Douglas A-4M - MAXIMUM TAKEOFF WEIGHT - WITH AND WITHOUT JATO

Seclion XI
Part 2
NAVAIR 01-40AV~I-l
SAMPLE TAKEOFF DISTANCE
FA,1 ·lJ9
applyin~ the corrt!ctions f or variation from standard
conditions. The first Hne speed check should be
made at the 2000-fool runway marker.
I
~ ~ i ::PSl;::::l::k
(For figure 11-8)
(J)
Runw:IY g l' adient
-2 percent
(K)
Headwind ..
10 kn
(L)
Runway I,ressure altitude.
2000 ft
(M)
Ambient runway air
tempprature '
30C
(~')
Takeof! weight
20.000 lb
(P)
Indicated airspeed
133 KTAS
MAXIMUM TAKEOFF WEIGHT - WITH
AND WITHOUT JATO
The maximUIll takeoff weight (figure 11 -9) is given as
a function of pressure altitude and ambient ai r tem-
peralUre. The d.'lta basis for this ch.art assumes that
the landing gear is fully extended. takeoff is at ai r-
speeds shown in figure J 1-8. the aircraft is climbing-
out with MILITARY t hrust with t he assist of g round
effect. multiple carl'iage stores are carried on wing
11-18
statio ns. and wing flaps a re set ilt the half-flaps
position. The maximum takeoff weight criteria is
based on the most critical oC the fallov:ing:
1. Excess thrust shall not be les," than minimum
establlstled by NATC flight test.
2. The safe (ire speed limit of 175 knots ground
speed shall not be exceeded,
NATC flight test of the »'lodel A·4E aircraft shows
that the above criteria. when met. will provide ac-
ce ptable climbout characteristics. Since , JATO burn-
out occurs allift·afL this chart is \'alid far bOlh with
and without JA TO assist.
SAMPLE PROBLEM
Maximum Takeoff Weight - Operational
(For fi':"'1.lre 11-9)
(A)
Ambient runway
air temper:1tu r e.
30
n
C
(B)
Hunw:lj.' pressw 'e
altitude,
4000 it
(el
foobximum takeoff wei ght
23.220 Ib
SAMPLE MAXIMUM T AKEOFF WEIGHT
F1\ 1 -140