Section XI
NAVAlR 01 · 40AVM· l
NAVAi R
Ol -4 0AVM-l
SECTION XI
PERFORMANCE DATA
NATO PS FLIGHT MA NUAL
NAVY MODEL
A-4M
TABLE OF CONTENTS
Page
Pa rt
A IRCRA FT
Douglas Aircraft Company, Long Beach, Calif. 90801
Controcl No . NOOOl9.70·C·0136
Page
P ;trl
1nttoduction
11-1
ENDURANCE ... .. . . . . . . •. . .. . .
11·63
GENEHAL • • • . . . . .. .
11 -3
Fouled Deck Endurance . . . . • . . . . . .
11-63
11·63
Per!ormance Data. Basis
Abb1·eviations, Symbols, and
Deflnitions . . . . .
Drag Count lrldcx System . . . .
Ai rspeed Corrections .. . . . . . . . . . .
Altimeter Corrections . . . .
11· 3
11-3
11-4
J 1-7
11 -7
TAKEOFF . . . . . . . . ... . .. • . . • .
ll-7
Takeolf Charts
. . .. ... . •. ..
Operational Tnkeol! Di s tance ... •..•
Maximum Tuke<>ll Weig ht - With
and Without JATO . • . . . .
JATO Firing Delay. Minimum Takeoff
Distance - Two MK 7 MOD 2,
5KS-4500 JATO Bollles . . . . . . . . . . .
Refusal Speed ... .•... . . .
Stopping Distance . . . . . • . .. • . . .. .
11 -7
11 -7
CLIMB . . . . . • . . . . . . • . . • .
11· 31
Clirnb ... . . . . . . . . . . . . • . . . . . .
Combat Celltog and Optimum Cruise
Altitude
.Ma>:jmum E ndurance
11·71
11 -71
. .•. .•.
. . .. . ..
11-73
11-73
. . . ... .
11- 76
DESCENT. • . . . . . . • . . • . • . . • • • .
11-79
11-79
LANDING • • . . . • . • • . . • . . • • . • .
11 -83
Landing . . . . . . . . . • • . . . . . • . • . .
11- 83
11-31
COMBAT PERFORMANCE . .
•.•. .
11-93
11-3 1
Combat Perform:tnce . . . . . • • . . • • .
Turning Radius . . . . . . . . . . .. • • •.
ManeuvetaMlity . . . . . . . . . .. . • ..
RANGE
11-39
M:\Ximum !\·Jach Number •••••.••.•
11 - 93
11 -93
11·93
11-98
Ra ~e
11 · 39
11 -39
11-39
11· 46
11 - 51
Facto r Chart . .. •. . • ... ...
Long Range Cruise • .. . . .. . .... .•
Max imum Range Cruise . . . . . . . . . .
Nautical Miles per Pou1td of Fuel . .. .
11· 8
11- 19
11 · 20
11·20
INTRODUCTION
I SSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS
ANO UNDER THE DIRECTION OF THE COMMANDER,
NAVAL AIR SYSTEMS COMMAND
11-71
. . .. .. .
. .••.. .
Ma.'<irnuin Range Descent
Fouled Deck Range . . . . . . . • .. • ..•
I
Alll HEFUELING . . . . . . . • . • • . . . .
Air Rcfuelifl!l Charts . . . . .
Tanker Speed Envelope. . . .
T>nker Fuel Available for
Tr~nsrer
.. . .. .
Tanker Fuel Transfer Time.
Fuel Consumption of T;-m ke r
During Air Refueling • . . . .
7
10 MISSION PLANNING • . .•. • . . . . . .
Mlsslon Planning . •• . •. . . . .. . •.•
ll·lOl
11-101
Section XI is divided into 10 p;uts to present
perrormance data in proper sequence for pl'e!light
pl:tnning. Sample proble ms and chart s arc proFAl-2
l November 1971
The operating data charls conlajned In this seetlon
vided to present the sequence of steps required to
provide the p ilot with information e nabling him to
realize the ma.'<imum performance c apabilities o!
the ail'craft. Use o! the Ch:t.rt material for preflight
planniflg and application o! the p1·e8c.dbed op erating
!Ind the proper values and solution of" gi ven
problem. P erformance data are presented in
~ l:'ap hiea l
procedures wUl result in optimum eHeeth'<!ncss or
lyt>e charts for TCAO standard day
conditions. In some instances . temperature
corrccttons !or non·s t:.indard atmosphere havo
the aircraft.
been Included.
ll· 1/(11· 2 blank)
~
'I
NA VAIR
01·40AV~J - 1
Scctio1) Xl
Part J
Section XI
Part I
NAVAlR 01-40AVM-1
Abbreviation
p
PART 1
Pt~rfor· m:\n('e data arc b:iscd on airc1·:'lft cha1-;u'l1;>n~·
tics obtained Crom t\·4fo; f' N:l\'v and TA-1F Conu·ac -
F
Fii
Flight
FPi\1 or rpm
Ff'E>l
Ftcq
Ft· <'qurnc~·
t'\ffc>Ns :1 r~· signlhcant.
Degr1>es
All P<'r!ormancc is bai=iPd on
All
charts a rc 3Pl>lica.blc to J.P-4 or- ,JJ>-5 fue-l. havill(? a
nominal <tensity of G 5 and 6. 8 J><>und~ per gallon
r·espN' l "·ety.
ABBREVIATIONS, SYMBOLS, ANO
DEFINITIONS
Ahhrf'\'iaCion
Fr
or fl
RCR
Runway condltion reading
per nunute-
RN!
Reynolds number index
RPM
Revolutions
~r
minute
( Engine speed)
Ft> Pt
Hor h
Alhtudp
Std
Standard
Ilg
1\h,:tC\ll'\'
T
hr
Hour
Static a bsolute tempera ..
cure at any a ltitude
!AS or v i
hidic:Hed airspf'Pd
standard dav
AOF
Aoromalic direction findrng
All
Altitude
'C
1· ~1drng
.'lirs1>eed - (AS
corre('tcd for position
error
cc
Center oi
do
Oil·e('t cu1·renl
~J'avi t y
Free s tream static
condition
c.·or-
!CAO
TnlPrn:ihrJllal Ci\'il
1\\•iation Or~1111J:~t llon
TAS
True alrspee<!
In
Tnr:hcas
Vol
Volume
KCAS
Knots calibrated airspt"("d
Wt
Weight
Kl.,AS
Knots equh13lcant airspeed
KIAS
Knots indicated airSPtt>d
Calib r .1 l~d
KTAS
Knots
Kts Kn
Knots
tru~·
airspcC"d
lb
Poundi:;
M
:'\laC'h numl)("r
MAX
,\l,1ximum
min
Minul()$
F.qtm•:tlenl airspeed
CAS
corrected for comprese>i
blll!y e llec1
min
Millimeters
E(.;T
1-;xhaust gas temperature
Nl\l
El'R
J::nglnc prf.l-ssure r :1i i o
OAT
Oelta - <h<1nge in (e. g.
gross weight)
6 or
P/ P
0
ex -
Delta - r •tio o! sta tic alr
Coemcient
friction
Rho - density or ahnosphcre al sea level !CAO
ol;rndard ct•y
o. 002378
slugs per foot
NautiC'al l\lil!!S
11 -3
11·4
pUed lo the performance charts. de!ines the pe1·!or·
configur ~ tion •
mance of that
complete listing Is made In NAVAIR 0 1- 40AV · IT.
Note th:1t lhc dr :tg m1 mbens (ot" ~' given store depend
on thP stor e station on which they a re carried. The
weights o! typical cxterm\l stort!S. pylons, tanks. and
adapters a re include<! in figure ll ·I, Tli. drag o! thl'
C' l<'an aircra!t includes the dr ag of the centerline
pylon. up1>er avionics pod. ln!light !ueling probe . and
drag c hute. bul no gums or wing pylons.
SAMPLE PROBLEM
or rolling
Rho - density o( :Hmosphere in slugs per root at
any nltltudc
Oi,1lside air temperature
on the aircr aH. The sum o! these indlvldual drag
number,!;. for 3 parti cular loading. reflects the dr3:g
index for that conligur ation. This Index. when ;tp-
pressur e to !CAO standa.i•d
sea level static air
p1·cssurc
Norrn:ll lood factor
Nl'\h
or the
cernal stor e configur ation. such as a bomb. tank. or
pylon. is assigned a drag !'lumber· value lh::tl depends
Some of the lndlvtdlU1 dr::tg numb()rJ:: us;()<! fo r deler mtntng drag tndexes arc shown in figure 11-1. and :i
w
or
The la r ge variety o! external store lo"dings per·
m1tted on the A · 4M a ircraft r equires a method or
da ta pr esentation that can reflect a variable external
configura tion. This method is called the Orag Count
Inde x System.
upon the slzc and shape o! the item and its location
Static absolute tem1>era •
ture at sea level JCAO
stanc:t:ml d.1y =
288. 2 deg-rees Ke lvin
TC('ted for instrumPnl
error
Altt>rnat1ng C'\1rrent
w
DRAG COUNT INDEX SYSTEM
Jn the Drag Count Index System. each item
Dcfinihon
.ll sea level. ICAO
v.
lure a t sea level; !CAO
standar d day
Sea level
;iltltude Lo i;peed o{ sound
eAS or
Pounds per square inch
F.thr<'nh~it
instrunwnt
Amb
psl
SL
Tblio of SJ>eed of sound at
CAS or V c
- r a tio of absolute
UJ:rn1>en•ture of any altitude to absolute t e n1per a
Gr.wlty forC't'
g
Thet~a
of mercuq •
D~finttion
tor flight tests. c:dcul:llions, and l'ngine dat:\ from
Pr:1u and WhHnl'y speclftcalions. All chaJ'IS ~ire prescntC"d ro1· ICAO st:mdard atmo'31>hcrc conditions.
althout~h ;:tmblcn· tcmperaturf• roJ·r pc·lion ~l·aLes a.re
pr uv1dt*d in ot number of ch:1ris where 1em1><.'r::tture
Definition
Sigma - r atio o( density a t
a ny altitude to density at
sea level. t CAO Sh\nda r d
day
Static atmospheric pres w
sure at sea level ICAO
stand.ud day • 29. 92 Inches
Abbreviation
.\ centc1· of gr.1,·1t\ poh1l1on of ?,.S percent MAC.
Abbrcviatio11
Static atmospheric pres w
sure at any • ltltude
GENERAL
PERFORMANCE DAT A BASIS
Dellnltlon
Drag Indexes
(for figure 11·I)
Assume the external configur a tion consists of ::1 300w
gallon Aero J WO ftiel tank on the centerline pylon . a
Gx300·pound MK 81 Snakeye bomb clu•ter on each
Inboard wing pylon. a nd a 530-pound MK 82 bomb on
each outboor d wing pylon .
NAVAffi Ol-40AVll1-l
Section Xl
Section XI
Part 1
NAVAIR
C!-401\V~ l-l
P:u·1 l
STORE DRAG INDEXES ANO GROS S WEIGHTS
Approx
MODEL: A-41.1
ENGINE: J52-P-408
and Su.i.p(•nsion I qufpmrnl
11)/ f'!l
tiZ'
DATA AS OF: I DCCEMBER 1970
DATA BASIS: ESTIMATED
aoo HourliC.ls 20-mrn .\mmo
70
Onc> A I UC > :.'O,\ .. l lt:t<'k- f>'!;)Qn
'"
l
:ll Stort" Sr:nion
J_·-+---
....
!m
A A J<R-1 MRR
,, .\ 31n-:s
rndc•~
I
1-..~
Ont' A FHO 20A- l Jt:ld•- P\ lon
Al RO.;,.\-! l.aunche1·
STATION
l)rag
\\'('htht
Gun~
DRAG INDEX FDR CLEAN CONFIGURATION <2l : O
l.">9
v:umt
,.
II
,,
,7
II
II
l'
I'
TfR-1
!05
,,
12
12
.\U,H-i
22:~
:!3
23
23
STATION
Approx
T<t1\IU! ~lOO Pod~ (I)
STORES UP TO
50D(l)POUNDS
STOR ES UP TO
IZOO(l)POUNDS
Sl"SPf'l;~fOZ\'
J:>O-<OAr l-\1d Tank;
1
FC"U f"'.\IPT'l' .! I
A bHO ;.WA- 1, 7A-1
300-GA I. 1-\lel T:lnk
fBol>t:iill: FU. I.
At:n o 1A-1
;'\o. of
S1orcs
Ot·~g
Index n.t !)l..,tc 8-t::ition
W£>ight
Jblca
lJ50 1136
t
10
22231 1'-3
10
-I~
5
···---
15
L.\IPTYf.?)
-
AIRCRAFT WEIGHT (POUNDS)
1\ERO 20A-1
:n:i!.I ' l!m
AlmO 'iA-1
2960/2·10
300-GA I.. Rt!luchng
Storr; Fl' LL.I
EMPT\'(.!)
Afo~RO 7A-J
2765/725
c1·c--s:>
A. Imo ZOA•l, 7A.-I
J«-5 /4~7
30<>-G:\ J. f\u:l T<lnk
(4
ESTIMATED WEIGHT EMPTY l:!J_ - - - - - 11,32 0
TWO 20 MM GUNS (NO AMMO)- - - - - - 344
1WO AERO 20 A-1 RACK·PYLONS ON
STATION 75 (2 AN04l-- - - - - - - - 140
TWO AERO 20 A-I RACK·PYLONS ON
STATION113. 75(! AND5l-- - - - - - 128
nvo 300· GALLON AERO-ID
398
EXTERNAL RIEL TANKS (EMPTYl- - - - AAMORPLATE--- - - - - - - - - - JOI
F'in~l;
rn.r
).I
F>IPT\'(,)
----·U)(>-<,;AJ, f'Uel "f'!\nk:
20
T'l' LL L.\IPT'l'fZ)
TOTAL OPERATING WEIGHT EMPTY-- - - IZ,437
NOTE:
(ll REFER TO NAVAIR Ol-4DAV·lT FOR CARRIAGE AND
I
RELEASE LIMITATIONS, AND EXCEPTIONS FOR CARRIAGE
OF CERT AJN STORES WEIG/I ING MORE TllAN Sl ATION
LIMITATIONS SHOWN.
(21 CLEAN AIRCRAFT CONFIGURATION DOES NOT INCLUDE
GU'-5 ANO WING PYLONS .
(3) OPERATING WEIGHT INCLU DES A CENTERLINE AERO 7 A -l
Pod-
19
21
19
EMPTY
i\<Yft;!):
l.
Hefcr to the l"iAVAIR Ol - 40AV- I T for :.ll other lJ)Ph<'abf(' <'Xl<'rmd store dr:i~ ind<'x :ind welghL d:-1~.
c~1 rna1te :u1d relC'ase U1n1tat1ons. and exct>1>tion" ror ('an-inge o f th(' bl0re$ w('ighing mon' th:in ~talion
limilutaons noted on shf'.-L I.
~Pcl\~f~~r~~¥J;, l\ND MISCELLANEOUS EQUIPMENT
FAl-117
J)
U-!l
30/ 11•!31
Mounlcd: Fl" LL/
~g ~~~~1r~~l~8r6PJ~~J1:rf~fJNMJ~s~Ro'iftt~11UTE,
Figure ll- 1. Drag Indexes (Sheet
~
l·I
2.
fo\lcl tank wclghl for ,JP- 5 (uel.
3.
H os~
and drogue: retract.ed/ extC'ndOO.
Figu r e 11 - 1.
11-6
Ong Indexes (Sheet 2)
- --
NA VAUl 0 1-40AVM - I
Extel'1tal
Store Item
Drag
Index
WeightPounds
Clean aircraft
2 MK 12 20-mm guns
with 400 rounds ol
To conver t rallbrated airspeed to t r ue ainspeed and
true Mach number .• figur e 11-2 is provided. fi gu r e 11 -2 ha.s compressibility elfe:cts built into the
graph permitting a direct step from calibrated to
true airspeed.
A position er ror is assodatcd with the
number
ind iCllted va lues :.nd the true Mrtch number va lues.
163
2 Inboard wing py:ons
12
140
2 o\ltboard wing p7lons
14
128
Altitude Correction for Position Error
46
446
(For figure 11-6)
70•
3000
Snakeye bombs
6•
1060
bombs
§
170
5585
As t he mission is flown, tanks may be d1·opped a1\d
stor es will be expended, changing the exter nal stor e
SAMPLE PROBLEM
o.to
§
0.10
(Data lo be lurnisht'<I at a later date.)
Mach Number Correction for Po5ition Error
~
0.70
(I>ata to be furnished at a later date. )
Airspeed Conversion
:
( For llgure 11 ·2)
~
700
-..
•:E 0.60
conJigu ration and thus the drag index.
...
l5
z
%
• Reier to NAVAIP. 0 J-40AV- JT.
(A) Calibrated airspeed
u
(D) True pr essure altitude .. .
25. 000 l l
o. 849
Several correctto:ts to the airspeed i ndicator reading
must be added to a r rive at the tr ue :lirspced of t he
:'lirc raft. Tu•o corrections peculiar to the indi cator
(D) OAT.
2o·c
itself are instrument error and lag. These er rors ,
(E) True airspeed .
I
~
360 kn
(C) True Mach number . . . . . . . . . . . . .
AIRSPEED CORRECTIONS
10
1.00
at a later date).
(For ligure 11 ·7)
Totals
PlESSUlE ALTITIIDE-1000 FEET
so
20
TiliS relationship is shown in figure (to be furnished
15
2 530-pound MK 82
so
M :~ch
I 300 -gallon Aer o - I D
fuel tank on centerline
2 multiple ejector racks
Section XJ
Part 1
AllSPllO CONVIHION
628
ammuni tion
R2 5x300•pOund MK 81
NAVAffi Ol-40AVM- l
Section Xl
Part l
......
0
.., O.JO
500
~
0.40
-
O.JO
100
565 kn
which are ue;ually small, a r e added a lgebraically lo
the indicator readi ng to obtain the indicator ai rs ~ ed .
..:c
........
:l;
:>
ALTIMETER CORRECTIONS
Calibrated airspeed ts equal to the airspeed t ndlc.,tor
r eadi ng corr ected fo r position and instr ument erro r.
Po$Hion error , showo ln figur e (to be Curnlshed at a
tater dale) . ls an err or i ntr oduced due to t he loca tion or the st.atlc source at :.. point of nona mbtent
static pressure.
Equi va1c nl ai r speed is equa l to the a irspeed ind.icalor
r eading c orr ect~ !or position error . Instrument
er ror, and for thC' compressibili ty at a particular
a ltitude.
T he a lti me te r is connected to the ~tatic source.
Pos it ion e rror. corrections, simibr to those for air ..
speed Indications, must be applied to the a ltimeter
lndlcattons to obtain t rue pressure altitude. The
corrections :u·e given in figur e (to be rur oished at a
tate r date). Instrument e r ror a nd altimeter lag ai·e
~lso prevale nt In the a lthneter system.
The lag
error (appr oximately 200 leet) could be stgnlltcant
in a low-a ltitude dive pu llout.
SAMPLE PROBLEM
I
EXAMPLE:
CAS : 360 KNOTS
PRESSURE ALTITUDE= 25,000 FEET
TRUE MACH NUMBn = 0.8'49
TRUE AIRSPEED !STD DAY!: 512 KNOTS
TRUE AIRSPEED t20°C} 565 KNOTS
0.'20
=
ft. 10
0
True airspeed is r elated to equiva lent airspeed by the
following: KTAS • K EAS x J/.[O
100
200
soo
400
CAUIRAtED AlltSPHD - KNOTS
Airspeed Correction for Position Error
-
100
FA1·5~
(For fig ure J 1- 6)
The quantity l//C may be found in figures 11 -3 and
11 -5.
200
Figure 11-2. Airspeed Conversion
(I>ata to be lurnlshed at a later date. )
11 -7
11-9
Section X1
NAVAffi 01- 40AVM-l
1\A VAIR 01 - 40AVM - I
Part l
Sc.•<·tton X I
Part 1
DINSITY ALTITUDE CHART
00
Dc-gn•cs
Dc>grt?(!S
Jl\lgrl;!(l.S
DegrCJ('S
Centittr:td~
Fahrcnh~ll
Centigrade
f.,ht'f'nht'"H
-33
-33
·31
-30
·29
-28
-27
-26
-25
-24
-23
-22
-2]
-20
-27. 4
-25 6
-23. a
-22. 0
·20. 2
- 18. 4
- JG. G
- 14. 8
-13. 0
- 11 . 2
-75
-103.0
·74
· IOI. 2
-73
-72
-7 1
-70
-69
-68
99. 4
-67
· 66
-6f>
-64
2.0
.io
1.1
~
...
-63
-62
...ill
-e1
-60
-59
·58
-57
·56
-55
-5·1
-53
w52
-51
..50
u. . ,
b§
I~
Q I so
-.•os~
"'
t: !:; 'U
>- !::
~41:
1.4
... >,..... ..soc~
~
...
-49
-48
20
-47
-46
45
- 44
Q
1.3
·43
-42
-41
-40
1.2
- .to
-~9
1.l -t :.ti:
-
;±t
-38
-37
-36
-35
-34
90
1.or-1.0
8-
1.10
97. 6
95. 8
91.0
92. 2
90. 4
&8.6
86. 8
85. 0
83. 2
81. 4
79. 6
~
· 19
76. 0
- 18
-17
-16
- 15
-14
- 13
· 12
- II
- 10
- 9
- 8
- 7
- 6
- 5
• 4
- 3
- 2
77 .
74. 2
72 •I
70. 6
68. 8
67 . 0
fi5. 2
63. 4
61. 6
59. 8
58. 0
56. 2
54. 4
52. 6
50. 8
49. 0
47. 2
45. 4
43 G
41. 8
40.0
38. 2
36. 4
34 . 6
32.3
31.0
29. 2
s. 8
4 0
2. 2
4
I. 4
o.
3. 2
5.0
6.8
8. 6
10. 4
12. 2
14 0
15. 8
17.6
• I
0
32. 0
I
33 .8
2
3
4
5
6
7
8
35. 6
37. 4
39. 2
41.0
42. 8
H .6
46. 4
Oc-g1·t·t.•S.
F:ihrcnhclt
9
JO
II
Sl.3
53 6
"'
57. 2
59.0
60. 8
62. 6
55. 4
64. 4
66. 2
68. 0
69.8
71.6
4
2J
'/;$,
2•!
25
26
27
28
29
30
31
32
33
75. 2
77.0
78 8
80. 6
82. 4
84 2
86. 0
87. 8
89. 6
91.4
93. 2
95.0
96. 8
34
35
3G
37
38
39
·10
41
42
43
44
45
46
I
48 2
so. 0
12
13
15
16
17
18
19
20
21
22
9. 4
7. 6
19.4
2 1. 2
23 0
24.8
26.6
28. 4
30. 2
~~,.e~s
C~nlit:r-:\dt>
47
48
49
so
98. G
100 1
102. 2
104.0
105. 8
107. 6
109. 4
11.1. 2
113. 0
114 . tt
llS. 6
118. 4
120. 2
122 ()
I •
-•o
-60
-4o
o
-20
20
60
40
TEMPERATURE DEGREES CENTIGRADE
TEMPERATURE DEGREES FAHRENHEIT
-1•0-120 -100-10 -40 -40 -20
.u
.10
.1s
.to
.u
20
.to
40
.ts
60
1.00
•<>
1.os
100
120 140
1,10
1.1$
TEMPERATURE RATIO - 8
FAl-60
11-10
Figm·e 11-3. Density Altitude Chart
f igure 11 -4 . Ccntti:r ndc/ fah r cnhcli Conversion
11·1 1
SertlonXI
Part J
Allllud<.•
f<'et
J'Cmpcrature
I
Ocoa;lly rtauo
" • P IPo
.r;-
I. 0000
I 0000
15.000
1000
o. n11 J
I. IJH.t'
13.0 1!1
St.ta l.t>Vf'J
St>cc.'tl o(
Sound nntio
r.
T / 'r
0
~9 .
000
I. 000
2s.n1
I 0000
2"l. '56
l),ltij.1..J
0.99:1
2i.r.:U
U.!t"l~'i
o. 090
o. ooo
~6. 'SJ'i
o. "~14;2
l.O:lfi'J
11. 0:J.;.
O.!H&I
I. 0·151
'J.Ol';G
..$.30'l
o. 979-1
1000
0 ... g~1
r. or.11
1. 075
H.7!'SS
(t,
o. 9$02
-iJ. tG9
:;, 09<
pp
H:tlln 6
o. 9'11
o. 9<2•
1. 0173
Altitude
Jn. 0£ Hi:;
I, 1)(100
2000
uooo
':l/:10
o. 9931
3000
972:i
o. 9G.:;b
o. 983
u. i,1;31
24 . ..~
O.F-3~0
I 093&t
3. J 13
:11. 603
o. 95'7
o. ,79
23. 97S
O. ~01 1
O. ~JOG
I 1107
1. 132
31.037
o.~10
O. 97U
:!!I. O"J.t
l).i7h.\
<ioon
0.7%0
1. 1279
-0. ~50
:lO. 171
0. 94SO
o. 972
22.:2;2.j
o. 7420
9000
0. 7t.i20
1. 1.i;,a
- 2. qs1
21,. ~O:j.
o. 93 ~ 1
O.!MD
21 31'."'
u. 71•~
10, 000
o. 73~•
J. 16.17
-4.812
23. 33,
o. 9312
O. OGr.
20. S71
11,000
O. 715C
I. 1•22
- 6. 793
1,.772
0. 02·11
o. 961
U.79J
O. G>77
1J, 6r1M
12,0-00
0.11932
I 2011
-~. 774
16.20C
o. on;;
o. 950!
1~.
02n
0. 6360
13. 000
O.U713
I. 2:!05
- IO. 7~1i
12. G40
o. 9100
o. 954
Jit 292
0. bl13
U,UOO
O. G500
1. :?.Jf)3
·1'2. ?37
9.01•
o. 9037
(). 9:JI
17. G77
Q. 5"175
O.UW'.!.
o. 60!)0
I. ~COG
17,000
•JI. '11lJ
5.SO~
O. S9G9
o. 91'7
l .Z~Hi
-lt..1.Hlc:t
1.l1'41
o. '1900
I 3021'
·I~.
6'-.0
-1. tr.za
o. ;;s31
o. 943
o. 9-10
IS,000
tJ, ;jG99
1. 3:.!-4G
-20. GG2
... 5. l!'ll
0. 8762
o. 9:JG
19,000
O. SSll
I. 3·110
-2:.?. 043
-c:.. 'i'S7
o. S09-I
o. 932
(f
Raho
p ""
lh 'i1'(1,i
lti.2Hi
1$,.;jti~
"'· n12
14. 336
0.5643
o. :;no
l),j20!l
o. 499·1
0. 4791
Tcmper:1tu1·c
I
,fO
•p
('
:ipf'<'<i of
Sound H:itio
Rntiu O
T/l'
0
;,1/ao
In. u! fig
Ratio 6
1>:p
0
0
33. OO{J
o. 3099
1.7!.164
- !'H.3·l2
- t;r•. 'tG
(), ;,;91
0 . '"':'1
i. 011
0.23G3
36. 000
u . :W~ l
I.
~31ri
- 56. 323
- 69. 3 ..2
(), 752~
O. "G';
6. 7t2
(), :t~·~3
31), 0~!!)
0 . :?971
I. ~3 Ii
-56. :100
-69. 700
o. 7QJ9
(). 1-iG?
0.:.!;.?34
o. ~ 13"1
3':' ,000
3'. 000
0. Q3i!O
7000
16,000
lk"ll~ity
f('('l
o. 2710
39, 000
6000
tS,UUO
Section XI
P;u·l I
NAVAIR 01-40AVM-l
NAVAffi Ol - 40AVM - I
l.!>209
0.20:10:
I. 0077
o. HH2
IO. 000
o. '!16:.!
~.
OJS:.
O. l"';;I
.JI, OOQ
O.:l:J.iG
2. 0045
o. l764
1.i. ono
o. 2236
2. 11'1"'
.;.030
0.16"'1
J3.000
o. 213J
2 . 1662
... 7!.14
0. 1602
11 . 000
0.2Q31
2. 21-.:9
-l.SG9
\'), 1527
-IS, (H.)0
o. 1936
2. 27:.?~
I. 355
O. HSS
·16. 000
0. 1'-t.tG
2.32~1
·'- l.)I
1-: .noo
(). 175"!
2. 3..,4A
3. 956
n_
u.
O. 121.lO
l:l"17
lJ22
I", 000
0. 1676
2. ·1'2Q
3. 710
19. U(lO
o. JS97
2. 5022
3. 59:1
0. 1201
so. 000
O. JS:?:!
:?.5630
3 ..125
(I, I) 1S
51, 000
O. U!\1
2.6~M
3 :?t> t
O. lOfll
.;2, 000
2. 1; ~92
3. IJ I
o. 1044)
.;3, 000
o. 13'3
o. 13J"
2. 7~·1G
J. 9G.J
0. O!l!)I
54 . 000
O. 1:?5G
'!. '216
2. >12fo
O. O!IM
s.;. ooo
0. 1197
2. ~903
Sti,000
o. 1111
2. !>GOG
S?.000
n. 10~~
3. O:t?G
O. OHi~
.;... , 000
0.
3. 1063
o. 0779
,'i9.000
o. ()9'.<i77
3. J'-IJI)
0. ()7.1!1
I, 393G
-2f>. 605
- 15.8~9
0. ~.:i5G
J.4179
-2~.~"'6
-19. ISG
0»<87
o. 029
o. n;
o. 92J
J, -1-42·1
- 30. ;)RG
·23. OZ!
o.•• ,,
O. UJ'I
UL 1n7
O.-I0-16
0.464:!
I. 1r.7'i
-32, VJ!'i
-26.6'>tl
o. "f,3:j0
o. 911
J t 537
0.3.,:7G
2;),000
o. .w..
I. 103<
·34. iNO
-30. 154
0 . h2M l
IJ. 104
o. J711
~b,UUU
o. 432~
1. ~2or.
-36 Git
-33.120
o. k212
10. b:.!1
60, OOQ
Q,
09414
3. 2503
;.! , Jl"
0.0709
o. 4173
o. 35j2
27,000
1.sv...o
-3 .... 4!>3
-a1.2su
fl.AH•
JO. 10'1
o. :13~~
Gl,OM
O.O;t!Ji2
3. 33RG
2.0J°'i
0.01>1:;
2g,ooo
n.11)'.l:)
J, S7t;.:l
~O.
-IN
--40. -i52
o. 807:>
9. 72!j
o. :j ...-...1
J, G,.!'iJ
-12.
~:;.;
-4-L n9
O. ~OOG
!'t 2~t7
n. :t.!50
u. JJ07
o. 0043
29,00-0
20. 000
0.532"!.
21, 000
o.~1so
22,1)()0
23, 000
o. l97tJ
o. •>07
2·1,000
1.31M
..z-t.G:?~
-12.323
o. "625
30. 000
U.3741
1.u!11n
-11 ..13f;
-47.0tlS
31.0(1\)
o. :mo~
J.1.1;:.1
-46.417
- 51.551
o. 7:137
o. 7%9
:11, ono
13. 7~0
() ... ;)!)~
13. l'"I
O. ·l IOft
12. ;;:rn
o.
1223
0. q!,l i
o.n10
o. ~ ...7
fJ,2<ii:l1
0.3413
L 1rol)1..
-''"'· 30!>
- 55. 111
0.17'\00
o. C!~:J
0.2709
JJ. noo
0.3~·1:1
J.U!Jl
- 50.379
-S~.G ~:t
o. 7731
o. >79
I).
34 . 009
Q.:1:u11
I. i'11.2!l
... r,2. :Mt
- tJ2.2-t9
o. 71;02
o.n:;
0.1·hl1
25"b
103t~
G2. 000
o. o~;:i.:.1
3.
-U~"
I. !>24
o. 0~150
3. :;029
L;>;3:J
O. OGl:'l
64. 000
0. 07767
3. si.;sa
1. 1·17
G.5,000
O. OH03
3 . G154
o. OS~1
o. 0$~7
-sr.. 500
.. G9. 700
o. 7.;t9
O. !o!G7
Ht.o\1'\HKS:
(1) One in. of Hg
70. 73:.! lb p(>r gq !t
0. 4912 lb pCl'
~q Ill.
~n. 31~2
r.n IC.AO Stantfa rtl &-n Li•\·(•l .\tr
fl) ()nA in. or Hi:
DATA BASIS: SAC.A
lo
t5 r
"1912 lb P'-"r '-Qin.
J\0
:->u.
p0
2!1. 9i J tn. of II~
Ml. · lnulS
O. 0<.12~7'i9 s lug IR'I'
7-0. 132 lb pc1r ,.q fl
I),
T~C'hnf~l ~<ttC
:U",::.?
no
Figure 11-5. tCAO Stand.>rd Altitude Chart (Sheet 1)
11-12
0. OS~~
63,000
OAT;-\ RASIS: "ACA Tf'("hnlcal Sot<'
llF.MAflKS:
o. onoo
,, :j67
t'U fl
Pigur ~
11·5.
ICAO Stand;1nl AltUude Ch;_u-1 (Shee' 2)
11 - 13
~ction
Section XI
Part 2
N'AVATR 01-40AVM-1
XI
NA VA IR OI-40AVM-1
Part 2
stations. nnd wing Claps :u·(' $Ct
SAMPLE TAKEOFF DISTAN CE
- ..
-'--------~--:;,·
'. --
PART 2
TAKEOFF
~
"
i
The takeoff charts present takeoff distance. maximum
takeoU we ight, JATO !iring delay, ond JATO ••keoU
distance. The charts encompass such va ri;tbles as
takeoff weight, equivalent airspeed, ambient runway
temperature, runway pressure altitude. headwind.
runway g r-~tHt>ni
2. The safe t1re spee<l limit of 175 knots ~round
SJ>C>cd ~ha II not l~ ex<.·e-edcd.
Note
TAKEOFF CHARTS
~nd
H:ilf fl~ps anrl MILl'T'ARV
thrust arc r ecommended for all takeo!fs.
U operatiooal conditions require t;Lkeoffs
for which comput ed takeof! distance places
the o lreralt In the region l:1beled TAKEOFF
IS l\<IARG!NAt. on the chill't. lilt-o!! speed
"\A 'TC rllght lest of the ~lodC'l A-4F. ai 1Tr.1f\ shows
that the abO\•e <'rit<"ri:l, when met. wtll pro"idc .u··
ccptnblc climbout ch.1.t:'lc·1~rislics. Since .JATO hurnout 0t."cu1·s at lilt-oU. 1hi s ch:nt i~ \';thd for holh with
should be increased app roximatel~1 5 to 10
knots. not to exceed tire limiting speed.
This wlll result in increased r;,ces of c limb.
Runway length ond loe:llion ol :ibort ge-u
must be eons idered i n planning this type of
takeoff.
:ind without J ATO :isslst.
SAMPLE PROBLEM
Variables . which ar e not considered ln the charls,
th.at will influence the acceler ation of the a ir crafl
during ground run a r e pilot bl':l.kin.g to mainta in di-
rectional control; runwa.y surface conditions which
constitute a Lower or higher value fo r the ro lling
cocUiclent of fricUon (µ); extetnal store loadings on
thE" wing stations which protrude forward or near the
le~ding edge of the wing and influence the flow !ield
of a.tr over the wing, reducing lift ::i.nd t ocreast ng re·
quired takeoff Sl)eeds; and rough or bumpy runways
which in.fluence the taxi attitude of the aircr;d'I, 1n·
troduci1ig aerodynamic brak1ng during the ground run.
Of these var iables, pilot bra.king, which is a function
of pilot lechni ~e, probably hos the gr~te•t !n!luence
on acceler ation· retar datlon and will incr ease the
gr ound run sig?lificantly.
Moximvm Takeoff Weight - Operational
SAMPLE PROBLEM
(Por Ciri1Jre 11-9)
Takeoff Distance - Operational
(A)
••pplym:.: thr c·orrectlons for \'aJ'i3tion from litandard
coodttionl\. The fln;l lin,.. speed check .shuuld ht•
(A) Ta.keof! weight ..
20. 000 lb
(B) Tukeoll airspeed
146 KIAS
(C) Ambient runwoy >Ir
3o•c
OPERATIONAL TAKEOFF DISTANCE
(D) Run.way pressure a ltitude
2000 ft
Oper<ttional takcoU distance, tolal di stance to clear
(E) Headwind . .
10 kn
(F) Runway gradient
·2 percent
(G) Gl'ound run di stance
2450 fl
(H) Total dist:in<·e to clear
50-loot obstacle
3600 fl
a 50·foot obstacle, without JATO assist. <\nd rccom·
mended takeoff speeds a r e show11 ill figu1·c ll ·8.
Takeoff dist:1nces are based on h>lf ! laps. MlLITAIW
thrusl, and 8 <!egr ees aircraft noseup t r im.
The t>keoH airspeeds and distances a r e based on
NA TC flight test data o! the Model A-4E a lrcroJt .
Nole the region in lhe altitude correction box whe r e
MA XlMUM TAKEOF F' W EIGHT MAY BE EXCEEDED.
This region reprei;ents an area tn which the minimum
3ccept:1blc thrust·to·welght ratio may be encountered.
resulting in marginal ciimbout capability, or tile safe
tire limit speed of 175 knots ground speed may be ex·
ceeded. Since temperature :ind a ttitude arc not in·
dc1>cndcnt . the boun<bry lines tn this box a r e s hown
for extreme a ltitude ·tem1)e rature combinations. A
moi;e detailed t1Xp lanation ot the margln:i.l rcglon is
given undei:- m:1.x imu m takeoff wcit;ht .
'The method ol
obtaining the ground run dlstance. total di stance to
clear a SO· foo: obstacle, take-Orf airspeed. and the
llne speed c heok a1·e described In the following
example.
Ambient runw;t)'
air ccmpcr>ture. . . .
30 C
f4J·U'I
(f'or figur e 11 -8)
temper ature . . .. . . .
§
the 1l<llt-fl.1ps
or th~ followin~;
I. £xct'ls~ thrust Sh.'\ll not be less than mm1mum
established b)' NA TC fligh1 •e•l
'
i
N
~~l
pos1tion. The m:tximum t.\k('<Jff wPl~hc '-'rtleria Is
b~\scd on llu:i mm:n r r iltcttl
m;idc
nt
the 2000·foot
~
SAMPLE PROBLEM
I
line Speed Check
rut1\\':.t\·
marker.
{B) Runw:w
pr<:'SSore
a ltitudc . . • . . . • . • . • . . . . .
(C) Maximum t:lkeo!C weight . . • . .
1000 ft
23. 220 lh
SAMPLE MAX IMUM TAKEOFF WEIG HT
(f'or hguri' ll-8}
.. 2 ~rcent
(IO H~tlwmd
10 kn
2000 It
CM) AmhlPnt runw.l\' .dr·
tc>n1pt-ratorc
30
c
T .ikeo(! wt·iRht
20. 000 lb
(P) lndlc.Hed .ilrspecd
t3:1 KlAS
(N)
LINE SPEED CHECK
A llne speed check is a s imple procedur e for determining that aircJ•a!t acceleration during takeoff run
is normal. If alrcract acceleration is not normal,
the line speed check 18 ~ufhciently early to allow
normal braking to stop the ai r cr:afl on the runway.
The pi lot selects a suitable and recognizatJle- known
distance down tho runway from lhe poiut th~t t;'k '"o((
run commences (such as runway diSL~UtCt! m:1rkcr.
runway intersection. etc.). The normal takeoff dis·
tance ch;.\rt ls used by entering the cha.rt at the selerted disL:rnce and working in reverse throogh the ch:t.r t.
11-17
MAXIMUM TAKEOFF WEIGHT - WITH
AND WITHOUT JATO
The nlo.\Xin1um
ink~off
weight {Clgu tt..' 11 -9) is gt\'Cn :.s
a fun<"tlon of pr(IS!-Our~· attitude .;ind ambient .air t('m·
p~:ratureThe d.11.1 ba.sts fo1· tins ch:.irl assumrs tl\.'\t
tht' hntHng {!e:ir Es fully e:x-torwt<"d. takeo(( IA •ll ah--
speeds shown in figure 11 .. a. the aS rcraft is chmlJmg
out w1111 ~ TILJTARY th.rust w1lh lhP assist of gr ound
cff('('I. multiplt> carrt3gc s tores ~u·e e1rrtt>d rm -A'ing
11-1 8
llUUATUH - Oltl!US UlllUll(fT
NAVAIR 01·40A VM- l
JATO FIRING DELAY, MIN IMUM TAKEOFF
DISTANCE - TWO MK 7 MOO 2,
SKS-4500 JATO BOTTLES
Section XJ
Part 2
Section XI
Pa.re 2
SAMPLE JATO FIRING DELAY
The minimum &round run d(st.tnrfl ;1nd the total dts·
cl(>,ir ~ 50·foot obst.tclc m;w be re-Jlizf'd by
'lrl n{.! lh(.) .JATO boU !es 'JO th:u burnout occur s ill
NA VAIR Ol · 40AVM • l
(A) Takeoll wetghl . .
20. 000 lb
(B) TakeoU airspeed . .
146 KIAS
(C) A mbienl runway
air temper:.ture . . .
30'C
lance to
lfl·ofl.
SAMPLE JATO TAKEOFF DISTANCE
{0) Runway pressure
Burnout .1l hfl-orr Is recommended for the
altitude . . • . . • .
fo llowan,I.( r· Pattans~
Burnout 3t llft·off produces the ,;hoJ·test tak{'-Qff
dislal)CO.
2000 It
(E) Headwind . . . . . . . . .
JO k n
(F) Runway gradient
-2 per cent
2. A int.-;ure can be de>tC'-ctcd e.a r ly and the takeoff
C...ln be :tllQrt('d v.•ell b~fore th~ refusal point.
(G) JATO firing di•l:rnce
450
ThP following 1rlm Settings are required fo r J AT O
;~tutudes ·''
JATO Takeoff Distance
01>t!talion to :woid ext·cssh·c nosc .. htgh
(t
low ~ross wei~hts du._. to noseup pltchln~ moments
~eneratcd by posslbl•• .JATO burning :l!ter li!l-oll.
(For l!gurc 11-11 )
Oro~s
\Veigh'
(Pound•l
I
ReC'ommcndc-d Tnm
(H) Takeo!! weight .
(0.1:Tees Noscup)
(J)
13.500
f'All41
17.500
22. 500
24. 500
With 1he ;,bov"" reC"ommcnded trim settings. Hu.· flight
trim Stick forct" \\ 1Lho ut ,JJ-\ TO burning \"O.J' les ll11P:1rly
"'Ith e:r oss wct~ht Crum :1ppJ·oxhnatcl~· 12 pounds pull
:u 16, 000 pounds ~ross weight to 3 pounds pull :tl
24. 500 poun<h;; JtrOS!; weight . 1'Ms Slick fore~ is not
since .a redurtion In angle·o!-a.tmck is
requ1rttd to maintain .1lrSJlflt>d o t· to <"Ontinu@
ob1cctton~1bl c
:tftt•lt•ratton
It ht rrrommen<led tt...1t the fi r mJ.t lx.>int be est~blishcd
bv c.tist:uw~ markct·s alongside the runw.1y. 1111s
recommen<l1Hon 1~ 111ade for the fotlowtng r easons:
Vsinl! :\ tim<" inten~.tl from hr.lke r ele:tsc ls
''tm~iden:•d to he too lnncf"u?";Ht•.
t.
2. l,;stng a irspeed as .t reference for ,JATO firing
would not be posl'\lblt> sinl.'"e. gencrallv •• IATO U.ring
occurs at a speed lwlt)w thfl speed 31 which U\C o\lr ~
spoed lndtc:uor begins to J'e~lsle r .
r le:tr a 50-Coot obSl..lCIC arc presentc.-d In r1gur e t 1·11.
T:'lkeorr distance" .i r e based on h:.1U-fl:q>s. ml1it~1rv
ttu·ust. ornd trim st-thngs.
·
The L1keof( airspflrdK 3nd dtstances arc b:t~ed un
JATO !light tesl d;i~1 CJ( tile ~lode! t\-11:; alrcr:t!t,
~ote 4he r ei,rion In tht .1ltitude corr ertton bo;'lt where
~IAXJMUM TAKF.on· \\EIGHT MAY BE EXCEEDF:n.
This rl>glon 1«•prei;ents an :.tre:i tn which the ntlnimum
:t<"CC))t:t.ble l hrusL-to-wcight l':lh<• may be enroun1ered.
l'(•sulting In mar ginal cllmbout cap:ibihty. or th<" sale
fo llowin~ t':X:tmples.
146 KIAS
30'C
(L) Runway pressure
alt itude ....
2000 ft
( M) Headwind . . . . .
10 kn
(N) Runway gr adient
-2 percent
(P) Ground run d istance .
1350 (l
(Q) "rotal distance to clear
50-!ool obstacle .. .. • .. .. . .
Takeoff Refusal Speeds
Configuration: Al1 corl!igurations
2500 ll
Note
I
Jettisoning of JATO bottles should be performed in 1. 0 g level flight. in cruise con!iguralion. at 01" below 400 KlAS (maximum) .
(A) Runway temperature .•.. • ..•
3o•c
(B) Runway pressUJ'C ~ ltitude
2000 ft
(C) Tr:msler sca le
(0) Field
...... .
len~th
REFUSAL SPEED
~ way or specl!icd lc11glh. figures 11 · 12 and 11- 14
present this cb.t:i fo r engine faUure during a mlllt:ir y
10 kn
....... . .. -z percent
(H) T:lkeo!! re!usal speed . . . . . . .
91 K!AS
thrust l.."1.keoH without JATO burning.
Figure 11-1 O shows Lhe ground run di st:t.ncc Crom
brake release to ignl!lon o! .IA TO. TakeoU speed.
gr ound nm dist.\ncc. 01nd total horizontal dist:inre to
Data i nclude$
distance coveJ·ea durlng a pilot reaction time ol 2
20. 000 lb
(F) Headwind . . . ..
(G) Hunway t,r radient
1.12
8000 It
( P.) Takeoff weight . .
The maximum r efusal speed is that speed at which
el'1gine failure permits stop1>ing the airc•·a!t on a ru1\·
SAMPLE PROBLEM
SAMPLE PROBLEM
(For Hgure 11-12)
fndepPndent. the bound1rv Hn~s in this 1>0x a r<' shown
for ext r t>me ;iltitudc-tcmpcJ'ature comb11-.;1hons. A
or obtaining the JATO !irin~ disla nre . •Jt\ TO takeoff
;u r~peed. JATO irroum.l run d1stanrP. and tot~tl dislance- to clear :'I 50-foot obstu·t.. ls de"frihed ln the
20. 000 lb
(K) Ambi ent runway a ir
temper atu r e .
tire lhnillng SJlt!Pd al a?S knots ~round !=IJW~I m:'S be
exceeded. Sinc-e t('mJJt'rah1re :\nd all\tud~ .1tt) not
mOl'e detailed E"XJ>l:lnarton of Lh~ r"U:\rgin,ll region ls
gh·cu u.n dcr i\lnximum 'f3keoff Wcisrht. The melhod
. ..........
Takeoff airspeed
JATO Firing Delay
seconds and for an 8-sccond cnglne deceleration time
STOPPING DISTANCE
B fr om mtllt>ry to Idle rpm.
F igure ll·l2 IS without
dr<lg chule deployed and figure 11-14 is with drag
• chute deployed.
!For fig\lr e 11 - JO)
l 1- 19
11 ·20
The slopping distance c harts (ligures 11-13 and 11-15)
a rc included primarily for use 1f the takeoff should be
§
~
NAVAm 0 1- 40AVM· I
Section XI
Part 2
S(>Cl1on XI
Part 2
SAMPLE TAKEOFF REFUSAL SPEED
Configuration: All
NAVAl!l 01-40A VM-l
Conf1gurahon~
HALF FLAPS
MODEL: A-4M
ENGINE: JS2-P-408
(A) Runway tcmpcratw·c
•• •• . ••
TAKEOFF DISTANCE
NO JATO
OPERATIONAL 18° NOSEUP TRIM)
DATA AS Of: I DECEMBER 1970
DATA BASIS: FLIGHT TEST (NAVY)
170
30' C
160
( D) nunw>y pressure o 1t11ucre . .
•
2000 It
ISO
CC) lndlcaicd
~lrspced
at abort . . .
140
91 KTAS
130
( D) Aircraft irross wct~ht • • • • • . •
20. 000 lb
(E) Heodwind . • . • • • • • • • • • • •
10 kn
120
110
=
..,z
.....
:z:
( F) Runway
gr ~tdien1
. . .. . .. .. .
-2 percenl
::>°'
.....
"......
... .,."
...
.....
ie
r- :z:
(G) Slopping dlstance . . . . . . . . . .
4500 rt
~
aborted. It ls not Ir.tended tor use In determlnirlf(
The data does not Include pilot
tcactton aud deceteralion tlme. Distances are based
on the 3J>plication ol rna:<imum bra.king effort wilhout
skidding the tires, tclow br:ikc energy limit speed,
and throttle po15itioned at idle thrust. To minimlze
dJvcrsion of pilot's ntention during this critical stage
of the t3keoU abort, it is recommended Lh:-1.l fh1ps be
I lelt In the position selected for takcol!. F igure 11- 13
tj ls without drag chut• deployed, and figure 11-15 ls
r-
l•ndin'( distance.
0
SAMPLE STOPPING DISTAN CE
............
0
.,.,_§
:a-=:
s
~g~
:~j
1
10
W with drru: chute doployed.
N ote
Slmttln~ down
<he en1.'ine ~t 80 KJAS will
shorten lhe J•olt•lUt considel"abh·.
I
SAMPL.E PROBLEM
2
s
0
Stopping Oistonce
6
I
I
I
I
I
2
3
..
5
4
7.
TOTAL DISTANCE TO CLEAR A SO FOOT OBSTACLE - I 000 FEET
(For figure 11-13)
Figure ll-8. Takeoff Distance
t l-21
11-22
7
9
FA 1- 14S -A
Section XI
Part 2
Section XI
NAVAJR 01-40AVM- l
Part 2
NAVAIB Ol-40AVM-1
MAXIMUM TAKEOFF WEIGHT
JATO FIRING DELAY
WITH AND WITHOUT JATO
HALF FLAPS
MODEL: A-4M
ENGINE: JS2- P-408
MODEL: A-4M
ENGINE: J52-P- 408
DATA AS OF1 1 DECEMBER 1970
DATA BASIS: FLIGHT TEST INAVYJ
~
t: t:L.1..
•TAKEOFF WEIGHT LIMIT= 24,500 POQNDS
25
t
TWO JATO' UNITS
HALF FLAPS
,
r
5
170
160
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: FLIGHT TEST INAVYJ
~~~~~·~,~~~~~~~~~~~!~.
..._,
"' -. ~.
Q
.•~;
,.,
......,
r
t
24
:i:
.....
140
:);
Q
z
::>
...0
:i:
=t
120
~
110
v
i5
22
...
,.._.
~ 130
23
/.,
21
£
"'<
....
::E
::>
20
::E
x
<
::E
19
18
•NOTE:
WHEN USING C-11 /C..11-1
CATAPULT, MAXIMUM
GROSS TAKEOFF WEIGHT
IS 23,500 POUNDS.
17 .
-20
-10
I
0
~
0
10
20
TEMPERATURE- DEGREES CENTIGRADE
I
I
10
20
I
I
I
I
I
I
30
40
50
60
70
I
40
30
I
80
I
90
100
50
110
120
I
TEMPERATURE - UEGREES FAHRENHEIT
fAl-146-A
JATO FIRING DELAY - 1000 FEET
Figure 11-10. JATO Firing Delay
Figure 11- 9. Maximum Takeoff Weight
11-23
11-24
FAl - 147-A
NAVAill 01-40A VM-1
Section XI
Section XI
Part 2
NAVAIR 01-40AVM- 1
Part 2
TAKEOFF REFUSAL SPEED
JATO TAKEOFF DISTANCE
HALF FLAPS
MODEL: A-4M
ENGINE: JS2-P-408
TWO JATO UNITS
DATA AS OF: 1 DECEMBER 1970
DATA BASIS< FLIGHT TEST lNAVYJ
MODEL: A·4M
ENGINE: JS2-P·408
170
"'...0
160
"'l
......fa
ISO
z
SPEEDBRAKES AND SPOILERS OPEN
HALF FLAPS
NO DRAG CHUTE
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
140
"'"'
< 130
...0 120
<
u
i5
~ 110 ,...._
=
-0
-20 -10
5
WEIGHT BASELINE
i
:i
ffi1.1.
"TAKEOFF WEIGHT LIMIT
~
20
: 24,500 POUNDS
:> ~
4
TEMPERATURE llASEUNE: o :(
_ 60
-120
10
20
30
40
so
22
=
~ tn
= 100
80
0
24 TEMPERATURE - DEGREES
CENTIGRADE
20
~:
!e
0
18
0
20
NOTE:
JETTISONING OF JATO BOTTLES
SHOULD BE PERFORMED IN 1.0g
LEVEL FLIGHT IN CRUISE CONFIGURATION, AT OR BELOW 400
KIAS (MAXIMUM!
GROSS WEIGHT
- 1000 POUNDS
NOTE:
BRAKE APPLICATION SPEED
IS LIMITED BY SAFE TIRE
SPEED. SAFE TIRE SPEED
Will NOT BE EXCEEDED
BY ANY TAKEOFF REFUSAL
SPEED COMPUTED FROM
THIS CHART.
HEADWIND
- KNOTS
40
I
RUNWAY GRADIENT
- PERCENT SLOPE
so
s
60
70
80
110
120
REFUSAL SPEED -
90
100
KIAS
130
140
150
FAl - 148
FA1·149· A
Figure 11-12. Takeoff Refusal Speed - No Drag Chute
Figure 11-11. JATO Takeoff Distance
11- 25
11- 26
NAVAIB Ol-40AVM-l
Section XI
Part 2
Section XI
Pa1·t 2
NAVAIB 01-40AVM-l
STOPPING DISTANCE
TAKEOFF REFUSAL SPEED
SPEEDBRAKES AND SPOILERS OP~N
HALF FLAPS
NO DRAG CHUTE
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
MODEL: A· 4M
ENGINE: JS2-P-408
SPEEDBRAKES AND SPOILERS OPEN
HALF FLAPS
DRAG CHUTE DEPLOYED
MODEL: A-4M
ENGINE: JS2- P-408
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
fl
-20 - 10
0
10
20
30
0
-20 -10
40
WEIGHT BASELINE
TEMPERATURE
- DEGREES CENTIGRADE
0
. I \~\\ \\\\\ ~
GROSS
WEIGHT
- 1000 POUNDS
10
20
30
40
50
TEMPERATURE - DEGREE C
GROSS WEIGHT
- 1000 POUNDS
HEADWIND BASELINE
0
0
HEADWIND
- KNOTS
20
20
HEADWIND
- KNOTS
30
40
40
I
-2
RUNWAY
GRADIENT
- PERCENT
SLOPE
0
RUNWA Y GRADIENT
- PERCENT SLOPE
2
4
6
10
50
60
STOPPING DISTANCE - 1000 FEET
70
80
90
100
110
120
130
140
150
160
REFUSAL SPEED - KEAS
FAl - 150. A
FA1 ·152
Figure 11-14. Takeoff Refusal Speed - With Drag Chute
Figure l l - 13 . Stopping Distance - No Drag Chute
ll-27
11- 28
NAVAIB 01-40AVM- l
Section XJ
Part 2
NAVJ\11'1 0 1-40AVM-1
Scrtion XI
P:H'l 3
STOPPING DISTANCE
SPEEOBRAKES ANO SPOILERS OPEN
HALF FLAPS
DRAG CHUTE DEPLOYED
M O DEL: A- 4M
ENGINE: JS2- P- 408
PART 3
DATE: 1S OCTOBER 1971
DATA BASIS: ESTIMATED
CLIMB
CLIMB
SAMPLE CLIMB SPEED SCHEDULE
Climb ch•rts (figure• 11-16 lhrough 11-20) present
Hu.• c•limh performanre for all drag index contigurations with the engi ne operating at milit.aa·y lhtusl.
Cllmb speeds arc pl'cscntcd in Cigur•c 11· 16 as :1 funclion of dr :.g index but independent or gross weight.
The f·l i mh 8peed st•hedule h:1 based on a minimu1n
time to climb and does not repa·esent a
n'l.;~ximum
t·:.rngc cllmb.
-20 -10
0
10
20
30
TEMPERATURE - ° C
GROSS
WEIGHT
- 1000 POUNDS
J•ue-1. dtslanre. and lime to climb are presented in
grou
hgurtJ!i 11- l'l through 11-19 as a run('tion o f
40
WEIGHT BASELINE
24
~ I IIIff//
22
20
18
I
I
urc 11 - 16.
SAMPLE PROBLEM
j
___________
______.......: ________
©
-
Climb Speed Schedul e
HEADWIND BASELINE
0
''
''
''
''
wf."1ght. prcssun: .dtilude. drag index. and tempera ture deviation lrom ICAO stanctlrd day. The cb.ta
a r c b:lscd on the climb speed schedule shown in fi~ ­
l©
(For lil(Ure ll-16)
(A) Crui~e :tltitude
10
©i
30. OOQ fl
FA,1•118
(13) Dr•g index . . . . . . . . . . . . . . . . . . 50
HEADWIND
- KNOTS
20
(C) Climb speed al Cl'uise (tllilud• . . . . . 292 KCAS
30
(D) Initial climb altitude • • . • • . • . . • .
40
(E) Climb speed at initial
altitude . . . . . . .
5000 ft
.. . . .
... ..... . .. . ..
(A) lnilial gross weight . . . . . .
18. 000 lb
( ll) Cr uise allitude
30. ooo
(C) Drag index . . . . .
rt
50
345 KCAS
(0) Temperature b.'\seline
- 2
RUNWAY
GRADIENT
I
0
SAMPLE PROBLEM
(E) ·rempera lur e devialion from
ICAO sland:u·d day . . . • . . . . . . • . .
• lO'C
(F ) Fuel to climb from sro
Climb Fuel
level
................
525 lb
2
0
4
6
GROUND ROLL DISTANCE -
8
10
1000 FEET
The method of presenting data for fuel. disl:tnce. and
time is identic:1I; tho1·efor e, only one sample is s hown.
COMBAT CEILING AND OPTIMUM CRU ISE
ALTITUDE
(For figure l l -17)
Combat celling. the altitude !or 500-lpm rate or
climb with militar y lhnu;t, and optimum c ruise
FAl - 153
Figure 11-15. Stopping Distance - With Drag Chute
11- 29/(11 - 30 blank)
11-31
I
Section XI
Port 3
Section XI
NA VAIR 01- 40A VM- 1
NAVA!R Oi -40AVM - l
Parts
SAMPLE CLIMB FUEL
SAMPLE CCMBAT CEILING AND OPTIMUM
CRUISE ALTITUDE
CLIMB SPEED SCHEDULE
MILITARY THRUST
so
MODU: A-4M
ENGINE: J52-P-408
DATA AS Of: 1 DltlMllR 1970
DATA BASIS: ESTIMATED
40
FA1·120
altitude, the attitude that will produce the mo.xlmum
(A) Aitcr:Ut gross weighl . . . . . . • . . .
lR. 000 lb
(8) Drag index . . . • • . • • . • • . . . . • . .
SO
cruise distance per pound of fuel, are presented in
Ugure 11· 20. The data are presented ~'s a function
of gross weight and drag lndex.
SAMPLE PROBLEM
(C) Comtx1t ceiling . . . . . . . . . . .
Combat Ceiling and Optimum Cruise Altitude
(Por figure I 1-20)
40. 400 !t
...
E
~
30
w
0
...;:::>
...
20
~
(D) Optimum C'ruise altitude . . . . . . . . • 34, 000 ft
10
I
CALIBRATED AIRSPEED - KNOTS
FAl - 121
Figure 11- 16. Climb Speed Schedule
11-33
J 1-32
Section XJ
Part 3
NAVA.IR Ol-40AVM-l
NAVAffi Ol- 40AVM- l
MILITARY THRUST CLIMB
MODEL: A·4M
ENGINE: JS2-P-408
26
FUEL USED
MILITARY THRUST CLIMB
1970
DISTANCE COVERED
MODEL: A·4M
ENGINE: J52-P-408
26
...
.........
24
"'0z
:::>
%
C>
§
24
5
<t "'
...
..
.....
"'0
~
20 :>
18
..
%
~
16
...
<(
14
>=
~
16
120
1200
;
i'
1000
g<
"'0z
:::>
800
80
<(
z
I
I
600
.....:i!
400
...u
0
>
0
u
0
20
tJ.
10
ALTITUDE
1000 Fl.
0
5
10
15
20
25
30
35
40
0
TEMPERATURE
- •c
Figure 11- 17. Climb Fuel
11-34
18
12
1400
~
~
14
12
...
......"':::>
l§
~
~
B
a.
22
...0
§ 20
:::"'
...""
~
<
>=
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
...
0
;?
22
0
§
Section XI
l?art 3
STANDARD
TEMPERATURE
•c
15.0
5.1
- 4.8
-14.7
-24.6
- 34.5
-44.4
-54.3
- 56.5
FAl-1 22
40
..
z
<(
~
0
IO
/J.
0
TEMPERATURE
-·c
FAl-123
Figure 11-18. Climb Di stance
ll-35
NAVAffi 01-40AVM- 1
NAVAfil 01- 10AVM-l
Section XI
Part 3
Section Xl
Part 3
MILITARY THRUST CLIMB
TIME TO CLIMB
COMBAT CEILING AND O PTIMUM CRUISE ALTITUDE
26
ICAO STANDARD ATMOSPHERE
DATA A5 OF: 1 DECEM BER 1970
DATA BASIS' ESTIMATED
MODU: A · 4M
ENGINE, J52-P-408
......--~.·~~........
~~---~~
"'0z
:>
2
~
MODEL: A-4M
ENGINE' JS2·P· 408
22
20
t-!:ttff:~J~Ttj::l:ittffift
50
:;;
~
!i:
C!>
w
8
..
...
..
3:
a!
DATA AS OF: 1 DECEMBER 1970
DATA BASIS, ESTIMATED
~
40
0
16
:>
;::
~
14
30
:>
..:::..."'
12
20
12
14
16
18
20
22
24
26
22
24
26
GROSS WEIGHT - 1000 POUNDS
50
:;;
~
0
8
..
...
5
..
....E!
40
0
:>
ALTITUDE
1000 fl.
0
5
10
15
20
25
0
20
10
0
30
35
40
(j, TEMPERATURE
-•c
c(
STANDARD
TEMPERATURE
15.0
5 .1
- 4.8
-14.7
14
- 24.6
-34.5
-44.4
Figure ll - 19 . Climb Time
16
18
20
GROSS WEIGHT - 1000 POUNDS
-54.3
-56.5
FAl-124
11- 36
30
:>
•c
fAl-12_,
Figure 11- 20. Combat Ceiling and Optimum Cruise Altitude
ll- 37/(11- 38 blank)
KAVAIR 0 1-40AVM-1
Section XI
:'!AVAii( 01-40,\V\1-1
Scc·t1on Xl
P:\rt.;
P>t't 4
Urlnth<'
K1 _\i;
"'
IJ •..,"lfj
o, "l.m
n. ;1;:.
RANGE
n.:1r.11
C),)o.jj(t
0,
t:'io
n.!'11
ll, "f\i
:)('l{l
I). ~120
-0.9:.!i
"· "i""
u. ">!il
\\'Jnd-IJ('$:.ft·t"
RANGE FACTOR CHART
altitude to sen level. A 250-pound !ut'l allnwan('f' l:ot
tndudcd tor approad1 and bndinlt
'rhe Range 1-"aclor chart (rib'\l r e l 1-2 l ) provldetJ a
means or corretlh~ spe<'iftc {or tolal) ran ~c tor
cxi stln~ wlnct clfcets. The 1lrcs(!otcd range raccors
constder wtnd speeds up to 120 knots Crom :tn}' rel:i-
h\'e whu.-t direction fo r ;tire raft speeds or 350 to
500 KTAS.
Oinb'O llang:t :md Bmgo Range .. Oea r f>own chart:;
are
pr~~t'u1ed
in fll:(UrP!' 11-23 :rnd 11-24
re~pec­
Uvcly. These chnns arc 1.u•o,·idcd rot ao a.lrl"1~H
configuration consisttni:c or four wtn.i: 1>Ylons. i:uns.
300·t..~llon f.'Xle r n:tl Cu~L t:tnks. with~ total
dr:t~; 1 ud&,!x of 6 l wirh ~._.~, r up :lnc-! 39 1 with ~cnr down.
;rnd two
The procedures Cor the ui-;.e of these <'harts nrc tden1it':1I tn th02'e for 1he f-"'uul(•d l)(•rk llarn:t~ ('hart; how~ver . an 800-pound fuel allow:rncc i:, included in
mngo Range and mngo Ran~c - Gear Down charts
USE
neterminc the reL1Uve wind direction by n1c:umring
!or approach ru1d londl111:.
(jn a d<"K:kw1i;:e di re<;hon from tl1e Cui:scl:tge rcfo r cnrc
plane) th<! angular dirh}rtmce heLWut.'n t he a irr rart
hc:adlng 3n<l thc true wind direction. At 3 given wi nd
direction. wind speed. and nircra.ft lrue :tir.i;pccd,
read the
r:111~c
Cattor. Multl1>ly the
LONG RANGE CRUISE
~pt:df ic ran~" by
thls raf'tf{c factor :o obtaln sl)<'cUl c range as affected
by wind.
The Long Range Crut8C cha rts :t re 8hown m flgures11 · 25 ll nd I 1.. 26. Lang a'!l.11!-lC eruh~t· iSj defined n::;
FOULED DECK RANGE
ihc hlghcsl Math number which will result ln
99 percent or the m:iximum miles 1>er J)O\lnd of luel.
E'.sscntially. tong range cruiwe pcrmitsnn i ncrc:tse
Occai;ions a rise
I
deck
bl'conu:~s
duri 1~
i.n
PART 4
carrie r 01>eralions whtm the
fouled and nirctaft c:l.1\1\Qt be laken
aboard until the <lzck Is c leared. In these Instances .
1t lb desir"bte for the pl10tl5 and the :ur o£Hcer to lte
:tw~u·e o( t.hc range c-a1>:1l>ilit i<!8 of 1hc unrccovcr cd
aircrnfl ·i n tlrdcr ~hat an immediate decision t·:t11 be
made concerning :he prope r cou rse or action. Should
the Cblim:ued "clear dec k"' lime be heyon<l lhe endur·
anc(! time or the ain·raft, lhcn tho :ti r c r :lrt m\ISl
OllhOr dep:lrl 1mrnE1d1ately for Lh~ bcneh u r land
aboard the ready deck oC a..11othcr carrier, ii :'lVnilablc. However, If it Is c lthcr desirable or mandatory that the alrcra!t orbit unill t he deck ls c lea r . It
is ncc<!ssa r y that the p11ot full y unde r stand the proper
procedure to obtain t he maxim\lm endurance with the
available fuel. Tile Fouled Deck Endui·ancc chart ts
shown In !igurc ll -32 .
The routed OCc k Rongc cha1't (llgurc 11 - 22) tabula tes
the range dist:1n<.:ts obtaln...'\blc for ...arious quantllles
of fuel on board at bnth the ini tial alHtuda and the
optimum, best ranl<e altiludt:>. The aitcrnft coMigu·
1-ation consists of fou r empty wtng l»'lons plus guns,
with o total dra g index or 33. Cllmb speeds and al r s1~~s fol' maximum range are included m the c h."}r-l
of 20 to 35 knots ln :iil'Sf><'f'd for an lncte:tsc oC
I perccm in Cucl consuinptlon. To use the Lon¥
nange Cruts<" Ch:\tts . :werage gross weii;ht. drag
index, ambient temperature. nnd de!;ircd rru1se
a ltitude must be known ror a Jth'en cruise lei,:. With
these k11own condhlons, 1011~ ran~c CJ'ulsc Mach
nunlber. engtne power seutns ln lerms of EPIC
and 6 pecHic r:l.ll!,rt! (naulu::.1 mile,. per 1><-Jttnd of fuel)
can be determined. Th<! 01>tlmum long range cniisc
altitudes arc aJso shown on flt-,rurc:.s lt-2a and ll -26.
~nd :l r e the :altitudes th:u w111 produce- the maxtmum
ntilet> per pound of fuel at the lon.: rnnge rruist>
I
I
II
I
r'b"'re
11 - 25)
I ~,
rcqutrcd to conduct :i ruaximum r ange descent from
(B) Cl'\li$• :illitude. , , .
I), ·~:i..
n. ~10.
(l.~11;
O,j1:J:l
fl.fl:!':"
u,~t;','-
O.:.i;JJ
n,nn-1
o.:.i~;.
0. ~I~ j
C>.9!)ii
(), 091
O.!f"'!..(
IJ.!IO'i
0.!":19:.!
l
n.!19':'
O. ll!~ I
1.06:.!
1.01ti
l.1!'11
l.l'ili
I
l.Oi-4
1. n~:I
1. 11:.
l.\lf;
I.I";
1,0li
I. Oi:I
l,l(ll
L 130
1.lfM
I
... o
o.~
:tao
I
25. 000 II
o. •t':"J
1.211)
l.<>·•:t
I . Uft'1
t.090
1.11.-.
1.11:!
1.~:i"'
1. o'i:•
1. n.... 1
I. Jn~
I lt:
1.lfll
1.1.;:;:
J.Q......
l. l:JJ
J.fj'o;
1.:?:N
.. . ,
1. 1)7~
l. Ui.
1.1~ ..
l. IV'I
l. .? h')
l. o;o
1.1'111
1. 1 12
1.Ml
1.01111
I.
l~!J
I. JU:!
l.J!J'.j
J. 100
1• •mo
I . ~:to
l.0'9
1.lif::
t . :?;?2
i.o ..o
1.1r.o
I, 2110
1. l)~;t
I.HG
l , JIO:!
1.:n2
1.111
F'l~urc
11-40
11.•u;I
I),~!!;•\
l.'.:'iC.
000 lb
11-39
o . .,.,~,
(), .. jl
as well as letdown tnstJ•uctlons.
The time at whi<"h letdown tS.hould l>e initiated iM gi\'e n
in tCTf11s or fuel on board. and represents the fuel
n, jilt)
I.I. ;:1J
'l. !! ii.
SAMPLE PROBLEM
(For
u. ':11
· 0(1
o. if;(I
I
I
l ..'O
- - - -1-----+-----11----n. i..a:-.
0 . 0 .....
0.'11'!
v.-..i;:
o. 'i;.!!t
conditio11.
long Range Cru ise-Mach Number and EPR
1110
0. 'i.'*~
I
I
'"
11-21.
Ra~o
Factor Chart
~
NAVAIR 0 1-40AVM - l
Scctlo11XJ
Part '1
Section XI
Part 4
NAVA!ll 0 1-40AVM- l
l>r:l):, JndC). • :Jj
Afrer-.:.ft \\'i'tght tL"ss Fuel) • 12 ,030 l'oundA
Drag Index • GI
Atr('rMt \\'eight (l.c&' 1-'u<'l) • 12 , 4a7 l'owkl$
All J')'lone nod Guns ( ~o .\mmo)
lh.:l!icn 't' fuel for J...:mUmg • :?:;O Pot.and&
All
JS~ -l'-·IO j
Sen Ll'\'Cl
..
..
H:mgc
R:U!f[('
Optimum
A111tudc
r.
10,000
Optimum
All nude
Feet
..
:.!0.000
H :Ulog('
Op1lmum
Altitud.:
Opt1nmm
Altitude
1t:.n1tt'
tbnccc
"'
:d
Optimum
Allitud4..•
20.000
Fc 1..'l
Altilud'-t
:toG
.iua
JU.000
290
/ill:!
10.000
;lu6
Saa
10.000
167
393
40,000
2M
.Sl!I
.I0,000
:l1.&
l..&4
10.000
r;oo
J4i
34V
•o.ooo
200
~&s
·~ .ooo
2~~
'02
J :">00
l 27
291
•10.000
1 ~2
31G
·1 0, oOO
2;;1
341
.10,000
40,000
1:100
lOT
:l:t~
-.io.ooo
l 55
:!6~
·lO,ooo
:?a
us~
10.000
JJ00 1-~·~"~-l-~~1~$~:._~~~10~.~oo~o__:-+__:1~2~·~r-~7
2~
11,.-_,r~'o.:...o~o~o~-t---;1 7A:---t~~
2~~s~-t:-4;;0:-.o:;;o;;;o_
7
~-~ !iuo1-_:":::"-+-.:.'::3:l:__~•.:.o:.:·.:.oo:.:o__:-+-'-:o.;.o-f-_71:::j;,.--ir-'::'o:-'::oo::o:--t--:'::,:-1--r-:-,1~:;:'.,,.---i:-4;;0:-.o:;;o;;;o:1 700 ,__:!_~~~-'0:_~1--.;."o:.:·::0070,.--t~~;::~~r-~-10::3:--~r-·::10:-.::oo::o:--r~1::0':---t~:-·;;;--~-r~·~o:-.o~o~o:soo JB
15,000
5:1
25,000
07
73
30,000
4~
If You Ar, ~t
~o.ooo Fc.•('t
Hnn,::u
H:Ulf:,C
30,'"oou
Optimum
J-'('('t
"'
Altitude
Ir \·nu Ar.- :u
,.t
H:itlF[\'
nt
Optimum
Ahitude
~; . ooo
J.'c4.'t
.,
Htmi.tc
0p(iMUnl
Optimum
Altitude
Altitude
.,
na.ug\.'
H;J.ng<-
40, 000
Optlmum
Altllutle
!"eel
,_
,
315
40.000
324
il0,000
9M
!l!l
IOtOUO
LO~
JIJ!o!
lGJ
3DU
10, 000
:13?
2300
1 12
:iu
.:o. ooo
202
~~:: ~:~
~:~
:::~;:
Pn!tuaurc Altitmk!
Full
-Kc"s '~~.
__
1100 ,__,_~-~-•1
~o.ooo
.\U1tuch.•
Optimum
Ahitudf'
1'\.•ct
r--N''-U
·10.000
190U
liOO
:J;Jfi
r---
l'f'tt
IG1
·SU, 000
Cnnsc Spt•cd
.._CAS
l\t'1\ S
l'ound~
HO
&s
Vl)U
At1..\
2a,ooo
210
0.76;1
200
Fib"llr e
1"55
l SS
11-22. l'oulcd D•rk R•nge
11-4 1
U \ 'ou An• al
40,000 l"cm
I'll
.,
n:tf16tl'
at
>t
:i.i>, llUO
011llmum
FeN
AlUtut.lt:
~Ml
:--'")U
t~~d
.i~G -----
-474
40, 000
Optimum
Allllufl*1
.,
H:1n1u·
·10,000
Optlmu111
Optla1um
F'ciPt
Allitllrk•
AltHUdl·
l\MI
N'MI
f.~t•N
~ ~!l-+---l-'3--t--10_._0_01_1_
·Hl,O~
•l22
•l;il
40,000
:n....
31S6
40,0UO
3~S
:rn:.
IO,Oo('I_
.io,c>~I)
~\3a_-+--~-'-'--+-•-'o. ooo
3:'iO
~:to
lO,ooo
lO,blJO
+-•;,;0•:.;;0.;;.00_;+-·-~~9-+--•..:.:J~'--f--'o,~,~~£._
S0,000
26~
2!.IJ
40, 000
:H'M
&Ol
·•O,oou
24:t
2.itt
40, ooo
:::67
:::-.1_-t_,_u_.o_o_o_
•l0,000
tM
2(12
1Q, UUU
;.!10
21U
1:ri'
,______
110()
04
-~
-ln. t>OO -+--1:_,1_+__1_r._•- + -•-o._o_oo_-t-_ 1G.l _
H-2
rn.ooo
11 ~
au~
HH
40.000
11-1
~
.1'l'\IUU1"C Allltud1.
Climb l>J.X'Ctl
MiHt1U'\' 1'hrulllt
C'."nJitC' six·W
l-0f't'I
h('Af; M:ach No.
h.(.'AS
11-42
10,~
'i9_~_3'-S-'-._uo_tt_
22J
1200
I
-10.000
1211
;2
Hang-(>
.Kaq:i;l.l
:~:::
--1--..fO,llOO
174
-"f---'1-'-02'--ll-..;.·IO;.:•.;.o,;..OO;_+-''°'O..:.G_-\a:;, ooo 1:cd
--
~:~
~~:
:1-40
2Gl1
20,001>
L>eFccnt Sflt't!<I
Suui l..t't(k>wn frooi At&itudt
K C"A1=
l'ounci~
t.n1ln~: hlh: - l"lpc"c."ffbr:t.k('J'i C10FCfl
~
rn.ouo
-~-~~~~~"'-~~~
whh hu•I H1• nir_11_
111_n~~--
~~~~~~~~-1~~-
~~---
~ :~------+-----:~-~-----
-+------1-,7------t----..,:l~
25$
z50
1 ~7
'l(j'j
1"l7
1.c1o10
Q.71H-
240
,.,
~9~
O. 7&1
210
1S7
9H
!140
30,000
3!J,U-O.):___-!----'o"-.~7r,",4--t--~22:;
10. 000
-t!> 1 ooo
_
IU,O!ltl
--+--'-"-·o_o_o_
~IO._~~~--t-~_..:2~00:__~.+-~~~~--'1~~=7~~~~~-t----~~·~53.,;_~~~~-
--2-s-.-00-_o.~::::::::;::::_:--.,o-,
. ,,..,r.4,.,..-- -t·
0. 703
2:.!1
..._ 263
LO, 000
o. 7fl.1
<0.000
-~,.-:;,.,:--+-,:c:~-::,.,:..,.:--1--,,.~o:-1::--+- ~:~
--+-----1-1---+---+-10';'
•t0, 000
17t
1:?3
-
~MIO
0. 78.1
.. o. 4)()0
:lOU
10•1
10, oan
4 _;•:.:0.:.;,o:.:o:.:.o_-1-...;.:!1.:.;s;_-+--a:.:5:.;;~_-+_'1-'-o~·'"'=-o
Ocwcc.•nt Spi.-cd
:J6S
o. 783
n·<:t
37.it
1 7~
10,000
30, 000
Nb.II
-I~
0Jl(lmum
Allltudc•
:SU.i
S·n5~~~~·l
:!5,000
:-;'\u
40.-000 --t-~3_
4 _1-;---H_S_-t-~-0~,0-11<1_
'-
Start Ll•tdown Crom Alhtutlc.•
t.:ngtnt.• Idle - Sr.;1"':.o'C;::db:::rc:•::k<:_:•:_
· l°'1c:.••°'c:.;:'d-t---''--'"'lh'-'-h'--""-'1_1!,-,e_m_o_1n_1"~~·--
0J)(imum
AJtfU1d1•
l 20
If
NMJ
l&OU ,_____
lO. 000
Altiludc
. _ 3::.:3:.:&_
UYou An.- 11l
30, 000 1'\:ct
- - - - . - - --..----·
ll:iMg•
ftnnge
01
nr
~fmum
Ovt.huum
J.'ccl
.io, u_oo_-1-__
10_0_+__1 _~0_,__,___10_._o_oo_-+
12;,
.;1
_
.
20, 000
.---Fl'(ll
36()
rn
G,000
13,000
::~
·I-
17001--"-"-+---t_'i:J_ _t-_IO,l.>OO
~
Climb S.1](.'t.'tl
M11it:trv 11lru111l
'12..
1s. ooo
t:
100~1~3~5~+~~14~s:._~~~
10~,=oo~o~-+-_..:1.:.so:_-+~__.:.
1 s~1~-t~1~0~.o~oo~_,~71=~a:---t~--:-:'6~3~-t:-'::o~.o~o~o91
?\Ml
25:.?
1;
oooi-.:t~s~2~-l-~=20=1__:~~·~0~.=oo~o~-+----=2.:.02:_-+~__.:.'~.:.J~-t~',-_".:..·",-_°",-:--1~~"~11:---t~-"~1::1~-t:-'=o~.o;;;o=o:i,>i
~1'U
~ 13001-_4_8_-+-__a_-J 30,000
noo 1--...:2:.:2.:..•_-i.1----=-·';;;_:_'.:.•:_-_-:,_-_.c.
..4~0.:...~oo~o~-=_-=_:-=_-=_~:.:·_&:i'"'·_-_-_-tt----_-_--:_2-s_2'=_-=_-=_~t=_-=_-.,.,10'=_.-::oo,__~,,o'=_-=_~t=_-=_~2~1.,..1::-----~:_-_-_-=2;1~-,_-_-_-~--~'::o~.-;;:o;;;o;;;::o~
500
A1tilude:
2500
ot
:•2·1
fJµUmum
l\ltiludt
f4.'('l
~100
30:1
O J1lm1uin
FcN
40,000
1&00i-:a:.:".:.o~-l-~="1XJ~·__:~l-':.:o.:..oo
:.:.:o~-+-_..:3.:.:;;i:__-l-~-3:.:G-:8~-t~4::0.:..,o::o::o~+--::"::'':--t~~3:;:'~'~-t--;'::o~,o=n::o40.ooo
10.000
100
2:Hl(I
301
..
•·~d
Run~c
AlUludc
N"MI
t.;)OO
20.oon
R11nJ.li'-'
al
Or,1fmmn
171'1
i--:•:.:1:_0-1_ _.:.·•r..::Mt___.:-1-•...:o.:..,o'-o-'o-+_'_s2_+--'-1_1_-t-',-,o_.0:-:0.,..0_-t-:-1·::,9---t--4:-:':::9--t:-1::0~.o;;;o::o_
i1t
-
NMf
11oni-:3~w=-~-1-~.:.•':.:1~~1-•:.:o.:.,o~o:.:o~-+-___.:•.:.•'=--1-~-'::':.:o~-t~'-:o.:...o:.:o::o~+--::'2::',.--t~~'::2::"~-t:-'::o~
.o=o::o1:wo
OptJnmm
_,___
Allllml.v
Rtlll'lp,4.'
1-~~+-~~~~1-~~~-+--
i
1 Dcc.·1.·m•.>cr 1370
Jr Yoo A ro nt
10,1)00 Fflt1 t
2'0'00
2300~··~99::__--1~....:::j":.:·2__:--1___.:4:.:0.:.,o:.:o~o~-+--"~::",.--+-~-5~7~1~-t:-4::0~,0::0::0~-r-;'.5"::'9:--i-~-5~7::!'~-r--;'::O,~O~O~O­
l901)
If You Are al
l.cvcl
ltnrig(
3t
,§
lf Yt>U Arc :n
+10,000 r-...
:lS,000 Fct't
__
Optin\um
ns f'J'"
Oatn JWutis· Ea;tlmatca
~ti
1900
!
l>nl:t
If \"ou Al'L' ul
}c~t
:taoo
~7
1-:x~rn:ll f~nkt<
M1Jdul: A- -IM
t;np.lnc: .J52-J''-10f.&
If YQU ;\rt· :u
If \•ou ·" '~ :it
10, 000 t'cct
H You i\.l"f' nt
Gun11. CNo An1mo) , nnd 'T\\•o :JOO-Gallon
R(:ffCT\\I l"u.t.:I for L.andlng • AOO JJound11D:ttr> ."I~ nf: I J)c.rcmbu r rntO
Ontn B:1H'w: fo.. J>l1m::l.h_·d
Mo<h•l: A-·I M
t:ng.inl•:
J')'lou~,
_ 1_
-~---o_
. ·_.e_•-~
__
1~7
2_0~~--~-----1~_1_ _ _ _
A01
_ ....__
927
NAVAlR Ol-40AVM-I
:X,ctton XI
Part -1
Section XI
Parl 4
NAVAIR Ol-40AV.M- l
LONG RANGE CRUISE
MACH NUM BER AN D EPR
MO DEL: A· 4M
ENGINE: J52- P-408
lJl'tt:!lm.lL'll.
3!'1
t\1n·r:'IJ1 Wt'ii;::ht (IA''" Fod)
12. tii Jlouflc1"
\fl P\lon,; 0 Gun!> t~u \mmu), ;a:nd T\\O 300·<t:iJh>n L~1f'n1:il 1'!lJtkir.
lh.•t.:('r\{ l\wl tor l_,;-mdm;t
..;oo roundl!
~Hwl<'I.
\· l~I
En:.'1nt':
J:>t
IJ:tl3 :Lii of; J lkCcntlA.'J' l!/7\1
11:u:1 Baals: 1-.stun:ntd
l'-10~
l( l w
ltaJij.tl ;LL
t•
I
t
I( Yi.JU \re
LC\ c1
lt:Ul~~
Upt1mum
10. uoo
1-tan~l· al
0pumunt
at
!\)UU.i\l t.·
,\JtitUt.lc
~·c·1.·t
1\llitud4:
XMJ
~)U
V~<'I
:'\~II
:ou
FC~1
2100
1:.?t"I
2~6
30, 000
Uri
t:.!!l
:10,000
:nou
1(1 ...
l'3
30. ooo
ll"i
:.!()()
30, 000
~aoo
9:;
J•JO
ao.ooo
t:JJ
liG
!JQ,tlUO
2100
,3
1:10
:10, 000
11~
1.. :~
:10. 090
ln<lO
10
113
30, 000
1•:•
I.?~,
30.000
Jit10
;\'j
>IU
30,0011
'l
Hl:'i
:~o .
foOO
I>
r,$
.:.>.000
b~
1:iuo
:l:t
13
io.ooo
19
I IOO
10
10, 000
33
l
23
It 'ou Arc at
!
~
~iUO
to. 000
..
.. 2.6
w
:::>
;:a
~
2.2
i5
~
2.0
1.8
1.6
HtutJl.l :at
OpUm\ltn
l<am:c at
IC:anu: :u
011t1mum
30. U{)ll
llµUUmlll
t't•t.•I
.\llJtudl•
.\hllu1.h:
Jl't.'l
\1Utm1c.•
:"\:\II
KMI
Ft't'l
:\~U
i\MI
lt:d
;!J.'1
l3'
30.UtlO
~;;;,:
.!.;,!
;,H•.000
0Jlht\1Um
\)UltH.lc;
30 .000
2.~li
.'....!,
~U. OllO
nt:?
30, 000
J(l(j
2Uti
JiJ,UUO
!lOO
lG:i
16t1
30. ooo
JS-2
l"':l
30,000
l:JOO
1:u.
JU
30,iJOO
1r..~
n~
JO.Iii)\)
1700
Ill
121
30. 000
l!J-1
134
:so. UUQ
1:100
M
91
!I0, 000
110
110
.to.000
1300
f"I
1:.!
30,0-00
l'l:'1
,5
$0,ttu<I
1100
"
I'
l·l,,f)OQ
lit)
li\t
:so. uuo
--
M.•1-rt 1..<'ldo\\lt
I" roll' .\llitodt:
Cllmb::i1"1CC'd
Ahnude
Cruise
t.. n:.tlnl' Hlk -
M1Uu1.n· ·rhrusl
!'JX-'(.'d
b(-)Cl'dbrakctli (.'h.'1:;,t'<.1
Fcu
K(' i\S
KCM.i
l\C..: .\."'t
Poundi.
;HO
.! 1 ~
mo
Wllh rud IU.•m:ilnhll:
.i.000
2•0
2JO
JriQ
'""
10, 000
:!·lO
2(1..;
1r.o
':w
15. UtlO
l IU
:lU!i
lli.O
ltJ,UOO
l:iU
"00
Jf.11
--- ---
i:i . OOU
.l(I:,
l'J.)
lbU
'i(,Q
30.00<l
l~.;
J)'li!j
160
.. 10
11~24.
~
.. 2.•
...
2t.1,UOO
3:;
Rnng-1.1 al
:?O.UGO
figure
I
2.8
0
L( 'lw ,\n,: .l1 .:JO. UUO 1-t.·t.'I
l"ct:l
Ol.:.!Ci.:nt Sl)('t-"Cl
Sfota
!
3.0
2.1.U1JO
21:,
>-
3.2
30, V\l'I
'I
l~:-i
.:?!!Oo
L••\••I
ooo
lil
;?.'iOU
Prrssure
at 10. 0llQ rc<'t
Opt1mun1
Of)tlmum
,\JtHmh.•
l.4.''t.'I
;fJ
,\re :u Sc:i
ll::ul.f:C :Jl
Sc:a
DATA AS OF: 15 OCTO llEll 19 7 1
DATA BASIS: ESTIMATED
3.4
Bin~o
Ra.nt.t(l
'">) .J
·dtl
.. :;i)
Gear Down
1.4
26
"'z0
:::>
~
24
22
20
I!
...
..
0
Cl
.~
~
I
16
14
12
FAl - IU
Figure 11- 25. Long Range Cruise - Mach Number and EPR
ll-44
tl-43
18
Section Xl
NAVAIB Ol - 40AV11'1-l
Pai·~
4
LONG RANGE CRUISE
!';ection XI
NAVAIR 01·40AVM- I
Part 4
(C) Orll{I: index
JOO
(DJ Mo1·h number ..•.•..•••• . . •••
0. 655
SAMPLE LONG RANGE CRU ISENAUTICA L MILES PER POUND OF FUEL
NAUTICAL MILES PER POUND OF FUEL
MODEL: A-4M
ENGINE: JS'l-P-408
ICAO
PRESSURE
ALTITUDE STANDARD
-1000 FT TEMP. - °C
DATA AS OF: t 5 OCTOBER 1971
DATA BASIS: ESTIMATED
"'0z
26
...0
24
OPTIMUM LONG RANGE
CRUISE ALTITUDE AT
DRAG INDEX
8
22
0
00
200
x
20
i
18
:>
0
..
I)
..
::i
0
I)
~
..."'>
<
0
s
10
15
20
25
30
35
40
(£)
£PR • • . • . . . . . . . . . . • . • • . • • 2. 35
15.0
S.1
-4.8
-H.7
-24.6
SAMPLE LONG RANGE CRUISEMACH NUMBER AND EPR
-34.S
- 44.4
-54.3
-56.S
SPECIFIC RANGE
- NAUTICAL MILES PER POUND OF FUEL
.05
,1 0
• •~
.20 .25
.30
.35
.40
16
14
t
12
MAXIMUM RANGE CRUISE
Maximum
Ran~c
Cruise chttrts. shown in
f~urea
ll·27, 11-28. ;t_nd 11 ·29. present the n('ccssnrv
mission plrmning d:1ta to set up maximum ran~C
cruise schedules for a const:int cruise altitude. To
long Range Cruise-Nautical Miles per Pound
of Fuel
(For fli;uro 11 -26)
(fJ A\'eragc
~ross
weight . . • • . . . . , •
18.000 lb
use the maximum r•tnge rharts, the :tveJ':tge gross
wetght. CJ'UiSC altitude, drtlH index , ~ntbtf'nl :1ir
1emper:1ture. rcl:.ti\!C wlnd . :md ~round d1st:1ncc to
he covered mul'Ot tw known. It is then possible to
determine trut! M;1ch number. true :'llrspecd. lime
enroutc. oautic!al miles per pound or fuel. fuel Clow ,
ar.d total fuel required. Optimum <-..tu1se a.lt1tudo
(altitude for Uesl r;Ulge) lines ;trc superimposed on
the J)rC$8ure :1Uitude plot.
(CJ Pressure nlliiudo •••• .••.••.•• 25,000 fl
SAMPLE PROBLEM
( ti ) Temperature devlmton Crom ICAO
standard (Ambtent temperalure • ... 24, 5 ~(.' ) , . . . , ..•.•• , • ,
10
..... ... . . . . . . .. .
100
(J) Dr;ig llldcx
c
MaJ<imum Range Cruise - Time and Speed
(For
(K) Prci:;suru :tltitudc ..• . . • . . .• , ••
FA1 · 167
(1..) Ambient tcll'lp~r,ature , . • . . • . . • .
-24. 5 ~ C
(M) Nauurul mllea per pounll or ruel • • .
O. t50
Figure 11-26. Long Range Cruise-Nautical Miles per Pound of Fuel
11-45
11-46
Cl~uro
l 1-27)
25,000ft
(A) Avcrngc g ross
wei~ht
for
crul:;c leg, .• , . . . . . .
18.000 lb
I
Section XI
NAVAI.R Ol -40AVM - 1
Part 4
Section Xl
Pa:t·t 4
MA XIMUM RANGE CRUISE
MAX IMUM RANGE CRUISE
TIME AND SPEED
NAUTICAL MILES PER POUND OF FUEL
MODEL: A·4M
ENGINE< J52- P· 408
DATA AS OF: 15 OCTOHR 1971
DATA llASIS: ESTIMATED
M ODEL: A·4M
ENGINE: J52·P· 408
80
...
26
0
z
...5
24
§
22
.
NAVAIB Ol-40AVM- 1
OPTIMUM CRUISE
ALTITUDE AT
DRAG INDEX
70
I
60
0
100
200
:::
...
so
t
40
...
0
z
::>
~
24
§
22
z
:z: 20
...
~
0
15.0
5
5 .1
10
15
20
25
30
35
40
-4.8
-14.7
- 24.6
- 34.5
-44.4
- 54.3
- 56.5
.40
t
__,I
I
I
I
;:
C>
OPTIMUM CRUISE
ALTITUDE AT
DRAG INDEX
0
L..Gl----- 100
1-o-'-l--l.-- -200
PRESSURE
ICAO
ALTITUDE
STANDARD
-1000 FT. TEMP. - ° C
SPECIFIC RANGE
- NAUTICAL MILES PER POUND OF FUEL
.05
.10
.1)
.:lU .25 .30 .~)
::>
...:EI
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
26
20
~
0
::;
16
lO
~
.
14
0
~
'
12
...
.9
.8
:
.7
ID
:E
::>
:z:
:z:
u
~
..
w
~
.5
.4
.3
.2
50
0
-50 -100
A MBIENT AIR
TEMPERATU RE
200
250
300
350
400
450
500
MAXIMUM RANGE TRUE AIRSPEED - KNOTS
- •c
FA1·160
FAl-169
Figure 11- 27 . Maximum .Range Cruise - Time and Speed
F igure 11-28 . Maximum Range Cruise - Nautical Miles per Pound ol Fuel
11-47
11- 48
Section XI
NAVAlR Ol-40AVM-l
St.>t:tiou XI
NAVAln 01-40AVM-l
Pai·l 4
Part 4
MAXIMUM RANGE CRUISE
(Ill Crui se nltltude.
25. 000 rt
(C) Or:\~ inclt·~. . . • . • . •
100
{0) Tnw M:t('h m1mbcr • . . . . ,
0.615
FUEL
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
MODEL: A-4M
ENGINE: J52- P-·408
8
7
"'0z
::>
I!
6
tClllJ)Cr'3U1re
JQOC).
(F) True airspeed • • • . . . . .
~
5
(Cl Tnilwind.
...
"'5
0
5?
"'
4
~
10
0
-
II
I
I
I
I
.40
0
0
z
.35
\ «' c;.
I
(M ) Tem1>c r3tu1-c d!!viation frum
JCAO standard (Am,JlPnl
tempoJ-atui·c -24 . soci
18. 000 llJ
25. coo ft
. •...
SAMPLE MAXIMUM RAN GE
CRUISE-TIME AND SPEED
28.0 m:n
~
100
(Pl Crul~• nllltud<· .
25. 000 II
(Q) Ambient temperature •
-24. soc
(R) Nautor:tl mllcsp<rpoundofluul.
0 152 N\11 lu
'·0
i5;::
.10
~I
.05
0
1000
2000
3000
4000
6000
7000
FUEL FLOW - POUNDS PER HOUR
I
Figure ll - 29 . .Maximum Range Cruise - F uel
11-49
11-50
~
II
I
FA\·l'H
FAl - 170
d
II
I
!
5000
!
CR~ISE- ~
SAMPLE MAX IMUM RANGE
NAUTICA L MI LE S PER PO UND OF FUEL
I
0
I
'J
I
~i
....
I
'
(NJ Ora~ lndcx.
or
u~
.tr
I
co~~\,
.20
i
r
10°c
380 kn
200 NMI
~
;.
11,_~1' I
~~ .25
ii:V>
!
1"1m• • • . • • • • •
~Toss wcl~bt.
~Ofo~I
.30
IM::>
~=
uA.
II
G (,I)
(Kl A\ct.lt;ti
SO kn
~ (H) Gmund di~t~ncc • •
1----
u:~
-24. s0 c
3
2
(For ligUJ"(" I 1·28)
(I..) Cruise nltltuue .
(€) Am,>icnt :\I I" tempera.lure al
°'"'"" .oltitudo (ICAO ~Lllnclard
Maximum Rang e Cruise - Nau tical Miles pe r
Pound of Fu e l
!
W
NA VAIH 0 1-40AVi\l-I
P;lrl 4
~
of Fuel charts. tht! aver.al~~ g:ros5 wct~ht. 1u·c~~ur(
'1ltlludc. cruise l\t:u·h num'Jer. drJg Index. :ind
:uubtenL :Ur tempc1'3lurc n1uhl lH-' known, I t \5 then
1.>n:,sible to determine true nh·:ipo:ed, naulit'••l milt 1 ~
1>cr 1>0und of fuel. fuel flow. :tnd cn!,llnc ptCS!->un
1·:tt10. It is J'C:commPndt>d 1hac cngfnc pre~surc l'::ttio
Maximum Rang e Cruise - Fu e l
!
I!
(S)
~outteal rmlt ·~ pi•r pound
nf fuel • • • • . • • . •
0.152
N~fl
'Jh
be U.!!:~d as the prlm:u·y O\<!asurcnwnl nf 1•ndm:• lhrmct
oulput r:1 lh ttr lh~Hl h •el flO'l' when ~Cllinq UIJ cruiN<'
schc<lules.
(T) Ma'.\1mu111 r.:mg.- Lnu" :ur8J>eed
380 KTAS
(W) Fuel !low
2500 lb hr
(X) Time . .
28.0 mln
Nautical Mile s per Pou nd of Fuel
1170 lb
(For r!~'IJrc 11 -30. •ho••l I )
!
(Y) Tot:ot fool r<!qulred .
NAVAIB Ol -40AVM-1
Section XI
Part4
Section XI
I
I
!
NAUTICAL MILES PER POUND Of FUEL
I
B
MODEL: A-4M
ENGINE: J52- P-408
DATA AS OF: 15 OCTOBER 1 971
DATA BASIS: ESTIMATED
10---~~....
MACH NUMBER FOR MAXIMUM
RANGE CRUISE AT DRAG INDEX
0
100
20
SAMPLE PROBLEM
s
(A)
14. 000 lb
(B) Cruise pressure altitude
30. 000 h
SAMPLE MA XIMUM RANGE CRU ISE - FUEL
!
6
7
.....s~
.....
.."'
..
~
::>
:i::
0. iS
9
6225
10
....
t:
~
(E) Thrust 1·enuin·d h ;1111'.;t
clean al remit • • • . .
E
0
(CJ D1·aK 111dcx = 0 (b:.tt(.)lifle)
(I)) Cruise \Jach number .
.D
11
SAMPLE NAUTIC AL MILES
PER POU ND O F FUEL
v
;;;
z
~
d
12
l
.2
r11.1-1!.&
NAUTICAL MILES PER POUND OF FUEL
·I
N011ll<"al \ lilcs por Pound of Fuel ch01·t s (figure
i
•
.s
.6
.7
.8
13
.9
TRUE MACH NUMBER
c
"'
z
26
0Q.
24
::>
II
.3
11-30. hhtwh J th1·Qul!h 6) )Jretj:ent rrulse data
lhro~houl the $tru"°' weighl. ni rspeed. and dra~
ran~c or
~cn l ed for US<'
Index
the ni1·e1-n!l. Thc&o d;:1lfl arc p r ewhen crutse d:ua nre required Cor
f::t :;peed rond1tmnn t>lht r lh;m milxlmum range or long
II r ;mp;e cruise. ·ro usa Lite NauLic:tl Milos per Pound
~
22
....
:r
!2
20
...
18
~
..
"'0
I)
:;
~
16
14
~
<
12
FA l - 171
Figure ll - 30. Nautical Miles per Pound of Fuel (Sheet 1)
11- 51
11- 52
NAVA!R Ot-40 AVM-l
Part 4
Pai·t 4
NAUTICAL MILES PER POUND OF FUEL
MODELt A·4M
ENGINE: JS2- P-408
NA VAill Ol -40 A VM-1
Section XI
Section XI
NAUTICAL MILES PER POUND OF FUEL
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
MO DEL: A·4M
ENGINE: JS2-P-408
.8
.7
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
~"'~"'"'"'"'~"'~"'~~"'"'"'"'~
NO REYN OLDS NUMBER EFFECT ON FUEL FLOW
.6
.0
.s
E
,,,o
....a
....
...."'
..<
.4
;:;
a
.3
:;;
.2
:z:
t:
~
v
40
30
z
~
20
v
12
10
13
...
"'"'~
.9
......
.7
"':z:z
.6
<
.s
..<
:i:
v
:i:
...
....."'
- 10
~ -20
.8
..:::
0
I
.4
.3
~
~
<
-30
-40
-50
-60
-70
.2
FAl-172
-eo
FA1 · 173
F igure 11-30. Nautical Mile s per Pound of Fuel (Sheet 2)
F igure 11-30. Nautical Miles per P ound o f Fuel (Sheet 3)
11-53
11- 54
Section XI
Part 4
Section XI
Parl4
NAVALR Ol-40AVM- l
NAVAJR Ol - 40AVM- 1
NAUTICAL MIUS PER POUND OF FUEL
NAUTICAL MILES PER POUND OF FUEL
MODEL: A-4M
ENGINE: J52-P-408
DATA AS OF: 15 OCTOBER 1971
DA TA BASIS: ESTIMATED
10
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
MODfl: A·4M
ENGINE: J52- P-408
PRESSURE
ICAO
ALTITUDE
STANDARD
- 1000 FT. TEMP. - •c
10
0
l S.O
5.1
s
-4.8
10
IS
20
25
30
3S'
40
4S
-1 4.7
-24.6
- 34.5
-44.4
-S4.3
- 56.5
-56.S
2
.so
2
3
4
6
GENERALIZED FUEL FLOW PARAMETER
7
(UNCORRECTED FOR RNll
.45
12
.40
"'
0
11
:::>
~
10
z
.3S
..s-.
.25
8
0
6
:::>
5
~
4
..."':z:
...
......
..
"'
.....
t;
z
:::>
0
.20 ~
~
7
"'5
0
~
0
.30
...E
...:::>
...
...0
.IS
5;::
:::>
I
.10
3
50
25
z~
0
0
-25 -50 - 75
AMBIENT AIR TEMPERATURE
2
-•c
fAl-174
Figure 11- 30. Nautical Miles per Pound of Fuel (Sheet 5)
Figure 11-30. Nautical Miles per Pound of Fuel (Sheet 4)
11-55
11-56
fAl - 175
NAVAffi Ol- 40AVM- 1
Section XI
Section XI
~
NAUTICAL MILES PER POUND OF FUEL
No uticol Miles per Po und of Fuel
I
II
DATA AS Of: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
~
..:e
:
(,J)
Tot.a.I thrust requ1 red1 6 anib
!
.8
.7
I
6225
0 . 7S
(II) Drag rndex • . . • .
.9
~
SAMPLE NAUTICAL MILES
PER POUND OF FUEL
(For f11,'Ure 11-30, sheet 2)
(F) Tllrusl required Aomu clean nircrn!t . . . .
MODEL: A·4M
ENGINE: J52-P-408
NAVAIR 01·40AVM-I
Part 4
Par t 4
JOO
8820
.1
SAMPLE NAUTICAL MILES
PER POUND OF FUEL
:>
z
.3
.2
200
300
400
TRUE AIRSPEED - KNOTS
600
Nauticol Miles per Po und of Fue l
.50
.45
(For flJM'e 11 - 30. sheet 4)
(P) Tot:tl thrust required, ~ amb
8~20 lh
(Q) Cruise Mach number . . , .
O. 7S
I
No uticol Miles per Pound of Fuel
(R) Gener alized fuel flow µnramctcr
(uncor rected for ReynoJds
(For lib'Ure 11-30. sheet 3)
I
I
, • . . • .
(S) Reynolds number Index (RNJJ
(L) Pressure :tltltude . .
30.000 ' t
(M) Crui8e Mach m1mber •
0 . 7$
(N) Reynolds number L'1dex (Rr<1)
o. 503
fAl - 176
Figure 11- 30. Nautical Miles per Pound of Fuel (Sheet 6)
11-57
number effect)
6. 23
(K) AmUlenL .1ir lempcr atur e •
11-58
• .
O. 503
(T) G<!llerallzed fuel flow
par~metcr
(corrected for
Hcyuolds number effect)
• • • • •
6. 41
I
NAVAJll 0 1-40AVM·l
Section XI
P-..t rl 4
I
SAMPLE NAUTICAL MILES
PER POUND OF FUEL
Sec tion Xl
P;irt 4
NAVAIR Ol-40A VM-t
Nautical miJes per
SAMPLE NAUTICAL MILES
PER POUND OF FUEL
pound or [ue l
Fuel
now
SAMPLE PROBLEM
( F') Total thrust requi red/ A nmb
8820 lb
I
(G) True l\.fach numbe r
0 . 75
d
(II) Engine pressure rntto
2. 55
0.174
Engine Pressure Ratio for Cruise
2550 lb/ hr
( Fo r llgur e 11-3 1)
SAMPLE NAUTICAL MILES
PER POUND OF FUEL
SAMPLE ENGINE PRESSURE
RATIO FOR CRUISE
I
~----········-··-
Noutical Miles per Pound of Fu el
r:
g
!
l
Nautical M ile s pe r Pou nd of Fu el
( l'or Cl1tUrc ll -30. •hect 5)
I
(l'or rt1?urc t l-30. sheet Gl
(Ul Gencroltzcd Cucl rtow
parameter (corrected ror
II
Hcynold6 numher eUect)
(V) t"rulsc Mach 11umbc1· •
(W) Pressure
I
~llitlldo
• ,
G. 41
(A) TJ•ue Mach
o. 75
30.000
numl~r
, . . . , • . .
O. 75
(I
(0) Amb1ent ,,ir tcm1>cratul'e . . • • . .
-44. 4oc
(C) T rue :urspeed
H2 kn
(X) Ambient 1dr 1ernpcrature .
(Y)
~aul ital
mtle5 JM"r
1'°'1nri ur Cu•I
• • • • • . • • • • .
O. 174
. . . . . . • . . .
l t-59
11- 60
NAVAffi 01-40AVM- l
NAVAJH 01-40AVM-l
Seclior. XI
Section Kl
Part 5
Part 4
EN GINE PRESSURE RATIO FOR CRUISE
PART 5
ENDURANCE
FOU LED DECK ENDURANCE
M ODEL: A -4M
DATA AS O F: 15 OCTOBER 1971
DATA BA SIS: ESTIMATED
ENGINE : JS2 - P-408
identical to those (or the Fouled neck F.ndur::uH't'
chart; however. an 8QQ.p0und fuel allowance is
included for approach and landing.
14
Occasions arise during carrier operations when the
deck be comes fouled and airc raft c ;:innol be t;tken
aboard until lhc deck is clca1·ed. t n Lhesc insta:1ces.
u ts <tes1ra.01e t or tne puots anci tile a ir 0111ccr to be
aware o! the endurance capabilities or the unrccover ed ai rt raft so that an 1mmediate decision ;:;m
be inade concc1·ning the proper course of action.
13
12
"'
0
z
11
...0
10
Should the estimated "clear deck" time be bcyot1d tl1c
I!
endurance time or the alrcrait. then lt must either
depar t immediately for the beach. or land aboard
the ready deck of another ca1·rier. i! available .
However. if it i11 either des1r:ible or m~u1dalory that
the alrcralt orbit until the deck is clear. it is
necessary that the pilot fully undc-rstand the proper
procedu re to obtain the maximum endurance with the
::i,vailah1e fueJ. 'the fouled Deck Endurance chtlrt
(ligure 11 -32) tabulates the endur•nce limes for
v3.rious quantities or fue l OI\ board a t both the i11itial
~\ltitude and the optimum, best endurance altitude .
::>
9
J>
E
.......
D
s
"'3
2
"'t;
.....
::>
7
The :tir c rart <:on£igura.tion COn8t8lls of four empty
wing J)yl oos plus ~ns wilh a total drag i ndex of 33.
The endurance v:llucs arc given in minutes: fo r Lhe
optimum altitudes include the time required for a
6
military thrust climb to that altitude and a maximum
r aoge descent to sea l evel with 250 pOt.mds of fuel
r emaini ng for approach and Landing. 'The clldurancc
5
:c
The Ma.xiznum F.11durancc charts ptovidc a 1'ncani; of
detcrmininJ: the M ach nu m~r ruld calibrated air ..
speed f o1· maximum endurance with t he associated
fuel How and fuel required for a s1>ecllied loite r time .
'rhese <l:atn are provided for ~t constant :1ltitude loiter
condition. Optimum loiter altitude lines. allitude
for best endurance arc sul)('r imposed on the ptcssurc
ahltude plots. To use these char ts. the average
gr oss weight. b;mk ;rngle, p ressure ;ll tilude. drag
index. ambient air temperature. and loiter time
must be known. The charts then provide M:ich num ber. calibrated airspeed. fuel flow . and fuel
r equ ired for maximum endur~Ulce.
SAMPLE PROBLEM
time~
fo r the initial altitude include only the descent
t ltne since no climb ls required . Climb speeds and
airspeeds for m3.Ximum e11dutance a r·e included in
the chart together with letdown instructions .
g
...
MAX IMUM ENDURANCE
Moximum End uron te Speed
3
I
(For !if,'Ure 11 - 35)
(B) Bank angle . . . .
15 degr ees
I
(C) Loiter pressure :iltltude
25, 000 It
(D) Drag index
100
The time at which letdown should be inttiated is
g iven in terms of fuel on board and represents I.he
f
0
1.0
1.2
1.4
1.6
1.8
2.0
2.2
2.4
2.6
2.8
3.0
3.2
3.4
3.6
,f P10
EN GINE PRESSURE RATIO - P1
I
fuel requir·ed to conduct a maximum range descent
from altitude to sea level. A 250-p<>und fuel allowance ts hlc!udcd tor appr oach and landing.
(A) Average gr oss weight
15. 000 lb
!
I
I
I1
Bingo Endurance and B i ngo Endurance- Gear 0()YJn
FAl - 177
Figure 11-31. Engine Pressure Ratio for Cruise
11-61/ (11-62 blank)
charts arc pr esented ln llgures 11 -33 and 11-3{
respectively. These charts are provided fo r an
ni rc raft confi(fllr ation consisting of four winu pylons.
guns, and two 300 .. gallon external fuel tanks wi:h a
total dr ag in<lex of 61 with gear up and 391 with gear
down. The procedures for the use or the charts are
(E) Mach number for maximum
endurance
w
0. 475
IJ-63
Section XI
NAVAIR 01·40AVM· I
NAVAIH Ot-40AVM·I
Part 5
BJ}:(;()
M <If: l D<'c<'tnbl"r WiO
O:it:> n!'l~i e:: l·"Nti m ~h"I
n~u:t
Ens:in..•: J.;2-P-oJO"
If \'oo .\1•c at JO, 000 l'l·d
Jo..;ndurrutc:1._•
t:1.dur9.m:t•
S<-a
"'
~t1 mum
L<'\i{•I
Altitude-
Optimun1
Altilude
Model:
l.~tlg.iuc:
10. 000
Fe<>l
Oplimu1H
"'
OpliO\um
Alhtudl'
AllJtud1..·
} 'l'(.'l
OpUmum
.\Jtiludl•
:\hnuh.•s
Minuh.·~
i-'1._•cl
Minutcti
~linuh.'fl
"'
20,000
Opli mum
All1luth.'
a.1 Optimum
Lc\•('J
AltiW<lo
1~>00 1---:-:-+-G.,."---1-3-s.;..
.o_o.;.
o-f--'-::;9'--l--·-',3---"f--'3-'G'-,o-'o-'o+--;0:_~1---':..:'--1-=".:.;;:..:
• oo.:..:.o_
~~:1---3.,.G_-t-_s_,_--1_3_5.;..
,o_o.;.
o-t-4G'--l--5'-r.---"f--'3-'S', oo:.:..:.o+--'-",:__:1--_:r.:..:'o_-l_;3.:.5:..:·o:.:o.:.o_
1-- "-"-+-4_.1_ _,_a_s_.oo_o-f--'-3n_ _1--·-"---":-:3.:.s:....oo:..:.:..:o+--•':..:_-1-__:;:.:2_:-1_:3.:.:;:..:•oo:.:..:.o_
J 100
2.i
3~
35. ooo
sa
so
:lS. ooo
10
rn
3,:,, ooo
J 900 ~====J=9==~~=="=·a===~==3=•=·o=-o_o-t- __ - +- -"-o- -i__,"_:;_.o_o_o+__
:u_ __,.__3_r._ _._J_s:...
, oo_o_
1---1~3-+-~"---1-3_
0;,,;
,o_oo
.;._-1---''D'--l---'2:.:2'----"-'-3:..:s:..:,oo:..:.:..:o+--=2~:.._~1--_:2:..:c.:._--1_:3=:;:..:•(:..:~.:.o~
700
:,oo 1 - - - - - ' - - ' o_
II
_,_1_
s_.o_o_n-+--12_ _.__1_3_ _,_z_s_.o_o_o+- '--' _ ..L_ _ 1_1_ _t_3_0_.o_o_o_
If Yw Arc tH 30. OUO Fc:d
2:100
1900
En<luranc<-•
al
Erdurancc
30,000
Opt1m~1m
f'('N
Altilud<.•
..
Eni l Ul':tnCl'
al
OplJtnum
·\ltitudc
1---"-a_ _...__
!JG_
'i~
If You ,\1'(' :u io. 000 l'('('I
.,
Endur:tn<'<'
l-'.ndUr:tl1('f'
1·~-':IJ1('('
at
at
Opl.imum
.\llJtmlc
O~imum
Fe(.'\
Ophmum
.\ll1llHlc
4.0, 000
.\ltiludc
..~\_'(.'l
Minull'l:i
Minulcio
l"<-'<'L
,\linut.ci>
3G . OOO
O(ltintum
.\ltiludt.•
l't><'~
t\llnulct>
3:;,0-0
-'o-+--'s·_,--+--9'-;--l-'3,;,,;;..;
, o-'o,;,,0-1--..,;,,9"..c•--1--:..:9:.:9_-l._:3.:.•·:..:o.:.o.:.o_
:J=i.000
"'(I
~1
M
3.>.000
~2
't3
3S,OOO
1;oo t--~,-o---t--~,2--1-3~:;-,oo:-:---o--l--1-a--+--1-:t---!l--,'-r,,;,,.o'-o"'"o+--'-1.:.4_-l·--,:..:s:-;--1_:3:.:5.:.,o:.:o:.:o_
ljOO~====r,=2=======r.•===~==:t=•=
.o=o=o=:====r.=s===:===·=·5====~=3=;=,o=o=o=:====G=G===~===•
;· ·•===~==3~:;=,o;o~o==
11001---"-'-~-·-·•---;_3_:;,;,,,o_o~o--1--'-'-;-+--":..:-'---11--3:.::;.:.
,o:..:o.:.o+_...:..:.'-.:.'_-+•:.:
'--1_:3~;.:..o:.:o:.:o~
1 100
.J:;
__
_L3:;,_0_
00__1-_ 4_•_ _._ _·1_•_-+-'-3:;_._o_oo_._ _._w_-+----''.:.
9_ -1-....:..'":.:":.:o:..:oo:.._
17
II
!--'-"-'==--+---""""c;:.:,oc..:.;~;;,;_---l---":C.:"'---'-1---"'~ll~c~•c~·c~"'~'~Spc~·~<~~,,,,_--l---'::.!!!S~'~~·~·l~l.~c·~W~o•~n"'-""'---
50
ioo
1---'-u-+_,_u_~_:1_.;_
. oo
_
o-1_
20
3.;, 000
20
_;3,;,,.
1
31
3~_._o_
o_
o_,__ _
34?_
22
t2
3:;,000
2:1
Pr('~Jolurl•
Climb ::,peed
Endura.rK·~~
.\ltitmf<>
'.\lihtal'\' Tht'l 1 ~1
Soced
Ell(;l1l(' Idle S1>..'C<lbraJ.(.•f. Clos ..'((
KC.\l)
t\C:AS
I1
F('('t
1"'''"1
Mo.th :\!,).
r-C.\$
:.ir.;
1'~
1sr:
10 000
1a oou
:'If.~
_3Gl
3(;;-,
"r.
J~~
l>.!5
1.. a
i~ ~~~
36~
St>n
l~!l
1"5
-
_,
32
3~.ooo
23
a• .ooo
1''nm1 .\ltilud1.·
\V1lh .t'u..•l lh'mauliru:.
Pound!>
2r,o
----1-----J.""-''-1_ __
292
30;
,,-, 7"'•"3---!--!--17',~7~---+----:;.;~.:;;~----1-----"~"'~~'-.
'
---
:iii~ -+----_-+--~; -'~-=i" ~, .~"-- _-_--!+_-_-_-_-_·--'1"'-_,~" ~"-.: : : : .-:'~: : : : : : : .:t1c:~"';~"'-~"-- _-_-_-_-_-_-_,+_-_-_-_-_-_-_-_-_-, ,_~"'l~"':"·~:_~~~--~~--~~Figu1·e 11-32.
11-64
Fooled Deck Endurance
Endul'nnr'<'
at Optimum
Altitude
20,000 Feet
.Endurance
Optimu m
"'20, 000
Endur:mcc
m Optimum
Ahitude
t·cct
AIUtudo
Feet
Minules
J•'f'N
Ntnuws
Mlnutt'9
70
,,,
3f'1. noo
t.2
14
35
35 OOD
'"
50
C7
" ' nnn
56
GO
35 000
4>
35 000
35 000
H
o2
30. 000
r.1
2~
42
3~
000
38
•6
24
3:.i.DOD
1600
1300
19
~~-4~~~
32
45
,,
3; 000
1700
J•I
l•
~~
-t-.3:; , 000
33. 000
39
32
25
20 000
l<
•
HOO
~
0
1
c.
)9
13
I•
U You ArP at
l( You Are at
30, 000 f'tOl
35. 000 l''CCl
F<"N
°'
nM
1'.000
30 000
'04
•10
35
~g
..
""
59
45
2300
2100
1900
30,000·
1:> Ooo
Oplimum
AlUtude
Minut('ll
n
000
1.500
..
~~:.J.Q.C!L_
30 000
Ga
·19
35 000
33
35 000
3&. 000
30.oon
2l
7
JI You \1·c nl
l0, 000 fee'
I
1a
Endlll':tnC~
al 30,000
Feel
,;
,'.!
Enduran.c.-
.MinutCJi
1'11n11lt's
>0
2$00
82
73
75
2300
GB
2100
1900
1700
1500
1300
1100
5~
2700
£r-dur:mcc
Opumum
Alt.true.le
Ill
67
ao
Opthnum
ru3.5,000
Altiut.:le
Fet:t
-
Fe<>I
.MinuU~.3
35,000
35,000
35, 000
83
3G. OOO
53
SG
·16
3fj
17
39
a•.ooo
31
32
23
2•1
35. 000
35.000
54
35. 000
30
-
70
35. 000
35.000
-
67
46
22
3.;,000
30
22
3j,000
35, 000
J)('.i;:ccnl
f('<.•t
KCAS
340
.Mnoh N'o.
KCAS
KC.'\S
J9()
187
5, 000
340
100
10, 000
340
l~O
IG,000
3·10
190
18:7
J!)()
18'7
lOO
1S7
2s. ooo
o. 76·1
4
Oplimum
AlUtuW.:
ft.'C\
3G, 000
35, 000
:rn.ooo
35. 000
~3
36,000
3:".,000
Stnrt l.cJ.dO\\TI
Speed
l.- rom Alllt.udc
Cloa.t.'tl
Wilh l"ucl lkm:uulntit
-
1-
~
__.:2.:;0•:.:0..:,00:__!-_;3:..:·10:__.j.__ _ _ _
fl.IJnutcs
71
tnbrinc 1dk~"pc«tbr;tkc.s
Mllttnry Thnuu
Sn Lc\•cJ
....
r.o
3:;, 000
3o
nt Opcfnu1m
AIUt.udc
~
Climb Spc<~
Ptessurl"
1\llJwdf'
,..
3o. OOO
3n,ooo
35,000
30.000
s;
t.l
37
21
SI
76
3fo
20
1'Unl.lte¥
09
""38
•G
.._
Jl"cet
35.000
- .....
Minutes
76
44
21
F:ndUMVl('('
nl <J0,000
•·eel
69
35. 000
35,000
Endu1·ance
Altitude
0 1xtmvm
.,
.52
29
Endurnm:c
ru OpUnnnn
t\ltim<lt>
83
!'11
44
0001--~3_
; _-l-_3.:.':..:.:..:_ __:3:.:;,;,,.oo-'-'o--l--=3.:.u_+--'~'u'----"f--'3=:;.:.
· o:..:o.:.o+-_:·•.:.•_-+---·.:.":._-1_:3:.:5.:.,oo:.::.:o~
soo
Er.dunuu:c
:11 10. 000
FC!<ll
!\Unut~s
MIJ1UlNI
2700
Optimum
Altitude
Endurance
EndUr:tnC<'
at S(!a.
l'r<>t
J( You Ar-e Bl
If You Arc nt
10, 000 F~l
ll You Ato at
1~~ntl u 1'211~<'
l•VU 1-----t--":...'"---1--'"-'
":...
· •.;..•.:.•--1---"""~·-+--•:..:'''----"f--'3.:.;:..:
•oo
~o+--=
63=---~1--_:G:..:D_-1_:".:.S~,O~O.:.O_
1
1 Dcccmtx·r- 1970
D::ita BG.Sis: Esllm3.l('d
~:ll.C\'CI
~~n<hll':ln('('
2100 1---"; --1--'-"---1--'3_s:...,o..co.:.o--1--;:..:'-+--':..:"-~:-:3.:.;:..:,ooo~+-_:.sa:..__1--......:D~3:..__i_:3=•~·oo:.:.:o_
~
Ont.:t :tJ1 o!!
A··lM
J:i2-p-i1os
If \'w ,\ 1•1._· al 20. 000 F('(•l
Endurance
at
ir
_. ; -
E?\-OURAXCE
Or :11t l.l'lde"< (.t
All'f:ralt WQl,<ht ( Less f'uel) • 12, 437 Pound.ti
AU !>)Ions , Cuns (Nu Ammo), CUld ·r wo 300·G:>.llon t.:xtcrn.al TankR
Hc.serv~ F\l.el for IA.nding 800 P ounds
).tod1.•I: A-tM
~
XI
Pa.rt 5
lk3JC Index
33
A1rcr:\ft \\>\• 1~bl (Ll•Ss Fuel)
12, 039 l•ouudio
All P) Lons and Cu.nt. (?-:u Ammo)
ll.<'jle-rt <' f\1el tor L."\nding
2;;0 Pounds
:n
~Ct!On
__
187
Pound.I!!
soo
S23
- 1 - - --'l:..:•.;.7_ _ _ _! -_ _ _...;S..:.39;__ __
SS3
- t - __
SG_7_ _ __
s<o
~-...;30~·~00..:.0;__1-----+~-""
0.7~~..:,1_-+--~100'-'----+----~1~8-~'-----!l---·~-~89~2..__ _ _
35, 000
_ ~: i'£!_
J90
lS7
~11
W , 000
O. 7CH
190
1~7
OJ:i
.J5. 1)00
0 . 1r,a
190
187
927
Figur e 11 - 33. Dingo Endur:ince
11-65
Se ction XI
NAVAIR 01-40AVM-l
Par t 5
NAVAIR Ol-40AVM-l
Part 5
~
MAXIMUM ENDURANCE SPEED
I
I
Urug lnJ...1x
:ml
.\ircn1f1 \\c1~ht (Leu l"ucl)
\II I.., luM, c;un~ f~o
.\1111h•1),
MODEL1 A-4M
ENGINE: J52-P-408
12, 1:17 l '\Juncf!'i
.m.J 1''11.u :1Vll· ·(;;dlon r :-;1eni;,I Ta,,kfO
l..1n•lln~
Jksc.•nf' l"ut>) fol'
.,tl!I
DATA AS Of1 1S DECEMIER 1971
DATA BASIS: ESTIMATED
l'()un\I~
~\_
\ln.tld
.\- D l
f:nRi••" J:;:' -i'-111>
I
l>,tl;\
a.a 1•f: I l'<'l·l·mlll'r 11J7U
t>.tt~
R1.:;:1i.: l1111n.1trd
_____
Jo:ndurnnc."(I
!:n•lur.11u•'-'
al
,__
al Qvtnnum
~· a
L~'\t·l
011llmum
ASutmJi.:
All1lu•Ju
rnrlunlflc'('
J..n,lui"1.nt:t.·
al 10,uoo
F1•N
a 1 (1pc 1t11u111
1
\1ti1vil1·
...
ormmu"'
.\llitu•k·
:\ll.nutm•
18
I
-
~
l .IUIJ
16
"
...>~
"'
14
2•
.
a.,
I+--':
_,_
2 ..
I
II
1,
'Iott
Iv, UQO
12
l 101I
)1•.ll()lt
I
~
0
ac
13
I
1..
i:
~
26
~:: !
Ir Yvu An' :tt lO. 111•~1 ....., ••
~
'"
~~,--11 -
Jo;uJu11UJ~t·
f'.'ndur:1nt•('
Ul Optimum
Ahlt.udt.:
at 20.001)
.f('("l
Optin1um
\ltitu!J11
,,
'"
~I
1-
..:u, liO!t
50
·~
JO
fi'N
0
12
.70
.65
l':ndu1 .n1..:\
1U Optlmu111
\hltu<i1
Fn,lur..irH.:(:
Ill JO,M>u
25
BANK ANGLE - DEGREES
4.l11tlmum
.60
1\ltltt.111\'
l1lnu1e--.--~--,,.,-,-.,--+---:,-,.ll,_n-uw-,--+--~:-;l,-ln-utc~
.\l rnult!~
-I-----~-.._--~
..
,·,
Z'iCth
.;:~(.>IJ
23011
~lUU
t !tOO
I
Section XI
ou
51J
!?;";, t)l)I!
.)~
.J.:1
:!.;.,, 01111
.J:t
lj
:!:i,01111
Ii
I..
2:;,01ttJ
,__ __
4•-'-----,---'-"---r---~2:~··-•_01_
• -+----•~"---+---'-a_ __,.•__2_j~·-"'-'o_
f-
~n --~---"-•---1---2;-",.Qo•.!
);'110
l - - - - · " - ' - - - - i- --J4J
1·.1111
f---~2~'---1--- 24
1n
l'.Hk)
lll!<J
!.?O,On(I
I :_t.;,uo~J
:ti
:.!:!
_2'~'·-"-"'-'-+----~-;---+~
1~
.::1, l!lld
'!i
'.!U,dO!I
~---r------~·1IJ
IJ
:.!IJ.U\f•J
,,;
2.1
Iii
------'------~'--------'-------'---~
r~.sl'rnt ~ll('•'•'
J>r1•t-lt\ll'-'
Cllmll ~'4..'l'd
t.r~lurtt!H.'t.'
Lnl:illl.' hllc
1
11110
.:::
.55
~ .50
z
0
.45
~
....40
:::>
•
~
.35
:-1:. rt l.c1<tim n
! r«.im .\ltllu•I<
Altltu1..;~..;'--+--"...:11_11_"°...:'_Tl.:..•;,:,n.:..'":...'--+---''-'r~,;,·<.:.."-'---,,---""'''-'"-''-''"-''-~'-''_<_'l_"_''-"1--T--\\ 11 h l tll'I HC'nualnlni.:,
.30
.25
S.-riJ.<"\f'I
11in
t , iJf10
llill
l U.VVO
l •iO
1n:.
...,0,flOU
..0,01J()
•
~----+--~~
1 •~··
F'igul"e J l-34. Bingo Endu r;1nce - Gear Down
11-66
I 00
150
200
250
300
350
400
450
500
lfiO
CALIUATED AIRSPEED - KNOTS
l!Hl
~o
_.10.vuo
.20
.....
FA1 · 180
1''igure 11- 35. Mrudmum Endw·:ince Speed
11- 67
Section lG
NAVAIR 01 -40AVM-I
NAVAIR 01- 40AVM-l
Part 5
(F) Loller p r essure altitude
Section XI
Part 5
SAMPLE MAXIMUM ENDURANCE FUEL
25, 000 fl
MAXIMUM ENDURANCE FUEL
(C) Loiter airspeed • • • •
195 KCAS
DATA AS OF: 1 5 OCTOBER 1971
DATA BASIS: ESTIMATED
MODEL: A-4M
ENGINE: J52·P-408
4,
SAMPLE MAXIMUM ENDURANCE SPEED
2000
..
<
4000
0
!'<'--+--.-........ % 25
...
FA1•176
(K) Bank angle
15 degrees
(L) Louer pressure altitude
25, 000 ft
Ci
IAS Wiii! 'i
~so, ~-.L--+--..L...;;.;..c.'-'-'-..:..:.;"-'--....i.~
(M ) Temperature deviation lrom
ICAO standud (Ambient
temper ature • -24 . 50C)
.. 10°c
IN) Drag index
SAMPLE PROBLEM
100
(P) Loiter p ressure altitude
Maximum Endurance Fuel
:Ql
:R) Fuel
(For !lgure 11-36)
(H) Average gross weight
Ambient air
15,000lb
temper~uure
now .
25, 000 ll
.
-24. soc
1900 lb/ hr
(S) Lotter tt01e
30 min
(T) F'\lel r-equired .
950 lb
PRESSURE
ALTITUDE
- 1000 FT
u
5
10
15
20
25
30
35
40
ICAO
STANDARD
IEMP. - ° C
15.0
5.1
- 4.8
-14.7
- 24.6
-34.5
-44.4
-54.3
- 56.5
FAl-181
Figure 11-36. MllXimum Endurance Fuel
11-68
ll-G9/(ll-70 blank)
Seclion XI
Part 6
NAVAJR 0I-40AVM-l
Section XI
Pa.rt 6
NAVA!R 01-'10AVM-l
TA NKER SPEED ENVELOPE
PART 6
TANKER CONFIGURATION
1-300 GALLON REFUELING STORE PLUS 2-300 GALLON TANKS
5 PYLONS AND GUNS
AIR REFUELING
AIR REFUELING CHARTS
SAMPLE 1 ANKER SPEED ENVELOPE
I
O'IOCU( ffUMCTCO
The air reruellng charts present the pertormance of a
tanker confib~ red with an air-r·efoeHng buddy store
-
-
-
O.flOCUE EXTCHOtO
on the centerline pylon, Cour wing pyl01lS, two
300-gallon external fuel tanks, and two 20mm guns.
All performance darn shown are based on an ICAO
shrndard atmosphere.
MODEL1 A·4M
ENGINE: J52-P-408
DATA A S O F: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
50
- -- - DROGUE RETRACTED
- - - - DROGUE EXTENDED
40
WITH DROGUE EXTENDED,
RECOMMENDED LIMITS ARE:
M AXIMUM - 300 KCAS OR
M =0.8
E
...
The operatmg speed envelope of the tanker :u r c ralt
18 shown tn f 1g\o-e 1 l·37 . Data are presented for
both drogue extended and d rogue r etr acted config\ltations as a function of gross weight.
~
MINIMUM - MAXIMUM
ENDURANCE SPEED
OR 200 KCAS,
WHICHEVER IS
GREATER.
30
'"Al·l82
SAMPLE PROBLEM
Tanker S peed En velope
I
I
(For Cigure 11-37)
(A) Pressure al titude
(B) Gross weight hose and
drogue extended ,
I
10
20, 000 Cl
(E) Maximt1m refoehng
Mach number
0. 65
(F) Gr oss wei ghl hose and
drogue r·e tracted
24, 000 lb
24 , 000 lb
(C) Minin1t1 m refueling
.M;tch number
0. 505
(0) Maximum rducllng
calibrated airspeed
300 kn
0
0
(G) Max imu m !\'l a.ch
number
,2
.4
.6
,8
1.0
MACH NUMBER
0. 86
FAl - 186
Figw:e 11- 37. Tanker Speed Envelope
11-71
11-72
Section X1
!>art 6
NAVA!R Oi - 40AVM· I
SAMPLE TANKER FUEL
AVAILABLE FOR TRANSFER
Section XI
Pa.rt 6
NAVAIR 01-<lOAVM- l
SAMPLE PROBLEM
TANKER FUEL AVAILABLE FOR TRANSFER
1•300 GALLON REFUELING STORE PLUS 2·300 GALLON TAN KS
5 PYLONS, GUNS AND AMMO
Tanker Fu el Available for Tran •fer
( For Clg\lre 11 -38J
(AJ Relucling radius
~----····-··--···· ®
!
i
.
i
i
400 NM!
MODEL: A-4M
ENGINE: JS2-P-408
(BJ J P-5 Cuel line .
(CJ Fuel available for
transfer .
3840 lb
TAN«RFu a AVAILABLEFOR TRANSFER
I
The tanker fuel a.vaUable for t,r ansfer ts shown :t.S a
function of rndlcs ln fli;ure 11·38 !or operallon with
J P-4 or J P-5 fuel. The•e data a r e pr e•ented,
asstiming standard buddy ... tan.ke_r re.se rves cons1stmg
or fue1 for 20 mlntJtos of maxln1u111 cndurnncc at sea
level plus 5 pcreCllt or all fuel not 1rans!crrcd. In
addition , a fuel :lllowance for rendezvous and hook-up
has been added. This allowance consists or fuel ror
S minutes at speed for ma.ximtJm endurance, with
hose and dr<>1,'\le extended. at 30, 000 feet pressure
altltud•.
TANKER FUEL TR ANS FE R TIME
The max1mun\ arnoulll or ru~ that can be transferred
to the receiver during a continuous refueling oper a·
Uon ts limited to 513 gallons. The 1unumg factor is
the ext ernal transfer rate of Utnker fuel from the
exte rnaJ fuel t:tnks and wing tru\ks to the z·efueling
store. II mor e than 513 gnllons Is to be transferred
to the receiver, refueling must be dHsoonhnued lO
aUow the refueling stor e to be replenished from the
tanker internal fuel. The cunc dcJay u; dependent
upon the amount or additional !uel 10 be trans!errcd.
SAMPLE PROBLEM
Cl
z
refoeUng h;:
I
;1r:1 •o mplii::h~
(A) File! transferred to
receiver (.fl'-5) •
:lf M\d\i lPs;A 1ha.n thOJ;;.t?
noted :i.nd :Ill tht avaUable rue! ls transferred, the
tnnker will return to b3Se with :rn excess or reserve
fuel.
6
:::>
0
...
I
......
~ 2
Tanker Fu el Transfer Time
11
( For flg\l r e ll-39)
Al r eiuehng r:ldil or less Lhan 250 nautical 1nilcs with
J P-5 fuel and less than 235 nauiical mile s wlth JP-4
fuel, the tanker ts w1able to consume al l of the
320 g;iltons of non-transferable fuel. Therefore, ii
=24,500 POUNDS
TOTAL FUEL ON BOARD
GALLONS
POUNDS
Jp. 4
1701
11,054
Jp.5
1626
11 ,054
'l'he relation.ship of fuel tra.nsfei·J·ed to receiver
ver sus elaJ)SCd time ls pre sented in figure lJ -39.
T he flow rale to tht receiver ::u rcraft is 180 gaJJons
per minute. Alte r 2. 85 nuuutes, r efueling Is tempora r ily d iscontinued 10 a llow the rclucllntt store to rm
rrom lhe external fuel t:lnkS.
I
TAKCOFF WEIGHT
7
I
i
l
!0
DA TE: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
8
(Dl J P-5 fuel
4500 lb
uow llne
(C) Elapsed tlnie
4. 87 min
11-73
I
0
0
100
200
300
400
REFUELING RADIUS -
500
600
NAUTICAL MILES
Figure 11-38. Tn.nker Fuel Available For Transfer
11- 74
700
800
FAl -1 87
Section XI
Part 6
NAVAIR Ol-40AVM-1
Section XI
TANKER FUEL TRANSFER TIME
TANKER CONFIGURATION
(D) Polnl wher e refueling
ls resumed . . . . .
4. 04 min
:E) Poinl where re(lleli.ng is
temporu r ily d i s~ontinued
2. 85 min
DATA AS OF: 1 5 OCTOBER 1971
DATA BASIS, ESTIMATED
MODEL: A-4M
ENGINE, JS2-P-408
NAVA.IR 01-40AVM-1
Part 6
SAMPLE PROBLEM
SAMPLE TANKER FUEL TRANSFER TIME
Fuel Consumption of Tanker During Air
Refueling
( F"or figure 11-40)
7000
6000
(A) Rerueling speed
250 KCAS
(B) Cross weight
20. 000 lb
(C) Fuel now - 20. 000 ft
2860 lb/ hr
!low - 30. 000 Cl
3020 lb/ hr
(D) Fuel
5000
i
I
:
.
l:
I
!
!:
! :' I'
:
4000
I!
3000
:© '@;©
FUEL CONSUMPTION OF TANKER DURING
AIR REFUELING
I
2000
The tanker fuel consumption wllh the hoc>e and drogue
extended is pre8ented h1 flgure ll-40 for two pres ..
sure altitudes for speeds throughout tho night
u
1000
4
6
ELAPSED TIME - MINUTES
8
Cn\1ClOJ)C.
10
FAl- 188
Figure 11-39. Tanker Fuel Transfer Time
11-75
11- ?6
SAMPLE TANKER FUEL CONSUMPTION
DURING AIR REFUELING
NAVAIR Ol-40AVM- 1
Section XI
Pai:t G
NAVAffi 0 1·40AVM·I
Section Xl
Parl 7
FUEL CONSUMPTION OF TANKER DURING AIR REFUELING
1- 300 GALLON REFUELING STORE PLUS 2-300 GALLON TANKS
S PYLONS, GUNS AND AMMO
PART 7
DESCENT
DATA AS Of: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
MODEL: A-4M
ENGINE: J52-P-40B
MAXIMUM RANGE DESCENT
sooo
SAMPLE DESCENT FUEL
Gr.ph1cal data orr prostnird tn figures 11 ·4 I 1hrough
~ 4000
0
11 .. 43 for maximum
GROSS WEIGHT
- 1000 POUNDS
24
~
r :-m~f.' d ~sc«nt
using idle thru"l
Md with speedbrakes closed. Recommended m:u<I ·
mum ro.ngc descent s1>ecd. Cucl consumed. dlstnnce
<·overed. and el3J>Sed ttme from ruiy des•red ;1.Jtttude
to S~Hl ltl'vC'1 :'lr() prcsenfl"d :1$ rt function of g ro.!:iS
wci~ht and di·ag lndc.. All data Is based on an ICAO
"'
"'z
ot .u1,l;1rJ ,tt 111u~v11t'Tt!' .
::>
~ 3000
I
~
ThP method or 11z·e1H~: nti ng dabl ror foel, distance, and
tim(" is 1df'nl1r:il. ThArrforP, only on,. sample prob·
it
lcm Is shown.
0
I
I
PRESSURE ALTITUDE
I
=30,000 FEET
SAMPLE PROBLEM
I
1000
200
I
220
240
t
260
Descent Fue l
300
2BO
REFUELING SPEED - KNOTS CALIBRATED AIRSPEED
..
I
4000
::>
GROSS WEIGHT
- 1000 POUNDS
:z:
....
24
0
~
(For figure 11-41)
I
(A) Initial gross weight .•• . •. . • • •.. 14. 000 lb
~
I
~
~
(B) Cru1Sc alliludc
35. 000 It
(C) Drag Index
0
3000
::>
(0) Fuel required from crunile
:ilt ltudc to sr:• level . . . . . . . . . . . . 112 lb
I
2000
~
w
::>
PRESSURE AtlTUDE :
...
1000
200
120
240
260
20,000 FEET
280
300
REFUELING SPEED - KNOTS CALIBRATED AIRSPEED
FA l- 189
Figure 11-40. Fuel Consumption of Tanker During Air Refueling
11-77/(11-78 blank)
Note
From figure 11-42. descent S JlCCd Is 200
KCAS.
Section XI
Pat·t 7
NAVAIR 01-40AV111-l
NAVAIR 01-40AVM-l
Section XI
Part 7
IDLE THRUST
DESCENT FUEL
FLAPS UP
MODEL: A·4M
ENGINE: J52-P-408
IDLE THRUST
GEA• UP
FLAPS UP
SPEED8RAKES RETRACTED
MODEL1 A · 4M
ENGINE: J52·P·408
GEAR UP
DESCENT DISTANCE
SPEED8RAKES RETRACTED
DATA AS Of: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
26
DATA AS OF1 1 DECEMBER 1970
DATA BASIS: ESTIMATED
24
"'0z
:>
22
...0
"'z0
:>
...0
~
...
:r
..:c
C)
:::0
8
22
...
:r
2
20
.."'
"'
0
16
C)
14
16
C)
12
120
12 .
"'
~
i
150
...<
v
;:
125
100
80
:>
<
z
...vI
100
.."'
60
z
<
:>
ii!
18
i
18
"'
"'0z
20
75
40
0
I
Ml
~
20
50
0
25
OESCENT SPEED SCHEDULE - KCAS
GROSS WEIGHT- 1000 POUNDS
0
FAl-127
Figure ll-41 . Descent Fuel
11-80
DRAG INDEX
12
14
16
18
20
22
24
26
0
100
200
185
175
165
200
185
180
215
200
190
225
210
200
240
220
210
250
230
220
260
240
230
270
250
240
fA1·128 - A
Figure 11-42. Descent Distance
11-81
Section XI
Part 7
NA VAIR 01-40A VM-1
NAVAU< 01-40AVM-1
Section XI
P-ttrl 8
DESCENT TIME
IDLE TH RUST
GEAR UP
FLAPS UP
PART 8
LANDING
SPEEDBRAKES RETRACTED
MODEL: A·4M
ENGINE: J52-P-408
DATA AS Of : 1 DECEMBER. 1970
DATA BASIS: ESTIMATED
~ LANDING
26
24
ApJ)rollch spocds, stall speech;, :tnd corrcspooding
angle-of-nttack units are presented few the l•tndlng
0
"'
!i
configuraUons in figure 11-44.
brakcs open, uslng thrust r eqmred to
~
20
a
tor npproach, ri?check the confiKu raLlon. If the
approiirlatc conltguratlon Is established. distegard
I
the angle-of-attack lndlcaLor and make the approach
at the indicated ttlrspeed from figure Jl-44.
18
i
~
m~inta:.n
4 - dc~rec ~Ude slo~c. IC an B!ll<IC-o!-attack indication
o! 18 u1tlts dots not produce the lndlcatcd airspeed as
determmed !ro:n !igure 11-44 at the flap settlng used
,_
x
These data aru pre-
sented (or an aircraft with gear down and spccd-
22
~
8
SAMPLE APPROACH SPEED
16
2
~
SA M..EPROBIEM
14
I
12
25
'
I
Approach Speed
!
i
!@
(For figure 11 - 44)
FAl-190
20
(A) Gross wo i~ht ... • . . ... • .. , • . 14, 000 lb
~
i
conditions: dry . wet, :and snow and lee.
~
(B) Stall 8peecl (f'ull fi:tps). . • . • • . . . 105. 4 KIAS
Ani:lc o! attack • . . • . . . . • . . . . 25. 8 units
I
i
All dts-
t:tnces are b:ased on ;ln :lircrafl with !:i(>eedbr:tkes
15
I
10
;::::
0
proachi appr oach speed.s ~Hi determlned from figure
11-44. m:i.~lmum braking eUort wJthout sklddlng the
tires, and the throttle set at idle throughout the
ground-roll.
(C) A1lptoach speed (Full !lap•). . . . . . 126 KIAS
Ancic o! attack • • . . . . .
18 units
I
To ut'le the l;\ndlng distance ch.arts . the temperature,
pr~ssure
!igures ll-45 and Jl- •16.
altitude, gros• weight, !tap dc!lcctlon.
he:utwind, nnd ruoway gr:.1d1ent must be known.
Landlstg g round.-r o ll dlsboccs a re fl ref>t>n~d in
Fl~urc
11-45 presents
g.rc>und·1·oll cti~l:'lntelS wilhoul drag chute ll.l\d fi.p;urt.> 11-46 presents ground·roU dlst:ances using the
dJ't'lg ChuLc. Dntn f1ro prO\•id~d for lh.ree runway
FAl-129-A
and spoilers fully extended, !laps as set !or ap-
distance to clear a 50-root obstarlc
The
1~ me:t~"Ured
hOr i1_,onl,.alJ}r [rom the 50• (00l ObSt...'kcJI" IO lhe end O(
the KJ'Ound roll and is determined by addll~ 715 £eel
to the gro~md-ro11 distance. nssuming a st.and.1rd
4-degree glide slop•.
Figure 11-43 . Descent Time
11- 82
11-83
Section XI
Part8
NAVAffi 01- 40AVM-1
NAVAIR Ol-40AVM- 1
LANDING DISTANCE
APPROACH SPEED
HARD SURFACE RUNWAY
DRY
SPEEDUAKES AND SPOILERS OPEN
RCR
23
NO DRAG CHUTE
DATA AS Of: ts OCTOBER 1971
DATA BASIS: CONTRACTOR FLIGHT TEST
GEAR DOWN - SPEED8RAKES OPEN
THRUST REQUIRED TO MAINTAIN 4 • GLIDE SLOPE
MODEl 1 A-4~
ENGINE: J52-P-408
=
DATA AS Of: IS OCTOBER 1971
DATA BASIS: ESTIMATED
160
w
µ
MODEL: A•4M
ENGINE: J52-P-408
H-
w. 111 ,
i$l i~
r
Q;;)
f
z
!>~
...<i5
br'
ry
120
-!20 -10
S;
t:."
~~
t l-
-
~
t-
~
..I<
!.-
t
~
],,
·t
µ.
........
100
.
90
10
~k~
-
h-<
~
11
J.,i,.. j
1-1
;.
--"-
?
~
~
~
.;
l~
.lj
...!
''-' l'. >-+ ...
tTt
•I
.... ' !+
w
0
10
20
30
~p
'-~ ;\.
f
...
40
APPROACH
FLAP
DEFLECTION
~
HALF
t-i
\;-"~
I->-
110
....
H-
.
UP
~
~
l
.l
A:'.
~
I+ H
.j
H
I
~
1'1~
·-
. r.
!>
.j •
t:.t.
rT
-~
"I 130
s......
"'"'c
......0
"":!I
.
"'
0
f+i-
..
~
Wl'
»1.
ISO
~
If
-t'· ' ·+
ri i!kt:!
~~ ' I J d ...,, -r,.,.j "
08 HJ 'r' t ~'7 + --+;
i;;.;
~
~
140
Section XI
Part 8
t
1
-:+._J
-
w. ~
H-+-
'
~
1~
+
~f-t
1nb'.
Ji
+1
~~
HEADWIND
-KNOTS
4
f-1-
'
·-
.ri!t'>..i..
·-
.H r-t
- 2
+
12
t+
13
·-+++
~+·
14
15
16
RUNWAY
GRADIENT
- PERCENT
SLOPE
-+-
.,.
0
+2
tJ..1
0
2
4
6
10
GROSS WEIGHT- 1000 POUNDS
LANDING GROUND ROLL DISTANCE - 1000 FEET
FAl-192
Figure 11-44.
11-84
Approach Speed
Figure ll-45.
Landing Distance - No Drag Chute (Sheet 1)
FAl-193
u-iss
Section XI
NAVAIR 01- 40AVM-l
NAVAIR 01-'10AVM-l
:Part 8
Section X1
Part 8
LANDING DISTANCE
LANDING DISTANCE
HARO SURFACE RUNWAY
SNOW ANO ICE
SPEEDBRAKES AND SPOILERS OPEN
RCR : 9
NO DRAG CHUTE
DATA AS OF: 1 S OCTOBER 1971
DATA BASIS: ESTIMATED
HARD SURFACE RUNWAY
WET
SPEEOBRAKES ANO SPOILERS OPEN
RCR: 15
NO DRAG CHUTE
DATA AS Of: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
MODEL: A-4M
ENGINE: J52-P-408
MODEL: A-4M
ENGINE: J52-P-408
:EH:;fH
l'I
i
rti11'/'\lJ-f! '
"fl
J#.'
.., fi:J~
~ 'i-1'-d()
... "1 ....
t:t ~-W
Vi
I
•'/,
1
~
-·
H
t
it
t-I
j
-
-V;
....
~
'
-20 -10
0
10
20
TEMPERATURE -
30
40
- 20 - 10
•c
0
10
20
30
40
TEMPERATURE - ° C
APPROACH
FLAP
DEFLECTION
BASELINE
0
10
HEADWIND
-KNOTS
0
t
10
HEADWIND
-KNOTS
20
30
30
40
40
- 2
RUNWAY
GRADIENT
- PERCENT
SLOPE
-2
RUNWAY
GRADIENT
- PERCENT
SLOPE
0
+2
L
0
2
4
6
LANDING GROUND ROLL DISTANCC-1000 FEET
Figure 11-45.
11- 86
20
Landing Distance - No Drag Chute (Sheet 2)
0
10
FA1 · 194
LANDING GROUN D ROLL DISTANCE - 1000 FEET
FAJ.195
Figure 11- 45. Landini; Distance - No Dr ag Chute (Sheet 3)
11-87
Section :ll.'I
NAVAJR 01-40AV.M-1
LANDING DISTANCE
HARO SURFACE RUNWA Y
W ET
SPEEOBRAKES ANO SPOILERS OPEN
15
RCR
WITH DRAG CHUTE DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
=
-20 -10
0
=
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: CONTRACTOR FLIGHT TEST
10
20
30
Part s
LANDING DISTANCE
HARD SURFACE RUNWAY
ORY
SPEEOBRAKES ANO SPOILERS OPEN
RCR
23
WITH DRAG CHUTE
MODEL: A-4M
ENGINE: JS2-P-408
Section XI
NAVAIR 01-40AVM-1
Part 8
MODU: A-4 M
ENGINE: J52-P-408
-20 -10
40
0
10
20
30
40
TEMPERATURE - °C
TEMPERATURE - °C
APPROACH
FLAP
DEFLECTION
APPROACH
FLAP
HALF
DEFLECTION
HALF
UP
0
L1
10
HEADWIND
-KNOTS
10
...
HEADWIND
-KNOTS
20
30
30
40
40
RUNWAY
GRADIENT
- PERCENT
SLOPE
0
+2
I
- 2
-2
RUNWAY
GRADIENT
- P!RCENT
SLOPE
20
Li. ...
0
0
LANDING GROUND ROLL DISTANCE -
LANDING GROUND ROLL DISTANCE - 1000 FEET
1000 FEET
FAl-197
FAl - 196
Figure 11- 46. Landing Distance - With Urag Chute (Sheet 1)
11- 88
Figure ll-46. Landing Distance - With Drag Chute (Sheet 2)
11-89
SecUon XI
Part 8
NAVAIR Ol - 40AVM-1
NAVAIR 0 1- 40AVM - l
SAMPLE PROBlEM
LANDING DISTANCE
HARD SURFACE RUNWAY
SNOW AND ICE
SPEEDBR.AKES AND SPOILERS OPEN
RCR
9
WITH DRAG CHUTE
DATA AS OF: 15 OCTOBER 1971
DATA BASIS: ESTIMATED
=
MODEL: A·4M
ENGINE: JS2- P-408
Sectlnn Xl
Part 8
(A) Outside a ir tempe ratur e
landing Distance
(For ligure 11·45, sheet 1 and figure l 1·46, !heel l )
(B) Runway pressure altitude . .
2000 It
(C) Landing gr oss welght. . . . . . . .
14 , 000 th
(D) Approach flap deflection . . . . . .
Hall
(E) Headwind
20 kn
Runway Condition : Wel
SAMPLE LANDING DISTANCE
.••.. .
C•') Runway g radient • . . . . • . . . . .
-20 -10
0
10
20
TEMPERATURE -
30
40
-I percelll
(G) Ground l'Oll distance:
•c
APPROACH
FLAP
DEFLECTION
No drag c hute . • . . . • . ...• . •
3200 fl
With drag c hute . . . ... . .•..
2020 It
HEADWIND
-KNOTS
- 2 l
RUNWAY
GRADIENT
- PERCENT
SLOPE
0
l
+2
0
2
3
4
5
6
LANDING GROUND ROLL DISTANCE - 1000 FEET
FAl-198
Figure 11-46. Landing Distance - With Drag Chute (Sheet 3)
11-90
11-91/ (11-92 b lank)
NAVAIR Ol - 40t\VM - I
Section XI
Part 9
St·dmn XI
Part 9
NAVAlR Ol-4 0AVM-l
TU RNING RADIUS
PART 9
600
10
30
1.02
20
550
COMBAT PERFORMANCE
soo
COMBAT PERFORMANCE
I.OS
10
SAMPLE TURNING RADIU S
20
450
1.10
s
Thi s par·t cont.:lins Lhc
,wrCornl311\'0 cha1·h, 3$iSOCJ3tcd
wlth th(' combat phase of the mission. Turnln.:
r:.tdtus, maneuvcrah hty. ma:dntum Ma('h nunt':>er.
nnd nid1l3rv fuel flo·.v 0. 10 im.·luded.
@ -
__
- ... _ _ ©
------
TURNING RAD IUS
40
3SO
\ ,S
@
s
300
50
60
4
3
Th<" 1,1r11ini: r:td1m; rnmograph, fiq\tre 11-47. present~ dat.3 for ~leadl' &tak level lul'n8 :L"l. a funct1un
<1f u•uc- alr~pccd. no1·m:il load facLor. bank nnit1l',
dlstonco u·~vole<l. aid heading change. When used
m t·nnJunrthm wHh the ln:td hu:lnr limHntlmu. of tlw
U:U
l.llSP£U
TUU
UDIVS
LOtD
UH
JACTOI AKUl
70
2
2SO
4
.2
1.0
maneuverability ch...\1·ts. tlgure 11-48. tile i.'erodyna·nlc. cn~lnc. and s·_ructural charactcrlstic.s or the
:urc1•aJt :.tre Laken 1nto :t~counl.
----+-------i
Note
s
6
.1
200
20
100
At normal lO\\ llvol a irspeeds a rout-th 1>lan-
50
nl.ng- ald tor turntni: ri'dJus Is the use of a
drnm on :..tn ONC (1:1 , 000, 000) ur 3 qu:t rt~r
on a PC (1:500. JOO).
TURN RADIUS
10
s
4
400
300
200
NAUTICAL MILESI
so
SAMPLE PROBLEM
(n)
True 1\lrspcod
49& KTAS
(C)
Tu rnmg ff:idtuK
6000 fl
so
10
--- --- ---
2
1.Q,..
111- - 5
ISO
100
3
10
NORMAL LOAD 8ANK ANGLE
FACTOR
IDEGREESI
180
11000 FEET -
30
80
7
.S
AIRSPEED IKTASI
ISO
Turning Radius
30
4
3
400
s
.s
------
1.0
.s
100
90
80
60
50
40
(D) Hendinit change •....•..•• . ... 90 dc~rees
(Fm•
fl~ul"O
(E) DiMoncc Tr•"olcd In Turn
IJ-47)
Prom l\1:111eu\1 ernbl1!ty Sample Problem J (Flg:·
11--18)
9200 h
MANEUVERABILITY
Ul"I'
M.tch Numher
I
.5
.s
0. 75
Low·althudo mnnou,•orabilhy charactcrlslic> of the
rl~'Urc 11-"8. These data
A- 4M ain·r3ft are shown ln
11000 fEET -
NAUTICAL MILESI
Lo~d
F:tc tor
. . . . . . • .
(A) Normal Load F>etor • . . • . . .
(Bank An~le •..•• 74. 6 Degrees)
3. 84sr
3. 84~
tt
Cunctlon of altltude. normal lvad factor
11-93
20
HEADING CHANGE
IDEGREESI
NAUTICAL MILESI
lo:\d f::ti•fl•l' !'ltl:\iunbt.1 nl ti "fW'c•ifiNI M:lrl1 1tumlwr
(sample 1>ro'blcm 1) or the nmxlmu111 (and 111 tot mum)
M3rh number fl'u- :t predrte-rmln~d load r:trtor re·
<1oirement (1:>.·un111e problem 2). The8t.! d:•la. :tr-f• pre-
i,ented ns
.2
DISTANCE
TRAVELED
IN TURN
11000 FEET-
pro\'idti a means ot dctcrmtninJt elthrr th(\ maximum
Normal
.1
TURN RADIUS
30
.1
FAl - 134
Figure 11-47. Turning Radius
11- 94
NAVAlR 01- 40AVM-1
Section XI
Section XI
Part 9
NAVAIR 01-40AVM-1
Part 9
MANEUVERABILITY
MANEUVERABILITY
MILITARY THRUST
SEA LEVEL
STANDARD DAY
FLAPS UP
GEAR UP
MODEL: A · 4M
ENGINE: JS2· P·408
MILITARY THRUST
10,000 FEET - STANDARD DAY
FLAPS UP
M ODEL: A-4M
ENGINE: J52-P-408
DATA AS OF: 1 D£CEM8ER 1970
DATA BASIS: ESTIMATED
GEAR UP
DATA AS OF: 1 OECEM8ER 1970
DATA BASIS: ESTIMATED
90
80
...
%
I)
~
.,.
()
.,. so
..
..:5
()
"'
I)
x
I)
x
~
40
40
0
t;
~
0
<(
g
30
~
"'~
20
I
....;.
0
0.2
0.3
0.4
0.5
0.2
0 .6
0 .7
MACH NUM8Elt
o.a
0 .9
0.3
0.4
0 .5
0 .6
0.7
FA1·135
0.9
fAl-136
Figure 11- 48. Maneuverability (Sheet 1)
Figure 11-48. fllaneuvel·ability (Sleet 2)
11-95
0.8
MACH NUMBER
11-96
NAVAIR 01-40AVM-I
SAMPLE MANEUVERABILITY
Section XI
Part 9
Scctlon Xt
P3rt 9
SAMPLE PROBLEM 2
NAVMfl
SAMPLE MILITARY FUEL FLOW
01-40AV~l-I
dr:.1! mdex :rnd p-oss wcli::ht at altitudes of .bea le''<•I
and 10, 000 feel.
Military thrust fuel flow is pr('-
Maneuverability
scmcd lt\ H,Hurc J 1-50 tu;. n fun('tion of pressure
altitude and Mach number.
(For figure 11 -48, sheet I)
SAMPLE PROBLEM
Altitude
Sea lcveJ
Maximum Mo<h Number
Gross weight . . . . . . . . . . . . . . . . 20. 000 lb
No rmal load factor required
(For fit!"rc 11-49)
3.0g
(AJ Oraii Index .•••• , .• , •. , . • . . . . 60
(DJ Normal toad factor x gross
weight . . . . . • .
60, 000 lb
(B) Gro"" wei~ht al sea level ..•. , •.. 18. 000 lb
(E) Drag index . , . . . . . . . . . • . . • . . . 100
(CJ
0. 833
(F) Mirl imum Mach number
at 3.0g . . . . . . . . . . . . . . . . . . . . 0.434
SAMPLE PROBLEM
(G) Maximum Mach number
at 3.0g . . .. . • . . . . . . . . . . . . . . 0. 731
Military Fuel Flow
MAXIMUM MACH NUMBER
(For
f!~ro
(A)
Prrn1surc altitude
11 ·50)
10.000 It
(13) \laci1 nurube r . . . . . _ . _ • . . . . . • 0. 90
Level rl11.thl mnxrnlum '.\•larh numh~r. :tl milil~4 rv
thrust. is shown ln figure 11-49, o.s a (unction Or
SAMPLE MAXIMUM MACH NUMBER
times gros;s wcighl, Mach nuinbcr, aod drag ind.ex
for zero longitudinal accelcratlon. SUpcrlmposcd on
the grnphs are line.is $hOwing maximum h!l, buffel
onwset, and structural limits. All data presented are
based oo the Crlginc dcvclopiitg milita1·y thrust.
SAMPLE PROBLEM 1
Maneuverability
(For figure 11-48, sheet I)
I
Altitude . . . • . • . • . . • . . . . . . . . . Se:.. level
Gross weight
18,000 lb
(A) Mach number
o. i5
(D) Drag index . . . . . . . . . . . . . . . . . .
50
(CJ Normal load factor x gross weight . . 69. 000 lb
Gross welght. . . . . . . . . . . . . . • . • 181 000 lb
Normal lo:id fact.Or at zero
longitudinal acceleration . . . . • • • . . 3. 84g
11-97
11-98
(C)
Fuol Clow .. , ••..•. , • . • .
•
. J 56 lb mln
NAVAIR 01- <lOAVM-l
Section XI
P8l·t 9
Section XI
Part 9
MILITARY FUEL FLOW
MAXIMUM MACH NUMBER
ICAO STANDARD ATMOSPHERE
MILITARY THRUST
ICAO STANDARD ATMOSPHERE
i.-
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
1 -
~tEVEJ. I ~ f.
....., I
"z
MODIL: A·4M
ENGINE: J52-P-408
DATA AS OF: 1 DECEMBER 1970
DATA BASIS: ESTIMATED
MODEL: A·4M
ENGINE: J52-P-408
1.0 -,..,...,...,...
"'..."'
NAVAIR Ol-40AVM-l
~ROSS
rt
WEIGHl
1000 POUNDS 1-1-.;._"-1-.i...;.......U
,_......t+r+H-rtiH-:-H--t+++i
.9
t-'12t
:>
:r
v
~
"il...
..
.8
,1
0
.......
"
40
80
120
160
200
40
80
120
160
200
.9
:>
z
:z;
v
~
"...:>
..
.8
I
100
DRAG INDEX
120
140'
160
180
FUEL FLOW - POUNDS PER MINUTE
FAl-1 38
FAl-13'
F'igure 11-50. Military Fuel Flow
Figm·e 11-19. Maximum Mach Number
11-99
11-100
l'AVAIR 01-40AVM -I
Sec:;llon Xl
Section XI
NAVAIR 0 1-40AVM-I
Pai1 10
Port 10
I
The Sample Mission Planning Problem Summary
ij solution of the problem is introduced at this J>Oilll so
!
•he pilot can see 1he oom1>lete graph!<' picture before
the :lch.Hl.l soluhon is broken imo parts.
PART 10
MISS ION PLANNING
Gross We ight and Drag Index
(From figur e 11-1 and NAVAl!l 01·40AV-IT)
ltPms
MISSIO N PLAN NING
Drag
\V('Jt~ht
Jndex
(pound<)
0
11. 427
SAMPLE Pl.AN VIEW
Zero fuel, zero payload
SAMPLE MI SSION PLANNING PR08l ( M
Two 20mm guns and ammo
14eo. ,,,n,.
TARGET
Optin1unt use or 1he alrcr3.!t to obtain m:iximum
performartce 'lt a mmjmum rate of fuel consumption
requires careful pr eflight planning for the nHsslon.
One of lhe mosL lmp0 rlant phasei; of n11ss1on planning
is the dctermln.a1ion
the m::&.x imum radius
action
1I
or
Two station 75 wing pylons
_
CllMS TO 2-5,000
l
net
628
12
140
•rwo i;tation 11 3. 75 wing
pylOl\S
or
Two .\ '1t-;R·7 on station 75
11
128
46
446
from the field which will allow return with a n adc-
One 300-gallon bobtail fuel
quate fuel rC11erve.
1:rnk oo
Df.SClNO'l'fO
!
station
15
183
Two 5x.~1K 81 LDGP bombs
28
2GOO
cc1lte rli111~
~l()AT
~'JO?Ftl1
To rind the mal<ln1un1 radius. a combat plan must be
formulated in advance, a nd a loiter altitude and distance must be e8ta.bl 1shed befor e the combat phase of
the mission is bcguo. Fuel consumption is high durln~
combat n10nc,vers and any delay In beglirning the
combat acuon will shorten the con1bat time. or seri-
~
Two lx!\lK 81 LOGP bombs
on st3.t ion l 13. 75
r
(800 gallons JP-5)
5440
External fuel
(300 gallons JP- 5)
2040
T
CLIM& TO OPTIMUM AlTITU-0(
ously reduce the amount of planne-d fuel r eser ve.
•'
'
C"U*Sl IA()( AT
OflTIMUMA\.llTUO(
APP!t04CH "-110
l.AllONCltlSUV\
FAl-199
The ro11owing 8a.rnpte problem is an exer cise ln the
uso of the pcrfor:naorc rharts contained in Parts 1
l
!
fat c tnal fu el
Cr&AT
~
FIELD
520
Ta.keolf Tol«ls
126
23, 552
-15
- 183
oott:NO TO su. uvn
100
700
)00
OISTANCC · AIR NAUTICAlMllfS
Drop 300 -gallon tank
400
r1,1.200
Total
Ill
through 9. The example is not Intended to r eflect a.n
actual m iss1on. The sample problem must rates.
through a grJ.phical solution, how the po rformanc~
charts can be rnt~g 1·ated tu (O r m a complete mission
Drop bombs
Cllght plai1. The steps used to develop such a plo\ a re
Total
-32
-3120
79
shown with the problem.
I
SAMPLE
I
Assumptio ns and Comments
versus air distance. Gross weig ht is also super ..
. 5440
Fuel used (external)
-2010
Imposed on the vcrtic:\1 scale.
PROB~M
I
Assume zero wlnd and ICAO standard day
r ond1t1on!'S.
TakcoLC and proceed un cour-sc al 25. 000
al maximum
ran~c ~tach
number.
fotlt
dcs~~nd
allttude
to
2. Assume the gun ammunitlon
lhe n11ss1on.
I~
Uona I rum ground observers then :lttnrk the target
v:Uh two du.sto1-s of SxM K 91 LOCP lxu\lbi:i alo1ti; with
two single MK 81 LDGP bombs. RetuJ"o to thc- held
al maximum ran0e cruise oltitude with 800 pounds o!
r esen·c ru..-L f\1llowinf: 15 a plan view.
l
Larg-~t. ~
3. Assuuw • combat allow:uwe of S mtnutcs at
mUita1·y lhrusl lU drop the bombti al cJw
11-101
I
The Urst s tep ts to derive gross weight and dtag
index values as s hown. The mlsslon problem is t hen
_ solved ill ii1cremental step8, working from takeoU
through descent and working b:...ckward Crom landing
Total
(zero ruel weight)
79
12, 769
Approach a nd l a nding Reserve Allowances
to combat.
1101 rtrcd during
·
5000 loet almudo: hold on suuton awaiting lnstruc-
I
Fuel used (inicrnol )
The p•·obl em is solved by 1>lotting fuel r emaining
I
'T'he landing r eserve js assumed to be 800 pounds
which will permit sea level landing patte rn operation
for 15 to 20 minutes . This poinl is plotted as showo
Start solving the mission requirements by working
backwar d from the landing r eserves. The solution
0 1\
follows.
zet'O n.auLical miles distanc;e.
ll-102
the Sample Cruise Bac.k1 Descent. and Laoding
Reserve plot at 800 pounds of fuel remaining and
I
NAVAIR 0J-40AVM-1
I De scent from Optimum Cruise Altitude lo
B Sea level
Time, iuel, and d\stance for descen1 can bl' deter·
mined from the
desc~nl
Section XI
Part 10
Section Xl
P:tn 10
These points are pioued as sho"'" on the S.1mplc
Cruise Uackr Descent , ~nd L.anding ll<'srrve plu1 at
fu~l r emarnini; t1f J4JO, 1910, and 2410 pounds
r especlively (ruel r emaining - rcbCr\'C rucl • descent
I
•
Combat
w
11-43). The drag Index !or this con!iguratio11
Is 79. Assume ;hat the weight at the beginning or t he
letdown is equal t o the gross weight with rese rve fue l
( 12, 769 lb · 80~ lb ~ 13, 569 lb). The o!)timurn c ruise
altitude !or this weight and drag index Is read Crom
figure I l-20
A Iive--mlnute sea level, maximum speed, combat
allowance is assumed to exJ)end the bombs over the
target. To per mit a conservative fue l allowance, it
is assu1ned thal the bombs have been dropped prior
to combat and the drag index 1$ ?9. Since the varla ·
tion i n maximum speed with g ross weight a t sea level
is small assume that the combat wei&ht js that weight
which is determined by the lntersecti01\ or the clinlb
li1le and the requ ired mission radius (combat weight =
zero fuel weight + fuel r emaining at 300 nautic-2.l
miles (15, 149 lb = 12, 769 lb + 2380 lb). From fig ·
ure 11-49 at a weight of 15, J49 pounds and drag index
of ?9, maxjmum Mach number - 0. 819. _F rom !ig: ·
u r e t 1- 50 at sea level and Mach number or 0. 8 19,
fuel flow .11: 169 pc>unds 1>er minute . Therefore fuel
for 5 minutes ls 845 pounds. The combat allowance
dlslancc points are 176, 284 1 nnd 389 :ur nauhc:ll
rnalC!'S (d1st.anee • descent dlst:rnce
lm·rernent).
i
dlstat1te
SAMPLE CRUISE BACK, DESCENT, ANO LANDIN G ltESUVE
F\l(L
I
Qlt0$$ W(fQff1
PO~OS
llOl.-'\0$
Optil';\um
Cnalsc
Altitude
(le<!)
Initial
Weight
(pounds)
13, 569
Distance
Tln>e
(minutes)
(nautical
nilles)
F'uel
(1x1<1 nds)
15
64
110
38. 700
fuel How at J2 pounds per minute , takeoff
accele ~lion allowa1tces of 150 pouods o! fuel used,
tj
fuel + crulsc rue:J tn('r<'-mcnt). The COl'rf'.!SJ>onding
charts (hgures 11-4 1
1hrl)U~h
NAVAJR 01·40AVM ·l
I
o f 8 45 1xmnds 1s addPd to t h" fot>1 " "m'11ining ;111
300 nautical nules. Assume that no d istance is covered durlng combat.
'l'hcse values are ploucd as shown on the Sample
Cruis~ Back, Ocscc11l , and Landing Rcsen•c plot at
fuel r ematntng ol 9 10 pounds (800 lb • 110 ib •
~l O lb) and 64 nautical miles dJ.s tance.
A&t£1.l5EO
THl\"OlttT\I~
C:ltl.llU U'IC.
SAMPl.E COMBAT ANl.l CUM& TO OPHMUM CRUISE ALTITUDE
CllOSSWEIQHT
P0\1'10S
. 7480
• 2410
Re tu rn al Optimum Cruise Altitud e
.
"Off: AJl61lll!AlfV VAt,UlS Of Flll.l C01f$\Uo1£D
.
2 • 1910
2l.SS2
and no d1staocc covered . Plot this point as shown on
I
the San1plc Takeotr, Climb, Cruise, Dcsct!nt, and
Hold on Station plot at 7270 pounds or fuel remaining
(7480 lb • 60 lb • 150 lb - 7270 lb) and zero distance
cove red.
Climb to 25,000 Feet Cruise Altitude
1'he time, fud, and distance to climb values arc read
from figur es Jl ·l8 through ll -20 at a drag index of
126 a1\d an initiaJ weight of 23, 342 pounds
(23, 552 ib • 60 lb • 150 lb = 23, 342 lb).
l.nilial Wclght
Fuel
Distance
(pound•)
(poundc)
(NMI}
Time
(minut<:3)
23, 342
740
37
6. 0
These \falues are plotted, as shown oo the sample
plot , at a Cue! ren1ai11i11g ol 6530 pounds (7480 lb
-60 lb • 150 lb =6530 lb) and a distance ol 37 nautical
miles .
l~, 17'9
• lA,"19
Cruise Out at 25,000 Feet Altitude
...
1410
T he opclmun\ croise ahttudc fuel requiremcnti:; can be
I
J),f.79
dete rmined from hgur·es 11-27 and 11 · 28. The d rag
index Is 79 and Lhe weight at end of cruise ls 13, 6i9
JJOUnds (12. 769 ib • 800 lb • 110 lb = 13, 679 lb).
l),,61.
6A
Assume arbitrary cr uise fuel increments and con-
l OO
1 Jt.
lOO
28A
300
OISTANCC-AIR NAUTICAL MlltS
struct t he r etum fuel -disLance hne as shown 0 1\ the
Sample Cruise Back . Descent. and Landing Reserve
ploL
,.,,
,
..
MOT[
llf.0TTCOA$ A ltl,HI fltlA..'iQ t,[
CLIM8
OISTA..'tCC
C.Jf/'a~v
l2is.
a.~74
.
'
77,1 •
Climb to Optimum Cru ise Altitude
Fuel
Increment
A·1e r:lge
(pounds)
(pounds)
Wei~hl
Optimum
Cruise
Altitude
(feet)
01;Jt1mum Cruise
Mach Number
500
13 , 929
38, 200
0. 685
500
11. 429
37. 100
0. 685
500
Ji, 929
36. 900
o. 685
Nautical Miles
per Pound (lf F\Jel
01sranee Increment
(na.ut ical miles)
figures 11·16 th.rough 11-20. Assume two arbitrary
injtial climb weights of 15, 000 and 15, 500 pounds
aod read the values a.1 79 drag mdex. Conslnact
r ight triangl e fuel -distance lines a s shown on the
Sampl e Combat and Climb to Optimum Cruise Alli ·
tudc plat beginning at the app ropriate fuel ~n'l3.h1lng
\lalues on the r etu rn a1 optunum cruise ::i.llltude linf:"
(fuel remaining .. assumed initial c.·Im1h we1gt.l -zer o
fu~I weigh t - fu el LO cJhob).
Weight
(pounds)
Fuel
(pounds)
Distance
(nautical
miles)
U,S.OO •
• Z)'JO
The tlmc, fuel , and dis Lance to cJln11> from sea le,·cl
to optimum cruise altitude can be dcterml11ed from
Ln!Jlal
CL/ll8 l"IA'.L AMEi OJSfAl>Cf 1$
F'uei
Time
(n\inutes)
Remaining
(pound>I)
0. 224
112
0. 216
108
15, 000
560
38
5. 9
l G71
o. 200
105
15. 500
600
39
8.0
2131
11·103
lltTUtSEGT'°"'
1Slf1Al.Clf»8Wt:l(;ll'l
T he initial cruise -out weight is 22, 602 pounds
(23, 342 lb • 740 lb = 22, 602 lb). and the drag index
ls 126. The fuel r emaining In the 300-ga llon drop
tank is 1090 pounds (2040 lb - 60 ib -150 lb - 740 lb •
1090 lb) a nd will be used duri11& the init ial porti on of
the cruise-out leg . Read nautical miles per pound of
luel fr om ligures 1l ·27 and l l -28.
o~
'V(t, •t:UA.lltlN'A!llO CltUISE t,IN(
• 11'1
tl)l
· U,lA9
• U,000
l4,'>00
• t(>1)
• lA,A ~O
Maximum
Fuel
Average
locreme1u Weight
(pounds) (pounds)
1090
I
.
I
100
22. 057
Range
Mach
Nuntber
0. 635
NMV
Distance
Pound Inc r ement
or F'ucl
(NM!)
0 .1 31
143
212 270)00) 0)69
20
)0
400
OIST.\NCE: ·AIR NAUTICAl MIU$
flA\ · 202
Plot these \'alues as shown on the sample plot at a
fuel r c mainrng or 5440 pounds (7480 lb - 2040 lb •
5440 lb) and a distance ol 180 nautical miles (37 NM +
143 NM • 180 NM).
Tax1, Takooff, a n d Acceleration
I
The h rst po111on of the plot 1s constructed by working
W.ckw~rdi:> rrom U\e Jancung reserve. 7he remainder
of the plot l~a1l be developed b)' startmg at the taxi ·
takeoff condition Ta.keoH weight 1s 23, 552 pounds
• with a drag index of 126. Ai;sume a fl\·e-minute ta.xl
11-104
At this Point t he external fut~l tank is dropped and the
aircrait weight is 21,329 1>0Und• (22,602 lb.
1090 lb • 183 lb - 21. 329 lb) with a dra~ index of l II
(126 - 15 ,.. 111). Assume arbitrary iuel increments
and cootinue Lo com;tnict the cruise out line.
I
..
NAVAIR 01·40AVM·l
Fuel
Average
Increment Welghl
(pounds) (pounds)
Maxlmum
Ra.ngc
NM!/
Mach
Pound
Number of f"el
Section X1
Part 10
It Is assumed that the holding cond.ltion is Clown
Distance
Increment
(NMI)
500
21,079
o. 635
0.137
69
500
20, 579
0.630
0. 141
71
0PuP.nt tn
5000
F ~@'t
A.lti.t ude from 25.000 FP.Pt
NAVAlR 01 -40AVM· l
111 •
race t rack pattern and the average bank angle ts
15 deg rees. lt is also assumed that the stores are
retained throughout the loner.
Average gross weight is 20, 062 p0<1nd• (23, 552 lb·
7480 lb • 3225
These values att plotted as shown on the sample pl ot
at fue l r c111ainln;< values ol 4944 pounds (r.44 0 lb·
500 lb= 4940 lb) and 4440 pound• (4940 lb • 500 lb =
4440 lb) with corresponding dista nces of 249 nautical
1111lcs (180 NM • 69 NM • 249 NM) and 320 nautical
miles (249 NM • 71 NM = 320 NM).
Section XI
Part 10
lb •~ lb • 20, 062 lb) with a drag
Index of 111. From figures 11 ·35 and 11 ·36 read
loiter conditions.
Ma.xiroum
Ho1d Trn\e
Average
Endurance
Weight
(pounds)
M>eh
Number
Fuel Flow
(pounds/hour)
20, 062
0.370
2910
at 5000 Feet
Altitude
(minutes)
31. 5
Altitude
The mission requi rements can be met, providing that
the bold time over the target is restricted to approxi·
Assume the intUal descerll weight is that weight which
ls determined by the intersection ot the crutse · out
line and the required mission radius (300 NM). rrom
the graph fuel rema.tning at 300 nautical m11e& is
4590 pounds: ther~fore the assumed initial descent
weight Is 20, 479 pounds (23, 552 lb - 7480 lb 183 lb• 4590 lb • 20, 479). Re~d time, fuel, and
dis tance to descent fron> figu r es 11 - 4 1 through 11 · 43.
CRUJSF AT
(TA~K
mately 30 minutes.
2-~.
000 J.""T
21,329
6·10
27 10
SAMPLE TAKEOH, CllMt, c • u1st. oucon,
ANO HOLD O N STAHON
01-:scE!\T TO 5000 ..,.
l)ESCE!<T SPLED - KCAS
20, 689
6.1
• r~os '~.':l'Gtll
. , . .0
. 1210
Clll1fSf: SPF.F.O - KCAS
14 . 2
OROPPFO)
30
'1,)51
. 2'."41
(6.llrilt
MtO ·
Initial
Weight
(pounds)
Time
(minutes)
Distance
(NM!)
Fuel
(pounds)
20. 479
G. 7
30
46
~000
FT
20. 043
1529
31.S
22:;
CM\llH W1TH
UU:ltllAl,TAhl(
CO)llJAT
In lhe following manner. The distance of 30 nautical
miles is covered Jn the descent. To :J.rr.ive at thercquired mission. r.ulius at 5000 feel, a point is
plotted o n the eruise·oul hne at 2'10 nautical miles
(300 NM - 30 NM • 270 NM) At lhls po1111 read Cue!
remaming of 4800 poul'\ds; therefore fuel rcn1aloing at
300 ru>.utlcal miles Is 4754 pounds (4800 lb - 46 lb •
4754 lb). The aircraft has arrived at the required
n\lsston radius (300 NM) with a luel ren1ainlng ol
1754 poonds.
l~,
CUMB TO 01'1'1)1\; M
J\(.TllTDE
(OPTl'101 IJ,T!Tl'DE
37,500 l'T)
FUEL n.ow
LU llH
o. ~ 19
10, 110
CLIMB Sl'Ff.0
11;,t.l!)
(F!:<,\L ALTITL'OF.
3 ~ ,5()() F'l')
llO
570
G. 0
900
30. 2
!!>a
no no
13,679
.\PPH.0.\CH .-\l\ll
remarnmg fuel. At this pol1\t H is adv1sPd that an
the varioos parts or th-O problen\ be integnued into a
single sun1mary 1>lot as shown :u the bcgl11ning of the
probl~nt.
Fuol :lVllil:tblc for l<"itcr le then found tO
be the fuel remaining at end or descent to 5000 feet,
le-Ss the Cue-J rema.ming at sta rt or conibat. Fuel
available is 1529 pounds (4754 lb - 3225 lb=
1529 lb).
CHl' ISE ~LICH~I t'UtL !'LOW
SPEEn /
KCAS
Ul 1111
I
IW
TAKEOFF AND lANDING DATA CARD
1.. \).;l)lNC
CeM:tin items or tn.keoff t>erformance can be entered
01\ lhe 'rakooH and La.ndini' D:ila C:i1·d fur c~. " 'Cmtnl
TV l'.\l~
reference. Entries illustrated on figure 11 f.12 are
rrom the sample n\Sssion problem and nm.}' ~c
read from Section Xl. Part 2. NormaJ lane.Ung 1lCr·
formancc data arc available in Pan 8.
II · 105
I
1
13 . ~69
ltl:;SJ·;nv~
__
H~U
1U.0
tiOCt
....____
f.'igure 11-51. summary of $.'\mple Mis8ion
11-106
l~
OESCE~'T SPF.ED- KCASI
110
The fl.1\al step Ir planning the mission is to determine
the loiter time ovallable over the target wllh the
T - 10001'1'
Kt.:AS OH .MACll
m
D~SC>:XTTO
$1!;1\ LJ::Vt:l,
2910
MACll :W'IJ3Ell
97..
CHL'ISL UAt'K AT
01'1'1Ml")1 Al.:l'l'l't:Dt;
n
n·~~ ~;~w
l.OtrnR SPr. P.ll - KCAS
1101.0 AT
n,•02 ·
These ..iatues are plotled as shown on the sample plot
Hold on Station al 5000 Feet Altitude Over
Target
I
220
I