a4 natops pocketchecklist
TRANSCRIPT
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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
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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
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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
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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
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..""" '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
IF YOU ARE AT If YOU ARE AT
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
AIRCRAFT DRAG INDEX - 61
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!
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AIRCRAFT DRAG INDEX - 60
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:)
...
IF YOU ARE AT If YOU ARE AT
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
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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
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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
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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.•
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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
Changed 1 May 1978 11
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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
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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
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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
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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""" ...
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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
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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.
Changed 1 April 1974
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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)
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, ",' 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.
Changed 1 May 1978 19
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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.
Changed 1 May 1978 21
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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
22 Changed 1 May 1978
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
1. EMER GEN handle • PULL
• 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
3. EMER GEN handle • PULL
• EMER GEN bypass switch • NORMAL
Changed 1 May 1978 23
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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
24 Changed 1 May 1978
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
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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
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"-'"'"~ 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
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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
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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
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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
NAVAIR OI·40AVD·16
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
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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
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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
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NAVAIR OI·40AVD·18
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
34 Changed 1 May 1978
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
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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
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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
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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.
Changed 1 May 1978 37
NAVAIR 01-40AVO-18
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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
38 Changed 1 May 1978
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:
1. Throttle (FWD COCKPIT) . . . . . . . . . . . . . . . . . . OFF
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:
1. Throttle (FWD COCKPIT) . . . . . . . . . . . . . . . . . . OFF
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:
1. Throttle (FWD COCKPIT) . . . . . . . . . . . . . . . . . . OFF
2. Engine starter button . . . . . . . . . . . . . . . . . . . . DEPRESS
3. Allow starter to crank engine . . . . . . . . . . 15 to 20 SEC
4. Engine starter button . . . . . . . . . . . . . . . . . . . . PULL UP
Changed 1 May 1978 39
NAVAIR 01-40AVO-18
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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
NAVAIR OI·40AVD·18
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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.
42 Changed 1 May 1978
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
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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
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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
Changed 1 April 1974 45
NAVAIR 01-40AVD-18 NAVAIR 01-40AVD-IB
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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
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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)
1. Transfer switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF
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
4. Transfer switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF
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.
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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.
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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·'
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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
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JATO TAKEOfF DISTANCETWO JATO UNITS
0
0=d~ " " I
40
- 2
~ ! i 1 ~ C ..hIhg 0
.. Ao ..
"e I
JATO Takeoff Distance (P-6AI8J
56 Changed 1 May 1976
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
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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).
58 Changed 1 May 1978
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
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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
60 Changed 1 May 1978
JP-5 FUEL POSITION
Figure 2. Fuel Control Fuel SeledorAdjustment
61
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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
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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.
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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.
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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.
3. Open aft fuselage lower access door.
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.
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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
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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
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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
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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.)
1. Open aft fuselage lower access door.
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."
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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.
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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
Changed 1 April 1974
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.
Changed 1 May 1976 81
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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
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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
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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
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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
88 Changed 1 May 1978
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
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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
90 Changed 11 May 1976
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!
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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.
Changed 1 May 1978 91
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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.
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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.
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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
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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
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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
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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
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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.
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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
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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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