, pause momen·tarily in SEARCH to allow antenna to change from

vertical to horizontal sweep and thus prevent jam·ming in center position.

AIR REFUELING STORE nA-4FJ

Limitations

1. Carriage . . . . . . . . . . . . . . . . . . . . 500 KIAS or 0.80 IMN

2. Un feathering (Normal Operation) . . . . . . . . 300 KIAS

3. Refueling Operation . . . . . . . . . 300 KIAS or 0.80 IMN

4. Drogue Retraction . . . . . . . . . . . . . . . . . . . . . .250 KIAS

5. Hose Jettison . . . . . . . . . . . . . . . . . . . . . . . . . . .250 KIAS

Malfunctions

1. Hose Jettison

a. Move hose jettison switch to JETTISON position.

b. Do not change position of hose jettison switch afterjettisoning hose and drogue.

2. Drogue and Coupling Losta. Move drogue position switch to RET.

b. Extend EMERGENCY GENERATOR.

c. Refueling Master switch OFF.

d. Select generator BYPASS and regain main generator.

NoteThe store may be dumped. Do not move RefuelingMaster switch to ON.

The above procedure is recommended to reduce the fire

hazard created by actuation of hose jettison. A secondaryprocedure is as follows:

a. Move drogue position switch to RET.

b. Operate hose jettison switch to JETTISON and leave

in this position until after engine shutdown.

3. Store Hydraulic/Electrical Failure

a. Ashore: Jettison hose and drogue only if dictated byother factors; i.e., arrested landing, etc.

b. Carrier: Jettison hose and drogue, if possible.

c. Dump or return fuel to aircraft tanks.

47

NAVAIR Ol-40AVD-1l NAVAIR 01-40AVD-18



TANKER SAFETY PRECAUTIONS (TA-4F)

1. Do not un feather turbine or extend drogue over popu

lated area or when other aircraft are close abeam or be-

hind.

2. Do not extend drogue if hydraulic leak has been ob-

served.

3. Do not extend drogue with any electrical failure.

4. Delay landing 10 minutes after dumping, i f possible.

S. Do not energize turbine after dumping fuel.

PRESTART (TA-4F)

1. Refueling master switch . . . . . . . . . . . . . . . . . . . . . . .OFF

2. Fuel counter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000

3. Drogue position switch . . . . . . . . . . . . . . . . . . . . . . .RET

4. Transfer switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

S. Hose jettison switch . . . . . . . . . . . . OFF (FORWARD)

6. Light switch . . . . . . . . . . . . . . . . . . . . . . . . . . (DAY) BRT

(NIGHT) DIM

7. Ship-tank switch . . . . . . , .. " . . . . . . . . . . . . . . . . . . . OFF

POSTSTART (TA-4F)

1. Ship-tank switch . . . . . . . . . . . . , . . . . . . . FROM STORE

2. Dump light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TESTNote

I f there is fuel in the store, the light should come

on. I f there is no fuel in the store, press PRESS-TO

TEST light to test bulb.

3. Ship-tank switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

PREHOOKUP (TA-4F)

1. Refueling master switch . . . . . . . . . . . . . . . . . . . . . . . .ON

48

2. Drogue position switch . . . . . . . . . . . . . . . . . . . . . . .EXT

3. Drogue position indicator ..................... EXT

HOOKUP AND TRANSFER (TA-4FJ

1. Drogue position indicator . . . . . . . " . . . . . . . . . . . . TRA

2. Transfer switch . . . . . . . . . . . . . . . . . . . . . . . . . . .TRANS

3. Fuel counter . . . . . . . . . . . . . . . (COUNTS GALLONS)

a. To transfer more than 300 gallons:ship-tank switch . . . . . . . . . . . . . . . . . . . . . TO STORE

(AFTER TRANSFERRING 50 GALLONS)

STOP TRANSFER AND DROGUE RETRACT (TA-4F)


After Disengagement:

2. Drogue position indicator . . . . . . . . . . . . . . . . . . . . .EX T

When receiver aircraft clear:

3. Drogue position switch . . . . . . . . . . . . . . . . . . . . . . .RET

After drogue retracted:

4. Refueling master switch " .. , . , . . . . . . . . . . . . . . . . OFF

PRELANDING (TA-4F)

1. Refueling master switch . . . . . . . . . . . . . . . . . . . . . .OFF*

2. Drogue position indicator . , . . . . . . . . . . . . . . . . . . . RET

3. Drogue position switch . . . . . . . . . . . . " . . . . . . . . .RET


5. Hose jettison switch . . . . . . . . . . . . OFF (FORWARD)

6. Ship-tank switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

IfcFuel dumping should always be done prior to any arrestedlanding either afloat or ashore.

49

NAVAIR OI-40AVD-18NAVAIR Ol-40AVD-IB



TA-4' TANKERMINIMUM N a IIMAININO .un. JUHanl

DATA AI 0 ', , MAY 1972

10 120 110 200 24G

TIME TO IACIIAMP·MINUTESTA1,",,7.'

Time to EACIRAMP Alter Transler- TA-4F

50 Cht'lnqecf 1 April 1974

ANGLE OF ATTACK-CRUISE CONTROL

In the event of failure of the airspeed system, the followingsample angle-of-attack indications can be used for climb,cruise, and descent.

ANGLE-OF-ATTACKCOCKPIT INDICATOR

CONDITION UNITS

Maximum rate of climb. . . . . . . . . 4.5 to 9.0

Maximum range descent or

maximum endurance at all

altitudes . . . . . . . . . . . . . . . . . . . . .

Cruise at 5000 feet . . . . . . . . . . . .

Cruise at 35,000 feet . . . . . . . . . . .

250-knot descent with

speedbrakes extended . . . . . . . . . .

10.5

6.6 to 7.0

7.7 to 9.0

7.0*

*Gross weight of 14,000 pounds. Add/subtract 0.35 unitsfor each increase/decrease of 1000 pounds gross weight.Valid for all configurations.

The above data are based on an aircraft with two 300-gaUonexternal tanks. For a dean aircraft these angle-of-attackindicator units should be decreased 1.0 units for the maximum endurance condition and 0.6 units for the cruise andrate-of-climb.

Note

When above speeds of 200 KIAS, an angle-of-attackerror of 0.5 unit is equal to an airspeed error of 25

KIAS or more.

51

NAVAIR 01-40AVD-1lNAVAIR 01-40AVD-18



I

INDICATED MACH NUMBER AT

TRUE AIRSPEED OF 450 AND 500 KNOTS

MODEL: TA-4F/TA-4J

ENGINE(S): J52·P·8A/J52·P·6A

DATA AS OF:

DATA BASIS: FLIGHT TEST (NAVY)

TEMPERATUREINDICATED

TEMPERATUREINDICATED

MACH NUMBER MACH NUMBER

°C OF 450 KNOTS 500 KNOTS °C of 450 KNOTS 500 KNOTS

- 2 0 -4 .0 .7236 .8037 13 55.4 .6823 .7561

- 1 9 -2 .2 .7222 .8021 14 57.2 .6811 .7548

-1 8 -.4 .7208 .8006 15 59.0 .6S00 .7535

-1 7 1.4 .7194 .7990 16 60.S .6788 .7522

- 1 6 3.2 .7180 .7975 17 62.6 .6776 .7509

- 1 5 5.0 .7166 .7959 18 64.4 .6765 .7496

- 1 4 6.8 .7152 .7944 19 66.2 .6753 .7483

- 1 3 8.6 .7139 .7929 20 68.0 .6742 .7471

-1 2 10.4 .7125 .7913 21 69.S .6730 .7458

-1 1 12.2 .7112 .7898 22 71.6 .6719 .7446

-10 14.0 .7098 .7883 23 73.4 .6707 .7433

-9 15.8 .70S5 .7869 24 75.2 .6696 .7421

-8 17.6 .7071 .7854 25 77.0 .6685 .7408

-7 19.4 .7058 .7839 26 78.8 .6674 .7396

-6 21.2 .7045 .7824 27 SO.6 .6662 .7383

-5 23.0 .7032 .7809 28 82.4 .6651 .7371

-4 24. ' .7019 .7795 29 84.2 .6640 .7359

-3 26.6 .7006 .7781 30 86.0 .6629 .7347

-2 28.4 .6993 .7767 31 87 .• .6618 .7335

-1 30.2 .6980 .7752 32 89.6 .6608 .7323

0 32.0 .6968 .7738 33 91.4 .6597 .7311

1 33.8 .6955 .7724 34 93.2 .6586 .7299

2 35.6 .6942 .7710 35 95.0 .6575 .72873 37.4 .6930 .7696 36 96.8 .6565 .7276

4 39.2 .6917 .7683 37 98.6 .6554 .7264

5 41.0 .6905 .7669 38 100.4 .6544 .7252

6 42.8 .6893 .7655 39 102.2 .6533 .7241

7 44.6 .6880 .7641 40 104.0 .6523 .7229

8 46.4 .6868 .7628 41 105.8 .6512 .7218

9 48.2 .6856 .7614 42 107.6 .6502 .7206

10 50.0 .6847 .7601 43 109.4 .6492 .7195

11 51.8 .6844 .7588 44 111.2 .6481 .7184

12 53.6 .6835 .7574 45 113.0 .6471 .7172

Mach vs Temperarure

52 rhanged 1 April 1974

JATO FIRING DELAY

HAL. FLAPS TWO JATO UNITS:

DATA AS 0 ., 1 MAY 1972DATA IASIS: FUGHT TEST (NAVY)

MODU, TA-4.ENGINE: J52. ' · I " ' .

170 .' •. ._,

; :·1· ,160 _. _' L ....-:

o I ) .

I

51

140

.. 130

! i i ! : ~ 120

5...110

100

, i ' I;::. ; ; . . . ~ ::. TAKIOFF AIISPEED

! .:...;..... . MAXIMUM TAKEOFF WEIGHT

14

1:;:: . MAY IE EXCEEDED. ifni TO

16 ; : : : : :: ;: . FIGUIE 11-9 FOI MAXIMUM

: S d ~ : : :T :1 : + 1 T I ~ ~ ~ O f . F :W:E1'GHT.2 4 ' ............. : .

I 12S'- . 2 : ' 7 . ~ . : ' : .; •I OIOSS WElG . .. ,t :I:.. : .' :I1-1000 'OUNII1__ ...._.._. __

I

...-2 0

~ " ' l ! : - I O :" . .... ::10( 0- a-iiiaiii- 10- . JEMPdATUlf 10\5 l IN ' - 60 ~ ~ i "Q 20- ! ' .. · · · t .......

30- :: : : . : t' : 10 "oxI!! U • • ....: 100 ! I 0(

:::- . " ' : : 120 ...

, : -I

06! z

~ " " I40

)oi!i:- 2 !

0( . . . . .

J-U"0zo.o

: : > = ~ = .,,'+2

0

FIlING DfLA Y - 1 00 0 FEEt

JATO Firing Delay CP-8AIBI

TA11·1I·'

53

NAVAIR 01-40AVD-18NAVA/R 01-40AVD.1I



110

..

'6 00Z..

150I

Cl...... 140...

=:c130

i

I120

110...

S4

JATO 'IRING DlLAYHALf fLAPS TWO JATO UNITS

MODIL. TA"'II DATA AI Of. 1 MAY 1972

DATA IASIS: fLIGHT TEST (NAVYIENGINf: JS2·'·6AII

JATO FIliNG DELAY - 1000 FEET

JATO Firing Delay IP·6AIB)

TAII·12·C

Changed 1 May 1976

JATO TAKEOff DISTANCEH A ~ F FLAPS TWO JATO UNm

MODllI fA.. , DATA AS Of. , MAT 1.72

170

4 5 • 7

TOTAL DISTANCE TO CUAR A SO fOOT OISTACLI-looo 'In TAII.13.'

JATO Takeoff Distance IP·8AIS}

Changed 15 November 1976 55

NAVAIR Ot-40AVD-tl

SECTION IV



JATO TAKEOfF DISTANCETWO JATO UNITS

0

0=d~ " " I

40

- 2

~ ! i 1 ~ C ..hIhg 0

.. Ao ..

"e I

JATO Takeoff Distance (P-6AI8J


TABLE OF CONTENTS

RefERENCE DATA

Sub;ect Page

Weight Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

Fuel System Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . " 59

Servicing Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

Pressure Fueling-Preferred Method . . . . . . . . . . . . . . . . 62

Pressure Fueling-Alternate Method . . . . . . . . . . . . . . . . 67

Pressure Fueling Air Refueling Store . . . . . . . . . . . . . . . .. 70

Gravity Fueling. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 72

Engine Exhaust Smoke Abatement SystemServicing (TA-4F) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

Engine Oil System Servicing . . . . . . . . . . . . . . . . . . . . . . .. 78

Constant-Speed Ddve (CSD) Servicing . . . . . . . . . . . '" 79

Hydraulic System Servicing . . . . . . . . . . . . . . . . . . . . . . . " 81

Util ity Hydraulic System Fill ing . . . . . . . . . . . . . . . . . . . .. 81

Flight Control Hydraulic System Fi lling . . . . . . . . . . . . . . 86

Brake Reservoir Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . 91

Rain Repellent Servicing . . . . . . . . . . . . . . . . . . . . . . . . . " 91

Liquid Oxygen System Servicing . . . . . . . . . . . . . . . . . . . . 95

Emergency Oxygen Bottle Servicing . . . . . . . . . . . . . . . .. 96External Power Application . . . . . . . . . . . . . . . . . . . . . . . . 100

Starting Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

Wheel Removal and Installation Procedures . . . . . . . . . . 103

Main Gear Wheel-Removal . . , . . . . . , . . . . . . . . . . . . . . 104

Main Gear Wheel-Installation . . . . . . . . . . . . . . . . . . . . 105

Main Gear and Nose Gear Tire Pressures . . . . . . . . . . . . . 106

57

NAVAIR 01-40AVD-1BNAVAIR 01-40AVD-1B



WEIGHT FACTORS (Pounds'

Total Operating Weight* (TA·4F) . . . . . . . . . . . . . **12,816

Total Operating Weight (TA.4J) . . . . . . . . . . . . . . . . 12,273

(Includes two pilots and equipment, engine oil, trappedfuel and oil, five pylons, guns, oxygen, two AERO ID

300-gallon fuel tanks, and armor plate.)

JP-4 fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6.S Ib/gal

}p·S fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6.8 lb/gal

JP-8 fuel ..... ........... .......... ... 6.7 lb/gall

One lS0.gallon drop tank . . . . . . . . . . . . . . . . . . . . . . 136

One 300.gallon drop tank

One 400·gallon drop tank

TER 7 rack

MER 7 rack

199

240

105

223

AERO 5A 1 launcher·adapter rack (TA.4F) . . . . . . . 99

PMBR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87

Air refueling store (300-gallon. empty) (TA·4F)... 72S

Starter pod (GTC-85, loaded) . . . . . . . . . . . . . . . . . . . 700

MK 76 bomb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 25

MK 106 bomb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

MK 104 shape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2000

20 MM ammunition (200 rounds) . . . . . . . . . . . . . . . . 142

*Weight based on BuNo. 155071, weighed Nov 1968

**Aircraft equipped with }52.P-6A engine, subtract 76

pounds.

For other weight factors, refer to A·4/TA·4 Taccical Manual(NAVAIR 01-40AV-IT).


GENERALThis section describes the minimum servicing information

the pilot should know. The TA-4F/TA-4J Maintenance

Instruction Manual (NAVAIR OI.40AVD.2.1) contains the:omplete description of all servicing procedures (See fig-ure 1).

FUEL SYSTEM SERVICING

The aircraft may be serviced by either the pressure fuelingmethod or the gravity fueling method. The pressure fuelingdcfueling receptacle valve permits single-point pressure fueling (or defueling) of the aircraft. Individual filler partsare provided for gravity fueling the aircraft.

fUEL CONTROL FUEL SELECTOR

The fuel grade selector on the engine fuel control shouldcorrespond to the grade of fuel being used. After JP-4 is introduced into the fuel system of the engine, the specific grav·ity switch on the fuel control will be set to JP.4. The setting

will not be returned to JP·5 until after the first flight duringwhich JP·5 has been used. When using a combined fuel loadof JP-4 and JP-5 on the JP-4 setting, the pilot must monitorEGT to ensure that full throttle operation remains within

the prescribed Umits. Use the JP-5 setting on the control whenIusing lP-8 fuel.

ADJUSTMENT (See figure 2.)

Open the left·hand engine access door and observe the fuelselector adjustment valve located on the upper aft end of

the fuel control. If the valve setting does not correspond tograde of fuel being added, adjust fuel control fuel selector asfollows:

1. Remove retaining nut that secures locking bracket toretaining stud on housing.

2. Remove locking bracket from stud.3. Invert locking bracket and insert over hexagon shaft.4. Using locking bracket as a wrench, rotate hexagon shaft

until pointer on outside of valve is aligned with indexfor grade of fuel being added.

5. Replace locking bracket over hexagon shaft so thatslotted end fits over retaining stud on housing.

6. Secure bracket to retaining stud with washer and nut.

7. Close left·hand engine access door.

Changed 1May 1978 59

NAVAIR 01-40AVD·1BNAVAIR OI-40AVD-IB



I

I

I

LIQUID OXYGEN 80TTlECAPACITY, )0 LitERSSPEC, Mll·O·21210

FUEL SPECIFICATIONS

APPROVED FUEL

ASHORE

JP-4 JP-5 JP·8

AFLOAT

JP-5

~ - - - - - - - - - - - - - - - - - - - - - - - - ~ - - - - - - - - - - - - ~ NOTE:

FUEL TANK CAPACITIES BASED ON

USABLE FUEL AND PRESSURE FUELING.

TANKS US GAL

FUSELAGE FUEL CELL 104

WING INTEGRAL FUEL TANK 560

EXTERNAL FUEL TANK, AERO lC 147

EXTERNAL FUEL TANK, AERO 10 295

AIR REFUELING STORE 295

EXTERNAL FUEL TANK, ATP-D1S 396

REMOVE eMERCENCYDXVCLN eOlTl [ FROMAIRCAAn PRIOR 10

SfRVICIHG,

\EUUG£NCV O)(VG£H80lTlt

I

FILL to 1800 PSI WITHGAS£OIJS OXYG!"SPEC, MIL-0·21210

IMP GAL

83.3

466.2

122.3

245.6

245.6

329.7

LITERS

369.8

2119.6

556.3

1116.5

1116.5

1498.8

tA18·tSC

N5118

Figure 1. Servicing Diagram


JP-5 FUEL POSITION

Figure 2. Fuel Control Fuel SeledorAdjustment

61

NAVAl. O\·40AVD·IBNAVAIR OI.40AVD·1B



I

PRESSURE FUELING

The preferred pressure fueling method requires the use ofexternal ac power. This method will be used at all times when

external ac power is available. I f external ac power is nOl

available, the alternate pressure fueling method will be used.

When the alternate pressure fueling method is used, the external fuel tanks must be gravity fueled.

PRESSURE FUELING - PREFERRED METHOD

The preferred pressure fueling method requires the use of

external ac power input and single·point fueling source. Perform the fueling operation in the following sequence.

WARNING I• Perform all fueling operations in a well·ventilated

area.

• Stop all maintenance on aircraft during fuelingoperations.

• Ensure adequate grounding of aircraft and fueling

equipment.

• Ensure that no aircraft radar is in operation within100 feet of fueling operation and that no electricalor electronic equipment is operating in the area.

• Ensure that adequate fire fighting equipment is in

the immediate area of fueling operation.

62

NoteAircraft must be on a level surface in a 4-degree

noseup attitude to ensure maximum capacity

fueling.

1. Ensure that WING FUEL DUMP /EMER TRANS

switch located on left hand console in both cockpits

are OFF.

2. Inspect fuel vent mast to ensure that it is not obstructed.

Changed 1 Aprif 1974

--f.ffp....r- - .. . w,

MANUAL FLOW IiVAWl ..

, " , f " , ' "

.. C"I"~ 1 ' t l l l - __""__________""" _ . , au. . . ....

OI' ... '

ANO NO FLOW

Q ' \ '

TAII-17

Figure 3. Aircraft Fueling

63

NAVAIR 01.40AVD·18 NAVAIR Ol.40AVO·1B



WARNING IFailure of air to exhaust through fuel vent mast

during pressure fueling by che preferred mechod

may result in rupture of wing integral fuel tank

and/or fuselage fuel cell and possible injury topersonnel.

3. If external fuel canks are to be fueled, remove caps.

4. Open aft fuselage lower access door.

Note

When air refueling store or centerline 400.gallon

fuel tank is installed on aircrafc, afc fuselage loweraccess door musc be removed to connecc pressurefueling nozzle co pressure fueling·defueling adapter

valve.

5. Remove cap from pressure fueling-defueling adapter

valve, and connect pressure fueling nozzle co pressurefueling-defueling adapccr valve. (See figure 3.)

Note

When the nozzle is connecced to che valve, the air

c r a f ~ is grounded automatically through che connection, and no further grounding of individualfuel tanks is necessary.

6. Ensure CHECK SWITCH on fueling panel is in FUEL

ING ON position.

7. Connecc external electrical ac power to aircraft. (Referto External Powcr Application.)

64

WARNING IProrer connection of external ac power cable plug

to alCcraft external power rcccptacle must be made.

Failure (0 insen plug completely into reccptaclecan result in presence of high voltage on aircraftmetal surfaces.

8. Place external ac power in EXTERNAL position.

9. Start pressure fueling equipment and open manual flowand no· flow valve on pressure fuel ing nozzle.

WARNING IRemoval of gravity filler caps while pressure fueling is being accomplished may result in injury to

personnel.

To prevent damage to aircraft fuel syscem, maximum fueling pressure must no t exceed 55 psi at any

time.

10. Immediately after pressure fueling has started, test thefuel vent system for proper functioning by holding thehand beneath fuel vent mast. (See figure 3.)

WARNING II f air is not exhausting from fuel vent mast, stop

pressure fueling immediately and investigate the

fuel vent system. Failure to comply may result indamage to equipment and injury to personnel.

11. During the initial stage of pressure fueling, performfunctional test of pressure fueling shutoff components

in sequential order given in steps 12 through 16.

12. Place and hold CHECK SWITCH in PRIMARY OFF

position. Fuel flow shall stop in 1 to 3 seconds.

I f fuel flow does not stop in 1 to 3 seconds, stop

fueling immediately and investigate cause.


NAVAIR OI-40AVD-1B NAVAIR 01-40AVD.'1



Note

Due to fuel flow through pilot lines of float valvesa 2-gpm maximum flow (registered on pressure fuelmeter) is permissible.

13. Return CHECK SWITCH to FUELING ON position

Fuel flow should start.14. Place CHECK SWITCH to SECONDARY OFF posi

tion. Fuel flow shall stop in 1 to 3 seconds.

15. Return CHECK SWITCH to FUELING ON position.Fuel flow should start.

16. Upon satisfactory completion of functional test, con

tinue pressure fueling of aircraft.

17. During pressure fueling, inspect for evidence of fuelleakage. Correct if required.

If a partial aircraft internal fuel load with full externaltanks is desired, proceed as follows and disregard steps

21 through 23.

18. Place and hold CHECK SWITCH at PRIMARY or

SECONDARY OFF position and place DROP TANK

FUELING switch to ON position. Fuel flow should

start into external tanks only.

19. When fuel flow stops, return CHECK SWITCH toFUELING position and return DROP TANK FUELING switch to OFF.

I f fuel flow does not shut off and overflows froman external fuel tank, stOP fueling immediately andinvest igate the cause as a float valve has not operated

properly.

20. When internal quantity reaches desired amount, dose

manual flow and no-flow valve and shut down pressurefueling equipment.

66

If a full fuel load is desired, >disregard steps 18 through20 and proceed as follows.

21. Place DROP TANK FUELING switch ON. Fuel flow

should commence to external tanks.

22. After fuel flow has stopped (cell and tanks full), checkfuel-delivered meter for indication of pressure fuelingsystem internal leakage. Maximum leakage must not

exceed 1 gpm.

23. Close manual flow and no·flow valve and shut downpressure fueling equipment.

24. Place external ac power switch in INTERNAL posi.tion.

25. Disconnect external ac power from aircraft.

26. Disconnect pressure fueling nozzle from pressure fuel·ing·defueling adapter valve and install cap.

27. Place DROP TANK FUELING switch to OFF position.

28. Close and secure aft fuselage lower access door if

applicable.

29. Replace external fuel tank caps if removed.

PRESSURE FUELING-ALTERNATE METHOD

The pressure fueling alternate method must be used to fuel

the aircraft when single-point fueling source is available,but external ac power is not. The external fuel tanks cannotbe fueled using the alternate method. Perform the alternatemethod fueling operation in the following sequence.I WARNING I

• Perform all fueling operations in a well-ventilated

area.• Stop all maintenance on aircraft during fueling

operations.

• Ensure adequate grounding of aircraft and fuelingequipment.

• Ensure that no aircraft radar is in operation within100 feet of fueling operation and that no electricalor electronic equipment is operating in the area.

• Ensure that adequate fire fighting equipment is inthe immediate area of fueling operation.

67

NAVAIR OI-40AVO-U NAVAIR 01·40AVD·18



Note

Aircraft must be on a level surface in a 4-degree

noseup attitude to ensure maximum capacity

fueling.

1. Remove gravity filler caps from the fuselage fuel cell

and the integral wing tank. Use any suitable means to

prevent entry of foreign material into openings.

WARNING IWing integral fuel tank and fuselage fuel cell grav

ity fuel filler caps must be removed prior to pressure fueling aircraft by the alternate method. As acelectrical powor is nOt available, a malfunction of

the fuel vent system or any shutoff valve could

result in rupture of the wing integral fuel tankand/or fuselage fuel cell with damage to the aircraft and/or injury to personnel.

2. Inspect fuel vent mast to ensure that it is not obstructed.


Note

When air refueling store or centerline 400-gal1on

fuel tank is installed, af t fuselage lower access door

must be removed to connect pressure fueling nozzle

to pressure fueling-defueling adapter valve.

4. Remove cap from pressure fueling·defueHng adapter

valve and connect pressure fueling nozzle to valve. (See

figure 3.)

Note

When the nozzle is connected to the valve, the air

craft is grounded automatically through the connection and no funher grounding of individual

fuel tanks is necessary.

68

To prevent damage to aircraft fuel system, maximum fueling pressure must not exceed 55 psi at

any time. One man shall be posted at manual flow

and no· flow valve to stop fuel flow immediately iffuel flow does not stop when fuel tanks are full.

5. Start pressure fuelillg e(luipment and open manual flow

and no-flow valve on pressure fueling nozzle.

6. During pressure fueling, inspect for evidence of fuelleakage. Correct if required.

7. After fuel flow has stopped (wing integral tank and

fuselage fuel cell full), check fuel delivered meter forindication of pressure fueling system internal leakage.

Maximum leakage must not exceed I gpm.

Note

If external fuel tanks are installed, the tanks mustbe fueled using the gravity method. (Refer to Grav.

ity Fueling.)

8. Close manual flow and no·flow val ve on fuel nozzle

and shut down pressure fueling e(luipment.

9. Disconnect pressure fueling noale from fueling.

dcfueling adapter valve and install valve cap.

10. Verify that DROP TANK FUELING switch is in the

OFF position.

J 1. Close and secure aft fuselage lower access door if

appl kable.

12. Install fuselage fuel cell gravity ftller cap and secureaccess cover.

13. Install wing integral fuel tank filler caps.

69

NAVAIR 01-40AVD-IBNAVAII 01-40AVD-lB



PRESSURE FUELING AIR REFUELING STORE

(TA-4F) (See figure 4.)

Note

The following procedures also apply to fuelingcenterline 400-gallon external fuel tanks.

WARNING I• Perform all fueling operations in a well-ventilated

area.

• Stop all maintenance on aircraft during fuelingoperations.

• Ensure adequate grounding of aircraft and fuelingequipment.

• Ensure that no aircraft radar is in operation within

100 feet of fueling operation and that no electricalor electronic equipment is operating in the area.

• Ensure that adequate fire fighting equipment is inthe immediate area of fueling operation.

Note

Aircraft must be in a 4-degree noseup attitude toensure maximum capacity fueling.

1. Remove pressure fueling access cover from air refuel

ing store and remove cap from fueling receptacle.

2.Connect pressure fueling nozzle

toair refueling storefueling receptacle.

3. Start pressure fueling equipment and open manual

flow and no-flow valve on fueling nozzle.

Note

Pressure fueling will stop automatically when airrefueling store is full.

4. When air refueling store is full, close manual flow andno-flow valve on fueling nozzle and shut down pressure fueling equipment.

70

- __ t TO FUELING

STATION OR

FIRE E X T I N G U I S H E R ~ MOBILE SERVICE

UNIT

TAIB-IS

Figure 4. Pressure Fueling Air Refueling Sf ore - TA·4F

71

NAVAIR OI.40AVD·18 NAVAIR 01·40AVD·18



5. Disconnect pressure fueling nozzle from air refuelingstore fueling receptacle.

6. Install cap on fueling receptacle.

7. Install and secure pressure fueling access cover on airrefueling store.

GRAVITY FUELING

Gravity fueling must be used when pressure fueling equip·ment is not available. It must also be used to fuel externaltanks when pressure fueling equipment is used without acpower.

WARNING I• Ground aircraft and fueling equipment during all

fueling operations.

• Stop all maintenance on aircraft during fueling.

• Ensure that adequate firefighting equipment isavailable in immediate area of fueling operations.

• Make certain that proper fuel is used for refueling.(See figure 1).

• Do not connect external electrical power to aircraftwhen gravity fueling.

• Do not start fueling or defueling operations within100 feet of aircraft operat ing radar equipment.

GRAVITY FUELING FUSELAGE FUEL CELL

(See figure 5.)

1. Open fuselage cell gravity filler access door; removecap from gravity filler port.

2. Insert nozzle grounding jack in grounding receptacleaf t and outboard of access door; insert refueling nozzlein gravity filler port.

3. Fill fuselage cell until fuel level is at bottom of gravityfiller port neck.

Stop fueling when fuel comes OUt of the vent line.

72

GROUNDING JACK

GROUNDING RECEPTACLE

REFUELING NOZZLE

FUSELAGE FUEL CELLACCESS DOOR

TAIB-19

Figure 5. Gravity Fueling Fuselage Fuel Cell

73

NAVAIR Ol.40AVD·1B NAVAIR Ol·40AVD·1B



4. Remove refueling nozzle from gravity filler pore; dis·connect nozzle grounding jack from grounding re

ceptacle.

5. Install gravity filler port cap and secure access door.

GRAVITY FUELING WING INTEGRALFUEL TANK

(See figure 6.)

74

1. Remove wing integral fuel tank filler cap.

2. Insert refueling nozzle grounding jack In grounding

receptacle on wing nose.

[ ~ ~ = : ] Do not drop fueling nozzle in wing tank filler port

becaues nozzle will damage lower surface of tank.Do not pull fueling hose over wing slats.

REFUELING NOZZLE

GROUNDING JACK

GROUNDING RECEPTACLE TA1S-20

Figure 6. Gravity Fueling Wing Integral Fuel Tank

3. Insert refueling nozzle in gravity filler pon. Hold re

fueling nozzle in one hand and support refueling hose

with other hand.

4. Fill wing fuel tank until fuel is at bottom of gravityfiller port neck.

5. Remove refueling nozzle from gravity filler pOrt; dis

connect grounding jack from receptacle.

6. Install wing fuel tank gravity filler port cap and locksecurely in place.

GRAVITY FUELING EXTERNAL FUEL TANK OR

AIR REFUELING STORE

(See figure 7.)

1. Remove tank or store filler cap.

2. Insert refueling nozzle ground jack in grounding

receptacle on left-hand side of external stores rack.

~ G R O U N D I N G RECEPTACLE

~ , ; - - . ; . . I - GROUND JACK

EXTERNAL STORES RACK

REFUELING NOZZLE

FILLER PORT CAP

TAlS-21

Figure 7. Gravity Fueling External Fuel Tank

or Air Refueling Store

75

NAVAIIt 01-40AVD·1B

Insert refueling nozzle into filler port. Hold refueling

NAVAII Ol.40AVD·11



3.

nozzle in one hand and support refueling hose withother hand.

4. Fill tank or store until fuel level is approximately 1 inchbelow filler port to allow for thermal expansion.

s. Remove refueling nozzle from filler port; disconnect

refueling nozzle grounding jack from receptacle.

6. Install tank or store filler cap.

ENGINE EXHAUST SMOKE ABATEMENT

SYSTEM SERVICING lTA-4F)

WARNING IThe smoke abatement additive (CI-2) used forservicing this system is toxic. Make certain that

Maintenance Safety Precautions are observed. (Refer to NAVAIR Ol-40AVD-2-1.)

(See figure 8.)


2. Remove dust cap from additive tank overflow ventcoupling and from coupling on hose attached to plasticoverflow bottle on cart. Attach overflow bottle hosecoupling to overflow vent coupling.

3. Remove dust cap from additive fill coupling on aircraftand from coupling on fill hose attached to back of cart.Connect coupling on fill hose to aircraft fill coupling.

4. Reset meter dial on front of cart to zero ( turn dial

counterclockwise) .

S. Actuate cart pump handle until additive overflows intoplastic bottle.

6. Disconnect vent and fill couplings, and replace dust

caps.

7. Close aft fuselage lower access door.

76

OVERFLOWVENT COUPLING

FILL HOSE

VIEW A

FILL COUPLING

FUEL

ADDITIVE TANK

OVERFLOW

BOTTLETAIB-22

Figure 8. Eng;ne Exhaust Smoke Abatement System-

Pressure Filling - TA·4F

NAVAl. OI·40AVD·IINAVAl. Ol.40AVD."



If deck or airfield temperatures lower than 28°P(-2.2°C) are anticipated, the smoke abatementadditive tank and associated tube assemblies mustbe drained to prevent freezing and possible rup·

ture of system components. (Refer to NAV AIROl·40AVD-2-1 for draining procedures.)

ENGINE OIL SYSTEM SERVICING

Servicing provisions arc accessible through the engine for·ward compartment lower access doors. The PON·5A pres·sure oiling unit is recommended for servicing the engineoil tank.

ENGINE OIL SYSTEM QUANTITY CHECK

Checking the engine oil system quantity shall be accom·plished prior to engine shutdown or within 30 minutes afterengine shutdown with external electrical power.

Note

When electrical power is applied to the aircraftseveral hours after shutdown, the oil quantity indiocator light will come on. The oil drains from theengine into the gearbox. Engine operation willpump the oil back to the tank. Engine must beturned up 75 percent or more for 8 minutes toestablish actual oil tank level.

1. Apply external electrical power to aircraft (figure 24).

2. Press MASTER PRESS·TO·TEST switch to ensureindicator lights are operative, and release switch.

3. If oil level warning light is self illuminated, system is

below 20 percent remaining level. This indicates danger.ously low oil state, and engine oil tank must be serviced.

78

4. The warning light comes on when pressed if the oil

level is below the 80 percent level. Service is required.

5. No light indicates a sufficient engine oil supply.

6. Remove external electrical power from aircraft.

ENGINE OIL SYSTEM PRESSURE FILLING(See figure 9.)

1. Remove oil fill and oil overflow dust caps.

2. Connect pressure oiling unit hose to fill connection.

3. Connect 3-foot hose with Roylyn 7776 o/4.inch(MS2447S·2) quick.disconnect fitting to overflow con·nection.

Note

Overflow hose should be not more than 3 feet in

length to prevent back pressure in bleed line.

4. Allow overflow hose to empty into open container.

S. Pump oil (MIL.L.23699) into tank until a con·tinuous stream of oil runs out overflow line.

CONSTANT ~ S P E E D DRIVE (CSD) SERVICING

The constant.speed drive (figure 10) is located on the forward end of the engine. The CSD is mounted on an adapterbolted to the engine pad and secured by a V·band coupling.The drive unit and components should be inspected daily.

Access to the CSD is through the engine forward compartment lower right . hand access door and the CSD outer andinner access doors. Servicing consists of inspecting for fluidlevel and adding fluid.

DAILY INSPECTION

The following inspection should be made daily:

1. Open engine forward compartment right. hand accessdoor and CSD outer and inner access doors.

79

NAVAIR OI·"OAVD.IB NAVAIR OI·"OAVD.IB



80

ENGINE OILTANK

FILL OR OVERFLOWCONNECTION

~ y ' Q U I C K ~ O I S C O N N E C T FITTING

. ------

LOWER ACCESS DOOR

I OVERFLOW HOSE

~ E N G I N E FORWARDCOMPARTMENT

F I L L H O S E ~ OPEN CONTAINER

PRESSURE OILING UNIT

% ~ ,

T A I B ~ 2 3 - A figure 9. Engine Oil System Pressure filling


2. Using flashlight and inspection mirror, inspect CSD

for signs of fluid leakage.

3. Inspect fluid level on sight gage.

FILLING

(See figure 10.)

1. Open engine forward compartment right-hand accessdoor and CSD outer· and inner-doors.

2. Remove lockwire and filler plug located at top righthand side of pump.

[ : ~ ~ I ~ . . : J Use only MIL-S·81087A, Type I fluid. Mixing orthe use of other than an approved fluid willcause CSD failure.

3. Add fluid (MIL·S-81087 A, Type I) until fluid levelis at FULL mark on sight gage.

Note

The capacity of the CSD is 1 quart.

4. Replace filler plug and secure with lockwire.

5. Close access doors.

HYDRAULIC SYSTEM SERVICING

The utility hydraulic system and the flight control hydraulicsystem are serviced separately.

UTILITY HYDRAULIC SYSTEM FILLING

(See figure 11.)

1. Open engine forward compartment access doors andutility hydraulic reservoir access door.


NAVAIR 01·40AVD·1INAVAIR OI·40AVD-1I



82

( ~ t ! FILL ~ ~ , ' " - - ' ..t'lffllRrl

LINE m I I I ' " - - - -DRAIN PORT

MAGNETIC CHIP

DETECTOR

CONSTANT SPEED DRIVEINNER ACCESS

Figure 10. Constant-Speed Drive Filling

MANUAL BLEED

VALVE

»

UTILITY HYDRAULIC

RESERVOIR

\PORTABLEHYDRAULIC

TESTSTANO

TA1B-25

Figure 11. Utility Hydraulic System Filling

83

NAVAl. OI-40AVD-1I

2. Remove dust caps and connect source of hydraulic

NAVAl. OI-40AVD-1I



84

fluid to FILL quick.disconnect on right.hand side of

engine compartment. (See figure 12.)

3. Remove utility hydraulic bleed line from retainingdips; pass free end of line through utility hydraulicreservoir access door and place end in suitable con·

tainer on wing to receive any possible overflow offluid when bleeding.

4. Fill reservoir until piston registers FULL on sightgage. (Gage is viewed through utility hydraulic reser·voir access door.) (See figure 13.)

Do not allow pressure applied to FILL port to ex·

ceed 65 psi.

Figure J2. Utility Hydraulic Quick·Disconnect

(OUlBDI

SIGHT GAGEPLATE

STA Y200

\

t"'"""\

«0 0 n 020-0 00(J 0 0 0 UTILITY

HYDRAULICC RESERVOIR

o nVIEW LOOKING AFT

TAIB-27

Figure J3. Utility Hydraulic Reservoir Sight Gage

85

NAVAl. 01·40AVD.1&

5. Depress manual bleed valve until sight gage is free of

NAVAll OI.40AVD.11



air bubbles. (See figure 14.)

6. Disconnect external supply source when reservoir hasbeen filled and bled.

7. Install dust cap on FILL quick-disconnect.

8. Install overflow line in retaining dips.

9. Close engine forward compartment access doors andutility hydraulic reservoir access door.

FLIGHT CONTROL HYDRAULIC SYSTEM fiLLING

(See figure 15.)

86

1. Open engine control access door and flight control hy-

draulic reservoir access door.

Figure 14. Utility Hydraulic Manual Bleed ValveFigure J 5. Flight Control Hydraulic Sysfem Filling

87

NAVAIR Ol-40AVO-18

2. Connect source of hydraulic fluid supply to FILL

NAVAIR 01·40AVD.18



quick-disconnect. (Figure 16.)

3. Remove flight control hydraulic bleed line from retaining clip, pass free end of line through flight controlhydraulic reservoir access door, and place free end insuitable container on wing to receive any possible

overflow of fluid when bleeding. (See figure 17.)

4. Fill reservoir until piston registers full on sight gage.(Gage is viewed through flight control hydraulic reservoir access door.) (See figure 18.)

WARNING IDo not allow pressure applied to FILL pore to ex-

ceed 100 psi.

S. Depress manual bleed valve until sight gage is free of

air bubbles.

J

J

.)

J

\ II STA Y262

FLIGHT CONTROL

HYDRAULIC FILL LINE TA18-30

Figure J6. Flighl Conlrol Hydrauli c Quick-Disconnect Panel


FLIGHT CONTROL

HYDRAULIC RESERVOIR

ACCESS DOOR

)

MANUALBLEED VALVE

/

"..j

TA18-31

Figure 17. Flight Control Hydraulic Manual Bleed Valve

FLIGHT CONTROL

HYDRAULICRESERVOIRACCESS ~ A . , __

TAIB-32

Figure 18. Flight Control Hydraulic Reservoir Sight Gage

89

NAVAl. 01.40AVD·llNAVAIR 01·40AVD.1B



RESERVOIR DIAGRAM

HYDRAULIC FLUID

MIL·H·5606

US IMPLITERS

QTS QTS

OIL LEVEL WHEN FULL 1.04 0.86 0.983

Figure J9. Broke Reservoir Servicing


6. Disconnect external supply source when reservoir has

been filled and bled.

7. Install dust cap.

8. Install bleed line in retaining clamps; secure enginefuel control and flight control hydraulic reservoir

access door.

I

Changed 1 April 1974 90A/(90B Blank!

NAVAIR 01-40AVO-18



BRAKE RESERVOIR SERVICING

(See figure 19_)

1. Remove brake reservoir fairing from canopy hingearea.

2. Remove filler plug from brake reservoir.

3. Insert filler nozzle of hydraulic servicing tank intoreservoir filler port.I 4. FiJI reservoir with hydraulic fluid (MIL-H-83282 orMIL-H-5606) until gage indicates full.

Note

When sight gage indicates reservoir is full, do

not add more fluid. I f reservoir is filled to levelof port, excess fluid will be vented overboardduring Right maneuvers.

5. Install reservoir filler plug.

Note

Clean any spilled hydraulic fluid by wiping areawith cloth moistened in naphtha.

6. Check brakes and bleed if necessary. (Refer to Maintenance Instruction Man ual, NAV AIR 01-40AYD·

2-2.2)

Note

I f brakes are bled, service reservoir as necessary.

7. Install brake reservoir fairing.

RAIN REPELLENT SYSTEM SERVICING

Servicing the rain repellent system consists of removal and.replacement of the fluid container with a filled and chargedcontainer. A visual inspection of the system gage must bemade during postflight inspection. I f the gage indicateshalf full or less, the container should be replaced. Visualaccess to the system gage is through the APX·64 (V) coderaccess door.


NAVAl. 01-040AVD-l1NAVAllt 01-40AVD-IB



TA1B-34

Figure 20. Rain Repellent System Service

92

REMOVAL AND REPLACEMENT OF

FLUID CONTAINER

WARNINGI

Make certain that aircraft ground handling safetyequipment, referred to in NAVAIR OI-40AVD-2-1,is installed and that no electrical power is connectedto the aircraft while servicing the rain repellent

system. Failure to comply may result in injury to

personnel.

See figure 20.

1. Open nose section of aircraft.

2.Loosen thumbscrew on clamp that holds container insupport assembly.

3. Unscrew container from manifold.

Note

Some loss of fluid may occur during step 3 becauseof the residual pressure and fluid in the container.Catch residual fluid with a doth.

4. Place new seal (MS2877S-S) on full fluid container.

5. Screw container into manifold and secure withlockwire (MS20995N32).

Note

Some loss of pressure and fluid will occur. Removefluid residue with cloth.

6. Tighten thumhscrew on damp that holds container insuppott bracket.

7. Inspect area for cleanliness.

S. Close nose section. Ensure that nose section is secure.

93

NAVAIR OI·40AVD·la

SERVICING RAIN REPELLENT FLUID CONTAINER

NAVAIR OI-40AVD·1B

8. Unscrew container from manifold.



Servicing the rain repellent fl uid conta iner consists of refill

ing and recharging the container. Before servicing the con

tainer, secure a portable manifold assembly identical to theaircraft installation with the exception that the check valveis reversed.

1. Place container on work table with check valve up.

2. Bleed off dry nitrogen by depressing check valve.

3. Cut lockwire and unscrew check valve from neck of

container. Empty remaining fluid from container intoa measuring bottle.

4. Fill measuring bottle with 425±25 milliliters of rainrepellent fluid (MIL-R-81261) and empty fluid intorain repellent container.

Note

Until the rain repellent fluid is available throughnormal supply channels, it is possible to mix locally.The following mixture produces approximately 5

gallons of rain repellent fluid.

10 percent (12.8 fl. oz.) Foster D. Snell Co.,Rain Repellent Fluid Chemists and Engineers,Solu tion 2911L·66 New York City,

New York 10009

0.5 percent (0.64 fl. oz.) Armour IndustrialWetting Agent Chemicals,ARQUAD 2C-75 Chicago, Illinois 60609

89.S percent (114.56 fl.

oz.) Freon·TF

E. I. Dupont DeNemours

and Co. Inc.,

Wilmington, Delaware 19805

5. Replace check valve and secure to neck of containerwith lockwire (MS20995N32).

6. Screw container into portable manifold assembly.

7. Attach hose from dry nitrogen supply to container andcharge container to 75 to 100 psi.

94

9. Cover container check valve with suitable protectivecap to protect against dust and accidental depressuriza·tion of container.

Note

Until container is used, store in dry storage areawith tag that gives servicing information.

lIaUID OXYGEN SYSTEM SERVICING

Servicing the lO·liter liquid oxygen system (figure 23) is

accomplished by means of a portable external source. Liquidoxygen from an insulated servicing trailer is transferredunder pressure to the aircraft system. Because of the natureof liquid oxygen no external pressure source is required, as

evaporat ion builds up sufficient pressure within the servicingtrailer to complete the operation.

FilliNG CONVERTER1. Make certain oxygen switch in cockpit is in OFF

position.

2. Open liquid oxygen compartment access door.

3. Remove filler valve cap from filler valve.

4. Purge filler hose on servicing trailer until oxygen flowsin steady, uninterrupted stream.

5. Immediately connect filler hose to converter filler valveand commence filling.

Note

Any prolonged delay in connecting filler hose mayallow liquid oxygen in hose to change to gaseousoxygen. Pressure in servicing trailer should be be

tween 45 to 50 psi.

6. When liquid oxygen flows from overflow vent port insteady stream, close fill drain valve on servicing trailer;disconnect filler hose from filler valve which will automatically return converter to BUILDUP position.

95

NAVAIR OI-40AVD-\BNAVAIR Ol·40AVD.1I



WARNING IWarn all personnel working on aircraft and inarea to stay clear of liquid oxygen overflow. (Seefigure 21.)

NoteI f the converter filler valve freezes during filling,remove filler hose and install filler valve cap. Checkfiller valve after approximately 10 minutes.

7. Relieve pressure in servicing trailer filler hose by en-

gaging filler nozzle in purging device on trailer.

8. Install dust cap on filler valve.

NotePrior to installing fifter valve dust cap, inspect cap

closely for evidence of water. If water or moistureis noted; dry thoroughly with compressed air be-cause water in cap may freeze in filler valve.

9. Install dust cap on filler hose nozzle.

10. Secure liquid oxygen compartment door.

VENT OUTLET;STA Y74STA Y136STA Y370

LEGEND

LIQUID OXYGEN

GASEOUS MIXED WITHLIQUID OXYGEN

WARNING IAREAS SHOWN ARE

HAZARDOUS TOPERSONNEL WHENCONVERTER OVERFLOWSDURING FILLINGS.

TAIB-35

Figure 2 J. Liquid Oxygen Handling Precaullons

NAVAIR OI.40AVD.ll



I

STA Y357

CONVERTERRETAINER

OXYGENFILLER LINE

LIQUID OXYGEN WINGNUTCOMPARTMENT FILLER VALVE

ASSEMBLY

IO'r-__- - - - - - - - - - - - - , ~ 8 N O M I " " ~ V A ~ U E n l = = = = = = = = = = = = : : ~ z.FALLOWAaLE lANGE =

• ~ U I O O X Y G E N z _ W c ~ : ! 2 ~ ! · M ~ · · T l O .

i

2 128

WEIGHT EMPTY" ,"OX II La

BIZ16Z024

POUNOS UQUID OXYGEN

12 16 20 2.

IIOU.S

SERVICING TRAILER VALVES

VALVE IDENTIFICATION FUNCTIONS

LETTER COLOR VALVE NAME FILLING PRESSURE TRANSFER VACUUMBUILDUP PUMPING

A YEl.LOW VACUUM Cl.OSED Cl.OSED Cl.OSED OPEN

B BLACKCAPACITY

OPEN OPEN OPEN OPENGAGE

C Bl.UE FILL·DRAIN OPEN CLOSED OPEN CLOSED

D WHITE PRESSURE CLOSED OPEN CLOSEo* CLOSEDBUILDUP

E RED VENT OPEN CLOSED CLOSED OPEN

*WHEN PRESSURE FALLS BELOW TRANSFER PRESSURE,

OPEN VALVE DUNTIL DESIRED PRESSURE IS OBTAINED.

LIQUIDSTORAGE

CLOSED

OPEN

CLOSED

CLOSED

OPEN

TA1B-37

Figure 23. Liquid Oxygen System Servicing

NAVAIR OI-40AVD·18

EXTERNAL POWER APPLICATION

Two methods of applying external ac electrical power to

NAVAIR 01.40AVD.18

STARTING REQUIREMENTS



the aircraft are available. The primary or standard methodutilizes an ac mobile electric power plant (NC-5 or equivalent) (figure 24): The second method enables a: groundcrewman to apply ac power, dc power, and starter airthrough the engine starter access door, utilizing the air

craft ground start disconnect cable. This method will supply electrical power only to the START/ABORT switchand engine ignition system.

RECEPTACLE GUARD

(OPEN POSITION)

POWER PLANTCABLE PLUG

TAIB-38

Figure 24. External Power Application

Changed 1 May 1976

A high.pressure air supply to the air turbine starter (installed in the aircraft) and external electrical power arerequired for starting. The following are approved startingequipment.

AIR STARTER UNITS

GTC-8S

MA·IE

USN

*WELLS Air Start System

ELECTRICAL POWER UNITS

USN

NC·S

NC-6

NC-6A

NC-7

NC-8

NC·lO

NC·12

USAF

B·IO

B·lOA

B·IOB

MD'3

*Set to low pressure ratio.

USAF

MA-I

MA·IA

MA-ITA

MA-2

MD-IA

MD-2A

MD-3B

RCAF

CAN·C

NAVAIII 01.40AVD-1I

COMBINATION ELECTRICAL! AIR STARTER UNITS

NAVAl. 01-40AVD-1I

WHEEL REMOVAL AND INSTALLATION



USN

*RCPP/RCPT/NCPP.105

USAF

MA-2MP

MA-3MP

M32A-60

*MD-3A

A source of 115·vac power is required for ignition. Twenty·eight-vdc power is required if a cockpit controlled start isdesired. Ac power can be provided through the externalpower receptacle (figure 24) or through the aircraft groundstart disconnect. Dc power (for cockpit controlled start)can be supplied only through the aircraft ground startdisconnect.

NoteIf 28-vdc power is not available, a ground startmust be accomplished.

*Set to low pressure ratio.

PROCEDURES

1. Removal (figure 25.)

a. Install landing gear lockpins.

b. Chock wheel/tire not to be changed.

c. Place hydraulic axle jack (cap.-5 tons) in positionbelow jack pad on gear strut to be jacked.

d. Operate jack slowly until tire is no more than 2inches from deck.

e. Remove valve cap and deflate tire, then removevalve core.

f. At wheel axle, remove snap ring and dust cap.

g. Remove axle nut retaining spring.

h. Remove axle nut using proper nut wrench.

NoteHave man in cockpit depress and hold correspond·ing brake pedal while removing and installingwheel. This will eliminate need for realigning keysin wheel with keyways in brake disc.

i. Remove washer and slide wheel/tire from axle.

j. Inspect axle and brake assembly for damage, wear,and security.

k. Make certain collar is flush against axle flange be·fore installing wheel/tire.

2.Installation (figure 26.)a. Make sure axle is dean and wheel bearings are prop

erly lubricated (MIL·G-81322).

b. Install wheel/tire assembly on axle while brake isapplied, engaging keys on inner wheel with key·ways in disc(s).

c. Install washer and axle nut; finger tight.

d. Tighten axle nut to 50 foot-pounds torque, usingspecial axle nut wrench (hex. 2Yz in. across flats)and torque wrench.

NAVAIR 01.40AVD·\B

NAVAIR 01.40AVD·18



Figure 25. Main Gear Wheel - Removal Figure 26. Main Gear Wheel - Insfallalion

104

NAVAIR Ol·40AVD·18NAVAIR Ol·40AVD·II

e. Turn wheel one or more revolutions in normalroll direction.



MAIN LANDING

GEAR STRUT

MAIN WHEEL TIRE

INfLATION PRESSURES

400

380

in 3&0Q.

• 340

zS320

:boo

l8 0....

l ~ O 240

220

200

10 12 14 16 18 20 22 24

AIRCRAFT WEIGHT· 1000 LBS.

PLATE NO 9825829·1

MAIN LANDING GEAR WHEEL

TIRE INFLATION PRESSURECHART

NOSE LANDINGGEAR STRUT

, RIGHT -HAND MAIN

I LANDING GEAR DOOR

\1A ( LEFT ·HAND DOOR

I " TYPICAL>

NOTE

THE ONLY MAIN TIRE SIZECOMPATIBLE WITH THE A-4AIRCRAFT IS 24x5.5.SER-VICE TIRE WITH DRY NITRO

GEN ONLY.

o

TAIB-42-B

Figure 27 . Main Gear an d Nose Gear TIre Pressures

106 Changed 1 Mav 1976

f. Back off axle nut until free.

g. Retighten nut until first lineup of locking holesand slots in axle applying 2 to 15 foot. pounds,torque.

h. Install axle nut retaining spring with earlocks ineither 5/11 o'clock or 7/1 o'clock position. 1m·

proper installation could result in loss of wheel.

I. Install dust cover and snapring.

j. Inflate tire to proper pressure as shown on chartplate attached to landing gear door (figure 27).

Note

The only main tire size compatible with A·4 air-craft is 24x5.5. Service tire with dry nitrogenonly.

k. Lower aircraft slowly.

1. Remove ground handling safety lockpins andlor

wheel chocks.

Note

One man can remove and install the wheel as·sembly but care must be taken to ensure that thebrake discs do not fall and damage the axle whenthe wheel is removed.

Changed 1 April 1974 107/1108 Blankl

NAVAIR OI.40AVD·IB

EMERGENCY PROCEDURES INDEX

AIRSTART ........... 12A HYDRAULIC FAILURE . . . . . . 17



ASYMMETRIC WING STATION

LOAD LIMITATION

NOMOGRAM .......... 26BBAILOUT - LAST RESORT

ONLY ...............•. 15

BINGO ENDURANCE (P·6At .. . 3BINGO ENDURANCE

(P·SA/S) ............... 2A

BINGO RANGE (P·6At ........ 2BINGO RAIIIGE (P·8A/B) . . . . . . 1BINGO RANGE·GEAR

DOWN (P·SA) ....... . 5BINGO RANGE·GEAR

DOWN (P.SA/S) ......•... 4DROP TANK TRANSFER

FAILURE ........•.... 268DITCHING·LAST RESORT

(EJECT IF FEASIBLE! •••. 15EJECTION ................. 13

CONTROLLED ..•........ 13

I M M E D ~ A T E . . . . . . . . . . . . . . 13

ELECTRICAL ...........•.. 23

DC CONVERTERFAILURE . • • . • . . . . • . . 24A

MAIN GENERATOR

FAILURE ............. 23EMERGENCY GENERATOR.

EQUIPMENT AVAtLABLE

TO PILOT ON • . • . . . . . • . 24ENGINE FAILURE .......... 11

ENGINE FUEL CONTROL • • • . 11

MALFUNCTION . . . • • . • . . . 11

THROTTLE LINKAGE

FAILURE ............. 11

ENGINE OIL .............. 26A

ABNORMAL OILPRESSURE •....••.... 26A

OIL LOW LIGHT ON • . . . • • 26AEOUIPMENT AVAILABLE TO

PILOT ON EMERGENCYGENERATOR .......... 24

FIELD ARRESTMENT

DATA ....••.....•..•.. 18FIRE . . . . • . • • . . . . • • • . • . . • • . 9

ELECTRICAL FIRE

liN FLIGHT) .•.•.....•.. 9ENGINE FIRE ON FLIGHT

WARNING LIGHT ONLY) •• 9

ENGINE FIRE liN FLIGHTWITH OTHER

INDICATIONS . • • . . • . . . . 9ENGINE FIRE (STARTING) .• 9WING FIRE (IN FLIGHT) • • . . 9

FLAMEOUT ............... 11

FLAMEOUT APPROACH • • • • . . 6FLAPS. LANDING

WiTHOUT •.......•...•. 21

FUEL SYSTEM • . . . . • . . . • • . • 25DROP TANK TRANSFER

FAILURE ............. 26

FUEL TRANSFER PUMPFAILURE . . . • . • . . • . • . . . 26

INADVERTENT FUELDUMPiNG ............. 26

QUANTITY INDICATOR

FAILURE ...... 25

Changed 1May 1978

LANDING DISTANCE ....... 20

LANDING GEAR .......... 18AEMERGENCY

EXTENSION .......... lSAUNSAFE MAIN GEAR DOWN

INDICATION ......... ISSUNSAFE MAIN GEAR UP

INDICATIOn ......... lSA

UNSAFE NOSE GEAR DOWNINDICATION ......•.. 18C

UNSAFE NOSE GEAR UPINDICATION ......... lB C

LANDING GEAR MALFUNCTIONLANDING GUIDE . . . . . , . 19

LIMITATIONS ............ 24CLOW ALTITUDE AIRSTART .. 11

LOSS OF THRUSTI

FLAMEOUT 11

MAXIMUM rAKEOFF WEIGHT

(P·SA/Bt ............... 16MAXIMUM"ToAKEOFF WEIGHT

(p·BA/Bt ...........••. 12FPRECAUTIONARY

APPROACH .............. 7SLATS. LANDING WITH

STUCK .......•....•.. 21

SMOKE ELIMINATION ...... 13

SPOILERS . . . . . " .......... 21

DEPLOYED DURINGFLIGHT ............... 21

STUCK ON LANDINGROLL .. . . . . . . 21

STUCK THROTTLE APPROACH(POWER FOR LEVEL

FLIGHT) ................ BTAKEOFF DISTANCE

(P·6A/B) ..........•••.. 12

TAKEOFF DISTANCE(P-8A/St . • • • . . . . . • . . • . . 10

TAKEOFF PRESSURE/FUELCONTROL CHARTS(P·6A/BAt .....•......... C

TAKEOFF PRESSURE/FUELCONTROL CHARTS(P·SB) •................. ()

TAKEOFF REFUSAL SPEED(P-6A/Bt .............. 120

TAKEOFF REFUSAL SPEED

(P-8A/SI .....••....... 129TRIM .....•..............• 22

AILERON OR RUDDER TRIMRUNAWAY ...•........ 23

LANDING WITH INSUFFICIENTNOSEUP TRIM . . . • • . . . • 23

LANDING WITH RUNAWAYNOSEUP TRIM . . . . . • • . . 23

RUNAWAY NOSEDOWNTRIM DURING

TAKEOFF ............. 22RUNAWAY NOSEUP

TRIM DURING

TAKEOFF ....•........ 22RUNAWAY STABILIZER TRIM

DURING FLIGHT . . . • . " 22UNDERWA TER ESCAPE • . . . • 17



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