Flight Handbook - Navy Model A4D-1,2 Aircraft [NAVWEPS 01-40AVA-1]

165 Pages·1961·23.72 MB·English

NAVWEPS 01-40AVA-t
gt.-HC·
Flight Handbook
NAVY MODEL
A4D-l. A4D-2

AIRCRAFT

,

"

•

PUBLISHED BY DIRECTION OF

THE CHIEF OF THE BUREAU OF NAVAL WEAPONS
NAVWEPS Ot-40AVA-t
Flight Handbook
NAVY MODEL
-
A4D-l • A4D-2
AIRCRAFT
•

PUBLISHED BY DIRECTION OF

THE CHIEF OF THE BUREAU OF NAVAL WEAPONS

1 April 1961
Revised 1 Tanuary 1962
NAvweps 01·40AVA·l
Reproduction for non-military use of the information or illustrations conrained in this

publication is not permitted without specific approval of the issuing service (BuWeps or

AMC). The policy for use of Classified Publications is established for the Air Force in

AFR 205-1 and for the Navy in Navy Regulations, Article 1509.

.--------------LIST Of REVIseD PAOe5 1550ED----------­ ..,
INSEU LAnIT REVilED PAOEI. MUllOY aUPlRSlDID PAOlI.
NOTE: The portion of the text affected by the current revision is indicated by a vertical line in the outer
margins of the poge.
Page Dtue 01 Latest P4ge Ddte 0/ Latest

No. Revision No. Revision

"Flyleaf .1 January 1%2 "'79 "',." ....... I January 1962

.1 .. ,.. "1 January 1962 "'80 ..............1 January 1%2

"2 ............... 1January 1962 "'SOA ., ........... 1January 1%2

"2A ....... , .. " .. I January 1962 81 ' ..... , , .. , , , I October 19M

, .. " .. "", .... 1 October 1961 82 . 1 O(:tober 196J

*8 . _, , , .......... 1 ]IUlUary 1962 "S3 ' , , I January 1962

*9 ., .... ,., .. ,.,. 1 january 1962 "84 1January 1962

10 , ...... ,"'"",,1 Julyl961 85 ,1 October 1961

lOA , ....... "", .. ,1 July 1%1 86 .1 October 1961

12 , .... 1 October 1961 87 ,1 October 1961

13 .... , , , , , ,1 July 1961 88 . , , , 1 October 1961

1S , .... 1 October 1961 90 , , I July 1961

16 "." .. " .... ",,1 July 1961 91 ........ , .. I October 1961

*17 ..•.. lJanuary1962 92 , .. "", ...... 1 October 1961

"19 ' .... 1January 1962 92A ....... "",1 October 1961

"20 '''''''''''''' 1 JOIIuary 1962 93 , .. " .... "".1 October 1961

*21 .. '" , ,1 January 1962 94 ........ , ..... 1Octoberl961

*22 , . , . , 1 January 1962 95 ...... ,', ..... 1 October 1%1

*23 ' . , , . , ..•. 1 January 1962 96 , ...... " .... ,I October 1961

-24 "", .. ,', ... , 1 January 1962 91 , .. " .. " .....1 October 1961

*24A ....... ,., ... 1 January 1962 98 ...... ,I October 1961

*25 , ... , .... ",.,1 January 1962 101 , ...... "",.1 October 1%1

3Z ."".. """,1 OctOber 1961 103 , ....... "",I October 1961

34 .... ' , ,. ,1 July 1961 105 ", ........ ,1 July 1%1

35 ,"",.,.,",' 1 October 1961 106 . , , ... 1October 1%1

36A ..... " .. " .... , 1 July 1961 l06A ......... , .. I OClOber 1961

37 , ,I July 1961 107 .•.... ' •.... 10croberl%l

39 ' ...... 1 October 1961 110 , ..... , ........ ,1 July 1961

40 .... "',, .. ," I October 196 1 IIOA "" ... "" .... 1July 1961

45 .. ", .. """,1 October 1961 !lOB " .. " .. " .....1 July 1961

"46 ' , , , , , '" . 1 JOIIuary 1962 lIOC ........ ", ,I July 1961

48 . , , " .. , , , ' , ... 1July 1961 1I0D .. ,.. .. .. , ..1 July 1961

49 ' , , , , , , , 1 July 1961 '1l0E .... , .... , !]anuary 1962

/j50 ., .• , .",...1januaryI962 II! ' " .... ,1 July 1961

50A ", .. "IOctoberI961 112 '" , ,1 October 1961

51 ... ",1 October 1961 113 ""." .. 1 OCtober 1961

53 ' , , ..... 1 October 1961 114 .... ",1 July 1961

54 ..... 1 October 1961 "'116 .... 1 january 1962

56 ' , .. , .. , , , , , , ,1 July 1961 "'116A ... ,.", ... ,ljanuary1962

"'57 ... , .. ,1 january 1962 1!9 '"'''''''''' 1October 1961

58 . ,. . . I October 1961 "'120 , ,1 January 1962

S9 """1 July 1961 120A .... ' ,I October 1961

60 .".,' ,1 October J961 122 , .. "",1 October 1961

60A , , ,.1 October 1961 128 , .. " .... , .. ,1 October 1961

62 .",.. " .. I July 1961 "131 , ., , , , ,I January 1962

"'65 ...... 1 january 1962 138 . ,1 October 1961

"'66 ",' . , , , . 1 january 1962 "139 ""1 Januory 1962

"'66A , .... 1 January 1962 "'140 ' .. , .. 1 January 1962

*68 .1 January 1962 "'141 ... 1 January 1%2

6SA .. . .1 October 1961 142 , •. 1 October 1961

69 ".",.",10ctober1961 "143 ' , , , ...... 1 January 1962

70 .. I July 1961

/j72 , .. 1 January 1962

73 .. 1 July 1961

"'7, ... 1 January 1962

76 ... 1 October 1961

77 .... ,. ,1 October 1%1

'" The asterisk indicates pages reviled, added or deleted by the current revision.
ADDlnONAl. COPlII O. THIS PUBLICATION MAY II OIUINID AS .OLlOWI, BuWep.
USAF ACfIVITIES,-ln .crordance with Technical Order No. 00·5·2,
NAVY ACI1VlTIES,-Use Publications and Forms Order mank (NavWeps 140) and submit in accordance with
instructions H~ted thereon.
For lifting of available material and details of distribution see Naval Aeronautic Publications Index NavWeps: 00-500.
A Reviled 1 January 1962
NAVWEPS 01·40AVA·l
!IINTERIM REVISION SUMMARYII
The following Interim Revisions have been either canceled or incorporated in this Flight Handbook;
No. 1 through 37 No. :;g" ........... ".Page 116
-.
INTERIM REVISIONS OUTSTANDING: (to be maintained by custodian of Flight Handbook)
NII.hn D.., PM,pflle
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Revised 1 January 1962 Flyleaf
NAVWEPS 01-40AVA-' Table of Contenl.
TABLE OF CONTENTS
SECTION I
DESCRIPTION PAGE 1

SECTION II
NORMAL PROCEDURES PAGE 47

SECTION III
EMERGENCY PROCEDURES PAGE 63

>
~
SEmON IV
AUXILIARY EQUIPMENT PAGE 85

SECTION V
OPERATING LIMITATIONS PAGE 117

SECTION VI
FLIGHT CHARACTERISTICS PAGE 119

SECTION VII
SYSTEMS OPERATION PAGE 121

SECTION VIII
CREW DUTIES PAGE 125

SECTION IX
ALL-WEATHER OPERATION PAGE 127

~
..
INDEX PAGE 137
NAVWEPS Ol·40AVA·l Fo....word
IMPORTANT
In order tbat you will gain tbe _x/mum benefits from
tbls bandbook, it ;s imperdtiv. tbat you redd tbis page
carefully.
FOREWORD
-
This handbook is written as a text for the pilot for and all of sections V and VI are currently classified

immediate study and later reference In order that he Confidential and are published in a supplemental band·

may gain complete familiarity with the aircraft be i. book, NAVWEPS Ol-40A VA .IA. In section VII, opera
­
assigned to fly. Thus, as complete a picture as is prac­ tion of the various aircraft systems is discussed. Section

ticable of tbe basic structure and installations of the VIII is not applicable to single. place aircraft. Section IX

aircraft along with the fundamental operating proce­ contains procedut!!s aod information pertaining to all·

dures is included. It is not the function of this hand· weather operation.

book to teach the pilot how to fly the airplane. as it is

assumed he is competent in this respect. However, the
A Confidential Appendix, whicb is puhlisbed under a
handbook contains information regarding behavior pe·
separate cover, contains all flight operating dara cbarts
culiar to the aircraft in various conditions of flight and
for the airplane and other Confidential material which
ground operation.
is supplementary to this Flight Handbook. Refer to
NAVWEPS OI.40AVA·l.A, Supplement to NAVWEPS
The book is divided into nine sections. Sections I, II and
ol·40AVA.l Flight Handbook for Navy Model A4D·l,
III are closely interrelated and contain information A4D-2, Aircraft.

relative to the physical act of flying the airplane. Sec·

tion I provides a description of the aircraft and its

It should be noted that the information in this hand­
systems, instruments, and controls. Emergency equip­
book will be kept current by frequent revisions. Since,
ment which is not part of an auxiliary system is also
however, a slight delay In the dissemination of revision
described. Section II contains information for tbe nor­
material is to be expected, ;t is imperative tbat pilots
mal operation of the airplane and describes all proce­
stdY abreast of pertinent tecbnicdl directives whicb fre­
dures to be accomplished by the pilot from the time the
quently co.'er crilicdl fligbt resmctions or new tecb.
';rplane is approached until it is left parked on the ramp
niques in operation of tbe direraft.
after completing one non· tactical flight under ordinary
conditions. Section III describes the procedures to be
followed in meeting any emergency, except those in In order to make the text as specific as possible, the
connection with auxiliary equipment, that could reason~ nomenclature used to identify controls aod other equip.
ably be expected to he encountered. ment is identical wherever possible to that used in the
airplane itself. Such nomenclature is capitalized. Also
capitalized and enclosed In quotation marks are the con­
Section IV contains the description and operation of all trol positions as tbey are identified in tbe airplane. For
auxiliary equipment which does not actually contribute example, 'The SEAT switch is sprlng.loaded to the
to flight but enable. the aircraft to perform specialized center (off) position, and a momentary movement to
functions. All limitations and resmctions which must "UP" or "DOWN" will adjust the seat accordingly.'
be observed during normal operation are discussed in
section V. Section VI attempts to evaluate any unusual
f1igbt characteristics, both favorable and unfavorable, An alphabetical index is included at the end of the book
tbat the aircraft may possess. A portion of section IV to fadlitate reference to the text.
IIi
Section I NAVWEPS Ol-40AVA-l
•
,.
•
1
Figure' -I. Model A4D-', A4D-2 Airplane.
Iv
NAVWEPS Ol-40AVA-I Section I
-

SECTION I
DESCRIPTION
THE AIRPLANE air bled from the fifth compressor stage and are lubri·
c.ted by oil from tbe oil system. The Wright J65·W.4B
The Navy Model A4D.I, ·2 Skyhawk is a jet.propelled,
and J65·W-16A engines are rated at standard sea level
single. place monoplane with a modified delta.planform
static conditions as foHows:
wing, and is manufactured by the Douglas Aircraft
Company, EI Segundo Division, Designed as a high RATING THRUST RPM
performance, lightweight attack airplane, the Model
Military 7700 100.0% (8300)
A4Dw1, w2 mounts two 20-mm guns internal1y(iJ, carries
Norm.I-oonulluouJ 6780 %oS,," (BC 10)
a variety of external stores, and is capable of operating
. either from a carrier or from a shore base. ENGINE FUEL CONTROL SYSTEM
>
MAIN DIFFERENCES. The main differences between The engine fuel control system consists of a fuel pump,
the A4D·l, A4D.2, A4D·2N and A4D·5 model airplanes fuel control unit, six flow dividers, a fuel primer sol~
are shown in figure I-IA. Additional differences be· enoid, and t\'Yo fuel primers.
tween the A4D·I and the A4D·2 which are not shown
in figure I-lA, are as follows. The A4D·2 has: FUEL PUMP. The engine·driven fuel pump is com·
posed of a centrifugal booster element and two parallel
a. Increased strength in the landing gear and certain gear·type elements operating in series. Should either
parts of the nose structure in order to withstand gear element fall, the operative element i. capable of
H·8 catapult shots at high gross weight,
supplying the engine with enough fuel for full power
b. Increased strength in the horizontal stabilizer, ele­ requirements under static sea level conditions.
vator, keel and fuselage mating points.
FUEL CONTROL UNIT. The engine fuel control unit
c. A strengthened horizontal stabilizer actuator assem·
contains two control systems: a primary system for nor­
bly and the horizontal stabilizer limiter switch reo
mal operation, and a manual system for use if the pri·
moved.
mary system should fall. When the engine is operating
d. A honeycomb tadpole rudder. on the primary fuel control system, the fuel control unit
an
e. An automatic dead reckoning system. provides fuel governing for engine speeds, including
idle. Operating schedules provide optimum tates of ac·
f. The C·8 gyrosyn compass system.
celeration and deceleration for all throttle movements
g. Improved fuel quantity gaging including provisions under any ambient condition. The acceleration schedule
for external fuel gaging. insures a safe surge margin during rapid advancing of
h. Provisions for use of 'I}ATOn the throttle, and the deceleration schedule prevents
.(2)
flame-out during rapid retarding of the tbrottle. When
i. An APN/141 radar altimeter.'"
compressor discharge pressure exceeds a pre-determined
;. A thermal radiation endosureJo value, a limiter causes a reduction in fuel flow with a
corresponding reduction in rpm, which prevents exceed·
DIMENSIONS. The principal three·point dimensions
ing compressor discharge pressure limits. This reduction
of tbe airplane are as follows:
in rpm normally occurs at low altitudes, high airspeeds,
Span ..... , . , ... , ... , ...... , ..27 feet 6 inches and at temperatures below standard, and should not he
Length , ....................39 feet 41)\. inches
misconstrued as malfunctioning of the fuel (:ootrol unit.
Height .......................14 feet ll'!1sincbes
Basically, the fuel control unit consists of two main
valves in series: a governor valve, and a contoured regu­
ENGINI
lator valve. The governor valve is adjusted by throttle
The airplane is powered by a Wright J65·W4B or
position, which spring.loads the valve against a balanc·
J65.W.16A turbo·jet engine with a multi·stage, axial·
ing force from a fly·ball governor. The fly.ball governor
flow compressor driven by a two stage turbine. Engine
senses engine rpm and acts to open or close the gover·
accessories are driven through an accessory gear box by
nor valve as necessary to maintain the throttle-selected
the compressor. Components driven by the gear box
are the engine. driven fuel pump, hydraulic pump, fuel "'MD·l Airplane. BuNo. 137817, 137823, 139919 through
I
control governor, tachometer generator, and the ignition 139970, 142142 through 142161; A4D·2 Airpl. ..... BuNo.
generator. Cooling of the engine is accomplished by the 142082 and subsequent.
routing of compressor air through various parts of the {''iAn A4D~2 AirpJanes having ASC No, 172 incorporated.
(;!)All A4D·2 Airplanes having ASC No. 200 incorporated.
engine. The main bearings of the engine are cooled by «HAil A4D~2 Airplanes baving AS( No. 156 incorporated. ,

Revised 1 Jonuory 1962
Section I NAVWEPS 01-40AVA-l
A4D-1 A4D-2 A4D-2N A4D-S
J65·W·4B J65W·16A J6$.W.I6A J52·P'()
NO YES YES YES
YES
FLUSH FLUSH flUSH SEPARATED
•
NO NO YES YES
NO NO YES YES
AERO I BB AERO I BB AN/AJB·3 AN/AJB.3
5 lITER 5 LITER 10 LITER 10 LITER
YES YES NO NO '-----'
2 PROBE 6 PROBE 6 PROBE 6 PROBE
YES YES YES YES
YES NO NO NO
NO YES YES YES •
SI NGLE TANDEM TANDEM TANDEM
YES NO NO NO
NO YES YES YES
3 3 3 5
YES YES YES YES
AVA· t-, 20628-1
Figul. 1-1 A. Moin Dilfelences
2 Revised 1 January 1962
NAVWEPS 01·40AVA·l Section I
rpm. The correct fuel pressure drop act""' the governor the automatic metering features of the fuel control unit
valve is maintained hy the regulator valve, which is pooi. by re-routing the flow of fuel to the engine aod d ..
tioned by, and compensateS for, ambient conditions and activates the compressor pressure limiter.
engine speed.
The fuel control metering schedules are not compen­
sated for fuel viscosity. The high viscosity of cold JP.5
fuel, relative to lower JP-4 viscooities at the same tern·
Operation on the manual fuel control system
perature, may cause a lean acceleration flow schedule
requires that the throttle be moved sloWly and
which does not provide a sufficient amount of fuel flow
smoothly to prevent overspeeding aad ex­
to meet engine requirements when accelerating. This
cessive exhaust temperatures.
inability of the engine to accelerate above a certain
RPM, usuaUy 78-82%, results in a "hang-up" condition. On airplanes incorporating J65 Engine Bulletin 240,
if the linkage between the COCkpit throttle lever and the
When the engine is operating on the manual fuel con­
engine fuel control unit breaks, the unit automatically
trol system, all fuel metering is accomplished manually
seeks approximately the 87% rpm position, which nOt­
by the throttle through direct linkage with an emergency
mally allows safe flight and controllable landing.
throttling valve in the fuel control unit, but with no
compensation for ambient conditions or engine speed. The engine can be shut down by moving the FUEL
An emergency solenoid valve, actuated electrically by valve to "EMER OFF". (Refer to MANUAL FUEL
the FUEL CONTROL switch in the cockpit, isolates VALVE CONTROL in this section.)
\
4 SSA67 8
21
1. sp...db"d<e
13. MK 12 MOD 0 20·mm gun

lAo JATO igniter terminal
13A. External {lOwer receptacle

2. Aft engine compartmem acce8S door 14. Fwd engine compo and accessory section access door
3. Oil tank 15. External pneumatic Staffer
4. Integral wing tank 16. Catapuh hook

5. Fuel nozzle grounding receptacle
i7. FueJ nozzle grounding receptacle

SA. AN/ARC27A UHF radio antenna
17A. Fueling points

6. Cockpit canopy air bungee cylinder 18. Barricade strap detent

7. External CANOPY JETTISON handle!!)
19, Wing slat

7A. Thermal radiation endosureCS )
20. Arresting hook

8. Picot tube
20A, JATO mounting hooks

SA. Fueling probe en
21. 'ra<.lpole rudder f21
9. AN/ASQ~17B Integrated Electronh; Central
10. Static vent O)A4D~1 Airplanes BuNo. 142142 through 142235-; A4D·2 Air.
lOA. Statk ventO!) planes BuNo. l42097 through 142141.
11. Apl'roach light {;l) A4D~2 Airplanes only.
12, Emergency generator ullAl! A4D·2 Airplanes having Ase No. lS6 incorporated,
Figure 1·2. General Arrangement
Revl.ed 1 January 1962 2A