Pilot manual flugzeug handbuch focke wulf fw 190a 8 english ocr

D. (Luft) T. 2190 A-8

For Official Use Only!

Aircraft Handbook Slitgtrtra,ni/a,t ed)ult 4/1)0.• 6IdJ2 •

2.

311gemleien 11. :

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(Effective July 1944)

Issued September 1944

This is a classified document. Misuse is punishable

Aircraft h

contents

Part 0

General

Part I

Fuselage

Part 2

Undercarriage

Part 3

Control unit assembly

Part 4

Flight controls

Part S

Wing assembly

Part 6

Powerplant

Part 7

Engine operating and fuel supply system

Part 8A

Armament installation Supplement I: A-8/RI

Part 88

Bomb release system

Part 8C

Special weapons system

Part 80

Special fittings

Part 8E

Camera system

Part 9A

General equipment Supplement I: PKS 12 Patin directional control

Part 98

Radio installation

Luftwaffe High Command Berlin, 5 September 1944 Services Chief of Technical Nr. 280513/44 (E'Ste. Re. E2V)

I hereby approve D.(LuftJ T.2190A_B __ "Fw 190A_B Aircraft handbook September 1944."

(Effective July 1944) Issued

It is In effect from the date of â&#x20AC;˘Issue.

By

order

Wit tmer

To reduce the preparation time of the Fw 1 90A_ 8 technical handbooks, the ar t 1st s hove used some drawings originally prepared for e.!lrller marks of this aircraft. Where there .!Ire points of differ_ ence between them and the Fw 190 A_ 8 , they ar e marked with an .!Isterisk t*J. See the general arran gement drawings attached as Annex A to Part 0 to resolve .!Iny differences.

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part 0 General

(Effective July 1944)

Issued September 1944

01

Genel""ei

I. General data A. Specificatians

Armour f ir-e.

An equipment bey, accessible through e hinged cover ,

1. Purpose The Fw 1 90""_8 is possessing both

platIng protects the pIlo t against enemy

5 i n9 I e_5 ee f

8

f'

91"1 t er e' r eI'" ef t

high top speed o!Ind good mtmeuver_

e

!lbllify . It can eiso be emp l oyed es e fi ghter_bomber cer rying b 0 m b s, or es en ex t ended rlmge fig h t e I""

cer rylng an underfuse l ege drop tenk.

is loceted 1ft the rear fuselage . A fabric bulkhead, elso l oca te d in t he aft fuselage, preven t s the suck_ Ing o f engine exheust f umes fo,..ward into the cock _

pit. b, Undercarriage

The undercerrlege consists of a two strut m.!lln geer unit Md e t"llwheel . The t ai lwheel can be swivelled thr ough 315(;1> end con be locked into posi t ion ,

Undercerriege ectuetion Is electricel; opere ti on Is monitored electrice l ly, by en undercerriege position Indicetor , end mechenice ll y , by en indicetor rod .

â&#x20AC;˘

â&#x20AC;˘

The mein undercerri ege members ere et t eched to the meln sper , retrllcting inwerds. When retrected. they er e comp letel y stored with i n eper t ures In the wing I eed f ng edge end ere full y covered by f e i rI ngs IInd covers .

Duri ng und ercerrlege retrection , the teJlwheel is pulled up end held in p i ece by "e cllble et t eched to the redlus rod hinge point on the rIg h t undercer_ rlege leg . The lowe r he l f of the tei Iwheel remelns exposed after retraction, serv i ng, In thet position , es en emergency tell skid .

Fig . 11 Genere l view

2. Type of construction The elrcrllft Is e slngle_englned , can t ! lever low_ wi ng monoplene , o f 1I11 _metl!ll construction, with e single vertlcel tei I I!Ind retrecteble undercerr iege .

c. Control surfaces The horlzontel tlnd verticlIl tei I surfeces are posi _ ti oned cent r ally on the tell unit ; the eiler ons, ou t boerd on t he wi ng tre lllng edge . The lending f I epS I!Ire pos r t r oned i nboe r d of the I!III erons on the win g lower rel!lr surfl!lce .

d. Fly ing

3. Airframe a. Fuselage The fusell!lge Is composed of a Dur el covering over a monocoque frerne . At Its forward end it is of circular cr oss_section t o metch the sh ep e of the power_ p ll!lnt. .... t the reer end It is of ove! cross _section .

It compr ises twomlljor sUbsections, the forwerd fuselege !firewa!1 to bu l kheed 81 end t he rear fuse _ lllge Ibulkhelld 8 to bulkheed 141 .

The engIne bearer IIssemb!y Is I!I tteched t o t he f i re_ well (bulkhelld 1) . The cockpit and fuel tanks li re housed in the for wllrd fuse lege . In an emergency , the cockpl t canopy clln be je tt isoned by t he ectul!ltion of an explosive chl!lrge .

controls

Elevlltors IInd IIller ons lire IIctullted by the pilo t' s control stick ; the rudder by foot pedllls . Movement of the con tr o I s is eccomp I i shed through ceb I es, DUZ flexible push_rods I!Ind be l lcrenks. Through differentfl!ll gel!l rs built in t o the eleveto r end rudder con t r 0 Is , the stick forces lire kept to I!I minimum close t o the neutrel posit i ons of these surfllces.

Recently, In piece of the rudder cont r ol differen_ tiel be II crenk , I!I torsion bar fixture {withou t d lfferentiel movemen t I has been Instl!llled.

The horizontal stllbi I ize r I!Ind f leps lir e electrlcelly ectueted. Synchronized movement of the flap dr ive mo t ors is accompl ished through synChronizIng swltch_

".

Genere I

02

e. Wing unit

5. Equipment

The wing Is o f one piece construc ti on . The mein sper Is continuous, t he reer sper Is divided by the fuse_ lege . Wi ngs end fuse l ege ere connec t ed et bo t h t he rneln end reer s per s.

o. Radio equipment

Mon o c o que type constructi on . The meln spltr forms pert of the lower shel l , t he retlr sper, pltrt of the upper.

FuG 25a __ IFF transponde r un i t FuG 16ZY __ Alr_ la-e lr end e lr_ te-g r ound VHF c ommunications and hom i ng se t

b. Built - in ormament Fusel oge l 2 x MG 131 Wlng_roots l 2 x MG 151/20E Wlngs l 2 x MG 151/20E

4. Powerplant a. Engine 8JNI B010 alr::: o oled, 14_cyllnder tw in r ow r e d /et engine wi t h two speed supercharger, r educ t ion gear_ ing and en g ine c oo ling fan .

A control unit (Korrmcndoge r'ctl eutometicelly adjus t s end monitors elrscrew RPM, boos t p r essure, fuel mixture , Ignl'I on timing edjustmenl end super chllr ger Sw I t chover .

c. Armament modifications Verlous wee pons Instelletlons a r e a v al la b"~; the ch a nges epply 10 the wIng moun t ed we e pons on I Y • The SUb_designat i ons are liS fol l o~s l A_B/R1 A_B/R2 A-B/Fe

2 x 2 MG 151/20E 2 N-X 10B 2 MK 103

b. A irs crew Three bleded cdju s tcb l e olrs crew wi th c onstant speed un I t . In case o f the fell ure o f the cu tome t ic adjustment c on t r ols , or of the en g ine, t he b lades can be e l ectri c ally posit i oned b y a thumb ac l ull t ed manuel swi t ch .

Airscrew d i ameter Is 3,30 m 110 ' 10 - 1.

c. Tank s Fuel tanks ! Two self _ sellllng fuselllge t anks wi t h a total capllclty of 524 L!ters 1115 . 5 gall . For_ w erd lenk 232 Llters 151 gall , r e llr t ank 292 Llter s (64 . 5 gllll.

A drop tank of 300 Llter 166 . 2 gall cepllci t y cen be car r ! e d on en ETC 501 rack ben eat h the fus e I age .

0 11 tank I A clr cu l er tenk~ protected by en e r moul"ed nose ring, wlt l"l a capoc l ty of 55 Lj ters 112 . 1 ge I I • An armoured ring also pro t ects the 0 1 I cooler .

Hydra u lic fluid tank If or c on t rol unlt) 1 Tl"le engine moun t Ing ring serves es con t elner. Capacity 5, 6 L1 ters 14 . 94 qt I .

Primer fuel tank I Bui l t Inlo the real" fuel tonk, CapacI ty 3 Llters 12 . 64 q t l .

Be h ind ou lkhelld B there I s elso prov i sion for the Instellatlon o f e GM-1 tank , B5. llt er 118 . 7 gill I capacity, or an eux i llary fuel tank, 115 L1ter 12 5 . 3 gal l c epee! ty .

B. Aircraft data 1. General measurements Ol menslonst Span • • • • •••••••••• • • • •••••••• 10,50 m 134 1 5, - ) Overall l ength .. . ......... . .. B, 95 m 129' 4, " ) Height ••••••••••••••••••••••• 3 , 95 m 112 '1 1,- ) Wlngs l Span • • • • • • • • • • • • • • • • • • • • • • • • • 10,50 m 134 ' 5, - 1 Max I mum chord •••••••••••••••• 2 , 30 m 17 1 6 - 1 Wi ng arell • • • • ••• • • ••• •• • ••••• 1 8 , 30 sq m t195 . 6 sq ftl Contro l surfaces l Hor! zonte 1 t 11 11 erea ••• Ve r tical le I I IIrea • • • • • Aileron ere ll • • • • • • • • • • • F l llp area ,

............

.

2 , 73 1 ~ 56 1 , 93 1 , 69

s. s. s. s.

m m m m

••s.

129 . 4 I' 6 , 8 120 . 7 11 B. 2 s.

s.

III III III III

Undercarr l age l TraCk • •• • ••••• • • •••••• • ~In t i re d ImensIons , •• lel I 't ire d i mensI ons ...

IhJlnwhee l rims •••••• • • ,

3 , 50 m 11 1'6 " 1 100 x 175 350 x 135 or 3BO x 150 VOM/B-2090 B_2 or A_3J VOM/B-2061 ..... ,

Tal lwheel rims ........ .

Me 1nwhee I brllkes ••••••• Geer r etraction ••••••••

KPZ/B-3512 B- 2 or A_2 hydrau I I c eJ ectro-mechenlca l

Genel"al

03

III Fighter operations with 2 MG 13,., 4 IN3 , 5112oe" !lnd Inera,"ed ran ge

2. Engine performance

1111 flghter. bomber opere li ons wltn 2

,m

supercharger low &e ll lng l

r"ke_off end

~r~ .ncy

"I I llude

Speed

"

"'.

pOWI ..

1970

13 mill m&l<1 C 11II'1II end combat power

.... xll'<lWT\ endurence er .. I . .

3940

"" ,.

'''''

Boos'

,.1

20 .2

1350

",.,

22"

17 .0

2'''

I ~ .6

l.e"

" Tok~of

f end emergen cy

..

'8~700

Cli mb Md c omba t powe,.

130 mInI

17,~OO

Mexl_ end urance cru ise

16,000

lll.ex 1_ ecolu",y cry I ee

17. 700

Speed

"'.

,.,

Boost

27"

a,.

E"" I Y equ ipp ed weigh t P I I o!

1608

'" "" ""

""

18.7

1165

22"

17.0

'"

2'''

15,6 ,,~

3, Flight performance

-

Or op ten k 166 . 2 9,,1 J

'"

112 . 1 g"l l

20. 2

,."

'" r ounds ) ." '" 1'51/2rE.

AnTnu n I t I on IN; Iwlny..r oo t sl12 x 250 rou ndsl

AmmunIt I on MU 151/20E lou tb o"rd1l2 x 140 rounds I Olapos"ble weIght on ETe 501 Winter_emergency equlp ..... nt Lo aded wei ght

For det8i led det e see the Flight performence tebles.

11

I

III

I

'" no

'" m -

67'50

' 020

...

6750

67'50 1160

7740

7~'

'" "" "" -

'" "" ,,,

'"

'"

'1'

'1'

'1'

'"

'"

'"

m

m

1140

"

'" "

1072 4- "

1 Q.404 --

"" 222 '"

"" '" '"

m

"

"

9"'52 -

10160-

--

- When 21_011 pr oJecl1hs end leunchers "r e I nslelled, Ihe aIrcraft wei ght Is I ncreased by 624 Ibs, -- When the 4 50L_2 rel e/ls e s ere filled to t he f R." ftdep ter, "Ircrelt we Ight Is decreased by 71 Iba,

4. We ight data

._- AI thi s te ke.off we l gh l,

t he tlrea are oyer l olWled. US" I n cr"es~d tire pressu re Ieee Pert 21 end leke off on l y 'r o.'1'1 e peved runwey or hard, eyen field,

Mlulon t ype,

I1 Fl ghle r ope,atl ons wl l h 2 MG ",,, and .. MG

"'0

Addltl on el eq u Ipmen t

Arnnu n III on IIG

1~20

I

Fue I , reer I6","ge ll

p~r

13 mIll "",xl

Mi nion t ype

Fue t , f orwerd 151 . 1 ge l l

IIIJp erc hllr ger 1'11911 n ltln gl Pewer

151!2OEs, e nd ETe

f or mIssIon I ypes I /lnd ll , 21-cn1 r oeke l l eunche ....; end el so I~e eddl . llonel f use lage fuel IlIIIk e en be Installed ,

En,lty Wi!!lght

Aate<l ollll .. d .. 10.111'10\11 d yn .... l c air pressure I

AI 11 lude

"IN;

We igh t In Iba •

,."

22"

13011'11111

13111,

IVI fl gh ler.bomber openllClls wllh 2!K. "la , "NI; 1'51/20Es, He 501 w l l~ " ETe 5011. l a or 50l. 2s en ER-" edepter

" , Re'ed 811 11ude , .. I II'IOIJ I d yn .... l e air preasunl

" ,,,,

IN;

",/20£_

WIth Ihe addltlonel lunJege fuel tenk, 11 5 LJr 125. 3 gell Instelled, the elrc re't we Igh t le Increes ed by abou t 26'5 Iba ,

i

,

,

Fi g. 2 1 M8jor

dimensions

04

Generel

11

-.,. t-'

,,, 1

,, ,, ,, ,, ,

2

) ,,,

", 1-

+-, Aircraft assembly

1. Major components No

F ig. 41 Mejor components At t eched

Des I gnet I on

to

1

Wings

Fuselege

,

Flops

Wings

Ailerons

WI ngs

4

Engine beerer essemb I y

Bulkheed 1

5

Power un It

Eng inE- be erer "ssembl y

6

Horlzontel st"b lllzer

Vertf c el st"blllzer sper. spindle drive IInd IIntl_ stress frerne /guide

7

E levlltor

Horlzont.!ll shblllzer

8

l.!l ll unI t wIt h vertl c .!ll s ta b ilizer

Re"r f usel.!lge

Ru dd er

Vert ic al steb Jllzer

10

Und ercllrrlage

'I'll n9 and u/c ra dius struts

11

hllwheel un It

T.!Ill un I t

2

,

,: +-2

,,

, ,,

Fig. 31 Bulkheed end rib leyout

c.

)

â&#x20AC;˘ +-,

05

Gener~1

2. Covers and panels

NO Q ty

No Q ty

left fuselage between bulkheads 9 &- 10

231

Location

Purpose

Purpose

Location

Instetletion end removed of equipment 1 n equip_ men t bey

1

1

Engine servicing

Engine cowling , top

Md

10-

24

1

Rt fuselage bet we en bulkheads 10 , 11

External power connection

Engine servicing end spect i on

in_

25

2

ReM fuselege lifting

Lif ting tube covers

Engine servicing Md

in _

26

1

VertIcal I eft

tank fi l ler

27

2

Wing

spection

2

2

Engine cowlings, side Id &- leftl

3

2

Engine cowlings , bot_ tom (rt &- jeft)

4

1

tube

spection

Forward fuselage, rt

Forw ord fuel

pipe cover

stabilizer,

Servicing tal lwheel uni t ond vertlcel stebilizer-

lower surfaces,

Extension of u/c fair-Ings when ETe 501 fit ted

rt &- left

5

1

In f use lege pene I

IlrmMlen t

To open tU""mamen t pene I

28

2

Wing lower r-t &- left

sur-ftlces~

lJndercar-dege lower- felr_ ings

6

1

F use 1 e 9 e

erm6ment

Fuselege weapons Instel_ let ion end removel

29

2

Wing roots, r-t & left

Servicing , installation and removal of wing_root weapons

2

Wing

undercarrlege upper fa/r_

pone l

7

2

Bulkheed 1, rt &- left

Access to r-udder pedels

8

2

Windscreen mounting unit , r-t &- left

Fuse l ege wellpons instel _ letion end remove I

30

9

1

Bulkhead 5 ,

Control surfeces cord stowege

locking

31

2

Centre wing cep

10

1

Forward fuselage, rt

Rear fuel tank filler pipe cover

Wing leedlng edge, rt '" left, betwe en nose ribs 7 '" 7e

32

4

11

1

Beh ind pllot 路 s see!

Stowage beg cover f I ep

Wing lower surfaces, 2 per side { I e f I &rll, be tw拢"e n mld_

lnsfalletlon, and I"emovc I drive motors

12

1

Rt fuselage between bulkheads B &- 9

Oxygen end eir tank fe 11_ er pipe cover

33

2

"

1

Forwerd f use I left

Wing lower surfeces, belween mid _ribS 6 '" 7

Inst allation end removl!d of u/c . Remove I of wing gun cerlr-idge c eslngs

2

Wing lower surfaces, between mid_ribS 7 &.

Insta l lation , servicing and removal of wing guns

1

2

16

2

left

(l

ge ,

Hand hold cover

Rt fuselege between bulkheeds " '" 12 lom! tfed I

F irsl eid kit

Tai I unit , rt &- left

log

leeding edge

servicing of flap

9 35

2

lnstel l lltion. servicing and remove I of hod zon til l stebJli zer

Wing lower surf ac es, Servicing a ileron contl"ols befween mid_r-lbs 9 & 10

36

1

Rf

Redio bet eccess panel

Fuselege undersides, rt &. le f t , beneeth engine support frame

To cover the u/c lower wheel helves

37

1

left fuselege between bulkheads 9 &. ge

Supplementary tank fi l ler pipe cover (GM..' or extra fuel tenkl

17

2

Fuselage undersides, rt &. lef t, fOI"Wllrd of fuel tenk cover

lnstellation end removal of win g _ r 00 t weapons ammunition boxes

18

2

Forwerd &. 1ef t

rt

Serv i c i ng and i nspec t i on of engine ac cessories

19

1

Forwar-d fuse I a ge, under-sides

Fuel lenks installelion end removal

20

1

Fuselege unders 1des, between bu 1kheads 8 & 9

Equipment

1

Fuselege undersides, between bu I kheeds 9 , 10

Bottom she l l eccess cover

1

Forward fuselege, I ef t

Entr-y step cover plete

22

lower surfeces, rt &. left

fuse lege,

t~ough

cover

fuselage bet wee n bulkheeds 6 , 8

06

Fi g. 51 Covers and p8ne ls

•

•

•

11. General maintenance instructions • • • • A. General servIcing instructions

metal panelling Isee LgN 11 11 9 Sheet 11.

3 . Rivets er e loosel Th i s section includes e ll Instruc t i ons r eqult- eel fo,. general servicing duties .

al when t hey ClIn be moved by instrument: bl when Ihey tire seeted lit

e probe eln

or

slmller

obliqu e eng!e

\ loose r ive ts which were pushed 'hr oug" Ihe

1. Threaded

plugs

Before use , carefully c l een threeds ",i th e c l een rag. Due to the danger of explosion, ensure that Oxygen connec tions are kept free of oil e nd gretlse .

To prevent seizure of bol t threads, smeer them ",i th Greph l te peste before use. Cover screws with t epe alter removel .

2 . Loose rivets In deciding ",he ther or not a riveT Is loose , consid_ er t he fol l owing l

skin et en engle!J cl when

tI

0,1 nYn thick probe (IIn be inserted bet _

ween the rivet heed end Ihe &ircreft Skin up to the rivet shefl IC!lused by joining tI slrong

component t o e week sklnl.

4 . Rivets tire nol loosel

el when they on l y hove b lock rims; bl when e probe (ennot be pushed under heed.

the

dvel

5. Rivets, liS described In p8r es 3el thr o ugh cl , must be replaced during overheul .

3. Push-rod connections

1. Truly loose rive t s rarely occu r! they e r e elmost al",eys due t o poor workmenship .

2 . Rivets wi t h bled rims around their heads are oft e n considered t o be l oosel fran pe st exper_ Ience, howeve r , t hey er e norlll&l l y oo t. The for _ mation of t he 5 e ri ms Is caused by e net U re i ' set t ing ' , due to st r e!';~es ",ithin deep l y mo lded

During i nstalle t lon, the depth of push_rod connector screws can be checked using the connector Inspection hole . When Inserted , the I nspection probe must con _ t e c t the scr ew threeds . Pr o tec t bell _beerlng bUShed push _r ods agains t dir t 'greese and wrop In o il paper I •

07

Generl!lt

4. Covers and panels

!!Iod l i qu id s oep or 500&. "Gl es'Jrit_Airc nlft cl e Me,.." wit h

Cover s and access penels must fit property and close f u ll y . The engine cove r tens ion locks mus t, .... hen locked . r emain under tens i on . The y e re so des i gned the t the l ock cov er cen be closed with nor mal hand pr essur e .

5. Pipes and tubes Al l open pipe endS er e t o be s e el ed wi t h ceps, or o ther simlla,.means , lop,.event the e n try o f di,., a nd f ore ign objec ts. Li nes , whe,.e ab,.esion cannot be avoided , mu 5 t be cover ed with leather . Before the engine is first run, and be f o re Ins ta l lation of its fittings. the lines must be checked wilh a ir p,.es_ su r e . The lines t o be checked mu s t be tightly sealed Md then tes ted using a l ine p,.essu,.e about 50J greater t han maximum sys tem pressure . After the air is shu t off , I h e line s mu s t not lose more than 5J pressu r e in 5 minutes . Leakage I nspection o f fluid bea r i n g lines is c err ied out while t he engine is ,.unni ng on e t es t s t and . Upon thei r reach ing system opera ti ng pressur e , check the l ines f or leaks .

Pipes tlnd tubes a r e coded with co loured rings, or g l ued - on coloured bends , i n accorde nce wi t h DIN 5, to identify the circui t s to wh ich t hey belong .

6 . Cleaning the painted surfaces Check the condi tlo n of Ihe ex t er n a I pa i n ted su,._ faces . Ce,.eful ly I"emove oil and e ngine exheust depos it s wit h Hlkerol 237 " detergent . Then , t ho r_ ou g hi Y rin se o ff t hese lIrees wi t h WCl t e r Clnd dr y them. Cleani n g t he exte,. nal paint wi th gllS , Ben zol , lerpenti ne 01" elcoho l mlx t u,. es , even if t"ey al"e i n di l ut ed solu ti on or in peln t Ih lnn e,., is forb idden .

Th ese s o lvents will l oosen the pelnf.

To recog nize and then remove corrosion damage , I h. aircrafl must be cleaned from time to time , " d esp ec1el l y during o verh eu I .

After dus tin g off the o utside su ,.feces wit h a soft_ heired b r ush , wesh o ff t he fl,.m ly fixe d dirt wit h cl een, luke _werm weter . Or. wash them wit h e weak , non _elke ll s oa p end rinse with water. Afterwerds, wi pe of f t he surfec e s wl th sponges e nd re gs. Cleen th e ma i n end t e l t whee ls f,.eq uent l y wit h water end br ushes 10 remove any dir t. The "Po ln l Cha,., " give s i n f ol"me l ion as 10 the cer e of pain t ap plied 10 stee l end elumlnum per t s .

7. Cleaning plexiglass To r emov e dus t end di rt from Plexigl ass s urfe ces, cl een them wIth wete,. e l 4CJOC to 5()D C, app lied with e natu ro l or visco us spon ge , and t he n bu ff dry wl th a po l iShlng clo t h . To cu t thr ough the heavier dirt .

we fer ,

I n a 1 120 solu l lon , elln

&150

be used.

When bu ffing I!I wet gless penel , put some " P lexlpo l U" on t he buff i ng cl o th. The use of abresi 'l e or o i ly poliSh i ng _, 5covr'"ing _, or vcr-nish c OI'\lloundS, or of gas or Benzol , i s

forbidde n

I t he g l eass panels

wll I become opaque l . Remove ver- nlsh , greGse , 01 I or pelnt wi l h "Sen ge jot ".

Dudn g bu ff i ng, remove I!Iny rema ini ng grel!l se ~md oil wi th " P lex lp o l 1I " . Rub strnIlI scnltches an d opaque glass pMl!!ls wi t h " Plexipol ' " un t il the problem is eliml ne t ed . Then finish o ff t he job with " Plexlpol 11 ". Smell scr e t c hes ce n !llso be re moved mechanl _ clIlly wit h tI twllt fe br ic buffing wheel .!Ind polls i'l_ I ng compound .

B efore pe ln t Jng I n~ ai r craft, co ver all glassed o!Ireo!ls wit h o ll _peper . Further servicing informe l ion Is i nc lud !'d In Luftwaffe pamphlet ~o . 1/96 of 3 . 8 .

1 938__ " Fl1gh l So!I fety Inspec tions and Required Equip_ me nt ". T h~ So!Ime pamphle t Inc l udes maintenanc e Inst r uc ti ons f or the bu llet_resistant g l ass p ane I end the wI ndscreen side panels .

8. Overhaul TAGL No . 257/ 42 provides f or tin ai l" frllme insp ect ion c y c I e of 200/5 . This means Ihe t a fler 200 e ngi ne hou r s e partiel ove r hau I , and efter fi ve pertlel overhauls e co"" l ete overhaul takes p i e ce. An Inspect ion cycle of 100/2 hes been set f or the 8NiN e ngine . A co mp I e le overhe ul i s t o be cerl" ied ou t on l y et Cl .....ein t enllnce Dep o t. If . over the s pece of e yea r, no pertiel ov er he u I Is ca,.r!ed ou l on t he en 91 ne 0,. elrfrl!me, a specl e l insp e c t ion is 10 be cerded out to conf irm t he servi c eeb l e condi t ion of thet elrfrtlme or e ngin e, and s o per mi t i t t o ret e l n I t s s t atus . After 200 t ake _offs c arr y ou t en under_ carrI age ac tuat Ion lest.

B. General instructions for aircraft assembly and disassembly 1. Basic instructions Avo id t he us~ of unsu i t eble t oo ls. Use special loo l s o nly f or t heir prescri bed t as ks. Ceref ul l y plan eec h job be f or e beg inn i ng 11. Ensure t hot I he elec t rlCtll d rcu l t s tire disconnected so th tl t Inadvertant frip_ p ing o f s wit c he s ","on 1 I ceuse antlcc lde n l. Flre_ t I go t Ing equ i pment shou ld be posi t ioned neer t he wor k erea . 00 NOT app r oac h tin ai r c refl wi t h e n open f I time , or smoke i n t he work a rea . On l y use elect _ ri ca l equi pme n t t ha t Is fltl ed wit h a sperk suppressor . Durin g drillin g, e nsur e t het eithe,. no red _hot c hips are ge nerated or Ihat adequate cooling o f t he dr Ill b It is mai.ntelned .

General

2. Aircraft walk zones For working In or on the elircraft, we ar on l y soft so led shoes. For s teppi ng on the outer wi ng poneis, fir s t lily the mllts provided.

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attached to the seme lifting hook . Af te r l i fting , the aircraft han gs i n 11 well_balllnced posi t ion; i t Is steered, during movement, by a cob le a ttached to the tallwheel.

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3. Placement of parts and tools To evold demage t o removed pert s , remove them co~ ple tel y, on padded sheetlng or ma tting, out of the wor k areo. Tools required for servicing and overhau l mus t be carefully placed on padded sheetlng on the aIrcraft. After Job completion, a forei gn 0 b j e c t s check must be carried ou t before the first fli ght .

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4. Marking of parts For major disassemb ly tasks i t is adv isllb le to imme_ d 1 ate I y mar k each removed pa r t, and so ensure tI smooth work flow during reassemb l y. Sped tl l care mu s t be ttlken t o correctly mtlrk the contro l stick con trol rod att echment points tlnd the reltlted push_ rods.

Fig. 8* 1 Trestllng the aIrc r aft

5. Control wire and cable tensions Cab le tension Is t o be measured with en F ~_t ension meter. New cebles must be prestr et ch ed tlfter spllc_ j ng.

C. Lifting and Ireslling 1. Lifting The short lifting c tlble i s pltlced eround the rod In the r etlr fuse ltlge , the long 0 ne around the l ifting lugs on the engine mounting ring; both cab les are

The eircraf t is to be tres lled only on the trestle points provided on t he und ersides of th e right end left wing panels behind the undercerriage pivot points, Th e rear fuse I a 9 e Is plac ed in !I si In9, lifted, end e fter pltlcement of the lifting r od onto the reer fuselage t restl e IW8_' 90 , OQ- l 021 , i s re_ leased.

Importantl The rellr fuselage tr es tle must have a 70 kg 1157 Ibl weight tldded to It when the complete tlir_ c raft, i nc l uding engine end tail uni t, is trest_ led; when the tai I uni t is removed , this weight must be Increllsed to 175 kg 1386 Ibl , If e rear fuselege tres tie IW8_'90 . 00_ '021 is no t

09

evai l llb l e , e makeshift e ...... engement is possible . I n thi s , th e reel"" f use l a g e is supported by!l suffi _ cien tl y l ong liftin g bar , be tween two suiteble

trest l es end is wei ghed down tIIS indicated tlbo ... e .

The r eel'" fuselege tre s ti e , WS_190 . 00- 105 , is used

f or I r es t l Ing only the e irc r ef t t ai I . The trestle is p i eced in the designoted position benea th the r eer fuselege , end wheel c hocks ere p i eced both in fron t

of end behind the meinwheel s .

D. Towing Towin g een be cerried ou t wi t h e l t he r eo t owing crew or tow i ng ve hicl e . When towIng wi t h e vehicle , evold put t ing it ree rwerds !T el l s t ru t fra c t ure) ,

The t ow i ng cah l es are i nser t ed through l oops on the up per shoc k s tru l s . A f orked ha r a t t ached t o the tai I whee I Is used t o s teer the ai r c r aft. Avoid backing up the aircraft during t owing .

Wh en towin g an aircraf t with a towi ng c rew, e nsure t ha t t he a ir c r a ft c on t r- 0 I su r-faces !'.Ire no l pushed !'.Igainst .

To t ow t he !'.Iircraft r- e!'.lr-w!'.Ir ds using a t owing c r e w, slide Cl pip e lor tu bel , s uffi ci en t ly l ong t o al l ow r ooml or tw omen push i ng per sid e , thr ough the li ft i ng l ube. One man handles the f or- ked tallwheel bar .

Be f ore towin g, fi r st e nsu re that t he tailwheel l ock. ing un! I is dise ngeged .

• E. Anchoring ond covering

Fi g. 91 Towing wit h e towing vehicle

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Fig , 12 1 Airc r aft anchored and cover ed Airc raft left standing in t he open /rust be a nc hored, t o Io u r grou nd ancho rs, and c over-ed. P l ace wh eel c h o cks i l'\ fr o nt of and behind each mainwhee l . The f': 0 1'\ t r 0 I sur faces locking cor d i s hooked on t o t h,. i e ft rudder pedal and connected to t he con tr o l co I umn, Th e va r-i ou5 contro l surf l!lces !'.Ire he l d In position by gus t l ocks . For t emortlry parkin g In ca lm wetl t her cond iti ons , us e of Ihe contro l surfaces l ocking cord i s sufficient.

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the aircraf t i s anchored by the t owing loops ; at the re lll'"j by the r-e ar fuselage I I f I i n g t ube .

Fig. 11*1 Tow ing rearwerd wi th e tow i ng c rew

The a irc r a ft rear anchoring l ine is inserted I n ol'\e

General

side of the lif ti ng tU b e , is pulled slightly more I han hal f wa y thr ough , wr apped over the f use lage , r e i ns erted in t h e l ifl ing t ube , and pu lled thr ough 10 t he o ther side .

The a i rs c r ew mus t be so pos it i oned that one prope 1_ ler bl ade poi nts vert lcll lly upwar dS .

The lInc hor i ng l ines are pu l led t igh t. In case of ra i n, t he lines mus t be l oosened as t hey wi ll con _ t r 1I c t when we ttened . On the o th er hllOd, i n s t ormy wellther l high win dsl , I he l in es mus t be lightened.

The power plant lInd forwllrd f uselage are covered by a sin g le sheet . Pu l l over co vers are also p r ovjded f or t he lI jrscrew spin ner , the p il o l t ube and the clInnon bllrre l s .

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D. (Luft) T. 2190 A-a

For Official Use Only!

• - • Aircraft Handbook

Part 1

Fuselage

(Effective July 1944)

Issued September 1944

Fuse I !!Ige

01

Description The Du~cl fuselcge, of monocoque construct ion, Is of circuler cross_section et the forward end for metch_ In9 to the redlel engine; end of QV.!! I cross_section

et the reel'" end for motching to the ttJll unit.

The fuselo!lge Is divided into e forwerd end e re!!! ... section (1 ,21.

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The fusell!ge forwerd section comprises the wlnd_ screen framework 11,31, the engine I;leo!lrer essembly

(1,41, o!Ind the fuel lank cover plInel 0,51.

Fig. 3: Fuel tonk cover panel

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The forwerd fuselage (Fig. 2) exfends from the flre_ wall 12,11 to Bu lkhel!ld 812,21, On the fir'"ewtlll are the attachment points for- both the en gin e bel!rer essemb I 'I 12,31 I!nd the wing mein spar 12,-'11, The win 9 reer spar attl!lchment points tire on bo th sides of Bulkhetld 4.

It conttll ns the cockpit {2,61 Md the fuel tMk comptlr-tment 12,71. The Itltter- Is enclosed by the fuel ttlnk cover- ptlnel (Fig. 31 .

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The setlt mounting fr-tlme 12,81 c lo ses off the r-etlr- of the cockpl t. It compr-ises two fr-lIIlIe segments, e.tte.ched to the fuseltlge s i des, tin d includes integr-tll setlt adjustment chemne ls.

A. Forward fuselage

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Fig. 4*: Rear- fuselage

02

Fuselllge

B. Rear fuselage The rellr fuseloge (Fig . 41 consists of II l ower shell (4.11. left ond right she lls (4.2 lInd 4~31, lIn upper dacklng 14.41. 0$ well os 0 fllbrlc ponel (4,51. lInd ~ re or frome conto l nlng mountin g points for the to i l un! t 14.61.

The 5hel Is ore compose d o f frame segments, longerons and outer sk i n pontls. The l ower frome shell se g_ me n t s are so cons tructed as t o also serve liS plat_ f orms for the Oxyg en bo ttle s , transformers, etc.; wh II e the side shell frome segments carry the 'NIT platform supports. The equipment access penel 14,71 Is lo cated In the l eft she l l , Its hinge being screwed onto the shell . The ponel, Internally strengthened, Is held open by e folded strut, end is he l d c l Clsed by four qu l ck_releese festeners which s i ide into the side shel l. A tube (4, 81, designed to acc omodete 0 lifting bar, forms part of Sulkheed 13.

The upper deckIng (4,41 Is co. mposed of two skin penels, rIveted to 0 U_sheped channel which ects liS II guide f or the cockpi t canopy centre roller.

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F ig . 6*: Windscreen unit

brecket 16,21 serves also es weapon, gunslght end Instrument pane I cerrler unit, as well as fuselage armament cover hinge point.

A self_supporting welded stee l frome 16 , 3) forms th e rear suppor t for the glass panels.

D. Engine bearer assembly

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FIg . 7 1 Engine bearer assemb ly

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A sealed pane I (F ig . 5 1 prevents engine exhaust fu mes from being sucked forward Into the cockpit.

The cellulose acetate line sheet 15,11 is held In pi o c e by a c::eb le 15,21 which Is stretched over the rolled Inner edge of t h>! frlSme (Bulkhead 121, and is sec:u red by a tension l ock (5,31.

Rubber collars 15,41 , enclosing alloy bushings , permit the passage of con trol cllbles through the pane l.

c. Windscreen The wind screen un l t (F ig. 61 Is panel led with three sheets of bul let res is tant glllss 16 , ' I . The mounting

The engine bearer assembly, onto wh i c h the en g ine m 0 u n tin 9 I" I ng I s secured , Is bu i , t up of s t ee , tUbing ond welded fittings. These fittings Include threaded sockets 17,21 f o r ettechmen t to the en gi ne mounting ring, and slotted lugs 17 ,1 1 for attachment to the flrewoll .

E. Fuselage fittings The p' lo fts sea t cons i s t s o f II 0 U I" a I pan I 8 , 1 I riveted t o an armoured back plete (8,21 . The seot is at tached t o the c hennel sections 18,31 at f our points; seat adjustment levers (8,41 are mounted on the upper attachment po ints. To l ock Ihe seat Int o posl t Ion, 11ft the l evers; this Inserts the lock studs Into detents In the 51 ide rails. To re 1 e os e the seet , Simpl y r o tete the levers Inwards.

A baggage compartment 18, 5 1 is 51 tuated

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A refrecteble entronc e lodder 18 ,61 Is positioned on the fusehlge left side. It Is l ocked In the retract _ ed position by tI sprlng.loaded I ever I n the l.!Iddel'" guIde rods. To lower the ledder, depress the ladder extension button 18,71.

e rmement cover 19 , 5J 119111n51 Inedvertent cl osing by hookIng the shoulder slrllps on t o it .

The wlng_rool ermement doors brllce slrul s .

(9,31 lire held open by

Fresh elr enters the c ockpit through I!I ventilation tube 18, 91. A valve, positioned on the f 1 rewel I , perml's fu I [ edjustment of the eh' f low, A rod letlds from the vlllve to a lever on Bulkhelld 3; the I eve r Is acluoted by the rlghl f oo l.

For the function i ng of the coo ling flap IIctUlltJon rods, see Pert 7.

•

F. Fuselage covering The fuselllge covering corrprises the Fig. 9 (see Ihe f o llow i ng pllge).

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1. Canopy The canopy IFIg. 10 1 c onsists of e ~tee l freme 110,11 w l Ih Plexlg less pe.ne l l l ng 110 ,21. The un it moves on be lt.beerlng ro l lers 11 0 ,31 In chan nels se t In t he fusela ge upper deck i ng. Wi t h in t he c anop y Is positi oned the he ed Of"mOUr (1 0, 41 which Is he ld in piece by 0 steel re t a I n In 9 r od 110, 5 1 end by two c ebles .

The can 0 p y Is op e ned end c l osed by 0 hand c r e n k 111 , 11, driving e reck.end_plnl on geer, 10Co!l ted on the cockpit rlgh' we l l . To prevenl t he c en opy fr om being mo v e d reerwerds beyond t he end of the drive se c t Ion "',2 1, Its lest t oo th Is l ocated 39 rrm "i 1nl frem the forward e nd of the secti on . At rest , t h e s pr i ng_l oaded e r 8n k ha ndle Is held In place by 0 s t ud I n t he handle 111, 31 ; 'h i s s t ud f i ts I n t o matChin g ho les arran ged arou nd t he circumfer_

enc e of the circul er bos e plo t e 111 ,4 ). To t urn the c ronk, keep t he hondle pu) led ou t, The conop y c on be op e n ed from outside by s l multo neousl y t urn in g end de pressing a sprin g. l ood ed, notched th umb screw, pos i ti oned over the cronk oK/e on the fu s e l oge right s id e.

The c tJnop y is j etl Is o ned b y on eXplos i ve chorge 111,12 ) w h i c h i s ec lue-ted by f Irm l y dep res sin g ' he red jettison lever In,' I . As the lever 15 dep r ess. ed., it c a uses 0 bushed str u t (11,2 0 1 t o rolse the h o od drIve sect I o n 111,21 from the pi n i on wheel 11 1, 6)J o!Ind simultMeously rotates the s ef e l y pewl 11 1, 10 ) t o releese the firing pin 111,111.

Th e outer tu be 111,13 1 of the j etfisordng mech onlsrn Is o!Itto!lched 10 the reer of the canopy . It c on tol ns the Inner, or f ir i ng, t ube 111.141 whi ch Is f l tled with three see l I n g ri ngs t O lMlntoln a t ight f i t.

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during n o rme I op enin g !lnd c losin g. Is fitted with two ro I1 ers 11' ,1 5f which mo .... e Ins ide the uppe r deck in g e hennel section t" .' 61 .

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len g th of ti me. serely the jettison mechen i sm wi t h wing s enw t1 ',H I .

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2. Fuselage side pane's By hooking t he eftoched e eb l es t o the e ngine beere r ess embl y, t he side p!l n e I s t9,41 een be positi on ed hor l z.onhlly. When so posi ti oned they must not be s te pp ed on.

Opening end closing the side penels By open ing or c los in g these pene l s in en i ncor rect se q ue n ce, one c en, In tightenin g the scr ew lock 11 2,41, exer t e force sufficient to e l lher dlslort th e pane l rI .... el h o l es or the pane I itself. The f o llow ing sequence MUST. therefore, be followed In opening or c losing the pane ls l To open: e lO pen t he qulck _releese fa s t ener t12 ,1 1 end the togg le cl ips (12,21; bl Lo osen the screw l ock (12 ,41. The hook t12,31 wi ll aut ornetieall y spring cll t of its guide.

To c l ose l el Lightly position the Pllnel; then with the heed of the screw, probe f or Its a tt echment base;

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b l Piece the two c lips In pos ition. b ut don" l ock them. Leeve the qulck_releese festener open; cl Turn the screw l ock until further r o let lon be_ comes difficult. M this po i n t the panel has the required te nslonJ dl Give the co rner of t he panel over the hook a solid blow of the fist to f arc e the hook over ell r ounded horn on the engine mo un ti ng rln gJ el Rotate t he scr ew l ock un til its ti gh t; the n l ock t he c l ips end t he f astener .

Fusel l!!l ge

G. Equipment 1. Radio installation The r l!!ldio gel!!lr 15 10cMed in the forwllrd fuselage between Bu I khellds 6 I!!Ind 8 . A hinged panel on the fuselllge right side provides llccess for equipment lldjustment .

T h!s gel!!lr is provided with two anten nl!!l units; one, a T_ shllped wirer stretches between the vertical stab_ i I i zer Md th e sliding canopy , entering the rel!!lr upper fusel('jge Vlll II frequency mlltching device ; the second, I!!I fixed rod , is IOC('j ted benellth the left Inner wing panel .

2. First aid kit Th E' first !!lid kit Is cont('jlned In II holder on th e fusel!!lge right s I de . Access to It is provided by II hinged cover secured by quick_releose fosteners .

3 . O x ygen bottles The Oxygen eq uip ment consists of three sets of sphericlll steel bot tie s, all mounted on a rllck In the equipment bay .

4 . Flare pi stol The f I ere pistol Is secured b y a rubber sleeve mounted on the cockpi t right side at Bulkhead 3. Its 6ImIunition is stored bene ath the right Instrument console .

06

D. (Luft) T. 2190

A-a

For Official Use Only!

Aircraft Handbook

Part 2 Undercarriage

(Effective July 1944)

Issued September 1944

Undercorl""i age

0'

I. Description •

A. Main undercarriage

Unit

"

.,

1. General

,

~Ift.,

•• _'" ...r

• "" ft

,,~,

_ " .... ~ ,)1 "" '."....'09<1",.,.,., ....

~

e . -,...u,d og.o

~

Fig. 1:

_oh

*"0. ' ~ ...... ,~

1 •• 11 _

1. I't ft~.

.1

Underc~rrlege

unit

, t C'OI ....."0<' &th ' 1 ~4 ;ft . " . ' -..or; ,,!! •• ,''',,

l A, I. " ••• Io g • kl ...... . "" " ~ ~o ''''"

The aircraft hos e two strut me!n undercarriage un it 11 r 1) which Is moun ted on the mel n spar'" tmd retrClcts lnwuds, When retrected, the unit fits Into oper _ tures In the underside s of the wing 11,21 end the fuselllge 11,31. The fuselage apertures are either'"

f u ll y covered by hinged doors (1,51 , 01"", when on ETe 50 1 rack I s fitted, pertle ll y covered by filted penels. The underwlng apert ures are seeled by fair.

Ings 11,61 attached to the undercarriage struts.

The main gur Is bo th retre ch~d and .. extended elect. rl cal l y . A cable attached t o the right undercerriage member causes the tell.,..heel 11,71 to retrect simul. teneously with the me l n geer .

2. Main unit construction The moTn geer consIsts of two EC.oleo sh oc k s tr uts 12,1' wh i ch have, at their upper ends, right_angled, tapered mounting es se mb I1 es 12,2); and et their lower endS, houslngs 12 ,3 1 f or the canti lever axles.

A scissors unit 12,4) connecting the upper end lower shock strut m e m be r s, IlIbsorbs torque stresses end ensures proper mlllln geer traCk in g .

Each me 1 n geer strut Is re t r I!I c t e d and extended Individually by e rotetln g drive unit 12,51 powered by en electric motor 12,61, bolted together, they ere mounted on the main sper .

To retraCt the meln geer, the drive unit rotetes the upper rad ius rod (2,7) whi ch pulls up t he l ower

•• ".e

~ Et K" " _ ' ''' 1 uo~, , M; •• ,..,

' ... r ' 041." .....

9 •• t,ot H"" 10c . I • • "00'_ ' Q So. I •• I

" 0"

ol'_io,'

11 ,.,1 0.'" ' ''' 0<110' cool.

Fig. 2; Meln geer uni t Iwith wheel doors fitted)

redlus r od 12,81 end with It the s hock s trut (2,11.

The mein geer members ore secured in the retrected pos ition by powerful l OCk ing hooks 12,91.

A seeled olr_ j eck 12,101 is attached, at one end,

to the drive unit and, et the o ther end, to an attech_ me n t point with in the wing l eading ed ge. Dur in g retrection if Is compressed1 subsequently, olding In the underc errlege lowerin g. In the event of e l ect _ rlcol foll ure I t ensures full undercarriege exten_ sion.

The tallwheel retr&etlon c ab l e 12,111 Is attached to o rod on the right s h oC k st r u t rDd/ us rod h i n g e po int.

3. Up-lock mechanism The mill I n gelllr up_loCk me c hen 1 s m cons I s t s of tw o lOCking un Its 13,1 I, sp urs on eech shock s t ru t 13,21 , and a DUZ_flexlble ceb le {3 ,3 1.

The operation of the up_lock system Is descr! bed below.

Undercorr i age

02

r..-- 2

I ~."

Z So!."

S

"" <<NO, ".mon' "n,.OO

u/< •• 4 U!t ••• i,ion

<00'0" ~" " O.

l i9~"

Fig. 41 Undercarriage controls

j

oo.oZ_!l •• i~ l .

• 'k,c ...

co o '~ ~II h

button. This causes the locking unl t hook to open, rei e es In g the undercarriage legs, and shrts the electric motors. When the gear is fully extended and locked down, a mlcroswltch on each upper radius rod au t ornat Ical I y swl tches off the dr/ ve m 0 tor s • Th i s position Is Shown by the Illumination of the green lights on the undercarriage Indlcetor unit.

"'"d l •

Fig. 31 Locking mechanism

4. Operation Un d e rc ar r leg e operetlon Is conlrolled by push buttons located on the cockpl I left Instrument console 14,11. The undercarrlege retraction button Is secured egelnsl accldentel ectlvation by a safely cover 14,21.

The indicator rod 15,11 shows full main gear extension when the white band at Its base becomes vi si bl e.

While only the red portIon of the rod shows, the gear Is In an unsafe condition.

Th e Indicator rod 15,1) Is attached to the rotating

7

undercarriage retraction After attelnlng the required minimum altitude, retract the undercerrlage by flipping up the red sa f e I y cover over the 'Eln' button and depressing that button. This causes the locking hooks to open and the electrical drive motors to start raising the gear. In the last portion of the retraction CYCle, the shock strut spurs come In contact with the lock_ Ing unit hooks which ore then forced up and locked In place; securing the undercarriage and simulten_ eo us I y swItching off the electrical motors. This pas I t I on Is Indicated by the Illumination of the red lights on the undercarriage Indicator unit.

In addition to the electrical monitoring of the gear posItion there Is also mechanIcal monlloring, In the form of en Indicator rod {5,'1 for each slrut. The top of the rod Is flush with the wing upper surface when the gear Is retrected.

2

6

,

,, In. ',,, ,,, o.' O~l v. ~o '&! I"r,

, ""h."

Undercarriage extension 70

lower

the

undercarriage,

depress

the

tAus'

,

" u'"

<ov«

' . '"Ieo l ...d..

•, •'0 '""• •_"1__uh; "",

.. " « 'd , _ ,.,"

" , \~

0""'9 od .. unll

Fig. 51 Indlcetor rod mechanism

UnderCllr,..' ege

03

drive outer cover 15,2',

~nd

Is led through the wing

upper skin by e bushed spherlcol beerlng 15,31.

Emergency undercarrloge extension In e llse of hi lure o f the elec tric tnOtor~ the main gear can be I 0 'If ere d by pu Illng the eme,..gency gear extension hendle, This monuelly unl OC kS the shock struts, whi c h, w! Ih the help of grllvlty llnd the setlled air_JaCkS, then fully extend, If the e lee t_

cous' n 9 hydraulic fluid t o move down the lines to

the brake shoe servas, for c ing the shoes 1190lnst the breke drums. Removing pressure from the breke pumps releases the brekes. The brekes operete on the Du oServe-Principle.

7. Undercarriage fairings & wheel doors

rlcel monitoring circuitry Is III so unserviceable, en s u re thet Ihe 'lfhl le bonds on the Indl c otor rods

are visi b le,

5. Main tires Th l 30~

r· creft meln tires meesure 700 x 175 rrmwlth mm diameter brakes,

6. Braking

system

, ... In 9""' 101.1.90 ~

"".. I .0.'.

1 t n~I". 1_ , .v..... ' v. I' • ~".. I • • '" "In~.

~ . "".I

...... I_ .. rw'

o .... jo . . Jng 1.. , __ • 1 ....u l ........ _

, - , _-:.:"_: ,

...

' ''w '

8 r. I •.-,... 1 .... "., g

s ,, ~

• ...rI...,

t o PI ... " _ I ...... ~ ..... . f2

t .... p.<) .. , ...

1) 101 1...... 1

1... . ..,.1.

,.! rn~ . I .. c • • ••

Fig. 71 Wheel door e c tuetion unit

, , 90- ... .....

2 er ••• ti ...

} s.-•••• , "".

The ap er t u re s in the unders i des of the wi ng en d fuselage are fu ll y sealed, upon undercarrl ege retrac tion, by two-p iece ,airlngs 17,1 end Fi g. 81 fixed t o the shock strut s , and by hinged wheel doors 17 ,21 !fixed falrlngs ere substituted for the doors when en ETe '01 reck Is flttedl.

• I t .' y•••• ••• • 1.

F i g . 6: BrakIng mechanism

The brtlk lng system consists of a hyd rauli ca l l y actuated brake shoe 16,1 I on eac h main wheel, brake lines 16,21, and a hydraulic pu~ 16,31 atteched to eec h Ee_rudder pedal 16,41.

Th e whee ls can be braked Individuall y . Th e bra kes ar e energized by toe pressure on the rudder pedalsJ

The wheel d oors 17 ,2 1 ar e etttJched by h i nges 17,41 t o the englm! 1000000er s u p p ort uni t 17,31, end ere o pened ond closed mec henlcall y by Ihe movement o f the main gear.

While the undercarriage Is extended, the Wheel doors 17,21 ere kept open by the tension of the spr I ng 17,91 connec ti ng the wheel door struts 17,5 and 71.

Dur ing the f inal phtlse of undercarria ge retraction, the melnwhee! presse s up agtll ns t a plate 17 ,1 0 1 on the underside of the upper strut 17 ,71 f orCing the

04

Undercarriage

•

---.

' -

•

• • •

I AU"_ft'

1

~ _~

.u....

•• lrI. ~

II . I~ .

cn"".,1

, T.I ....... I..- •• klnll p i •••

• , _ 1.1, 1·11 , AtI . . _ , . . !la ~ ...... 101 . 1"1 ",t oo <....... 1 1 ........ h t.lnl • _t1nll nol . .

• GooI •• •• 11 • •

Fig. 81 Right undercarriage falrlngs I Inner I

,.

•

•• •

Fig. 91 Wheel door positi ons during retracti on

Fi g. 8al Wheel doors Ihe wheel door 10 clost. The door 15 locked up by a spring-lOaded catch (1,111 which en 9a ges the INlln geer lower hiring 18,<41 ISu also Fig. 91.

Our 1 n g undercarrl age exlens Ion, Ihe ac:t i on of the strut spring (7,91 forces open the wheel doors.

When an Ele 501 undercarrl age rack 15 fI tted... I h e wheel door. are replaced bywhee I falrlng plates (wheel d oor .truls are also removedl. To decrease the un co ve red area over the whee la caused by Ihe

Fig. 101 Under carrioge Ileft I retracted

Undel'"c&I'"r"loge

05

remove I of the "heel doors, the meln ~er faldngs 17,11 ere lengthened by screwing en extension piece onto the bo ttom of the lower falrlng 18,41.

B. Tailwheel 1. General

, _~.~

_ To ra;'e .1e't'OIQI'

1 ( I.ve to. coo ' ,o l roe.

.

,00II _<r _

...

."'

". , ~ lOC" ; . ' .... 1. .. ' ~ .. I.. ' ...

G l"" . in9 ... ..

,

1

~ooc.l "9

.o t ,.

• ~1 ~~ 9 r .II_.t _ 01", . ..

10 U:... "'""• • I,,, ! " '''~'' ~. , ~. I ·I 12 ~.' "r ~ SIO,I,,\!

Fig. 121 Tallwheel locking unit

2. Tailwheel unit construction Th e tollwheel unit Is c omposed of an EC-shock strut t ",l) topped by e combination roller unit end dawn_

, r.l t,,"n l "oc' ."",

1

1 Rol lor ... 1' .... _ ' oe ' ) lolh.,.. . , _1)"9 or .

• , ...... _ 0' _""1 ~

1. 1, .. " •• •

6 0<> 0, ,0«0

Fig.

n

"1

Q 10,,,,,.

e lOC O' O'

1 'Po, ".1 1

9 ( .'. no l"" lee " loy ' 0 \.I>oc" . ""t 9" '"

"

. r~

~ , " .. II ...... 10

U 10 ' ... . ' ... .... '.,

fo.d • • "If

Tai Iwheel ex t end ed

The Itlllwheel Is retrecled simultaneously with the ma' n geer by e tallwheel retracti on ctlble atteched t o the right undercarrle ge leg which raises It Into the verti c al sttlbllizer and hold s It there.

The tellwheel can be roteted through 360t an d has a cenhrJng lock.

A fabr i c cuff 111,131 prevents dirt from enter Ing the upper portion of the tallwheel unit.

lock 111,21, a mounting anm (11,31, 0 forked housing 111,41, and a tallwheel 111, " . A drag yoke 111,61, att&ehed to both the diagonal spar (11,71 and the mount i ng Gr m 111,31 by bushed bearings, guides the movemen t of the tal Iwhee I un I t and absorbs hor I zon_ tal stresses on It. The locking unit 111,81 15 linked to the elevat or and Is ac t 1 Vtl ted when the c o n t ro J stick Is pulled fully back Isee Fig. 121.

During take_off this c an be used to pr eve n t ttlll_ wh ee I shlmy tlnd possible ground looping. When the tallwheel Is extended, the down_lock Is wedged Into tin enlarged cavit y at the base of the shoc k strut guide 113,101. It Is held there by the heavy duty s pring 113,121 to which It Is etteched.

Durin g undercerriege retraction, the retrectlon cabl e 111,11 1 pu lls the rear end of the down_lock ou t of the guide cavlfy __ tlgtllnsl the f or c e of the spring 111,121 __ and up the guide 111,101.

When retracted, Ihe tal I whee I Is not locked Into pos ition, but Is held In piece by the tension on the retraction c able. The mounting arm 113,31 Is drewn up through the drag yoke (13,61 to rest ageln51 the diagonal spar (13,71.

Undercarriage

06

..

'~~ I~"<' I"" <oblo ~ "".oll.n "~.I.

6 7

'~lle1 G<l l~. tu'"

) ~.ttor 8 8"1'~ '0 , "."nln g '.llor 9'.1 101 , hgtn" bo"., ...-011 lO '.II'r 11 10110' . 0.1 ,., 1" " n" 0" .~_I""k ~

Fig. 141 Tai Iwheel retraction system

, 2 , o ,

o

Sh"" • • Ir . ' .nl. "M o""._loc o _nllng .... for • • " "".. I """.1"9 IOIl ""UI

7 01 0gon.1 .por

~oll.r

O,"g

y.k.

8 loll "h •• , lock 9 ,oeklnll or..

D. Additional undercarriage details

. 0 Shoe", •• ,.1 9ul •• Il

~ .lr . <lIon

cobl .

12 £.'.n.lo • • prl"9

" F.""" c.1t

Fig. 131 Tllllwheel retracted

, o

3. Emergency tail skid When It Is retracted, approximately one hlllf of the t a I I w h eel rema! ns exposed end so can serve as an emergency tal I skid.

o o

o o'

o

, , ,

o

o

,

c.

,

• Monitoring unit

The electrical monltol'"ing unit shows the pilot the position of the main gellr. hllwheel position Is not monitored.

Mlcroswltches on the main gear rlldius rods and In the locking unl t Indicate, t h r 0 u 9 h red or green lights, the mllln undercarriage pos! tlon.

o ,

•

, hut 2 DUI_tl . . I" '.

J ""1o,,

e•• "

~

50111 .1. 001 , 6 ...... . ' , p' U;!

" 'e...

coonoc ' I••

• l",, " '. ". i t e ao l.

9 hu' "" «<0",,1, ...... 1"9

Fig. 151 LOCking unit

I . ."

Undercarrllllge

07

, , lIr- oo.e

1,.,*

1 " ... t o •• , J p i"

'0".'

pi.,.

, , ., t

o

~ot. l . l"~ 7 •• ,.

e

• er """ nu t

I S"<>C~ • Ir . t Z Stl .."... "., ,

_.1 . "..

3

""11

' ''''or f.'r '''g

!/"

• Irh • .."or 10'''''11 p l.t, ~ G"l~ • • " ...... 1 0"""'-'" 6 . _ . 1. l cI"g O"IK"-"' ou l.luo. o

po,.'

I """ . ' - . , Doll.

Fig . 17& Lower falrlng

Fig. 16 : Mein geol" lowe,.. s trut

attec~nt

11. Inspection th e unloaded shock stru t s must bel

11 Ensure the meln gear end tellwheel tire pressures ere 4S shown I" the following tablel T!lke_o ff weight 'p to kg t I bs)

Nr.81 n.hee 15

Tallwheel .1, psi

.1,

psi

4,75

70. 0

5 , 00 5,00

73.7 73. 7

'300 4600

9500

5,00

10 n O

5,25

73.7 77.3

4900

10830

5, 50

81.0

DurIn g ho t weethe,... ensuI""e thot the stated tire pressures III re not excee ded by more than 0 ,3 eo t u 14,4 psi i. Check f or t i re creep by comparIng the

red marks on the t ire and rim. dl s plecemen t Is not permlttedl

More thon 8 m m

2 1 Check braking system for correc t pressure and the broke pedals for permIssIble play.

31 Check t he main gear shock stru ts for l oss of 01 I. If so, add Spind le a ll_Green In GCcordance with the appropriate Instructions . The pressure w!thln

"

[365 psi!

Main gear 25 atu 31 otu [455 psi J Tall s trut Check for a secure fit of the shock strut leather s leeves as they protect the sliding surfaces of the struts from s and, dirt and dust.

C"rr y out adall y ch~k of thesea Jed air_ jaCk pressure. Spec lfledl 95 atu 11400 ps i I.

D. (Luft) T. 2190 A-8

For Official Use Only!

• - • Aircraft Handbook

Part 3 Control unit assembly

(Effective July 1944)

Issued September 1944

Control unit assembly

0'

Description A. General The control unit assembly consists of the horlzontel

, , /r

stabilizer- emd elevators 11,11, the vertical stabi_ lizer and rudder 11,21, the ailerons (1,31, and the lend Ing fltlps '1,41. The control surftlces heve no

servo trims, only ground adjustable labs. The hori_ zontal stabilize,.. con, however, be electrically adjusted, in f I i9hl, for changu of trim,

/

All control surfaces h a v e mtlss balancing, and ere,

except for their leading edges, febric covered.

-

, , ••d,.",., .... ,11 ...

2 (I ••• l or • • 11 ~ Co • • r

•

I

J I rI .. I • •

• ~"" I I .'_"

•••

( .I " ~~

..n. \

Fig, 21 Elevator unit together, to which ere screwed the iel!ldingedges (3,21 end the tips 13,31, The s t e b i l l z e I'" Is etteched to both sides of the d I eg on e I spel'" by tI plvotel mounting. Its letldlng edge uppel'" tlttectwnenf point connects 10 tin electl""ic motol'" through e drive spindle; thus pel'"mitting sttlbllizer edjuslment. Vel'"tlcel stresses 1I1'"e passed , thl'"ough the dl""lve spindle to the vedlcal stabilizeI'" (see Fig. 71.

I

~

('".'orun""" ""Ho, 'r

5 M l ........

Sldewtll'"ds movement of a tl""iangultll'" stl'"ess f th the letlding edge the tell unl t fOl'"Wel'"d

• ,..."'ftll "op.

Fig. '-1 Contl'"ol unit assembly

See Pal'"t 4 concel'"ning actuation surftlces end the Itlnding f I eps.

of

the

contl'"o\

the stab! lizer 15 pl'"evented by r am e 17,31 which Is connected I oweI'" attachment point and to bulkhead,

1. Horizontal stabilizer The hodzontal

stabilizeI'"

Is actutlted by a spring-

B. Elevator unit The e I ev a t or unit hes tI aynmetl""ictll tlldoi I, hes rounded ends, end I a of t rep I 1. 0 I d tI I shtlpe. Its I e od I n 9 edge Is on the fuselege longltudlntll exls while Its ro fa t I ontll tlxls Is positioned 11,5.Rn 10,45 1nl tlb ov e It, It conalsts of tI on e_ pi ec e hol""lzontal stebllizer 12,11 end two elevetor helves 12,21.

Thehorlzonfel steblllzer 13,1115 of A.luminum construction "lth 0 one_piece lSp er. Btlslctllly, it consists of tin upper ond lower shell, riveted

_ 1,0"'. '

.1 .~1 1 1

.....

) 1105

.

Fig. 31 Horlzontel stllbilizer

Control unit assembly

02

loaded switch located on the cockpit left Instrument console, and can be moved between +4- end _1- (see Pert 9A under 111.,6. 'Horlzontel st eb III zer_ .Incidence Indlcetor' end Pert 4 'Flight Controls' r.

2. Elevator The elevetor comprises two Interchengeeble hell units, eech of which is etteched to the steblllzer by three pivot bearings 14,11. The elevator halves ar e Joined et their spars and leedlng edges 14,21.

The elevetor ectuetlon lever Is positioned bet'l'leen the two flanges Isee Fig. 71 .

Each elevator helf unit consists of two freme penels, a spar {to which the leedlng edge is rivet. edl, end ettached ribs. It 15 fabric covered.

Th e elevator Is both aerodynanlcally and mass b a I. ancedJ In addition, it hes ground adjustable trim tebs {4,41.

\ V"" e. ' •••• 11' ....

2 J

~" •••

~

Co • ••

f. "

,

"""~

•• f.c,-", , . _

• '.lOoct''''' .e",

p,.t.

"'.""0.'''' ~.t,I ...

1

l'.err'e.' ,••••

!

~"'." • • •

1. 11

.lob"" " " ,.. _, '"

"v.' •••

1I.c_.' M'.

Fig. 5r Rudder unit

• \,

6 _ " .... t . ' • • " ' .... i . d el ......

, \ I .".'

• •••

2 C........ etl ni

;.g.

'''.!1'

,,

} !Ie'o·u . ....

• 'r!. ,.0

Fig . 41 Elevator half unit

c.

• Rudder unit

Th e centrelly mounted rudder unit consists of the verli ce l slabilizer 15,11 and rudder 15,21 .

1. Vertical stabilizer The verllcal stabilizer end tell unll comprl se a sin 9 le uni I which screws on to the fuselage re e r sect ion (attachment bulkhead) 15 ,31. The vertical stabilizer consists primerily of left 16 ,1 and 21, end right 16,3 and 41, panels end a diagonal spar 16, 51 . The panels are stiffened by ribs; and cepped by a fonned leadin g ed ge (6 ,13J, end e rounded tip 16,11).

The diagonel spar 16,5) carries the f orged fittings f or the tallwheel drag yoke 16,171, the horl zont8J stebi Ilzer (6,161, and the tei Iwheel retrection cable pulleys 16,141. Ineddlfion, the t el lwheel shock strut guide 16 ,151 is atteched to It. ~Ithin the vert ica! stebllizer ere elso posltionedl the

, ..... O' ~'.".

I ~ ....,

I UQP"

~'".' .

•• • • ,.

,.ft ,o n

";~'

• l ow.' . ... , • • Ig. , ~ QIo<; .... ' IOP'6 ~h 8 1 ~I. 9 ~ ,. 10

a

Q ~,. "

'0.'.••'2 o..

"

~o"

110

"

Tt . OP"'

I ) ' " ... ' "~ 00;.

14 ~ .I," e l' ''''

c•• t. Dult .,

H ~ . 'roell ... C", . ",,1 • • ' " • •

f._f._

16 _11"" .. , .... , , ,,....... __ .,I.g "d'M

'7, 8 T . ... " ~"'.' ..... ; ,••• " 'oe_.' ....e•• ' r lOO •• '00_"' ~"

' . ~""U, 20 A" . . . ,

"'.d ' • • 1100_ "' .011 .... lI oe"'''' fr ....

21 ' •••• ell . . . 001 22 <' OI'e eu"

Fig. 6, Vertkal steblllzer construction Ileft penels removed I

Control unit ossembly

03

elevator dIfferentIal bellcronk 17,121, the horlzon_ tol steblllur trim motrr

unit,

and

the

three

17,101, the t a I I wh eel

rudder

attachment

flttTngs

16,18-201. It. large Inspection door 16,211 In the left upper panel permits servicing of the tellwheel unit.

Th

le

horizontal shlblllzer passes through the

t a I I

unit. loprateel the Inside of the toll agolnst dirt, 11 hbrlc cuff 16,221 Is fastll!ned to Rib 11 16,91, and secured to the tellWheel shock atrut by tin elastic band. The tal I wh e le I extension spring

passes fhrough the cuff) this sprIng attaches to the tallwhee I down_lock and to e fitting on Rib 12

16,101.

At Its forward

end, the fabric cuff Is

secured by snap f.asteners.

~ L<>ooer ,1.0' .... 109 4 AUee_.' ... , .. , ... r"GO'" oct • ." ... I••• r J (l.e.rle.1 I. . . 1..- •• 1' l.gM

1 . . , .....

~ ... ~ 2 T ~I. rob , 1.\>0...- .Ivol ..... '"11 • Co.lro pl.or .""09

e l ."";o •

Fig. 8*1 Rudder I h re e pl\lot bearings (B,3_~I, and Is positioned by an actuetlon le\ler bolted to the centre attactwent point Isee elso Fig, 61.

D. Ailerons ".H .11 •• _ •• 2 ...,...lIov l"e

• 1. 1. ~

'r_

lr' .... tIO'.r ,Ir ... fr_

• l lnO.g. rOG , , , •• ,II I.r l.eIG.ne. rol., "n l ' 6 M.... llo"'., .'nll l ....

1 (1 ....1...

, (, ........ ee ••• II ... I ••• r 9 _llon,,1 .... ilia.... 1 1 _ 0 '

""1 01 ' 0 _'10,1., •••• tt .....

11 Orl •• .,1., ••

or'. _''''

12 (I •••• or G'II" •• "., o.lI e ro."

Il Con 'r ol e •• ' "

' ''- '5

~ ... dor

.II,e_.' filling.

.or,,'

'6 1,11""0.1 ,hOCk 11 $I\oc' 01 •• 1 tIOl~ .

1l 1010•• ' ....... rlng U Drog ~oo . __ 0"01 .... . e •• ' 2D Gr.g ,00 .

2' 1.1' ...."' ,,,,,01,,. ".'.go 27 f .....t.

e.1f

2' [,.,;: ,rI •• , I .... , . . . . . . 11' ... l.el.'OIe.I.dleo,''''

••

fig. 71 Tall unl t/vertlcal stabilizer cOll'ponents

2. Rudder The rudder Is constructed, In e manner slmller to the elevetors, of the following c"",onentsl 2 fnme panels, , ~er, end 7 rlbs-_It Is fabric covered. It has aerodynamic horn belanclng IB,'}, mass belenclng end 0 ground odJusteble trim tob IB,21.

The rudder Is ettached to the vertlcol stabilizer by

, ' Mer .1I.e_.' p.lo' ,..- coo.rol r od

~II "

'11""9

: C,o're •• Ioe_.' ,olnt

, 0.,.10•• tt ... _ . , ,.In'

• Id . . . .

Fig. 91 Aileron

Cont~ol

Fig, 9al Al

le~on

o.

unit assembly

skematlc

The al le~ons a~e const~ucted In the same menne~ es the othe~ cont~ol su~f aces; with mass balancing, t~lm tabs and fabric covering IFlg .. 9 and 9al.

• Flop

«"'re .1I.e..... ' IIIIIn9

2 " ndlng 11 ...

} S... I_drcyl . r gr ••".' •• .c ol e cover l .g

• "'.g

E. Landing flaps The lending flaps Interchangeable.

a~e

~ ~

Vh"'ng hol . " , nglf'op .1I .<me", pol ••

1 A<,,,., ....

r ...

8 Grou.dlng .1 ..

Fig, 11, Landing flap mechanical position indicator

of split_type design and are They also have mechanical position Indication; this consists of a graduated semi_circular sc a le 111,31 mounted on the flap actuating erm 111,1). There Is a cI~cular hole 111,5) In the upper skin of both wing he Ives to pe~mlt viewing of this scale f~om the cockpit.

F. Control lacks , $por

Th e~ e are c[~s evallable with which to lock the control su~faces. These su~faces can elso be locked by connecting the control stick 112,11 end the left rudder pedal srm (12,2) by a cord ",Ith e snep fast_ ener at one end, end e buckled strap et the other,

) c_ , Ir_ •••• ,

f".

2 "".0' Ir_ p ••• ' ~

0 " '~ o"oc'-.I HI" ngo po, lIl ... seo"

Fig. 101 Landing flep

They consist of e spar 110,11 end two freme panels 110,2 and 31. The lower su r f ac e Is metel covered, the upper surface Is open.

The landing flo!lp is atto!lched to the wing et points.

three

They are actuated electrically; the actuating o!Irm Is attached to the c e n t reattachment point which has been reenforced.

The flaps can be set to three posltlonsl f I I ght. hike_off, o!Ind landing. RetractIon o!Ind extension are controlled by push_buttons on the left Instrument consol e, The flap position Indlcetor lights are contained In the undercarrlage/lendlng f lap Indica_ tor unit,

Fig. 12: Control surfaces locking cord ettechment

D. (Luft) T. 2190 A-8

For Official Use Only!

• - • Aircraft Handbook

Part 4 Flight controls

(Effective July 1944)

Issued September 1944

o.

Flight controls

Description Elevllltor deflectIon Is limited by mechtmlcel stops

A. General

In the control stI ck mounting bose.

The flight controls consist of the elevator, rudder, IInd elleron control surfaces, and the flap and stabilizer IIctulltlon mechllnlsma.

Th e three sets of control surhces hove no Infllght tr Im capab i lity, possessing onl y ground IIdJusteble

The eh!Vlltor control trllln Is shOWn In Fig. 2.

The construction of the differential unit 15 Illus-

trated In Fig. 3.

trim hbs. The stob! Ilzer IInd landing flaps are

actuated electrically.

Transmlsalon of steering movements to the con

t

r0 I

sur-foee. ,. vIa 11 system of push_rods, DUZ_f lexible

push_rods, end control cables.

The control t r a I n to both the rudder and elevotors contains differential bellcranks which keep control stiCk, or rudder pedal, forces to a minimum near the con t r 0 I surface neutral pasl tlons. About the s e neutral positions, a large movement of the contr-ol stick, or- r-udder- pedals, will result In only a IImall control sur-face movement. This difference decr-eases as control sur-face deflection Increases.

Notel In later pr-oductlon series elrcraft, the differential bel Icrank for the rudder Is r-eplaced by non_dlffer-entlal bellcranks.

B. Elevator controls

• Coot.o! o, k.

4

2 £1 0. . '''' • ..",.1 '0""011 , .... l ""'''-rod • 8oIlc r.~_ 11Iu ....... e ft, ~ C.. "ol ntl n

1 P........ od ft a. II . , •••

"

The contr-o 1 stick Is In the neutral position at a point '-30' forward of ver-tlcal (FIg. , I. Co n t ro I stick IIIOvement Is 2Qilt30' forward, and 21-30' re ar-_ ward.

\1

~Ie.o .",

. ''' ..... 11.' unit

'.,""'od

10 EI , .. I ... 001.0.1.., ... ...

ll .......

Fig. 21 Elevetor controls

-

' ( I ........ o<1.o, lon I ......

I C.. lro l . tlc ~ • , •• ~"'H 2 C."'r ol "Ic~ _"".~ , ... ~ AIt ... o. cO"lrol ' ... . 1011

'or

Fig. ,. Contr-ol stick movement

I Sl~ • • 1.,.

2 l .... l r.... I"" 'or

1 ,.., ,,. 1 .ohl •• "

• 0111 " •• 110 ' er..' ~ ~"'I . I ' ....

6 ".'.0110. ",., . ...... , 111 11"11'

Fig. 31 Elevator differential unit

02

Flight controls

c.

Rudder controls

The ailerons 15,1) ore moved by the sldewards motion o f the co n t r o I stick 15,2). The transmission of control forces Is os shown In Fig. 5.

The rudder control train Is os shown In Fig, 4.

A hole in the cockpl t floor through which the aileron control ann 15,21 posses Is protected by a dust cover,

The position of the rudder pedals tan be adjusted to suit the Individual pilot, by rotation of the adjustment grips 14 ,81 to vary the le n g t h of the ad j ustable push_rods 14,31. The acljustment forward and oft 15 55 n1'T1, for a t ot a I of 110 mm 14.3 1nl.

These grfps are within the reach of the seated pilot and can be moved simultaneously.

Aileron deflection is limited by mechan ica l stops In the control stick mounting base.

Rudcler deflection Is limited by stops within the differential unit.

E. Flap and stabilizer controls 1. Landing flap controls

1 EI ••• d . _Ior 2 " ..... g.... hou . ln g

,0.1 •• ,plndl.

1

EC-~ •••

.,1'''0.11., u.l.

6 Coo l,.1 c •• I••

~

~ ~O<l • • ,

I "n il

p"".'

2 ~"d •• , "'~ , AdjIJ.I •• ,. pu._. rod

• OUt.f ' ••

4 F ... gO • ••• hOr f l l1l.iI

7

I.'. rod.

6

~ud.",

c ••• log

fI ••

A<lju."." .u,,,.,.od

7 8 9 10

Se"'C"g • ••• ,.

FI ...... 1110• • c.l.

lZ

Con., •. rl •• l

VI •• lng ".1. I • • 1'iI uP."" .<In "'n9 I • • e••• ,.

1\ 6t.

eo."•.,.,.

Fig. 61 landing flap system

$ Adju.t •• '. 9'"1.

Fig. 41 Rudder controls The flaps are positioned electrically, the drive motor push_rod being attached to the f [lip c e n t rei attachment fitting. The two motors are synchrcnlzed to ensure equal flop movement.

D. Aileron controls

Each flop drive sys tem consists of an electric motor 16,1 I, a wonn gear h 0 u sin g 16,21, and a d r I v e sp I nd I e (6,31~ all contained within a single unit wh I ch Is attached to the wll':g by 0 pivoting forged anchor fitting 16,41. An adjustable push_rod 16,61 connects the motor t o the flop 16,5). The anchor fitting and adjustable push_rod are accessible through servicing parrels 16,7) In the wing lowerskin 16 ,101.

, /

• •

1 AII.,o" ~

Con',.1 .lIc' ) Alle,on cOntr.1 . .... ,0 • • or I

~

P".~.'04

e.I1 •••••

• " ' •• on con",,' .,. ..

e. II <r ."~

Fig. 5 1 Aileron controls

'

The flop actuation buttons ere l oca ted on the left Instrument console 17,11. An Individual push_button Is provided for each of the three flop posl t Ions tOut, Take_off, 1nl. The flop dl'"lve motors ore act u 0 t e d when one of these but tons is depressed J they ore automatically switched off when the designated flap position Is reached.

A push_button will remain down until another flop selection Is mode, at which time It will pop back up.

Flight controls

03

Flo!1p

position

Is

middle two bulbs

indicated {7,51

electrically

by

the

in the 6_bulb ind"lclltor unit

17,61, The bulb colours erel red_'ln' end green_ 'Out'; there l!i no e I ec t r 1 C ell monitoring of the

'Take_of f ' setting.

There is elso mechllnlcl!l flo!Ip indiceotlon, see Pe,..t 3 Fig. 11,

_'or

I [ 1«.d< 2 • .,.. ..... g ~or .o"" ' i

' ''''1 . . .. 'n<l" 1

I Left

,no""""'", ........

"on

2 P.. ~ · ... fo< 'Ov/' ~ P.. "· .. "",, I., ·To•• ·.U' 4 Pu.~- •• It.n

'0<"

'In'

~

PO'''_

6 6·_

• ••• ' Ieo' ~

~ '~ ol l '

"301'9 •• ~ .

. ..

"W" .'hC'-"

po'"

6 " 01"1 , ... 10 ' . ... ," .... ~'.blilz"' 'n<l.,,,,,, ",., "ni'

Fig. 81 StabiliZer trim unit " dieotor .,,,,,

0.0;«,., ,,,;,

7 S'ob~; •• , ifl<i<Io ... """'"..

I S oob ~~ ., """ ... ;'eII

Fig. 7: Fltlp end sttlbilizer contro ls

2. Horizontal stabilizer adjustment The 5 fIIb I I i ze,..

1nd dence c

~

be III

tered t o COl1llen_

so!Ite for chenges in Illre,.."ft trim, Ac tu et' 0 n Is through en electric motor 18,1) with attl!lched wormgear ho using 18 ,2 1 !lncl drive spind le 18,31, The motor Is mounted wi thin the verticel stebllizer (8,4) end is et lecl'1ed to the leedlng edge upper eltechment poinl (8,5) by the drive spindle tB,3).

The stebi I izer cen be r 0 I e led through 50, from +40 relative 10 the fuselege longltudl nel exis, 10 _10, The normel posllion, es Indlceled on the tall unit IF lg, 9) and on the stebilizer trim Indicetor 17,7), Is lebelled ' 0 '. The '0' merk Is ecluelly +24» reletlvelolhefuselege thrusl line, The li mit pos! t I ons ~re Indiceled on the tell un it by red stripes eond + (plus) and _ (minus) notetlons, T h e steobi IIzer trim switch 17,8) Is loceoted on I h e left Instrument console. The electric motor wi I I run for es long es the sw It ch Is displeced from Its spring_loeded ' Of f' position, As the s teb I I I zer reeches Its upper or lower llmils of movement, the drive motor is switched off by the stabilizer Incidence relay unit (8,71. The stebllJzer Incidence I s man I t ored by en I n d 1 c e tor (7,7 1 on the I eft instrument console. For further detells see Part 9A 'Generel Equipment',

I,

,

Fig. 91 Stebi lizer merkings on tall unit

D. (Luft) T. 2190 A-a

For Official Use Only!

• - • Aircraft Handbook

Part 5

Wing assembly

(Effective July 1944)

Issued September 1944

Description

• le ..... '::P I

Cl·

1 ~.,.

""oe

~ \ 'Ul ~~ .~~e

~ ~."' 590t

11 _ , oh.1I e ~~P " she l l

1 "'''9 tl .

• l ",'ng .... 9. I.. " .0< " '" ~ I .. dl , !; ' ' \1< .. I. ", . " Cl I., tI ['91"

ou'" sec ',.,

g . 'n~ r ........ " .otOun" ' g p~I., '0 r """OII'g .0 1., I .... ~ •• " .... ' """ t

""g , ••

Fig_ 11 Wing unit twheel cover panels removedl

The wing Is of one_piece construction . The meln spar 11 , 11 jo in s the right and left wing pane Is; while the r-eer Spell'" !l,2t is divided by the fuselllge.

The wing Is of all_metel monocoque construction. It is divided Into two shel Is, the lower one containing the meln spel" 11,71, end the upper one, the reil,. sp8r [1, 8 1. Both lire full l oed beerlng members. The

skin panels ere stiffened by ribs end stringers, end ere riveted t ogether.

The l eGdl ng edge pene 15 end tip units 11,31 ere screwed onto the " Ing penels end ere detocheble. The I eed I ng edge un i t compr I ses inn e r 11,4). m I d die 11,5) end outer sections 11,6). The wi ng tip houses e nevlgetlon li gh t.

eftoched . A mounting lug, onto whi ch the fuel ce ll cover plete Is tltteched, Is fixed to the tower pert of the meln sper.

Upon retrection, the main wheels lie In the tlree between the leedlng edge Irner sect i on 12,4) end the engine lower support unit 12,31. The wheels ere protected agelnst engine genereted heet by wheel cover penels 12,11.

Aileron end f lep mount Ing points ere tltteched to the wing fre l ling edges end wing lower surfaces respect_ Ively.

The meln sper ond skin penels tog ether beer wing 10ed stresses, whl le the skin penels elone beer wing torsionel s tresses.

On the meln sp er ere posi ti oned the mounting u n J t s for the meln getlr end the wing guns .

The tllleron con tro ls end the flap drive motors lire contelned within the wing s. Weepon, undercarrlege, tlnd f Iltp octuetion components ere accessibl e through detechabte servi c ing penels on the unders urfllces of the wi ngs.

The wing me I n sptlr is et t tlched to B u , k h e e d 1 by hexegonel bolts 11,9) which attech to both sides of the fus elege . The two portions of the reer spar ere etlch etteched by e single bo lt 11,1 01 to either side of Bu lkhead 4. Streamlined felrlngs cover the me!" sptlr tlttechment points.

Th e engine lower support unit 11,111 Is etteched t o the wing centre section. Positioned on thIs unit ere tw o hinge mounts, to which the meln wheel doors ere

1 " "n l to_ . .... h 2 ._. i n ....r

~ £nSI" ~

I ~

1""", .... por. ~.I .

I "ft~r ...... 1...

\ ~M l n; "' ~

<tu, ...'

Fig. 21 Wheel cover penels

D. (Luft) T. 2190 A-8

For Official Use Only!

• - • Aircraft Handbook

Part 6 Powerplant

(Effective July 1944)

Issued September 1944

01

Powerplont

Description 1. General

provides short

term lncre!lses in the emergency top

speed at eltltudes below 1000 m 13280 ftl.

The elrcreft powerplont Is e BMN 8010.

The BrWi 8010 Is an e ire 0 0 led, 14_cyt Inder, fuel injection engine vdth two_shlge supercho!lrger, reduction geo!lrlng o!Ind engine cooling fo!ln.

The en gin e opero!ltes on the four_stroke combust Ion principle with fuel Injected directly Into the cy II nders, o!Ind ho!lS, for supercho!lrglng, o!I single impeller unit with two self_setting speed ratios.

In flight, the operetlon of the engine Is governed by a control unit.

This unit regulates boost pressure, engine RPM, fuel mixture, Ignition_timing adjustment, and the supercharger switchover control; the pilot need only operate the throttle lever. The contro I unit 15 attached to the right side of the eccessory casing. Special pressure and dreln pump s are fitted t o circulate the system's hydreulic fluid. This 011 Is housed In the engine mount Ing ri ng.

For more

dettllls on this system see Po!Irt 7 'Engine operetlon

end fuel supply system'.

A newer method of Increeslng the emergency speed of the fighter hos been to Insert a pI lot opereted stop cock In the pressure [Ine of the boost reguletor.

The result is thet, et 2700 rpm, the boost pressure, at low setting coIIn be Increased to ebout 1,58 ete (22.04 psi I, end et high setting, to about 1,64 8ft!

123.3 psi I. When thIs s ys t em Is Incorporated, C-3 supplementtlry fuel injection Is no longer necessary

end Is, therefore, omitted.

2. Starter system

The powerp lant is outfltted with a primer fuel injection s y stem. This system spreys primer fuel Into the boost I ines of all 14 cylinders. See Part 7 'Engine operation and fuel supply system' for m or e Informo!ltlon about the system.

A number of fighter_bombers equipped with the ~ 8010 are outfltted with e C_3 196_ ochlnel supplementary fuel injection system. This system

.&1"

1 To.-.I"n t" • • 2 ~ . .r 0".

• Toro l "o

1 Dd • • • ".1.

6 (.gl.o """,ollng r 'n9

~

I •• rrl . ! SI.".,

Fig. 21 Starter instello!ltlon

An Inertlo!ll starter is used to start the engine; It cen be energized either electrically or manually. It Is fastened to the accessory casing by a centre I nut.

The e [ec tr Ice 1 starter switch Is located on the right instrument console. The starter crenk Is Inserted In the powerplant left side; It Is stored in the equipment compartmement; to the right of the access panel.

The turn' n9 mot I on of the s tar t e r cro!lnk on the torsion tube 12,11 Is ultimately tro!lnsmltted to the starter 12,5) In the sequence shown In Fig. 2.

Fig. 1*1 Powerplo!lnt

When the starter Is energized manually, the starter br us he s are d I se n g 8g ed by 8 hendle which Is positioned on the lower left sIde of the auxlllery Instrument panel.

Powerplent

3. Ignition system The engine Ignition current Is supplied by e Bosch twln-tllOgneto which Is m 0 u n t e d on the eng i ne nose c uing.

The two Ignition circuits are electrically Isolated from one enother, one •• rves the spark plugs ne a r the Inlet '0'0 Ives, the other serves those neer the outlet valves. Each plug is fired Individually, Ignition timing being regulated by the control unit.

4. Supercharger air Intake

02

Inteke elr Is delivered, by the cooling fen loceted et the front of the engine, through two shellow duct s (6,11 (p os I t J oned on either side of the co \Of I In 9 1 to two elr Intekes. Dust f 1I ters, which pre ven t the entry of foreign objects, ore fltll!<! onto the Intake openings.

T est 50 have been made on the use of air ducts wl th external Intakes (Fig. 31 on various types of a I r_ craft __ especlally fighters. The Installation of th is type of duct will result In Im proved performance ab ove the reted altitude of the engine through Incr e ased dynsnlc air pressure. Benea th that elt l tude , en gl ne performance Is betler- when using the Interi or ducts.

5. Exhaust system

.. . ' .

'

• •

•

.. ...

·

• •

The exhaust syst~ (F ig. 41 cons i s ts of twelve pipes, divided Into thr-ee groups, wh ich upe I exhaust geses past the sid e end bottom panels of the engine cowling • Ell C h side unl t cOll1)rlses four plpesJ eech pipe Is Individually IIttached to the engine by support struts.

Five pipes belong 10 Ihe bottom group. Those of Cy linders 9 end 10 are welded to ge t h er to form e common unit. The three pipes from Cylinders 5, 7, 9 end 10 ere joined t oget her. The Cy linder 6 pipe Is welded to thet of Cylinder 5; the Cy linder 8 pipe Is et tached to the combined Cy linder 9 end 10 pipe, wh I c h Is, In turn, 11 t t a c hed to the engine by a support strut.

Fig.

3*. Cen tre cowling with external air- Intakes

The side exhaust units ere t o be so positioned that the distance between the pipe Inboard edges end the fuselage side penels Is approx!metely fhr-ee times as greel es the dlstence between the pipe 0 u t boa r d edges and the COWling skin.

6. Powerplant truss The p o wer p I ant truss, wh!ch supports the eng! ne mounting r In g, consists of the engine beer-er assembly end the engine lower- support unll.

The engine bearer assembly 15.11 compr-Ises six we Id ed steel tubes whi ch serve es the top and two side plc k up points for the engine mounting ,r I n g 15.21. This assembly is alteched t o the f i r ew a 1 I (Bulkhead 11 at four points.

Fig. 4;

E~hau.t

lhe engine lower support unit consists of the engine lower support strut (5,61, the fIG 131 casing c h ut e attaclVnent s t ru t 15,71, and the wheel door attech_ ment end support struts 15,81. The unit Is fixed, at Its rear end to the lower edge of the main sper, and at Its forward end to the engine mounting ring. The support strut (5,61 is adjusteble In length. system arrengement

tthe numbers Indlcete the cylinder numbers to which the exhaust pipes belong'

T h. e engine la attached t o the mounting dng by le n b 0 Its which pass thr-ough the ring end screw In t 0 r ubber shock mounts fixed to the rear of the engine.

Powerp lent

03

.'- I

~

Mo ,.

opo,

~"nl

, ,ogl •• 001'" . .. _ Ir 2 ~ngln . _ M i ni r,nll

6 (ngl •• , _

) Upp er otro<_. ' pol.,

1 .... '}1 Udn9 <"w r. 0110<_.' . ,,",

• ,_, '''oe_"'

,.1.,

8 ...... , G_

OI>l>PO,' . " . ,

'''0<_"'

. n d " " PPOI' l

' ''y"

Fig. 51 Powerplent truss

, Slu po •• " .. 11 • • 1. I . .... d<K " 2 SI ...... 11 .

, ,_ •••1,.

• ""'tI" DOno l

Fig. 6*1 Cowling centre section

7. Engine cowling The engine cowling consists of three Interconnected canponents;

the forward section which Includes the

ermoured rings protecting the 011 cooler and 011 tenk !see Port Ell 'Special fl ttlngs'l, the centre section, 8nd the powerp lant rear folrln95 which enclose the engine accessories I!Iree and form the

transition to the fuselage (see Fig. 9,<4 and 5 In Port 1 'Fuselage".

The cowl i ng centre section comprises two side penels [6,1 I wh I c h ~erve as elr Intake duct~, two si de shells (6,31, end en upper penel [6,41. The side cnd lower shells ere at tcched to the side panels by hInges. The up per shell Is f I)(ed, at the rear to a mounting brocket 11,51 etop the engine, and at the front to the cowling forward sectIon. The two si d e ~h e I I s which, when open, can be used as servicing platforms, ere prevented fran opening too far by restraining wires which attach to the engine lifting rings {see Fig. 81.

egelnst which they tie, The lower shells, secured to one cnother by toggle clips, lie egelnal two seml_ cl rc u I ar fittings 17,31 which ere screwed 10 the bottan of the engine.

The support brackets 11,61 which attach to both si des of the engine mounting ring support both the fuselage anmament cover end the fuselege side panels and act as plckup points for the stde panel screw locks.

The side cnd lower shells have toggle c I I p s J the side shells also each have a quiCk_release fastener.

Onto Ihe Inner side of the upper panel are built the following. In the centre, a tube for cockpit ventl_ letlonJ and, on either side, cooling pipes for the f use I age weapons dli ....1n I t I on boxes.

The hinge pins which connect the side penels to I h e side and lower shells, elso fix them to brackets [7 ,1 J on either side of the engine. At their forwerd ends, all components of the cowling centre section lie egalnst e rubber seel positioned elong the outer r I m of the circular oil tank. The side shells ar e also supported by seml_ circular fittings 11,11

I 510e ~&Ul •• pp .... !

2 SI • • ~ ~ . I I ' . Ppot!

J L"...c ..... ,1 o.P~OI'"!

• UIIP,c pon,l .1!0< ...... ' "" .0'"

'$vppor' ,,"'c, .! on ,~ •• "~I". ",.011011 ,lOll 6 Alcllllh! ... 11 .. 1I~ c. n" ... l l nll rl.1I

Fig. 7s Centre cowling support end ottechrnent points

Powerp lont

To evold cooling losses, the baffles of the forward and rear cylinders are joined to form an elrtlght wall (7,7J which Is sealed to the cowling by a rubber ring around Its circumference.

As the forward edges of the cowl ing ere also tight ly sealed, the 81r required for combustion, for engine cooling and for oil cooling cannot escope this area unused.

Th e powl!rplant rear hiring comprises three ptlnels.

The upper one Ifuselege armement cover! is atteched to the windscreen mounting brecket and opens upward.

The two sldl! panl!ls are hinged to the wing assembly and open downwardsJ they conteln the engine cooling flap s (see Part 7 'Engine operation and fuel system' I.

8. Airscrew Thl! elrcraft Is fitted with a three bladed, constant (10"0'" diameter. speed alrscrew of 3300 rrm

Fig.

a-I

Engine In lifting harness

04

lnflight blade pitch adjustml!nt Is normally au to_ ma tic (dependent on RPM), being controlled hydrau_ Ilcelly from the control unit. The pitch ctln also be adjusted menlJally, eg. when the automatic pitch control falls, and on thl! ground.

To change from hydraulic (autometlc) to electrlcel Imenuall pitch edJustment, move the pitch contro I switch on the left Instrument console to the 'MemuaJl position. The propeller pitch can then be adjusted by depression of the appropriate si de 0 f the thumb switch on the throttle lever, this switch hos two settlngsl 'RPM Increase' and 'RPM decrease'.

When rei e as ed, the switch rl!turns to the neutrel 'Off' position.

The pitch control unit, with ettached swltchover motor end RPM governor, Is built onto the forwerd left sldl! of the engine. Propeller pitch Is monitor_ ed mechanically by an Indicetor on the euxl I i ery Instrument panel right side.

Limit switches prevent the movement of the propeller bledes past their allowable pitCh limits.

D. (Luft) T. 2190 A-8

For Official Use Only!

• - • Aircraft Handbook

Part 7 ,

Engine operating and fuel supply system

(Effective July 1944)

Issued September 1944

01

Engine

oper~tlng

end fuel supply system

Description A. Engine operoting system The following nohllons refer to Pe,! 9.... , FIg. '.

On Ihe left Instrument conso l e Is positioned Ihe

thro ttle lever t' ,ll); and, on the auxiliary i ns tru_ ment panel, Ihe fuel hnk selec t or lever 1',181, the engine 5to,.le,. brushes withdrawel kn ob 1',141, and the fuel cut_off control lever 11,1:31.

The coo li ng flap actuation crank ",311 , with Its position Indicetor, is sltueted st the bottom of the me' n Instrument ptmel. After use, the er-link hend le Is f ol ded bot:k.

The throttle lever 13,11 elln be locked t o melnttlln e

predetermined setting by ti ghtening the t h rot tie f r let f on knob [3 ,81. Throttle lever movement is trlllnsmi tted t o the control unl t performance Gdjust_ men' lever as shown In Fig. 3,1_6.

C. . . . .

'-'i

t,K'"

..

01 ...<1

'.... '". , " 1 I .... "'. p. ,._ ,oG

,,\ SI ",,, b_.,on ~I ,." ••• • ' • • • " " Coo l l'q I"r 0<'"0,1,,, Of'" ~ . ,.-

• P"".,oG

I ~O ,IY ,

\

.",I 'I".I'dlu""

) , ... 1... b., 00"'" " .... " ~ ' ... . 10. 0"

I n 1,.,1 0 1 tI, •• o"

6 Co",o' ,.1, or', .......;o

·" i«...... 1

I~ • ...-

I ..... - o< ' ~ ...... " ........ , I ' e' eo""ol

_ ''''0'"' ,,;cll .... ,.0.

9 J .. , 1_'

n' .. '....

"'0"" I"",

~ 3 ..~II"t

'''''or ~". ,.,

• Oot • • , .,.,. ! .... _ " ' 1".ltI., ~ , .... , ' , . " . . . . ,04

oloe.

Fig. 2: Throttle diagram

11'1 e pi lot ISdjusts the throttle lever In accordance with the supercharger p re ss ur e Indic at ion rather than by throttle position alone. Moving the throt tle and thereb y ttie performance ad j ustment lever of a sf opped engine to' the Infllght se tt ing should be avoided, because due to lack o f hydraulic ass 1st, Its subsequent movement to the fully closed position wIll take greater effort than wh en the en gin e I s running.

Movement of the fuel tank selection I ever (3,91 Is transmitted by a torsion bar 13,10) and push_rod 13,11 1 to the right fuel .... alve (3 ,12 1. The fuel valves, Interconnected by a square ahaft (3,13), are positioned on tI fitting on the rur of the firewall (BulkhelSd 11. The lever settings ere, "Aut" (Open) " Vor derer behalter zu" (Forwerd tank closedl

21

"'''«''' "'!i'" "" ......,"" c..t _o ll • • 1... co. " "I 1•• __

n ... ;. .... 1. ~3

II 10... 1..... ...

,.... , c.,· ...... ,...

U

' .... ' n l .. 11 ... to_

11 ' .... 1 •• , ...

Il ,,,,. 1 •• , •• c_lI~q .... /1

"

C. b"

,. "'o.n "rp"

19,.' 10,

10' .... . 1....... . 1\ • • 11 , ,, ...... , . .

, ,.,.,11. ,.. ..-. _ "

"n" ....

,. 1... ~ .......... 1••• , 1, ! O ~,"'.r'"

~

I .....

,'"

I••• ,

.. i.q l . . . ' .... ' ... b' ....... . 1' ....

••••• 1 .... !I . .

,,_I.

n ' .... ,0...'

0< .",,1_

.1 ,,, .. ,•• •1.. "'0'

)0 ""," . 1'. ooun'I., ., « ko' )1 "",,,, , Ion ". "..., .It • • "'".,""

Fig. 31 Engine opera tion (overview)

"Hlnterer behalter Zu" IRear ttlnk closedl "Zu" (Closed) The cooli ng flaps are actuated from the coCkpIt by a hand crank 13,1711 end their position Indicated on a sca led plate. The transmIs s ion traIn is Illustrated In Fig. 3,17_22. The coupling co llars on ·the actuat I on rods (3 ,221 serve as separation polntsJ these rods are &d.jushble In length. They must be adjusted to place a prescribed tensi on on the cooling flap s and thereby prevent their Inadvertent opening In flight.

Importantl At "0" flap opening, the actuati on rods must be set to a tension of 40 kg 188.2 IblJ otherwise, there is e posslblty o f the flaps being there is a possibility of the flaps being pulled

Engine

oper~llng ~nd

open by the slipstream during high speed fl ight .

Before opening the fuselage side ponels ensure the flaps are opened ebout 1()t.

and 4,211 end, If req uired , on auxiliary fuel tank IFi g . 5) within the fuse I a ge fixed t o Ihe rear of Bu I k he ed a I end a jettlsoneble fu el tank (4,261 beneath the fuselage.

that

The sterter brus hes wllhdrawal bu t t o n 13,15) Is p osi t ioned on the auxilIary panel left side) ~ cab le (3,161 attaches II to the brush wlthdrawol mec~anlsm on the starter unit.

T he fuel cu t_off contro l lever (3,23 ) Is sp r I l oeded to the ' Open ' position. During the fuel check It must be held In the 'Cl osed ' position. con tr ol lever Is connec ted by 0 shafl 13 ,24) 10 cut_off valve 13,251 whIch Is positIoned on the fI lter housIng.

02

fuel supply system

Us e of the oddi lionol tenks 15 dependent upon I h e t ype of mi ssion undertaken. To house the fue l required for Increased ranges, either the drop tenk 1300 Lfr /66 . 2 gel I or the auxil iary I an k (115 Ltr/ 25.3 ge11,or bo th (415 Ltr/ 91. 5 gall, con be fitled, On " missi on wIth both cddltlonal tanks fltled, the drop tank Is el'l'f)tled first, so that, in on emergency, it c en be dlsce rd ed .

n 9pump The I he left

1. Basic fuel system (main tanks only)

B. Fuel system

The msln fuel tanks or e conteined in e specls l compertment benee th t he cockpit . This comperlment is divided Int o two by 0 vertlcel wall and Is sealed by e scr~ festened cover p~nel.

The fuel system comprises two fuselage tanks (4,1

Both fuel tllnks ~re fItted wit h e I ec Ir lea I fuel pumps 14,81. Tne pumps s t art opereting ~s soon os

See elso Fig. 4.

•

I

,7,... ....'.0' '....I." ~ H....

f~"

\ , _ , ffll ~. p ol •• • fi ll ... 11 • • ~

6

,,- , .... " OO' v•• ,; , u 'on I IM

, ." " ., ....

~ .... ' q . ... ,

. _ "" It

I,.. , .,,1•• ,

tI • • ' . _ '. ' :1 .... ' •• I w " 'oo' lI n. 11. 0 1 •• 1• •

I. r l " .. ,

., , ... , 1111 " \ ) . . . , " " ,,1110. , _ .".. , . _ .. ' .0' 11 . < ...... ,, "" •• ,.,. "

[",) 1 . . ' .,. , . _

. . . . . , 11 • • " ,.. , . _ " .

' wo'in.;.' . '.... ...... '

,

'ot'

11 1• .;.<" .... _ • ~ !;eoc. '"'u, n """ 11 ..

"_00'.''''

'9 ' .0',~._ .... ,.... '0 '.<' 0_'

"n. , ••.•• ,.1 •• '. ,.. _or. '.0' IOn"

le "•• ,, ••• ,••

11 f •• , ........ ......... .. g 11 ' ' ' ' . ,....... \ "" i '

"n.

71 >1............ IIn. ',u••"o,,; •• ' . 0 • ." , ... 1

U

!xc... . <0 .........", ••

"

R.... ' . . ... .. ... . . . ' .0

~

UO •••,.,. t'90

l'

i~_'i

.u.t.....,

.r." , •••

13 fw.' !l .. , •• ." I ••• I • • • •• 10•• I • • ~ ,

79 fK ">D'I }(I

\.0...,..-

~ . ,.

) 1 ' .. 1 . _ ~I II H • •

) 2 , .. , If ...

n ' ''' ._

'a ........ ,..-, "••1°9

.-.........

,,,..,, <...... < II "i! " • •

) . "" _o f! • • , •• )~

""'- 'sf.... , ..," "'''c"

)0 , ....

n

FIg. 41 Fuel system {general I

" • •

A. ... I .....

,_ , . _

10....

o.

Engln@ operating end fuel supply system

the eppropriote circu i t breekers t1,57J OA the right instrument console ere depressed, end they serve to SU pp or t Ihe action of the engine mounted tMelhekJ pUftll (4,1 8 1.,

A f ue l geuge 11,361, positioned on the auxll

j IIl'"y

Instrument panel, meas ures the contents of each fuel tenk Individually; swi tching to the desired tank

vie e selector lever 11,431.

I IS

The fuel gauge reeds

c orrect Iy In level f 119ht.

The f o ,.ward tank Is fitted with e fuel low level d ev ice, A I'"ed warni ng lerrp (1,41) positioned on the r ' ght 8u)(11181'"y Instrument pl!lnel Ill umi nates at

approximatel y 90 _100 Lt,. 120-22 galll Return_to-base wer-nin g ). A fuel low level device i s 8150 fitted In the reer hmk; It causes .!l white light t o illl.mln8t~ wnen the contents fell to 10 l t r {2.2 grllllTenk switCh_over w~rnlngl.

The fuel pressure Is monitored by the e uxill~ry ins trumen t p~nel.

~

geuge 11,201

on

Eech ten k is provided with e sep~rete filler po I n t 14,31 on the' u se lege right side. Fuel is poured thr ou gh the filler line 14,41 until It begins to beck up 10 the external filler connecti on vi~ the o v~rflow line 14,51.

Fuel lenk ventil~li o n Is ~eeompllsh~d ~t th~ ~pproprlete filler point Ivenll_ I~tl o n line 14,611; ventlletlon of Ihe Boseh floet_ end_p~ndulum de_eer~t or 14,'61 I a k e s p Ieee thr ough the forward flll~r point. Th~ spill tube for the rear filler point c onnects Into the rear tenk ventiletlon line; I ha I for the forwerd I~nk f i ller po I n I c onnects 10 the fuseltlge lower surftlce. The fuel I1 nes 14,9 & 4,111 run from the ~pproprll!!lte tenk fuel purrp (4,61 10 the engine fuel pump 14,161.

excess pressure ' <4,241, end ~ reverse pressure 14,251, velve. Rubber sleeves (s y 5 t em 5ep~retlon points) c onnect the fuel end elr lines to the d r 0 p tenk.

Fuel Is forced from the drop tank to the reer f u e I tan k by tllr pressure drtlWn from I h e supercherger.

This eel I on 15 elded by I h e EP_H fuel put!\' w hie h begins 10 run ~s soon as the ..... bWurfbeh·61Ier .. circu it breaker Is depressed.

When tne supercharger pressure Is less then th~t 0 f the surrounding elr, the EP_1E fuel pump elone feeds the fuel to the rear lank .... fuel transfer limit swl t c h '<4,361, built Inl o the re~r tenk fu~1 pUITp '<4,371, reguletes fuel flow from the drop lank. With the drop lank f i t t ed, Tuel Is drtlWn from the reer fuel lank unt I1 its contents heve fellen to 240 l t r (53 g~ll. At th~t point tne trensfer Ilml t sw I t ch opens end permits drop tenk fuel to flow Into the reer tank until the drop tenk Is empty.

The drop tenk contents are monitored es r 0 I lows r when, efler the limit switch hes open~d, the rear tenk fuel contents sink below 2<40 ltr, the drop tenk Is ~t y . This does not resul t In the swit Ching off of the supercharger ~Ir pressure.

3. Fuel system with auxiliary tank Old. Self_sullng tank.

Int o e~ c h fuel line Is built ~ fuel valve (4,1 0 1 and filter 1<4,121. The filters ere set Int o sui t~ble epert ures Ifllter housln gs l on the forwtlrd side o f th e f1rew~ll. This slllng o f the filters preven ts gas f UITI@S f rem reach 1ng I he c 0 c k P I I. The rig 1'1 t filter connects Into the forwerd tank fuel lineJ th~ left one, Int o the reer tank fuel line. The two filter houslngs ~re c onnected by e spill lIne which connects into the one from the forw~rd f Iller p o int; It prevents the ~ccumul~tlon of fu~ I at the bottom of the houslngs of letlky f I I ter s . Th~ two fuel lines ere connected 10 onl! en o t her by e line which con_ t a Ins e cut_off valve '4,341 whlen remetns 0 pen d uring ~I I normal p owerpl~nt operetlon. This ensures thet bo th suction chambers of the Malhek fuel pump ~Iways conteln fuel even when one t~nk is empty.

2. Fuel system with drop tank T h e drop hnk 14,261 Is suspended frem Ine sh~ckles of the Type 500 release ge~r within the ETe 501 reck by ~ metal bMd. The drop tenk is c onnected to the reer fuel t~nk 14,21 by ~ fuel line 14,261. "'n EP_1E fuel purrp 14,271 Is bul I t into the line at the reer of thereck. "'nelr lin e '4,231Ietldsfromthe s uperc herger t o the dr op tank and c ontelns bo th en

,

~•

~

_""",10 1 .. ,.,..

J

• ll l .. , , • • 1 '0' "

'."'u' ., '.~

• TO"

~

."". I. ~ .... , .h. . d 8

6 , ... , "" ., pol. , 1 " 11 ., 11 ,,*

e Uo<o. II ...

11 . ,

9'.""."0' 11 .,

h) $0" I 11 • • Il , • • ~ 11 " ' 0. - ",,1 1 12 ' .0 1 11., ' ) ~ ... 1• • , '0" , . l.j.l .. " , .... , 1, .... 10'011 10 ' , I • • •• '

• • , ... c~

vo h ~.

11 11" . , ......

Fig. 51 Rear fuselege

8u~1Ii~r y

tank

U n",

Engine operetlng end fuel supply system

04

Newl Non se I f _s ee I I n g hnk with dreln cock .!Ind superch.!lrger elr pressure fuel jettison.

A descdptlon of the new system I'll I I be .!Idded up 0 n completion of the relev.!lnt construction documents!

The euxlllary fuel tenk Is fastened to.!l housing 15,41 et the reer of Bulkheeod 8 15,5) by two straps (5,2 & 3) .!Ind Is fueled through eo filler point 15,6) on the left fuseleoge between 8u I khe.!lds 9 end 9.!1.

During fuellng, the fuel f lows through the f i I le r 11 ne (5,7) to the hmk; when the hnk Is full, the fuel becks up the overf low line 15,81 to the filler point, .!Ind from there, vI.!! e ventlletlon line 15,9) out the bottom of the fuselege. The fuel spill I fne 15,10) .!Ilso connects Into the ventlletlon line.

On the top of the tenk Is positioned .!I un I t (5,11) conhlnlng the fuellng, overf low e.nd feed I I ne s es wel I .!IS the fuel pump. The electric fuel pump sterts oper.!lt I ng .!IS soon es the "Kref tstof fpumpe Z use t z beh'ld ter Rumpf" circul t breeker Is depressed.

Fuel flows through a feed line 15,12 & 15) to the re.!lr ten k (5,13). Connecting Into this line Is e T_jolnt 15,141 with the drop tenk fuel line. A check velve (5,16) Is Instelled before the T_jolnt in eech of the two lines. This prevents the flow of f ue l from one euxl llery tenk to the other; or, when one of these two tenks Isn 1 t f i t t ed, prevents loss of fuel through the unconnected feed line.

, 5uP ,'c"",g" 01, li no , B300' .1, " ood ' I•• ) Vol .... I 'h ho".I.~ 4 0 oC'lng ~

' v" ••d

d"" I~"' O' '0.

6 Co. 'eol ".It ) "~II<o \ .. 'I_cn.lI ; ng ,,,. ~ e i.~ I • • ' ..re' . ....."11 Q Opuot l .9 ,Od .. I' h "" "0.

10 _ Inuc, n n _"., 109 , .."'"

The fuel frensfer limit switch 15,17) regul.!ltes the flow of fuel from the euxl II.!Iry tenk In the serne wey es for the drop t.!lnk.

Fig. 6: Emergency power system

There Is no monitoring of euxlll.!lry tenk contents~ the te.nk Is empty when the reer tenk fuel leve [ falls below 240 Ltr.

The increesed power Is gained by bleeding elr from the supercherger pressure line (6,11, in which ere foceted two nozzles connected In series. A flexible tube (6,21, through which e portion of the boost air CM be drewn off when the velve (6,3) Is opened, Is connected into the supercherger elr line between the fuel mixture ch ember end the boost pressure reguletor. The two nozzles, the first of which he s the smeller Inside d I em e t er, ere so constructed, the I when the .!Ictuetlon v.!llve 16,31 is opened, the el r pressure within the boos t pressure drops to e very low I eve I; this causes the throttle velve to open wide, thereby Incre.!lslng the m.!lxlmum obtelnable boost pressure, et 2700 RPM, from 1,42 ate, to 1,58 eta at the low supercherger se t tin g, and to 1,65 eta et the high supercharger setting. The h I g her boost pressure resu I ts In Increased f u e I consumption, due to the greeter quanti ty of fuel injected Into the cylinders.

C. Emergency power system See Fig. 6.

An engine em erg en c y power system Is provided for this e I r c r e f t . This system is to be Instelled In eccordence with Fw 190 ModlfJcetlon In st ru c t Ion No. 133.

This system provides, for fighters with non_dereted 8~ 8010 or BIrW 801TU powerplents, e short_term Increese in power up to the reted eltltude of the en gin e. This emergency power cen be melntelned In level or climbing flight for up to 10 minutes (Watch the oil tempereturel). Because of potential oil end cylinder heed co 0'1 n g problems, It Is reccmnended theot during e climb, the system, If feeslble, be turned off. During system operetlon In hot s umme r we a the r, the 01 i tempereture wi I1 reech mexlmum permissible limits. This. system must only be switched on In f I i g ht, et full throttle, .!Ind with the propeller pitch control on 'Automatic'.

The ectuetlon velve (6,31 Is mounted In e hou sing on the decking in front of the windscreen mounting freme 16,101 en d behind the left fuse end distribu_ tor box (6,5J. The flexible line 16,21 which connects the ve Ive to the supercherger air tine Is encased within a hellcel entl_chefflng tube (6,7).

The velve Is opereted by tJ button (6,91 loceted beneeth the left side of the meln Instrument penet.

Engine

0'

The

following

Inscription

Is

placed

oper~tlng ~nd

nellr

this

button.

fuel supply system

the r-ear fuel tenk, has 8 co!ipl!lc1ty of :3 Ltr 15 Qtsl.

The pump (7,1 Emergency Power

Pu I I 2700 RPM

L = 1,58, H ~ 1,65 Button depressed Velve 'Closed'

=

Button pulled

=

Valve IOpen'

When the emergency power unit Is Instel led, only the following types of spark plugs can be usedl al Bosch DW 240 ET 7/1A bl Bosch DW 240 ET 7/1B cl Bosch ON 250 ET 7 Spark plug cl is to be used only if spark plugs al end bl are not avelleble.

Aircraft fitted with this unit are to be marked with e yellow ring 150rnn outside dl ameter and 1011111 wldel which Is to be pieced on the.rear left corner of the fuselage armament cover.

D. Primer fuel system

J

is positioned et the reer of the left

Instrument console.

The tank Is fueled through 8 filler point 17,31 which Is 51 tueted beneath tI sliding co ... er on the forword fuselage left side. The f I I I er point Is connected to the primer fuel ttlnk by the filler line

17,4) end ventlltltlon line 17,51,

Another 'Ine,whlch leeds from the primer tllnk filler point to the reer tenk vent 11 et Ion line 17,61, provides for venti lotion In Hlght.

E. BMW 8010 lubrication system Oocumentatlon for the TU_powerplant wll I fol low.

See Fig. B. The circular 011 tank is positioned In front of the engine and behind the 011 cooler (B,61, and Is protec ted by an armoured ring. The tank has a scaled con ten ts measur"ing probe within the filler cap 18.241; the filler point Is located on the left side of the nose. 011 consumption measurement during flight Is not possible.

The ring shaped 011 cooler Is positioned In front of the 011 tank and Is al so protected by an armoured I" I n g.

Between the two armoured rings Is a gap 0 f about 1011111 for the exit of the cooling air.

During low t~eratures, the system Is filled wit h warm 011 forced up through Filler Point 118,181.

The oil cooler Is filled first, while air Is expelled from the systemJ then the tank is filled. A line connecting the Input side of the main pump and the In put side of the auxiliary pump Is contained within the 011 pumping unltJ this line enables the excess 011 wh Ich Is delivered by the oversl zed auxiliary pump to be returned to It. The warm oil must be hot enough (over 658CI to allow the thermostat (8,41 to open the radiator flow circuit.

I SUM-~~I . . ~ p"",, 7 S""l l on f . .d lino 2 ~rl_ r fuel line 8 P.... uro foe. IIn, 3 f iller polnl g Fk .... 11 Ir.n.lll .... po l nl (Fil l •• IIn. 10 5opo •• llon po l n' 12010. , ~.. 'll o' l o. l i no ongln. "","n'lng .lng 6 R.... ton~ f l llo' pol n ' I' Clrcu l .. f ••• 11 . 0 h.r n...

12 5u"or .hor ~" olr p'. .,.re Dip..

Fig. 71 Primer fuel system This system facilitates engine starting by sprl1ylng primer fuel Into the supercharger air pressure pipes of all 14 cylinders, and there atomizing It. The system Includesl 1 AP_20 SlJN,...Prlrner pu~ 1 tank with filler point and associated feeder I J nes.

The pr i m er fuel tank (7,21, which Is contained In

The engine Itself Is It lied wl th warm 0 I I through a special fi Iler connection 18,1!H. 011 Flow Circuit Oil Is drewn from the tank by the auxiliary pump and fed past the thermostat 18,41. At an 01' temperature below 6S-C It flows through the warming chamber 18,51 to the main pump, above 658C It f lows through the radiator block (8,61 to the main pump. A temperature probe 18,81 which d Ire c t s the f low of 011 between the auxll1aryp~ and the cooler, Is positioned betw~en the cooler and the main pump.

The main pump then forces the 011 to the engine, following which, three engine return pu~s feed the hot 011 back to the 011 tank. The 011 flow clrcul t then begins anew.

06

To ensure

11

aelween the meln pump end the engine, the 01 I passes through en 011 filt!!!,. 18,11) posl t I oned on the engine mounting ring.

co nt Inul ng supply of 011 In case of

failure of the thermostat or of the cooler, I!I I In e con nee fa the output side of the ouxlllery pump cl 1 re et I y to the Input s ide of the moln p~. To

Cold weather stertlng sequence

guarantee 11 constont 011 pressure of 8 otU 1118 ps') to the engine, the moln p~ has over-shed d lmen_

0 11 I s prepared

slons and Is fitted with 11 shunt line.

The engine ventlletl on line

18,1~1

f or

cold weother starting by e

connects Into the

elrcular 011 tonk.

,' -.

12 10

,1 'ot'''' _8'" .1, ._ ' 0",, ' " . ...... _ 10 _

" 011 11 11 ...

11 , I .. I r_ . r , tI " .r

'

) o..'.ul u •• , _ •• ',........ ,. "

• '_-0'"

, 0 ' I __ ,.,

--

".

1.""

I ll>

c_'

.,oc' '_TO'...,

..

H~"

.. ' . ... _

' .~k , ~ '.'

......

coo,''' ."'''\1 _... 1• • ...- COl. .... 1... . , ... 11-,

' '''~

. ,I

,. 011

11 ...

U Oil ' ''~ .~ . I .. . 01 •• 1J , _ " , . . . . 1,..

1.

15011 , _........... ", • • 11".

...

11 • • ,,.. ...

T ~. , .' .t

1. _ _ I" t ~" , ilu

£~Ii'''' ' 11 .. , .. " .... " 0 1' •• n.'" _.H"~' It ...

• 0 11 COO," , H ... I ....... , ... to

•9 I".. ,

11" ~

I)

' 9 . ......1. t ll' ..... Ino for 0"9 1. 0 10 , ... " • • _11"9. 1. " ,, __ , ...

I .~_

~

"1.",, .... "'." .... . , • •

' S ...... I ' 11" ... ,.1., r....oo l .~

,._, ' •• 1' Il'hr

M d

Fig.

81

,_

BMW 8010 Lubri cati on

syst~

..._1

'I ,''''

c.. . 11. cO"'o. ' .

0

\1 •• -

07

Engine opertltlng end fuel supply system

speclel mixing nozzle 18,21) which Is built Into the 0 11 return line 18,131.

Fuel Is teken from the output side of the No e I he k fuel pump tmd fed t h r 0 u 9 h e cut_off valve to the

mixing nozzle t e!

C

I re u I er tube with fine holes),.

where It Is added to the a ll.

To complete the cold weether starting procedures see the Fw 190 Operetlng Procedures.

011

11 ... '"

temperlltur-e

monitored by epproprlete

end

pressure

(1,141

ere

instruments on the l!Iuxl'_

lery Instrument pemel Il, 9 1.

The various 01 I lines ere colour coded In accordance wl t h DIN L5 end ere mer-ked with flow d 1 rec t I o n

arrows.

F. Aircraft tanks

FuelTng capacity, Forward tenk et leest 232 Ltr 151. 0 g811 Rear The two positioned They ere secured t o

tank et leest 292 Ltr 164.5 gel I. self_sealing fuel tanks 19,1 & 21 are within the fuselege beneeth the coCkpit. held by hbrlc straps 19,91 which ere the coCkpit floor by edjusteble bolts.

Eech tenk Is fitted with en electrlcel Immers I on pump 19,3J, e filler hell!ld 19,4 &. 6J Ithet of the reer tenk olso contolns II!I fuel trensfer limIt sw I t ch I, and 0 contents meesurlng unit 19,.7 & 81 with attoched fuel low level sensor.

Attll!lched to the filler heeds of the two tonks ere. 0 fill er line 14,41, onet-on overflow line 14,51, to thot of the forwerd tenk, the de_oerotor ventllotlon line (4,201, ond, to thot of the reor tonk, the oux lllar y fonks feed line 14,281. b. Underfuselage drop tank

Fuellng c epocltYI 300 ltr 166.2 goll.

1. Fuel tanks

The drop tank la, when carried, suspended beneoth the fuselage from an ETe 501 rack and locked In t 0 position by four set screws.

Fuell C3 (!;l6 Octanel a, Fuselage tanks ,

The drop tank Is connect ed to the fuseloge feed, and air pressure, lines by rubber sleeves iseparotlon polntsl.

In II!In emergency, It cll!ln be jettisoned by pulling the T_shoped hondle label led "8omben". c. Rear fuselage auxiliary tank

Fuellng capacltYI 115 ltr (25.3 goll.

See Fig. 5.

The ouxl Ilery tll!lnk Is, when required, mounted behind Bulkhead B. It Is fastened to 0 support by f abr I c strll!lps [two horlzontllll and one vertical J. The tank has I !I heoder un l t c o n t a I n I n g a pump, filler line, an overflow line, ond 8 feeder line.

III

It Is self_selllllng.

2. Primer fuel tank See Fig. 7.

Fuel. Alrcroft primer fuel.

Fuellng cepacJtyl Approxlmetely 3 Ltr 15 Qtsl.

I

1 R.... f ~. , I.n~ } EI, etrl • • 1 'u , ' ~""" • f lllo. ~ ... _ tr h f ~.1 , ."" .rer 110.11 . ~II ~ ~ '~. , Ionk I!."~.

5

""l",o

6 f _ .. ~ tonk f l l l,r ~ ••• 7 Co" ' ~" ' . _ • • ~rl"~ ~"I ' wl ' " I"" ' ty,1 IOnl or 8 Con ' ento _o.~. ! "g ~"1I with 1_ 1... 1 IOnsot" 9 S.~u " n~ atr ....

A ~ j •• t'bl.

bo i l .

Fig. 91 Mll!lln fuel tanks

The tonk 17,21 Is contal ned within the reor fuel tenk. It Is filled via an ~xternol filler point 17,31.

The hnk Is protected by Its locotlon within the reor tonk.

08

fnglne operetlng end fuel supply syatem

80' Rodrlng + 20' Spindle 01 I green (Shell AB 111 or 90' Redrlng + 1DJ HydraulI c 011 0435

3. Oil tank 011 tank cepecJtYI "

Ltr 112 gall.

a! I tank contents ..... st not be perm I t ted to fall below 20-2' Ltr (4.4-'.' gal).

011 type. Only Inteve-Redrlng.

The ring shaped 011 tank (10,11 Is located wit 1'1 I n the aircraft noae. It Is filled through a fuellng nozzle 18,241 on the aircraft nose left side. 011 Is drained from the tank by opening the SUM._ ttlllk draIn valve 11 0,101, after ottechlng en 011 drain tube to It. The tenk Is protected egalnst gunfIre by an armoured rIng 110,81.

Winter mlxturel 5DJ Redrlng + ,DJ Spindle 0 11 green IShe11 AB 111 or 70' Redrlng + 30J Hyraullc 011 a.l35

It"'"

• Oil )011._

,

1 0'1 "n~ 2 _ H r ol>OC:. _ftl ' OQ

, c-...

~ ,, ~ ,

11 __

• Oil 11 _ _ ~ ~I ...

6 1114 ..... '. ' 'CHler _ • Oil

I."~

... _

• Co_ 10 hn k .... . '0 •• I .e

1\ e. .... ""_0'

Fig. 10. BMN 8010 ermoured 01 I cooler end tank

4. Control unit oil tank The engine mounting ring aerves aa control unit 0 I I tank. It Is fIlled 10 the level of the filler opening I1 ocat ed on the upper left sIde of the ring).

CepoeltYI

',6

Ltr 14.9 QIs).

Ceutlonl Add 011 only hrmedletel y after runn Ing up the engTne. Reaaonl when the engIne hes been sitting for SOMe t IlIIIe, the control unit fIlls with 01 I end the 011 level withIn the 11'10 u n tin 9 r I n 9 slnka. If the tank 'a then filled, when the engine I. starhd, the elCtra 011 In the control unit will att.mpt to move back to the tank. The reau I tin g excess prf!ssure In the system wIll probably dnagf! both the c ontrol unit W'td the mountIng ring.

A thin t~f!rature_reslstlng 011 mhture Is used, the mIxIng ratIos for summer and wInter arel SIM",oer mlxturf!1

U~ .

Ire- , .... I. 111 1...

• lI.e Ir_ ~

s.c.... , ~ ,

6h,""

, " , ...

cI_ _tlft,

Fig. 11. BoWl 8010 011 filter

'0 _

d.,

Eng i ne oper eting end fuel supply sys t em

09

Fi g . 12 1 Fue l t enk comp ertment wi th f ue l t!!nks

r emoved end lnst e ll ed __ , . t • •• , ..,

,

~o.

1

Q• . ,

.....

' . ~I

1 A• • II • ." ' ... .

• P.... "~' ~ ,rI ..... 1• • 1 , ....

.""... "., e

I ... , t . .... 0 " .. ~ ol . ' " . , ... 1• • 1 11 11 ., ,. , .,

o 0. . .. , ...

11 ....

' 0 v•• • " ." ... li no

11 h ilI 11 • • ~_ ""i t n 'uti " .,

" 'ut'

I . ,.,., •• ,., '~ '

"""'0 ,., 1•• 1•• 1

•• , " . , , r•• , •• ,•• ,. " I'_r l

16 " " "

n , .. , " "

"1 ",," ,•• 1,.,.,.,

.. in" ., '." ._ 19 , ... , ' .... 11 •• , 0 _

•• , . ... . . , ..... """ .

10 . ... ' 1. ;'", .. , _

"n "«0 ......' ...... 'uo' "".'. 11 _ • • , .. n

I . .. .... . . ... 10 1• • 1 • ..,.. , !I .. ,

.,.11 '01'''''

' . . . .... . . . . I •

. .t

. ... , h ,,, , ..01

" '." ''''''' ''''' '1... , ... , 11 ... " <O " " " " ,~

16 • • , 1 , ... 11 . . . . . ....

11 Cu '_ ~ 1I • • , ., 21

~.

!

I. ....

II. ~

... I •• ' , .. , . _

20' ." " ••• t" ",, ;1 ..,1,<" JO ' . 01 11. . . . .... . . , ... . . ,.,

11

'uo'10. ,I 11, ..1.. ,

t .... I.

r, .. ,,., ,

' 1 . , . or • •• ". ', no " '~ " ( ""' ~'" ' . .....

II h t u ......." • • • 1• •

' ,M I

). t "'c \ " ' " l~ tr_1! " .' .~ l6

ue

Wl

H !oo..; . . _ ....

n ' ", 1""1 " ~' ~ "'I"; O" ck. , "00 .S'-"'-o""" . ..... , 1-. . , ,,. , I ln • ., el ' e, ' ., f • • ~ " no ""' nn •

•

~ ~. rc " . 'I .,

. 1, ., ....... . 1,..,

O} f ..." • • eo . ... ... . ....- I"~ "M

" ~u. ' ........ to'l' 'n"._M ..... , ... ,......

06 . ·, ... ou .... •• _ ........ ...

O~

~

Fu.' .... .9. '..... ' ....

'3""' ....... ",1._" .

I . ....

<7

O ~ ~'r I~be'

!I ... , ....... .

Fi g. 13 1 Fue l sys t em

sk~ t lc

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part SA Armament installation

(Effective July 1944)

Issued September 1944

9

•

Ia "•g"

. ...._-J,..:' f ~ , 1'< =. . . , -- ____. "

1 FUIII 'g' NO. " , 2

Wlng_~ ool

1~

mach ine gun.

NG 151/2OE 2CMn c an nonS

, Ou tb oard MG \51/2OE 20mm c annon S -4 ......... n lllon box .,techmeRI bracket. ~ li nk bi ll •• ~nl dflcord chu le 6 MG " , forward """'RI

7 St L ", /58

moun t 8 ......... nl ll on fted chut.

I) R,,,I 168 ,...fle c lor gunsigh t 10 SZKK -4 o .. _ n l " witch __ , r o und ~ t~on

counter _ _ , and con lro l unl l

11 KG ' }B <:OI\ lr o l ,tick 12 Fuse la ge ... epC>llI .",••lhl t lon boxu

'400 rounda •• chl l in k bt l l •• ~ l lc er tr ldgt ce ll ng d l.c ord Chute 14"Fu$el eQe weapon • • yn chr onlzln g gea~ 1 ~ IIdJueteb le r ..~ 16 R..~ lllounl .uppo~ 1 D~lI<;kll 17 " on_adju. 'l b l l f orw erd ~un t HI Cann on b l nl tub l 19 ...... _ n t co l I l""at ton t ube "

""0"'"

f'"ig " ~

Sy".rn '~'""'t ic:

20 Barrel support cleoop

21 Wlng.root ,".""ona .ynchrOl'l ll ln~ IInr 22 Wl ng. rool W'ap onl _ n l l l on boxU (250 rounds .0<:1.)

23 Hot aIr pipe for ammunit ion 2. Ou lboard weapon. emmuntt lon

war~lng bo~ ••

1125 roundS nch )

25

~unl "

on

box rta ... " ... splnslon arm

26 Moun ting bracket 4 cos ln g eje<; ll on c null 27 Cartridge c os lng ...llrl.v., cove"

28 Cold olr pip'" for .""",nlll on coo ling

Ar-mement Inst!llletlon

02

I. Description A. General The basic el"mament of the Fw 190A-B consists of three gl"oups of weapons. These el"el .

2 MG 131 mech lne guns in the f use leg e upper cowling with 400 I"ounds per gun (1,1) 2 MG 151/2QE cannons in the wlng-I"oots, one perside. with 250 I"ounds pel" gun (1,21 2 MG 151 !20E cannons I n the win g s oulboal"d of the propellel" ar-c, one per side. with 125 r-ounds per gun (1,3) All weapons ere f i r e d electrically, and use on I y E_type errmunlflon. The 1N3131s end the wi ng_rool Mt3 151/20Es ore synchronized t o fil"e fhl"ough the p,..opellel" el" c; the outbo&rd MG 151/20Es ere unsyn_ chron I zed.

The positioning of the ammunition be lts is lndiceled by a l oedlng dlegr.!lm on each errmunltion box.

The fuselage emd wlng_r-oot we.!lpons ar-e swi t ched 0 n

by Switch I. the outboar-d weepons by Switch II (Sw itch I must fir-st have been switched onl . The outbo.!lr-d weapons must not be switched on less then 3 seconds efter the ot her weepons. This intervel wl I I ens u r e thet cock I ng of the fuse I ege end wln g_r'"oot guns hes been completed. As the elr'"cr'"aft batter-y can su pp or'" t the simult.!lneous cocking of e m.!lximum 0 f only four'" we.!lpons, this action evofds the c i r'" cu i I ovel"IOtId thet will othel"wlse I"esult. A special instl"uctlon plate Is fitted.

Two flr'"ing bu t tons, A end Bl. ar-e fitted on the KG 13B contl"ol column gdp (1.11). The A_but ton fires the fusel.!lge lmd wlng_ r'"ool weap ons ; the Bl _butt on fil"es the ou tboar-d weep ons .

EO_COCking units end EA-firing units el"e atteched to each gun .

The EO unit Is ut ilized fol" eutomatlc weepon cocking, bl"eech_block position indicati on , and I"ounds countIng; the EA unit, fol" weapon fldng.

Cartridge casings and [ink_belt segments ar'"e __ except f or the coslngs of the outboard weap ons __ dlscar-ded.

The fuselage weap ons are hermonized t o 0 I"ange of 400 m (435 ydsJ; the wing mounted weapons, to a range of 550 m (600 ydsl.

The opera ting system fol" each weapons group Is fully electr-Jcol en d Includes ( Inc l usive of c il"cu i t bl"eekel"S and electrlcel I ines)1

B. Fuselage MG 13ls 1. Weapon mounting TIi e first weapons group, two MG 131s, is positioned In llie upper cow ling, for-ward of llie Windscreen mounting freme, in Stl 131/5B fixed mountings 11,71.

1. SVK 2_151/131E fuse and distributor'" box, and 2. EOSK-B1 gun cocking control box .

Each operating system Is routed thl"ough the SZKK 4 switch, round count er, end contl"ol unit 11,101.

o

e".cnbloc. ... , •• , ligh'.

00

0

ft"".d. c.......

"".. chbloc:' cool ... II,M.

o

ft ••• d. __ t ••

o 0

' " " 1.,11... .

, 1 ~tl ""~ " ••• poo ~"'

"'6 I~ /2 OE o.'b ••• d

MG IoIG 1$1/20E

MO 151/20[ Wing ,o.t

Fig. 21 SZKK-4

I~I I2OE

O.,b",d

c."t" '"c~.1 ,2 'or ••r. ,.ooorl •• r '.ooorl

1 Ch.I •• uo.'" br.,_.I, ~ C•• ln~ .J .c ll .. chull 9 ~" i " ~ .0• •t' •• ~"'

.,.,_.1 """Mlt ............ , ......

~

~

10 lQC~ln~ "I .

~

E' oclrlc., con'acl pl.l.

n

6 ~ ..r '.P.or' -..ollog . 1.,

' 2 ".r!l , .1

.~j".'

..."1

Icr ••

Fig. 31 Fuselege MG mount and ca,..riel" unit

Armament ln5t8118tlon

03

The

weapon

brtlckets

mounts

(3,2)

13,1]

which,

In

ere

fixed

turn,.

lire

to

carrier

screwed

to

Bulkhead 1 and the Windscreen mounting frame, The gun mount consists of 8 fixed forward su pp or t 13,31, en lIdjusttlble rear support 13,41, end a cast

bearer.

The forw8rd support, into which the gun

locked,. has

tI

recoil

is

fitting 8nd cen be rotated

tlbout Its ver-tictll end horizontal axes.

The retlr support me u n tin 9 pins [3,61 secure the MG 131 rear m0 u n tin 9 br-ticket tlnd lock the weapon

Into position; adjustable set screws permit vertical and horiZontal adjustment of the weapon. The Cardsn type suspension

of

the

forward support pel""mlts

precise alignment of the weapon.

The carrier bracket, of welded sheet steel construc_ t I on, Is e.tttlched to Bulkhetld 1 tlnd the Windscreen moun t I ng frtlne. At Its forwtlrd end It Includes tI c tlr tr I d 9 e casing ejection chute 13,81. To either sIde are screwed support brtlckets 13,71 for tlttach_ In9 the feed tlnd ejection chutes. The ammunition box tltttlchment bracket 13,9) Is fastened beneath the cartridge casing ejection chute.

top, they tire secured to tltttlchment brtlckets 14,31, on the si des by guides 14,41, tlnd at the bottom by hi nged chutes 14,51. Etlch box has a hInged cover 14,6), which is locked by two sprlng_ loaded b 01 t s 14,71, through which the ammunition Is loaded. They tllso etlch htlve tin enclosed chute 14,81 through which the belt segments and cartridge casl ngs drop Into the s I I p s t ream. To Improve ammunition stortlge, wooden supports are positioned on the floor of each box.

Ammunition In these boxes receives cooling air which Is extracted from behind the engine cooling fan.

Two f I ex' b I e pipes 15,11 on the underside of the centre ccwling upper panel Md two tubes (quick separtltlon polntsl) (5,2) with termlntll f i t tin 9 s 15,31 carry tllr to the turmunltlon boxes (5,41. To secure them, the terminal fittings are pushed rear_ wtlrd Into the ctlrrler brackets 15,51. The cooling air then circu lates through the ~unltlon boxes.

2. Ammunition stowage Ammun I t I on for the MG 131s Is contained In two anmunltion boxes 11,121, each of whIch CM hold 400 rounds In tI Type 131 dlslntegrtlting link belt.

The Imllunitlon boxes 14,11 tire positioned within the f uselage In front of the mtlln spar tlnd Bulkhetld 1 In the tlrea above the me I nwhee I doors (4,21. At the

I F ' . . '~I. pip.

2

T~ ~.

) , ,, .. 1•• 1 •

"" I. ~

_~ 1 110fI

U •••

Fig. 51 Fuselage MU ammunition cooling

3. Ammunition feed chutes The /K, 131 s are a d tI P t e d f or I ef t tlS we I1 tlS for r I gh t hend ammunition feed. This permits the respective feed chutes (6,11 to be positioned on the outbotlrd sides of both MGs. The cover 16,21, which removes to permit Insertion of the ammunition belt, Is held In pltlce by stud s 16,41, Itltches 16,3), and spring clips 16,51.

I _ I t l o. DO'" 2 WO . . I ~ .o rs

~ H l n~'d

•• 11 .. _ . , ••• e orlddgo <&.I . ~ 6 ~ ! "~U 00_..

l -...I1 ! •• D••• "..,...... , .r.~~...

4 Gul •• Dro<Uls 1 Spr '~ g_ l o'.Od .01U ! c l ••• b.11 •• _ . , "." <o,' r log' c •• I.~ enu t.

o.u"

Fig. 41 Fuseltlge MG ammunition boxes

The I ink_belt segment discard chute 17,21 joins onto the cartridge casing ejection chute (7,31 which Is mounted directly bene8th eech MG. The belt segments tlnd cesings drop out of the bottom of the fuselage through, In sequence, the above chutes, the MI'I'Iunl_ tion box chute 17,5), end the hinged lower chute 17,7).

Armament Installation

C. Wing-root MG lS1I20Es 1. Weapon mounting

.2 _ ",ll ... 1_ c ""~~

Two wing-root MG 151/2OE cannons comprise the second group of weapons.

Eech gun Is secured In en StL 151/26 fixed weapon mountJ which consists o f a forward and a rear sup p 0 r t. The forward suppor t 11,171 provides the rec o l' housing and the forward lIthchment pol nt for the wetlponl the rellr sup p 0 r t 11,151, the lIllgnment adjustment mechl!lnlsm and rear attachment point. 60th supports are atteched to the win g, the front one to the meln spar, the rear one to a fitting between Centre rIbs 1 end 3.

Cft.'~

pl . n

~

Sjld.v cllu

Fig. 61 Fuselllge MG ammunition feed chute

The cannon barrel Is housed within II b IlIst tube 11,161 wh I c h Is secured to the forward support and to the wing lelldlng edge.

To steady Its bllrrel, the cannon Is fitted with a clamp 11,201 __ 0 three pIece ring with set screws and lock nuts. In the blllSt tube tire 3 holes t h r 0 u g h which the set screws pllSS.

I

,-,

'- ,

••• •

•

•• ••• ••

1 _ . , lion

2 ....

~O""

1I!l1.~

} MI.,.G GOOl""

•, f ••d <""'0 'oc ~

6 0 10.... cn.'.

FIg. 81 Wing-root Cllnnon layout

• _

,,' " .... loo. c.... ,.

.... ...........'.'"V......

2

(I n . . . . "

, ' ." " ogo ~

~

c ... ~ cn••• . jo.,1 0. cn. I.

•• _ " • • h ~

loc 'o...... It _ _ ", _

e ... .. ,' , . u.I.V <,",'0

6_ "' ll ...

2. Ammunition stowage boo

7 KI ",.d tlo •••• CO."

a ~ I"V.

p i . .. I t • •• 1•• , .... , .,

1,,. ••• 1",

. 'd• • ,., •

<"u'o ' 0 _ . 11 1... ..... 0" .. _ " , ..... <•• , Q , • • ••

" SH " ' 1'111 _111""_'

Fig. 71 Fuselage MG ammunition feed and discard chutes (Seen from the front I

The amnunltlon b o)( es f or the two HG 151 / 20Es ore positioned within the fuselllge behind the main spar.

They are accessible through the fuselage bottom v I a two hinged doors.

ElIch STmunltlon box 18,11 Is hooked onto the fuselllge centre support by Its nose fittIng {8,21, guide fittings gIve sldewards support, and the 8ccess doors gIve vertlclll supp ort.

Armement Inshlletlon

05

I n the throat of each arrmunltlon box Is

tI

r 0 I I er-

over which the errmunltlon belt moves as It the box.

I eaves

A wedge s h e p ed

divider piece Is built Into each

5Mft [10,7) Is pressed In agtdnst the force of the spring (to,91; penmltting the feed chute slots 19,2 1 to drop down over the notches. The sheft Is now

released and the slots are locked into place.

ammu n i tl o n box to Improve the efficiency of the

ammunition feed.

A hinged door 18,3) on the top of each box opens to 91 'le elccess to the box tlnd permit lcoding of the

ammunition belt.

3. Ammunition feed chutes To permit direct feeding of the I!Immu n' t 1 on. the NoG 151/20Es are both rigged for inboerd feed, le.

the left weapon hes right side feed, etc. Anmunl tion is fed to the guns through amnunitfon feed chu tes IFig. 9).

, (I ,'-bol , .' •• 0 •• ' ~hUlo 2 , <" r idge • • • 1' 9 ojoo,lon Oft"" 3 "'ogo. " •• • "'ogo

Fig. 101 Left MG link

~

S.rl.II-' .....d bolt.

6 Oulr l!l\lor beach"

7 ~ ..d 8

c~u, .

.o,et...

1000 109 " ' "

~nd c~~t~idge dispos~1

chute

D. Outboard MG 151120Es 1. Weapon mounting , ("", ollng .,". , Hlng.d 00..'

2 Rdo l .ln 9 0 1010 4 . 'og. ~ 5p,lnll-'oodd bol ,.

Fig. 91 Left gun feed chute

The ~unltl o n feed chu te Is atteched to the ammunl_ t Ion box by two studs 19,1) and Is secu~ed et I t s outboa~d end to the belt link end ca~t~idge dlsposel chute. The two seml_c1~cula~ ~etelnlng slots (9,2) ~est on e sheft to which they e~e secu~ed.

A hInged cove~ 19,31, locked by two sp~ing_loeded bolts (8,5), gives eccess to the chute.

The link_belt segments e~e ejected f~om the outboa~d side of each weapon th~ough a comb i ned I Ink _ b e J t dlsposel chute (10,1 I and ce~t~l d ge casing ejection chute 110,21; the 18tte~ positioned directly beneath the gun. Both a~e sc~ewed to the wing lowe~ skin.

To aid In loeding the amnunltion belt into the gun, tI flep (10,3) on the uppe~ portion of the chute can be op en ed. A. slotted shtlft ( 10,71 fitted into the out~lgge~ b~~cket (10,61 secu~es the emmun ltion feed chute (Fig. 9). With both units In posl tlon, the

, e"re l re i .... . . I •• " 2 l" ""g .1 "

• 0 .... 109 cylinder ~

, <>r •••• 01.., 1.

Fig. 11,

Outboa~d

$., 109 <, ""d"

6 A!to.'-ft '

cannon

forwe~d

!lon~ .

suppo~t

The t h '~d weepons g~oup consists of two MG 151 / 20E cennon, loceted In the left ~nd ~lght wing pMels outside the p~opel le~ e~c. Eech weapon Is secu~ed In enStL151/11 fixedmount,whlchconslsts ofa forwe~d tlnd ~ea~ suppo~t. The guns 8~e positioned on

06

Armament Installation

thel r sides to facilitate l!I1'II1unltlon feeding. The for war d support houses the welSpon trunn Ions; f 1'1 e rear support secures the weapon reor aft ac hmen t points.

3. Ammunition feed chutes

The forward support Is attached to a bracket w 1'1 I c 1'1 Is, In turn, secured to the wing lower shell between Centre ribs 7 ond 8.

To reduce the weep on f i r I n g shock, a recol I unl t [11,4 & 51 Is fitted within the forward support.

The rear, odjusfable, mount is fixed to a mounting brocket which is, In turn, secured to Centre rib 7.

The weapon can be adjusted to~1. vertically and horizontally, ond can be removed without affecting its adjustment.

, r..~ '''yl.

•

~rI"9_'o,~"

1 HI "'l'Od "op

~

_

3 S"Y""9 "oo.s

~

" ' og.

slws 01 1' 0. boil c.I ••

Fig. 13, Outboard connon ommunltion feed chute

2. Ammunition stowage The ammunition belt is fed to the gun through 0 feed chute (F ig. 131 and an l!I1'II1unltlon leo!!d_ln sect Ion 114,11.

The hinged feed chute, comprising 0 chute 113,11 and o hinged flop 113,21, is secured to the l!I1'II1unltlon box by 0 hinge assembly ond by two hooks (13,31.

I

Qo" '"

1 H '" if~ c ••• r

, r U G ."", ...." ~ 1.'l'Oo ."•• , ..... _'d ,,,' ' ' _ , cl .... ~ ...... 1, lo'ot ".'.

'.'.'.'"g .lIp$

Fig. 12, Outboard gun tmnunitlon box

The arrmunltion boxes 11,241, etlch of which can hold up to 125 cartridges In a Type 151 ernnunltlon belt, are mounted par tI 1 I e I to, and outboard of, their respective weapons, betw~en Centre ribs Band 9. The MG 151/2OE mounted In the left wing htls right 1'1 and feedJ the one In the right wing, left hand feed.

The front end of the tImTIunltlon box Is secured to the forward rim o f the gun bay aperture by a spring_ loeded boil assembly which grips the two suspension claws (12,41. At thl! back 11 Is secured by a sprlng_ looded bolt which slides through a fitting at the lower rear edge of the ammu nit I on box. The bolt essembly Is retained wit 1'1 I n e hinged mounting arm which Is, in turn, flxl!d to the rear sport A wooden strip Is placed In the tmnunltlon box to keep thl! belt as neorly horizontal tlS possible. In tlddltlon, there are two horizontal rollers to aid tmnunltlon feed Ing. At the top Is a hinged cover 112,21 wt>lch opens to permit loading of th~ emnunl_ tlon belt. Two ctltches 112,31, riveted to the sides of the boX, lock the cover and secure the ol1l11l,mltlon feed chute to the box. Warm air for a mm u nit Ion warming enters through tin opening 112,51 In the front of the box.

The hinged flap, which is open at the top, has tw o spring_loaded studs 113,41 which are inserted In t 0 motchlng holes In the !mTIUnltlon lead_In section. A cat c 1'1 (13,51, riveted to the bottom of the flap, prevents tmnunltlon belt movement when the flap is open.

The l!I1'II1unltlon lead_In section (14,11 Is riveted to o br ec ke 1 114,21 which also secures the cartridge casing ejection chute 114,31. The bracket is attached to Centre rib 7.

The casing ejection chute hos a spring steel barrier (14,41 which prevents the return of ejected casings to the weapon, thus avoiding the possibility of a firing stoppage. The casings ore expelled I nto the eree between Centre ribs 6 and 7J from there they are removed through a hand hole In the wing lower skin. Addltlonel sheet metal Is fitted tlround the area to prevent structural damage by the e j e c t e d casings.

, _ I l l ... 1• ..,. 1. " <: "on 2 voll ~nl t09 ."C'o l

1 "','n9 o jo. lloo ."_ "

•

~."nv

..... ,

~ ." '

....

F ig . 14, Outboard cannon ammunition letld_In section tlnd cortrldge c asing ejection chule

Armament Installation

07

The link se gmen t dIsposal chute Is riveted to the

weapons bey cover door, and guides the ejechd link segnents from the cannon Into the sllpstrell'l'l. When the cover door Is locked, the link se!J11ent chute

must not touch the gun.

F. Collimation tube The Installation location of the collimation tube Is show n In Fig. 1_19. Its dl.tance from the fuselage

centre_line Is 1220 mm.

The tube sighting hole In the wing leedlng edge I. taped over when not In use.

4. Ammunition warming

The collimation tube securing nut 116,11 I. secured The ou tboerd weollpon ......un I t I on boxes ore heeted b y werm ok which Is drOW'n from the exhaust pipes for ey l i nders 5 oIInd 10. The oil' flows through a pipe 11,231 within the wing leading edge and then through on op en In 9 In the fOl"Word end of each .......mltlon box.

In a spherlca' support In the wing leading edge, the mounting bracket (16,31 I• • ttached to the rear wall of the leedlngedgepanel. The collimation tube 116,2) Is joined to the mounting bracket (16,3) by • connector segment 116,41.ond odJustment brocket. The tube con be ollgned vertl c olly ond horhonhlly by two set screws 116,6 & 71, the settings being moln_ tolned by locknuts 116,81.

E. Gunsight The weollpons ore olmed by 011 Revl 168 (1,91 op t I co I sight which Is fixed to thewlndscreen mounting freme be h In d a buJ let resistent glllss ponel 50 nm thick oIInd set at on oIIngle of 2,.. The shellow slope of the windscreen ensures thot the reflection of the 51 ghtl n9 Imege is not visible to the pilot. The field of view downwords Is 30.

The guns I ght ben plllte Is fixed to the support bracket 115,11, end, the mounting unit 115,2115 fixed to the Windscreen mounting frame. The brocket ond mounting unit ore Joined by hexagone I screws 115,51 lInd spherlcol woshers (15,71. The spherlcol 5h ep e of the beerlng_ surfoce oree between the two units perm Its pree1se adjustment of the reflector sight.

The gunslght Is connected Into the olrcroft power supply by depression of the oppropriote circuit breeker on the right Instrument console.

I

s..c.,,,.., "''''>'.'

2 _nll"1 ~"" J Ht ...on.1 ..,._

• Wu"

, ..... too.1 ocr ....

6 hon.,.

7 ~n .. l u l ..oh ••

Fig. 151 Gunslght mounting ossembly

I TWM aec:... 1ftv ... , 2 Coli I.H ... , _ ) _ H " I 1or...1<e'

• Cool....:' .... , , _ ,

, "";..., .... , "'lO(.kO'

Mjw._,

6 _lIco' .. ;"0'''''' .c....

1 _10",,'0'

e l oc""ul'

Fig. 161 Collimation tube

ocr ...

OB

"r"moment Inshllatlon

11. Installation and removal For removal, the weapons must be uncocked and locked. All inshllation end removal work can be carried out wl th the aircraft In the tall down p osi ti on ,

C. Outboard MG 151120Es Removal I ') Open weapons ba y cover door, 21 Remove alOllUn j t I on box.

A. Fuselage MG 13ls

31 Un scr ew the weapon actuation cable from the EDSK-B1 distribution box.

41 R@mOve bolt cover. The gun mus t not be cocked and the breechblock must be In the saftled pos ition.

Remove I I 11 Open the fuselage side pan e I s and the fuselage armament cover.

21 W! thdraw the weapon ecluation cable from the EDSK-B1 distributor box and the firing ceble from i Is socket.

31 Pull ou t the f or ward s upport r ota te If le f tward to the s top.

l ocki ng pin and

41 Pull the weap on reerwerd until its reer gu ide bushings ere free of the rear mount gu ide pins.

51 Swing the rear of the weapon upward s and withdrew It from the forward support.

Installatl onl For Installati on , the sequence Is reversed.

51 To withdraw the berrel f orward, depress the barrel release lev er , al E it her from the weap ons bey, by reaching forward beyond the forwerd mount end pressing the lever~ whereby a second person removes the barrel, or , bl From 'hewIn g lower s u rfa ce through a 10nyn diameter ho le with a screw driver, direct i ng It toward the f usel age .

61 Remove the firing c ab le from its socket.

71 Un lock the gun from Its forward support. For that, pull out the lOCking pin and r ot ete It left to the stop. Press the spring_loaded ke ys In the guide pins and withdrew the weapon rearwerds.

Instellatlonl Installation reverses the above procedure.

B. Wing-root MG 151120Es D. Fuselage weapons ammunition boxes

Removal I , I Open wi ng _root armtlment doors.

2 1 wl thdraw the firing cable from the electrical circuit terminal board, an d the weapon actuation cable from the EDSK-B1 distributor box.

31 Remove bolt cover.

041 Open and remove the barrel support clarrp Is now no longer adjustedll.

{Weapon

51 Depress the barrel releese lever. Ro tate barrel ' /6 tl'l t ur n to the left end withdrew it.

61 Relea$e the weapon from the forwerd support lPul1 out locking pin and r ot ate 9~1 and wl tl'lclraw reerwards. Simul taneously, depress I h e sprlng_ loaded keys in the guide pins of the rear suppor t.

Installatl on l Reverse the sequence of the ebove procedure.

Wh e n the underfuselage ETG rack is installed, the removal of these boxes Is not possible d ire c t I y .

U n d e r these cl r cums t ances , the ETG c err J e r mus t first be swung down.

Remove the wheel folrlng plates.

Rotote the cartridge casing and I ink segnent chutes forward and wl t hdr aw the biiiirun 1 t1 on boxes downward.

Instellation reverses the above procedures,

E. Wing-root weapons ammunition boxes The removal end Instel let lon of the enmunltlon boxes presents no difficulties. Hinged doors secure the boxes against shifting and falling out.

A,..mement Installation

09

F. Outboard weapons ammunition boxes Remov,~d

f' bolt. Slant the box downward for remove I rearwards.

I

Open the weapons bey cover door.

The tlrT1'llunltion feed chute hi nged

First release the IImmu n i t i on box from the re.!!!'" suspens 1on p 0 1 n t, then f r-om the f orwo!ll'"d one. Li f t the forward end of the errmunition box slightly; this f,.. e e 5 the forked t tin 9 from the sprlng-Io!lded

flap is unlocked

Installation Is reversed.

Md lowered.

Ill. Weapons testing control I Takeoff setting I fin e pit chi elt 2400 ,..pm.

During functional testing no jems ere IIllowed,

Before en aircraft undertakes .!Iny 0 per a t Ion a I missions, Its wellpons must be h.!lrmoni zed and.!l

functional test carried out.

11

The aircraft must be trestled and

end be pointing into the butts.

21

31

41

otherwise repeat the test,

restrained,

Mount the calibrated, rotating disk. Carry out synchronizat Ion firing point Inspection (Reference point is '/3 bl.!lde width in front of the propeller trailing edge); al so complete a firing circuit continuity check.

First, carry out a synchronization test on the MG 131s and the wing_root MG 151/20Es. Fire 21 rounds per gun.

Ensure that the belt links separate properly.

Verify the operation of the rounds counters for the MG 15t/20Es. The synchronization test pattern lairscrew without compensating weights fitted) is f I red .!It an engine speed of 1BOOrpm. Propeller control: 'Manual' pos! i ion, takeoff setting (fine pitchl.

71

The aircraft Is levelled In accordance with Its bench marks.

81

The itlrget (Annex 1) Is positioned vertlc.!llly, with its height set In rel.!ltlon to the collim.!l_ tlon tube.

The colllm.!ltlon tube Is sighted on the aiming cross deslgn.!lted for It. Fol'" this, the tub e must previously h.!lve been level led.

91

The weapons are so adjusted th.!lt the centre of the firing pattern lies In the centre of the tllmlng cross.

101

The Rev! gunslght must be sighted on the appro_ priate .!Ilmlng point.

11)

The shot pattern for the MG 131s must be fired tit one time (21 rounds per gun).

Mtlxlmum spreed for 100~ of the hltsl Height = l00cm Width = 80cm .!It lOOm r.!lnge

To compute synchronlz.!ltion operating tolerances for the MG 131s, use the following v.!liuesJ Muzzle velocity = 750 m/sec (2460 fpsl Round advance time = 0,003 sec Alrscrew reduction gearing: 1,84:1 Weapon radius 685 mm 126.6 inl

spretld for the wins-root MG 15l/20Es 121 rounds per gun), Width c 60cm at lOOn ro!lnge Height'" 70cm Width ... 30Cm at 5Cbt renge Height. 35cm

S hot

=

For computation 0 f synchronization operating tolerances for the wing_root MG 151/20Es, use the following valuesl Muzzle velocity = 705 m/sec 12310 fps) Round advance time: 0,005 sec Airscrew reduction gearing = 1,84:1 Weapon r.!ldius 980 mm [38.6 1nl

=

5)

The computed to lertlnce figures can be exceeded by 4~. Permitted firing p.!lttern dlspersionl 20J of the computed toiertlnces.

61

For synchronization test firing, a callbl'"tltlon disk with the predicted imptlct tlretl cut out, ctln be used.

The synChroniZation firing p.!ltiern for aircrtlft wl t h co~ens.!lt i ng w e i g his fit t ed Is ver I fled without the ctlllbr.!ltlon disk fitted. Propeller

Shot sp re rounds per Height", Height c

for the outboard NI3 151/20Es 121 gunla Width = 80cm .!It 1 DOn I'" tin ge 70cm Width lE 40cm .!It 5Cbt rtlnge 35cm

ed

121

Inmedl.!ltelyefter test firing. the .!Idjustment screws fol'" all we.!lpons .!Ind the gunslght must be locked In place.

131

Te 5 t firing c.!ln t.!lke piece Immedletely before commencement of flying, so long as the aircraft has already been completely prepared end ground checked, .!In d the functioning and adjustment of the weapons system Is not tlffected by subse~ quent meinten.!lnce on the .!Ilrcl'"eft.

Ar"mement In5Ia ll&ll &n

'0

IV. Adiustment A. General The alignment of the we&pon$ Is as

sh~n

In Annex A.

The gunslght sighting line 15 &dJusled t o f ocus on Ihe sighting trlengle of the ter gel sheel, thu s placing I I perettel t o Ihe a I rc r aft longl t udine l axis.

B. Adiustment procedure Cerry oul adjus tment s In accordance with l . 0 .... 4 /7 .

The lar gel IAnnex BI Is positioned a1 100 m I ln excep t1 onal cf r cumstances 50 mI d j s 1 an c e and Is p laced vertically.

Tesl fir i ng of the NG 1315 Is carried out using Type Ub . E . 13 /ITII hlgh. exploslve am mu n I I i on ; o f t he NI3 151/20Es , us i ng Type UI> . 151 20/ITII high-explosl ... e lIIiiflUnlllon, withou t the Type E sel f. des tr oying fuse 111 5 g tIIm'Iunltlonl.

For weapon adjuslment , remember Ihe follow[ngl Be f ore cannenc l ng adjustment, loosen the set screws on the mount rea r supports. Adjustments can now be made to these screws. The verllcal and horizontal adjustment screws of each we apon ar e eesi Iy access.

I b le .

In order t o edjust the gunslgh t, t he i ns t r panel COW li ng must f i rst be removed .

U/l'l

All connect i ons wh i ch were loosened during th is operat ion must now be r etigh te ned and secured.

Af ter cOl'fllleting ell edjuslmen ls, remove al t t oo ls from Ihe aircraft .

Inser! the co l li ma t or In the co lllmctl on tube and adjust the target to the appropriote height .

"••

'.;;.

Fig . 171 Aircraf t Irestled ond reslrelned, synchronized weap ons callbrotion disk f i lled

en t

, Sefe t y swi t ch I 2 Sofely s wit c h II 3 Br eechb lock con trol lights tMC; 131s) Inormel l y mounted horiZ on t a ll y) 4 Rounds coun ter s . wi ng_root MG 151/20E5 5 Rounds counter s . outboard NU 151/20£5 6 Revi 166 guns i gh l 7 Guns lght mounting unit Fig . 18 1 SZKK. 4

11

AnnsMnt InstDllatl on

Fuselage MG 131s

•

1 Fuselege ermament panel 2 Fuse lage side panel F ig . 21

1 MG 13 1 link belt se gment /ce rtrl dge

casing di scard chute 2 MG 131 ammun it ion boxes Fig. 19

I \

, MG 131 link; belt segmen t /c o!Irtr ldge

casing d iscard chu te 1 HG 1315

2 Anmun ll lon coo ling pipe :3 Stl " ' /56 weapon moun t s 4 Ammuniti on feed chu t es Fig , 20

2 Olscar d chute hi nge :3 MU 131 ammun i tion box 4 Discard chute l ock re lease l ever ') MG 1,}1J20 atmlUnlt l on box l ock

F' g. 22

•

•

" Wing-root MG 151120E.

1 NG 15112DE 2 Weapon cocking end firing le&ds 3 EDSK_Bl gun coc k I ng c ontr- ot box

FIg . 25

Amnunlt l on feed chute (open)

2

N{3 ,

51/20£ wllh breech open

3 Arrmunltlcn be l t gu ide -4 link bel t d i scor d c hu te

Fig . 23

1 Ree f" maun I

2 So l el y s c r~ 3 We epon rolotlon disk -4 HoriZon ta l ed Ju slmen t screw 5 Link bel t d i scord Chute

6 Cor t r ldge casIng d Isc ord chute 7 Forwtl r d mount loek l ng bu tt on

F ig. 24

1 2 3 -4 5

Arnrunll Ion fe~ c hu tl!

NG 151/20£ Forword mount locki n g bu tt on

Monuo l c horgfng hondle EA fll"fng unI t

FIg. 26

" Outboard MG ISI120Es

1 LIn k

!>~I !

~jec t ion

chute

Fi9 .

~O ,

[nsh lllng

th~

lo .. d"d "",,"u ni tlon box

Fig . 27. M&nuel gun chsrglng

1 Corl ridge ,eslng ejection chute 2 Cortridge tos;n g ret ri eve' cover F ig, 28

F i g . 29' Cl051n9 Ihe [ood ed ~ n il ion box

1 .t.mrunition be ll c o t ch

fig . 31. hTmu nl tion feed IIthd", d

F i g . 32 1 S.. rr ej remov o ' [Me t hod bl

Armement I nsfelleflon

I

t Ammunit ion box

2 Ammunit ion feed chute :3 N6 151 /2OE

4 Lin k be lt ejecti on chute Fig.

:n

"

"

Armllment Instellellol'l

SltIItloot Io . ' , _

~

.... ,,,, I........ , ,3

mm

'" H.,.

s.,. .......... 010,['

2" 2 ili a I~IJZQ IQ"U •• t , l om 5... "",1'o".u... ,~ l _ t IIIG " '/2: 0 IW,", 2 Cf. 5.,,, P... "". I~I

to.',

-

-..-., ,........... ' ...

Sit., .... 110.

v., , ~._

30 '"

4OQ ..

'" , . OM

120..

" 0 ..

_ U"",

1l~..

SSO,"

Annex A

,., m

Alignments

Weap on s I

Fusele ge l 2 MG 131 Wing_roo lsl 2 MG 151/20 Oulboerd l 2 MG 151/20

Arrmunlfionl

Hermonlzat ion 400m, Crossover I parellel Her-manl zallon 55Om, Crossover I 600m Hermonlza t lon 55Om, Cr ossover I 400m

13mm Spr . Gr .P at r, Ub . EI .

2cm Spr, Gr . Pa lr . Ub . 151/20 2am Spr . Gr ,P el r . Ub . 151/20

Gun' Ire st ri ke h ble e t sOn end l OOn, In cm Fusel ege 2 NO 131

Reon ge

""

5""

1"""

I

"

~

95, 5

13

121

13

142

13

Wi ng_root 2 IN:, 151/20

Dl.Jtboerd 2 MG 151 / 20

H. _2,5

S.

H.

S.

.3

6, 5

237 , 5

"65

6' 76

53

206

.... nnex B

.,

"6

Ar memen t i ns t e l l eti on

Append i x A

01

Revi 168 A. General

2 . Tec hnic al dota

1. Gen e ral

IIpprox .

5 i ze : He i gh t • • • • • • • • w i dt h • • • • • • • • Length • • • • • • • •

IIpp r ox . "0 app r ox. 00 app r ox. 130

op t iclIl gun5 i gh I de5 i gned I 0 , ' Rev i 16S ' I, use ..... ith a i rc r af t fi x ed wellpons , both synchr on i ze d unsynch r on i zed .

Th •

"

,,'

,,

mounted • My posi t ion . gunsigh t It bu i l t_ in d i rrrner rh e os t et . eo , t t e d wi t h e t tll ched IIj r c r of l e l ect ri clI l 1h • 10 sys t em sprlng _I OIld ed conl ec l s .

Th.

'", "

,

1

"

•

7

,

4

,,,,

,

I

Bu l b sp ecificll ti on • • • • Ti n te d glllss • • • • • •

by

o, a

',o/eight • • • • • • • • • •

Night fil t er

•

•

• • •

•

• •

• •

•

•

• •

•

•

• •

"

• •

Ton e 71

kg I I . 76 ~ ~ ~

14. 96 in) 12 . 36 I 0 I 15 . 1 2 '0 I

wetl , •

"

[Dark gr een )

8

/

, ,

I 9 29 ----.~

28 ____ 27 _

10 11

12 26 ~-

13

5 6 7 8 9 10 11 12

14

13

15

15 16

' 1.

22 ,__

1 2 3 4

_ , 17

· 19

14

17 18

19 20 21 22

23 24

25

A O

26 27 28 29

vo I I

90' opecl t y

I ,/ , f

'"

Tlnt ea gl ess r e t aining sp r ing ! in te d g l ess pl ete Re fle ctor p lete r e tol n l ng s pr in g Ref l ec t or p lote Objec t i ve lenses Light bulb hous i ng Oirrrner r he os tat Ol rrrner sw i tch Bu lb ho l d er L i ght bu lb Ni gh t f iller F i lter sw i t c h Bulb hous i ng co ver Non_r e f l ec ti v e g lass cover Sighti ng Ima ge lens Sp r ing_l oed ed elec t r i c el con t llcts B lede re er s i gh t Verti c a l ad jus tmen t screws Hor iz ont a l adju s t ment screw s Horizonl ll l IIdju stment sc rew Ve r t i c al tld j ustmen t screw Post _ t ype f r on t s lgn t 8 11se p lllle 5 11 i ce crystel cepsu l e Ad just men t spr ing Cer den mou n t Lens c hamber Mi r r or T i n t ed g le ss sw in ging s upport arm

App~ndl)("

Armom~nt

02

Th e vertic a lly moun ted engr av~d sighting i m&ge compri ses a n aim i ng c r oss w i t h de f lec t ion gra d ua tion m&rk s . an d & ran ge ci r cle . The angu l &r dis t&n c e bet_ ween gr"&d uollons is 1°. The ran ge ci r" cl e dlomefer I s equa l t o 10' of th e r" enge lie . I t has a diamet er o f 10 yds &t lOO yds nm gel.

B. Description

I h e bu l b hous i ng cove r 1131 .

The m i r r 0 r 1281 Is posi t ion ed In" C"rdan mount 1261 ; spring len s ion 1251 ensur"es a positive r"e sponse 10 any adjus t ments .

The base 1231 seals the bottom of the len The base pla te 1231 sea l s the bot t om of the l ens chamber" 1271 , and a l so e c l s as the gunslgh t e t tech _ menl poi nl.

In I'Iddltl on , It houses a 51 1l cl'l cry stel capsule 1241 , wh 1 c h Is used to absor"b any molstUr"e entering the chember .

3. Mechanical sight

1. General T he 127 the bu l b

ins t a llatI on

Revl 168 consis t s basically o f the lens c hamber I . To t his Is attached the r"eflector" p let e 14 1, movable II n ted glass p l ete 121 , and the 1 I g h t housIng 161 .

Th e mechonica l sight consists of a blede rear sight 1nl and a post _ type front sight 1221 . The front sigh I comp r ises the upper pori Ion o f the refleclor pia t e left reta ining spr"ing 131 .

Th e sight , efter l ooseni ng screws (181 end (191 , con be edju s ted t 30 ver t Ica ll y end/or hor izontal l y .

2 . Optical sight 4 . Lighting system T h e optlc~d sight includes the l ight bu l b 1' 01 , th e nl g ht filter 1111 , Ihe non _r" eflec tive cover g l ess 1141 , the Sight i ng Image lens 1151 , th ... mi ....... o r 12e l , Ihe focussing I en ses 151 . and t he r ef l ector p la te 14 1.

The ref lector , end tinted g l ass , pla t es are lightly held In p I ace by retlllnlng springs 131 end The tinted glosspl~le 121 ispos; t;oned by (11 . men u lllly r o tllt lng its supp ort IIr ms 1291 . The l ine of si g ht c an be odjusted !-2, 5° horlzontelly w it h IId _ justm~nt screw (201 , end t3 0 verll ce ll y w i th lid jus t_ ment screw 121 J . These scr~ ws ere reache d by rll lsing

4 19

27 -+-

• •

The light in g system I ncludes t he dirrwner rh e 0 s I a I 17 I , I he bulb holder 191, and the light bu l b 11 0 1.

The bulb draws po wer" fr om the lIi r c r e(t electrical system 12 4 vo lt l , vill two spr ing_ loaded contllc t s 116) . I ts br"ightness I :; controlled by .!I dlrrmer switch \81 . To redu ce sIgh ti ng image gtore d u r in 9 nlghtope r alions , thenl ghtfllter {1 1 1 cenbe r o t oled i n front o f t he ll gh l bulb (101 by th e fil _ ler sw I t ch (121 ; t his sw itch Is re ached by rlllslng the bulb hous i ng cove r 1nl .

Arm8ment Inst81'atlon

c.

Operation

Wh e n t he li ght bu lb I s t he s l gh l lng Image . Th i s the m irr o r , and I s thr oug h th e obje c t l .... e j e c ted r-ear-wa r-ds f r om a pp e a r-s , 10 t he sight i ng I ty , a nd , Iher-ef or-e , 10 tar- gel al ong the line o f

s .... ltched on , i t i l luminates Ima ge i s then r-eflected off s o adj usted by its pass a ge l e nses Iha l whe n ' I Is pro_ the r- ef l ecl or- plate , it e ye, 10 or-igi nal e at l nfln _ sup er-Impose itsel f upo n the si ght .

The opt i cal sI ght pe rmit s the sightin g eye l 1 . To sh l fl 11 di stence o f up 10 app r- oxlmllt ely '50 rrm 11. 97 In 1 wi th ou l IIller-ing the l in e o f s i ght , II nd , 2 . To .... ar- y 11 5 distance fr-om Ihe r-eflec t or- plllte fr-om IIbout 200 rrm 17.87 in) t o about 450 Il'I'l1 11 7 . 72 inl wllhout af f ect in g the size of Ihe lar- gel . usi ng Ihp. me c ha n1cal S i ght . on I he olh er- hand , 1 h e e ye mus t be & cc u r a t e I y I Tn ed up wi Ih the 'r-onl si ght __ rear- si ght &x l s .

/

R, .. i 168

'iqIIlinq imoQ'

Append i x A 03

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part SA Armament installation Supple:nent 1: A-8/Rl

(Effective July 1944)

Issued September 1944

o

__ 11

(j)

" •

@ -

,..~y

a

'1~

iE

~ ~"--J

"

-"G . "

--------t~

,• ,I " 0

25 -:-:-..

,• -,• , ,••• 0

0

®

~

20

"

~J~~~~W~~

" 1 Fua el a ge MG 131 1~ mac~ ln f guns 2 w l"~_r oo l MG ' ~1/2OE 20mm c annons 3 Du t ~o8rd MG 151/20E 20mm c annons 4 AmPIun lllon box atlectvT\enl br . ~ kel s 5 l ink bei l s e~n l di sca r d c ~u l e 6/K; 131 lo ..... or" lIICun l 7 Sl l 131 / 58 weapon moun t

a AmmuniTIon fee d enu te

9 Rev l 16B refle e r",.. gunsl gnr , 0 Sl. KK ( erm"""," t , .. I ten __ , r eun<l

coun t e r __ , end con tr ol un11 11 KG 136 con tr o l S lick

12 Fusel age « e apens omrnunl r lon box e~ (400 rounds esc hl 13 lin k bel l sl!gmenl /c anr l dge ,,,,,Ing d ls csrd chute 14 Fuse lage .. e apons synchroni zi ng gear 15 AdjusTeb le resr mount 16 Re ar mounl suppor t braCk et 17 Non_ ad jusT a b l e f orword meun l 18 Cannen ol ost tu oe 19 ......,"""'n l col1 1msllon tube 20

aer re I supp er I

c l ""1'

21 wi ng-roo t wesp ens 5ync~r on lzl ng 9~ar

FiQ I: System

ske rnal;c

22 wl n9- r oo l «e apons ommunl llon ba~ ~5 1250 rouno a ~ach) 23 ~o t air pipe for ammunition warming 24 Ou t board ~eapons ammu n ItIon boxes (12 5 round .. ...ch) 25 A/mIun l ) /"" box r ear suspens lOfl ar.,.

26 R"slralnlng cord for ~ ... pons car rier frsne 27 Ou tb oa rd ftea pons c arr i .. r f r em<' 28 Car rie r from .. f orward mounllng po i n t 29 Carrier from .. r ~ 1I(" moun t ing point 30 Co ld air plpn for .....,un lll on cooling

•

Ar mllmen t

Instill lilt ion l A_8/R'

02

I. Description The wellpons system of the Fw 190A- S/R' consists of: A . 2 synchronized MG 131s in the fuselege, with 400 rounds per gun.

S. 2 synchronized MG , 51 /20Es in the wing _ roo t s , with 250 rounds per gun .

C.

4 unsynchronized MG 151/20Es, two be n ell t h eech outer wing pl!lnel , with 125 ro unds per gun .

Use E_ t ype anmunltlon for all MG 151!20Es .

11. Gun mounts A. Fuselage MG 131s The MG 131s are positioned w ithin St . L 131/58 mounts which are fixed to a light me f al carrier unit . These are , In turn , attached t o B u I k he I!I d 1 I!Ind to the Windscreen mounting frame .

B. Wing-root MG 151120Es

Centre ribs 1 Md 3 .

c. Gondola (Equipment peckage

RI

MG 151120Es includes the t wo gondolas)

E llch MG 151/20E Is positioned In Iln ST . l 151/7 gun moun t; t wo fixed 10 ellch wellpons cl!lrrier frllme . This carrier frl!lme clln be swung down for wellponS load i ng and servicing.

It Is covered by a strellm lined flliring Igondolal .

Each weapon Is posi t ioned In an St . l 151/2 mounting un i t .

The forwllrd moun t Is attached to the mal 1'1 spar; and the rear moun t , to a carrier unit between

Ill. Ammunition placement and loading A. Fuselage MG 1315 The MI'I1un I t j on i s pos' t i oned with i 1'1 Ihe f use I age f or-ward of B u I k hell d 1 .

The 400 roul1d boxes are removed from the aircrllfl for loading ; then are si id up inlo Ihe fuselage through the wheel cavities , and Ilr e held there by the hinged belt segment and cart _ ridge casing chutes .

B. Wing-root MG 151120Es Thearrtllunilion is positione(:l within Ihe fuse l age behind the main spar . The 250 round boxes are l oaded outside the aircraft end slid up into t he fuselage .

Hinged doors secure the box es Ilgainst sideward move _ ment , and against fal ling oul .

C. Gondola MG 151120Es The aTmluni l ion Is car r i e d in 125 round boxes Ihllt I le w i thin the w in g s , parallel t o , Md above . the weapons .

Th e bo x es ere loaded outsid e the aircraf t and Ihen , af l er sw inging down the cllrrler f r em e . positioned w i t h i 1'1 th e wing . The box es are s ecur ed at the I r f orwe r d and rear ends by spring _l oaded bolts (See Fig . DJ .

Armomen l l ns tcllotl on l "-SIR'

0'

•

IV. Ammunition warmmg

c. Gondala

A. Fuselage MG 131s The MI'IIun i I j on . pos f t i oned f or-word o f Bu I "'heM 1 IInd directly behind Ihe engine, is co .:> led by dynl!lmfc eir

drewn from behind the coo l ing fen .

MG 151120Es

Wa r m oi r, dr!'!wn from the en gine exhausts, Is led . v i !I pipes in Ihe wi ng leedlng edge, 10 Ihe fro n t ot Ihe weaponS boy .

B. Wing-root MG 151120Es Worm eir redillled f r om the engine pre vents

the

errwnunltlon l erT'p ero t ure from ftllllng below _35"C .

V. Weapons sighting and alignment (See Annex!s A end 81

A. Sighting

C. Adjustment

Th e Reld 16B gunsighl Is p o sit i on ed

beh ind on

or moured windscreen , 50 mm thick ond set ot on engle of 15° .

The 5hollow slope of Ihe .,.i ndsc l'"een enSu I""es the t

the reflection of

the si 9h t I 1'1 9

IIMge on Ihe

wi ndscree n surfoce is not visible 10 the p i lot ,

For w eapons adjustmen t, a tube is provided in th e left wi ng _r oot f or positioning of e 7 , 9 nTI'I eo I 11 _ mator . Verious bench marks ar e p r o vided on the air _ e reft t o ensure ecc urefe levelling .

The

fie l d of view downwards is 3° .

B. Alignment T h e we apons are t o be edjusted t o t he a I i gnmen t specified in Annex B.

VI. Weapons electrical system Th e electricel1 circuitry for each we !!lpon is routed thr ough th e SZKK _ 4 switch, round coun ter , and cont r o l unit .

The f use lage and wi ng _ rool weapons !!Ire switched on

by S!!Ifety SwitCh I ; the ou t board wea pons , by Sefery Swi tch 11 ISw; tch I must a lready be ' On ' ) .

The ou t board w eapons must be t urned on no l ess than 3 seconds a ft er the other weapons .

This Interva l 1'1' 1 11 ensur e t h a f the cocking of 'he inboar d we apons has

been comp leled . As the ai r c rMt CM support the slmult!!lneous ch!!lrglng of !!I maximum o f only 4 gu n s , 11'115 action evoids the cu rr en l over loM Ihal w o u I d other wise result. A speci !!I I inst r uc t iOl1 pla l e is fitteCl. T w o f i r i ngbu t l ons , AandB1 , are fitled on the KG 138 control co l umn grip .

The A.-b u tton fires I h e in DO a r d weapons ; Ihe B1_ Du t t on , the o u t DoarCl weap ons .

Armament Instl!lll.!ltl on l "-B/R'

"'"'

o

0

"'O<~.IO<' '''''0' ,,,...

11 _ _ -

o

...., "'''0.'

~~""I'

11 ,

,."..

11 ,

, ,".or

' •• 0'

Ai ...

.,.,.,.

~ •• ~.,.

Fig. 21 SZKK-4

VII. Camera installation Pt'ovision h.!ls been m.!lde fot' the inst.!l l l.!Itlon of .!I BSK 16 16rm< movie c.!Ime t'.!I In the wing le.!ldin g ed ge, within the pt'opeller Ill' C [See Pllrt BEl .

The CMlet'&

Li." •• 1,

I Li..

t

~

t..11

w.~~O".

c""9 ch"" h~"dl.

Fig. 3 1 Twin gun p.!lck I n position; gondal.!l down

CM be tt'lgget'ed by the firing of the guns, or sep.!lr&tely by .!I button on the throttle l evel'.

I Ammu",hO" tu. C""tO 2. Am,""";,,"" ••H 3. C.,ri., ... ".i';09 co.d

4, Cannon b.".I.

Fig. 41 C.!Innon p.!lck being lowered, gun b.!lrreis secured In gandal.!l

0'

Armtmenf Installatlonl A-B/R1

Fig. 51 Cennot\ pack fully down

I. C.... i. r ,n r ",ow"l i", po;'" 2 A ........ 'to<o bo.n 3 . "'",,,,y.iliOft I.u C,,",U . ith

.. C.",-,

IOt •• rG

_Ij~,

'~ftl

6iI11t4

.",.-;,.;,1010

Fi g. 71 Ammuniti on stowage area

.. , 'cor lrldg. "'OII"I'"~

p,olte, i.,

poi.,

cuing

cwl l (in

chult

OO"~o",)

Fig. 6 . Gun peck In posltlonJ barrels removed

Armement Inste ll!ltl on l ;"' 8/R1

06

•

S I'T<>Q ........ ..,"""

~ .....

..<00'

r~ "

Z_ 'MG ' 51/ZQ Iw,"'l ' ... ' """ Q",,'Olol.

Z '''' Spo G< . P....

u.

~

= T4 - !2 ""

Annex A

Et-

.

s, S.

'"

'"

I, I

93

..,..,..,

~

-

0

•

x

••

•

~

-

cl,

•

Will9 toot MG 151/20

Al ignment l

We!lpons ; Fuselage l 2 MU 131 Wing_roots: 2 MG ~51/20 Gon do la,l nners 2 NC, 151/20 Gondole,outers 2 M.G 151/20

H!lrmonl z!!tlon Harmon iz ation Harmonization Hormon i za t ion

40Om, 55Om, 55Om , 55Om ,

Crossover I Crossover: Crossover I Crossover I

Amnunltion: par!!llel 600m aoOm 900m

13mm Sp r.Gr.Ub. EI .

2cm Spr . Gr . P!ltr. Ub .1 51 2cm Sp r. Gr . P!!t r . Ub . 151 2cm Spr . Gr . P!!tr . Ub . 151

Gun fire strike t !!b l e et 50m and 100m, in cm

Renge

Fuselege 2 MG 131 H, S,

ex,

95,5

,ex,

121

1C)ex,

142

n n n

Win g_root 2 MG 151/20 H.

S.

_2, 5

.3

44

8' 78

85

Annex B

Gond .,i nner 2 MG 15' /20

Gond . ,ou t er 2 HG 151/20

H. _1 0, B

S,

H.

S-

237 , 8

_7

27'

37

223

41

258

78

208

83

244

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part 8B Bomb release system

(Effective July 1944)

Issued September 1944

Bomb re leese sys t em

0'

Description

\ Elt ' 01 , (0

0

,

"."

1 ,." " ", ,.,1,. 00" " , '0 ' .

,

' , • • M; ••

1.... """

. 11,

~

IS, ,.." '"", • •• •• <t .. ' • •

? • • •••••

'·.k., .. ",,11

I !to %, , ..... . , .""

• •• 1.1 "

IQ "" H " '.· .. 0' .1' , • " _ ,. t .... . ,"""

"

' ) "~ ... "' •• ,. ,

o •• o d

• """_ " ' \'."1"'

1)

1""' 9' ;(, " ..... , ••• ,.

Fig . , I Bomb releese system skemo ltc

General The F... 190A. 8 differs from eerller- A.series flir c r!!!f' r n the t ! t s ETe 501

Cl!lrr 1er

nil!

bee" moved f o rwtlrd 200 rm1 17 . 9 1nl. This reposiliol'dng hes been mllde necessar y by the bui Idlng of em Cl uxll ll1ry fuel IlInk 1111 0 I he 1I 1rerllfl reel"" l uselllge.

Simpllficetions heve been mode 10 the bomb releose system ... 1thi n the .1.. 8 prod u c I ion r un . These (Ire conce r ned prJmer lly .. / 11'1 Ii'll' electrlCl!I1 reltest' e nd monitorIng ci r cui ts.

A . Bomb release mechanism To t his belong 1 ETC 501 11,11 ETC 501 cerrler 11 , 31 Felring 11 ,-4 ) Armsne n l penel [ 1,12) The ETC 501, the ETC 501 cerrier, end the f e I r I n g !!Ire fitted to the underside of the !!Ilrcrefl.

The ermsnenl p !!lne[ I s locel!!d heh.een• the euxlll ery instrument pene l end the coc kpit floor.

Bomb

~ele8se

02

system

1. ETC 501 The ETe 501 CM be loeded wl th bombS or disposelble cerrlers to !! tot!!1 weight of 500 kg 11102 Ib!J or with eln ER_4 eldelpter unit for four bombs o~ dispos_ eble C!! rr le rs, eech of e mexlmum weight of 50 kg (110 Ibl. Type 500/XI I releese unit 15 fitted into the ETe 501.

A.

The selecto~ switch on the ER_4 edepte~ Is to be set to the no~mel setting lslngle ~eleesel.

300 LI~ 166. 2 gel I d~op tenk cen be fitted i n pIece of bombs . Fo~ this, spece~ be~smust be otteched to the ETe 501. These be~s ere not ~equlred when the E2 metel hnk is fitted.

A.

Two cotter_pin s!!ftied bolts, one e!!ch through the forw!!~d !!nd re!!r fittings, secure the ETe 501 to its cerrjer. DurIng servicing, the c!!~~le~ 8nd ETe 501 !!re considered to comp~lse one unit .

"

(II~

) . ~, ~," "~

6 >."";-'G,O,,,

2 . ... ~ .... f1" '''~

Notel Befo~e

lo!!ding the bombs, ensure thet full cmnunltlon boxes for the W; 131s Md 'he wi ng_ ~oot MG 151/20Es helve been Inserted, !!S this c!!n only be done with the forwerd por t I on of the ETe 501 c!!rrler swung down. To insert the MG 13' !!mmun I t I on boxes, remove the wheel cover fell ~ in g 5 Md swing the I ink_bel t segment end certrldge c8sing chute on the engine lower support frerne forwerd.

2. ETe 501 carrier unit The cerrler (Fig . 21 is of e speci!!l the ETe 501 .

,

design

) ~,.c " "'ng . ........ _ "", Ing

~ I .'

." ,"

" or rl .. , , ' .... ' ••••

I ~' ••."'er .... l '"~ " .. ,

••

8 , .'

Q

h i .or ....

Fig. 21 ETe 501 celrrier unit

3. Fairing The hiring consists of the following three pelr'sl Forwerd portion (3 ,11 Centre po~tion 13,2 1 Reer po~tlon (3,31

to hold

The ETe 501 Is secured to lIs cerrler byl e forwerd flftlng 12,21 , end bye reelr fittIng 12,31 . Tight _ ening the set screws 12 , 8) wllhln the upper mounting pletes 12,41 secures the ETe 501 cer~ler; tightening the set screws (2,91 within the lO'Ner mounting pletes 12,51 secures 'he ETe 501. The etttlchment of the c errler unit to the fuse I ege mounting points !the forwerd mounting point i s on the meln sPelr, the reelr mounting point on Bulkheed 4, elnd e stebilizing strut moun t 1 ng point on 'he engine lower suppor' strut I Is elccomplished by two bolts Md e strut. The forwerd, sprlng_Ioeded, boil Is fitted with en engeglng leve~ (2,61 elnd is locked by rotetlon of 'het lever; the reelr bolt Is secu~ed by eI co tter pin, Md, 'he stebilizlng strut is et te ched bye screw_on co I I er.

The reer end of the Celrr ler unit is forked and secured '0 a fitting on Bu Ikheeld 4 (carrier rear suspension poin t ! .

To the un d e r s 'd e of the carrier reer segment is f I x e d, In an eccesslble posl tion, en E55 electric motor which drives the EP_lE drop tonk fuel pump.

, ' '''wor. ~ ... " ...

2 ' ,n'" 0.. ,10" ) ~." ."flG" • sc.. 1..,, _ ~

,

SC U ' C h " ~ "

6 ,". 1 . ro ,,~ ,.

. 1, 11,,.

"••

I . ".,"~ lie . ' . ' .... ' • ••

~ 8 ... ,

Fig. 31 Feiring

Bomb reteease system

03

It is et leached t o the fuselege

bottom with counter_

sunk screws, T he forwerd end centre portions 13 ,' & 2) er-e joined by 6 h i nge ; the forward portion

The system Is connected In t o the eairerefl cl r cu il by depressing circuit brNlker V')O on me n t conso le.

Ihe ri gh t i nst r u_

being secured 10 the ETe 501 by e screw lock 13,4).

The lines 13 , 5_81 whi ch lie wl thin the fll/rlng centre portion connec t the eirerefl systems to the ETe 501 cerrler end th us to the eq u I pmen t on the ETe 501.

T he ermement panel (4,1' contains the ZSK 24411 bomb f us i ng se lee t Ion bOX 14,2 1 end t he SAN. 77 Fw 74 retellse indicl!ltor lights 14,31.

It is situe ted between the l!Iuxll iuy instr ument pl!lnel end the coc kpit floor, I!Ind Is connected t o these by screws.

• c-- ' 'i<'o\

".

1 _

~ _

,0,., ,

"'i:-..o' ."

" '.e" ""

.

1

"' •• " , '

'00'.9

v

"i

•

•

device

The Re vl 169 is used .!IS the sighting device for the bombing system; ; I Is more f u lly dIscussed in P8rt 8A ,

4. Armament panel

,-+-

c. Sighting

OD>

.~ , ~

~

.... '""""

D. Emergency bomb release Pu I I in 9 the emergency bomb relel!lse hl!lndle 11,131 _ _ re lel!l se force ~ 30 kg I w!th movement of at letlst 24 rrm I_I I!Ibe I led " Bomben " cl!luses the jettison of My 1 0l!ld being ctlrried on the ETC 501. When the ER_4 tldapter 11,21 Is mounted. tln emer gency reletlse of the indlvldul!Il 10l!lds is not possible, In fl!lct, dur i ng emergency rele tlse the adl!lpter Itself Is dropped; in this event , the fusing end relel!lse lel!ld pl ugs tlre torn out.

Nolel Bombs 10tlded on 1 h e ER _4 adapter, when relel!lsed mtlnutll Iy, fell sMetied even If the lSK htls been sw itched on. Bombs loeded di re ctly onto the ETC '501, will fell ermed If the ZSK htls been switch_ ed on •

••• 1.0 1, .'0' ' I,M'

,.,

E. System removal

Fig. 41 Armament penel

B. Release and monitoring circuits This ci rc ui t i s used for the relel!lse and monilorlng of thebomb reletlSesystem.ltc on sistsof the following un ! ISI 1 ZSK 244A fusing se lect or box 1 SAM 77 Fw 74 Indiclltor un l t 1 bomb reletlse button The ZSK tlcts es the ml!lln switch for reletlse unit.

the

electrlcel

The indlctltor un it is sec ured to the ermtlrnent penel by two screws. When 0 250 k g or 500 kg bomb is cerried, on l y the ri ght htlnd indicet o r li gh t Is connected into the f usi n g selector box c i r c uit. When the ER_4 IIdl!lpler rele tls e un its 14 ETe 50/XIIII tlre loeded the three other indi c at or ligh ts tlre tllso connected i nto Ihe fu sing circuit, After a bomb Is reletlsed, the IIppropritlte indi c ator li gh t i I l uml _ ntlt es.

T he bomb reletlse B2 _button 14,41 Is I OCl!l ted on the KG 138 control grip .

If the eircreft Is to be flown wl th out the bomb relellse system, the ETC 501 cl!lrrier, wl th integrel ETC 501, hiring I!Ind 8ulkhetld 4 suspensi on fitt i ngs must be removed. In the stlme Wtly, the electrictll letlds, the fuel lIne letlds, the elr pressure l ines, I!Ind the emergency reletlse coble to the underf uselege trou gh 11,61 are no longer necesSl!lry. A stretlml i n ed cep to ftllr in the f orwerd mounting points on the mtlin sptlr, end tl plate to cover the opening for the underfusell!lge trough tlre provided in the elrcreft equipment bllg.

Since , when the ETC 501 cerrier unit Is tlttllched, 1 h e underctlrr i tl ge whee 1 covers ctlnnot open or c l ose properly, the wheel covers ere exchl!lnged for f i x e d felrings when the E1C ')01 rl!lck Is lnstl!llled. These fixed feirings cover tl smell portion of the under_ f us e I 11 g e tlper l ures in t he seme rMnne r tlS do I h e whee I doors. I n thl!lt ctlse, the un dercerri tlge felrlngs I!Ir e lengthened.

For opertl t ions withou t the bomb relel!lse mechtlnism. the fixed fl!liring pltltes tlre trllded for the whee I door un its, end the lengthening segments ere unscrewed from the underctlrri l!lge lower ftliri ngs.

D. (Luft) T. 2190 A-8

For Official Use Only!

• - • Aircraft Handbook

Part BC Special weapons system

(Effective July 1944)

Issued September 1944

SpeclDI weapons sys tem

01

Description A. General The Fw 190"_8 is ou t f i I led 10 cor-ry the 21_cm BR

wellpons sys tem, The 21 _ cm BR unit ser ves t o fire e sp i n st ll b i liled pr o ject j le , Ihe 21 _cm Type 42 mor l a r 5 he I I Ilnfor _ me t Ion cOl1 cerni ng th e wetlpoo is c on l e l ned i n Ihe f ol l owi ng two pub l i celions, H,D ... . 461/ 62 end H. D... .

11 9/9 841 . As e i med fire with this we!lpon Is not possib l e , It cen only be fees l bly used IIge l n51 for-gt! tergets lenemy bomber formotlonsl . The pl'"ojecllle Is

! . ...,"1 '

le c... •• " ...

11 ' ."

j•• • •_ . " ,~,

" ('«" .'U' , ••• • 1

2 _ •• 11 . , """01.. orOC >"

_le",.

11 ..... _

) .... 0< ; .\1 • fl r l ' i , . , . . ." , • • "'w l r i, I 6 fw p,"'" ,,«".h

, 't.'"

11 . 1'11 •• •• , •• • , . " .. ,. U n ,, " n"1

) ~"" l_,)"ll'E ,,," 0.' "", ,1 ..... . ... I)" .... ".1 .lIu

16 ' "" . d.

0 ..... _ . , •• II ck '.ol

I~

" "11 ..... . , ..

'e' l ,"~'\

J

11 ............. , , . " . " ~&O,

"'on. v "

" P'.e conn«,., .... I . &'~

Fi g. 21 Sys t em skema tl c Fi g. 1*1 Fw 190 wit h 2t _CRI BR system

"fired from a launchi ng t u be 12, 11 , one of which is l oceted beneath each win g panel. Each launching t ube is suspended !:Iy a carrier s tr u t 12 ,41, from a h 00 k [2 , 21 fl)(ed t o the wi ng lower surface ; end Is l ocked in t 0 position by four bracin g stru t s 12 , 31 . In on emergency, the launching t ube can be jettisoned by severing the carrier st r ut . The two projectiles are f i red s imultaneous l y by depressing the B2_button 01'1 the KG 136 con tro l grip .

lugs 13 , 41 welded 10 the uppe r portion of the l aunching tube. The tube hangs beneat h Ihe outboard weapons bay , suspended from a hook 13 , 7) which is se c ured to Centre rib 8 (2 , 51 by two screws and

B. Equipment 1. Launching tube The launcher consists of a tube [3 ,1 ) 1,3 m 151,2 inl long end of 21 0 tm\ 18. 32 i nl calibre , To the in ner surface of the t ube are altached __ at 1200 in t ervals __ thr ee gu ide rai l s 13,21 , Three retaining springs , loca ted nee r I he rear e nd of the t ube, ho ld the She l l i n p iece ; e s c rew bolt 13 , 31 , e' lis lower reor end, prevents the wlepon from sl i d i ng oul ) end, o s pring_ l oaded cOntecl16 , 3 1, at its upp er r ear end , fires the weapon .

The bracing s tr ut lower s t uds [3 . 51 fIt in t o bracing

, l .... nch'''' 'v.'

1 "", .. ,. 1,

) k . . . .~"

• lIr oc' ng ' ug.

, Br,,'n, .1,."

, (..-,r _. ... _11_"'u' ....... ,.......c...

6

, """'I

I . ...

F i g. 31 Launching t ubl beneath right wing pane l

Special

~eapons

cr-own nuts Isefetied by cotter- pins) . Two s uppor-t b r- ac ke t s 12,61, IIttached fo Centr-e db 8 al this po i n t, ser-ve t o str-engthen the mount Ing lIr-ell. The IlIu nching t ube is eleveted 7° r-elative to the fuselage longitvdinlll axis.

02

system

4. BR-armament panel The 8R_ar-m&ment pan e I 15,' I contains two ar-mament switches 15,2 & 31. This panel is attached to the .!Iuxi I i.!lr-y instr-umen' pllnel 15,51 by 'wo br-a eke t s 15,41.

2. Bracing struts To lock the launChing t ube Into position, the upperstud s 14,3) of the four- br-acing s tr- u ls .!Ir-e fitted in 10 the wing l ower- skin thr-ough sui t.!lble holes orr-jrrmed bu sh i n gs. Th e length of each st r- ut cen be changed by r-otation o f the l ower- st ud 14,11, and it cen be locked in len g th by tightenin g the lock nu t 14 , 51 IIgalnst the str-ut co llar- 14,41.

The r-ounded ends of the lower- studs 14, 1 1 inser-ted into the lube br-acJng l ugs .

C. Sighting device The Revl 168 r-eflector- sigh t lsee D. ILufl) T.64031, ser·ves as the si ghting device for- th is system . Afternotification by a TAGTT , it will, al the IIppr-opr-iate time, be r-eplaced by the Revl '6F.

er-e

2

,

T he s tr- u t t ube 14 , 2) is 230 rrm 19 inl l ong . The over-Il l! lenglhs o f the for-wllr-d IInd r-ear- str-uls ar-e liS shown In Fig . 4.

,

3

,

5

,

I

+ -- . .

.-

•

,

'C(RUlr

~

J"( 'or", .~

~O<: ' " ~oC • •

!

'6'.

, . ...... t ••

,

2 5 "ul t"o.

• Strut <at , .,

"", ,<,

~

!ld"~

I ',o Jocr l' , ,al)

• p,".

~

_Oi"

9

+ld"~

"d'Q ,....

C.c· l., /, . ' .... "nl' 1 . ,~ . pa' ~ B ~ "' ''' InQ Ino ".!Oc"v. 'uO.

ro".I • • ,

,toa

Fig. 6 1 21_cm BR system side view

Fig. 41 Br-aclng slr-ul The field of vision thr-ough the Revi ViEW findermust be li t lellst 7 ,50 in e ll dir-eclions fr-om the sighting line.

3. Release strut The cer-r'"ier- sIr- u t Ir-e leese sir- u t) contllins en elect_ r-Ically pr-imed explosive char-ge whiCh, I n en emer-gency, sever-s I I end so r-e I eeses the launch i ng tube.

D. Control system The contr-o l system consists of the electr-ical fir-ing end r-elease ci r- cuits .

The fir-ing ci r- cuit is used to fir-e the pr-oject/les while the r-ele!!se cir-cuit jet lisons the launChing tubes.

5

Operation a, Firing

I

,,~.,". n'

2 ........ ~

u., t

n' •• I1<n

"'~_ n'

.w ll< "

•• t,.c _ nt o·.c·," ~ilO' ~Ml '

, , • • 1,1 ." I • • " ...... . . . .. 1 " ,",, 1. 0. cI ' ov l' ; , .... o t,§ ,01.,

Fig. 5 1 Ar-m!!ment switch IlIy out

Complete the fidng cir-cuit by activating ci r- cu i 1 br-e!!ker- p 1 tr-ight instr-umen l console) , Sefety switch I (SZKK4 conlr-o l unit) , end tog g le swit ch P802 (mar-ked ifS icher-ungss::h!!1 ter- Ger-'ilt 21" end I oc eted on the left side of the BR lIr-m!!ment pane ll. To f i r-e the shells p depr-css the bomb r-elee se butlon , 82 , loceted

Speciel weepons

on the uppe r- left side of the contr-o l gr-ip.

Fig. 71 KG '38 with 82 fir-ing button

b.

Release

I n en emer-gency, the leunching t ubes CM be r-ele.!lsed by sever-ing the cer-r-ier- sl r- uls w i th eXplosive cher-ges . Cir- cul l br-e.!lker- P1 end Sefe t y switch I comp lete the r-ele.!lse ci r-cui t. To fir-e the cher- ges, ecl u ate toggle switch PBO' Imtlr-ked "Ab spr-engung Ger-'et 21" end l oce led on the r-J ghl side of the BR er-mernen t panel I . To pr-event ecciden tel actuation of the t ogg le switch, It is he ld in the safe position by e spr-ing_loeded plete .

I,. ,

.,.,

..1.' ""2 ,,, ,

,

I

I

/f-\ II

" ~6 -,): ,

-," -s ,

"

I 'J L-J Fig . 8 1 Positioning o f t he br- ecing sI r- vIs

syst~

D. (Luft) T. 2190

A-a

For Official Use Only!

Aircraft Handbook

Part 80

Special fittings

(Effective July 1944)

Issued September 1944

Sped el fI ttl ngs

0'

to gether .

Genera l ' Speclel fittin gs' specifies the airc r aft armour .

The armou r pr otects the pilot , the oi I coo ler and the circular 011 te n k, I ts position i ng wi t h in the 1I1 rcreft is as shown in Fig . t.

•

--

• 1.

•

The back armour consis ts of two separate p I ate s whose inner edges a re screwe d to the sell! gu ide r ~ I I s , Md wh ose outer edges a re screwed 10 Mgle pi e c es i n the fuselege wells. Nuts ere riveted to the guide r"lls and t he engle pieces ; the ple les a re fastened from the reer by screws •

.

,

/

,

,

5

•

3

,

,

/

rp l" •

,,

,

,

•

\ \

\. /

/

, ." 6' " •• , • • O< ~

~I '"

or...,,, " ... , • >' ... 1• ., 0'_"' • .... """,' t', _, . !no . <" ," ' .... .. 0 0''' '

L8 ... ,

2 "0<'

I~ _ '

~

" ''''' , • • or .... r ~

_ ,

.'.,

• ,

1!.Co _ '

' ~ . ''''' '

,:11

•

( ~,'

.1..."., " ,,,or_, ,I•• " nt '.

o

•

I, ~ _ '

Fig . 11 Aircreft ermour layou t

, "''"Go' . , ...

2 t ... I "

, e. •• , ""'

• ~.'"r l "g '.'"

~

It. I , .

• Ar ~Qo ,,'

<... 1.,

Fig . 31 Shoulder ermour

A. Cockpit a rm our The cockpl t e rmo ur consists of t he back ple t e (1 ,11 on the pll o l' s sea l, two back pllltes 11,21, a shou l der p lete (1 ,3 1, and e heed pla te 11,41.

The shou ld er ermour can be attached in ei t her of two weys (see Fig. 3,a & bl , al The shou lder armour cons ists 01 bo th an armour plln el (3,11 lInd !!I c!!lrrier unit 13 , 21 .

0

I

0

0

•

0 0

•

0

•

..'I

The ermour pla !e Is posit i on ed behind th e cerrier Md is I!!ttached to it by three nuts , Thismethod of I!! t fachment ellows f!!l st replacement of the ermourpleting. Th e carrier Is riveted to the f usel!!1 ge .

0

0

•

0" "

,

~I~'"

-

-2

0

0

.'" .

F i g . 21 Back a r mou r, seen in direc t ion of fli gh t

Prote c tio n ege Jnst gun fire Is elso pr ov ldedl ",1 from t he fron tl by the bu llet resistant wind _ screen 1' , 51 ; b 1 f r om the sides : by bu I I et res i 5 f "n f g l ess pene l s 0 , 81 on ei t her side of t h e fono e r d windscreen pene I; end . cl from be lOW: by Ih e two fuselege se lf_ sel!! l lng fuel l enks , The

seet

rear

p l ate

end

se!'!t

pan

are

riveled

bl I n t he second des ign , the a r mou red c llrr ier itself serves es t he shou l der ",rmou r (see Fig . 3bl .

Th e he",d ",rmour is bui lt i nto the cenopy !lnd is secured 10 it el Its bese, by Iwo guide bers secured by hexagonal bo l ts, ",n d, a t I t s t op , by a sc rewed on support s tr u t. The s tr ut Is s e cur ed by two C a b I e s (see P",rt 11 . In newer prod uction !!Iircr",ft, the heed armour is s e cured by e Sheet fairi ng a nd t wo c e bl e s ; Ihe s Jppo rl Is the n omi Ited . a ) The bul let resisttlnt wi ndscr een Is housed in e steel fra m e, end is secured l o! t bye scr ewed on mo l ded fremlng . bl The side pletes slIde Inlo the nose_over freme end ere secured by e bese rl!! bbet .

Specfel fittings

B. Nose armour The oi l coo l er 14 ,21 end ring _sheped 0 11 hl nk 14 ,4 1, both o f mef c hl ng cl r cu ler construc t ion , ere enc l osed by ermou red rings whi c h form the forwerd portIon of the engine c owling. The coo ler ermour Is secured by hexe gonel s c rews: t he 011 tenk ermour by crown nut s , The , Ive open i ngs In the "rmoured nose rin g, required f or lis inst e"et lon , are covered by f ormed disks 14 , 9 1•

,.•

.8

,.

<.,

•

, , , , t ••

•

f., ..--."

,

• Somf .,

1 Of' <_ fo,

) un ....

• t f , .. ' "

~ ~orl

. , .... ,

I ' < ~ f ..

0 _ _. '

, 11 • .., 11t

.n

I ( •• t ...

I• • '

f. I,I .~

or_' ." ...... , " ' . " ' •

9'_ .""

Fig. 41 0 1 I cool er end 0 1 I tonk armour

ten piece rin g, con s l stlng o f fi ve support breckets 14, 51 joined t o five seml _c lrcu lor 10lrln95 14, 151 , Is positioned be tween the coo ler onnour e nd the coo ler. The rin g 15 secured to the 0 11 cooler by c row n nuts end t ie bolts, A.

The elr ex it gep between the 0 11 coo ler ond t he 0 i , tonk ormour is 10 mm.

02

D. (Luft) T. 2190 A-8

For Official Use Only!

Aircraft Handbook

Part BE Camera system

(Effective July 1944)

Issued September 1944

01

ClImerc system

Description The cemere cen 11150 be trl ggered by depressing tI button (1,91 on the throttle lever (1,101, thus

General The 'Type 16 Gun

the Fw 190A-8

camere'

(BSK 161

Is Instelled In

Its In51011ellon In the field,

flghte~

in previously delivered ellrcraft, Is mtlde for ..... 8 series elr-crl5ft using Fw 190 Modlflcetlon Inst,..uc_ tlon Nr, 85.

/

The 'Robot' m I n lilt u,.. e Clll11era 15 Instet led in ell

-

--

--

/ , /

ground_etteck alrcreft (Series FJ end extended range fighter_bombers (Series GI. It 15 also possible, In fighter errcreft, to replace

,,

the aSK 16 with the 'Robot' using en edepter un I t .

t' on, the lead from Ine the weapons system Is not etteched,

,

In the 'Robot' In st tll 18

camere 10

-

. -

A. BSK 16 gun camera The aSK 16 cemere

11,11 Is mounted on en edJusttlble

platform (1,4) In the lel!ldlng edge of the left wing penel between Rlbs3b 11,21 end A (1,31, end Is etteched to the efrcreft electrlcel system by e plug connector 11,51. The cemere lens opening In the wing leedlng edge Is covered by e hiring end g I e s 5 window (1,611 the cleer gless penel cen be exchenged for e coloured light filter.

The aSK 16 Is e 16 rrrn movie cemere. The film roll Is 15 m 149.2 ftl In length, end Is driven by en electric motor In the cemere. The motor controls e switch which limits film movement to 3,75 m 112.3 ftl per run, end perml ts four film runs of from 43 to 57 seconds duretion eech. Depressing the firing button for the fuselege end wing_root weepons sterts the c~ere.

,

os~

' 6 c_o

2 '"b" l ~'b •

• c -. ~ , .tI,... , ( ''''''' 'eo ' c..... u .or

1 ll« " 'eo'

J~"C"""

. ... ,""", "' ''ch

"".

Q ,~. ' ."~ 'Q I .... U' . , ......

""'.".9 '_go .'.jo< ' or

6 "'rl_, _It" . ,••""".,..U,"O".I!, " '0.'''' ~...... ''''' uh' Fig. 11 aSK 16 IBelllstlc gun cameral system

---

\

\

-

-

I

\ '-----.. .. , ./ ,.--

,----/

'-.

\""...,' c_'.

1. "

ID

"'-- _

..

I R, •• • C_ro

-- c

.,."or..

,.,u' ...... , ...

• '.'r'.9 .I! _.,...... ~ (I • •

--

'r',,",

1 L_.

• T... . ltl. ' ....

Fig. 21 'Robot' cOllIers Instelletlon

Q

tl .,""., "."01''''' •• ,. ,

'0. '" (0" "' " I . R'Il"' ,.", __ , "'''0.''

Cmlere system

e n e b I i n g gun camenl photos to be pressin g the f i rin g bu tton.

teken

wl thout

• • B. "Robot" miniature camera With the ' RObOt', Model II, miniet ure cemere, sin g le photos can be teken from high a I t i t u d es down to eppr oximetel y 2000 m 16 562 ftl. The camere is eimed thr o ugh the gunsl ght. Freme size Is 2,4 x 2,4 cm, end the film roll is 1, 6 m 15. 25 ftl long.

The 'Ro bot· c e mere 12,11 is, es is the BSK 16 , moun ted on en edj ustable pletform [ 2, 4 ) in the wing leedin g edge between Ribs 3b 12,2 1 and 4 12,31, end

\

~v. ' 6

c .... ' . ~ ~lg", l~i I ... ~ • • roj«' .' ~ c ......

) "' i" , t oOl . ~\ . 1f o'O\

• • '." ."" ' ''' ~'' . ' ''.c'-" ' ... fh l"g •• 1" ,

' o r~

. o l "'

Fig. 31 BSK 16 camera

,l c-,. >""" " Iot" .......

I .... . ' 1. 1" 9 •• 1. ,

}

~

.• •••• _,.t,

• •. "jw " " "' ~ ' ''' ~'''' ." oe_ "' .01., . ... , • • ,.If .....

6 "'on.," c_ .. ~

I " ' '" 00.00<• •• , I"i

Fi g . 41 'Robot' cemere

Is atteched to the ele c t r l c e l c onnection,

02

circuit by e plug

The film Is edvenced by e sp r 1 n g device on t h e camere; this spring must be wound bef ore each f I I g h t . Neer the spr in g Is sltueted en ectuati on bu tton. When this button is pressed, the shutter is released and the film edvanced one freme.

The c ircuitry for releesln g the shutter Is connected to e bu tton 12,71 on the t hrottle lever 12, 8 1. This b u t t o n ectlvetes e megnet slt ueted on the c amera mount. The megnet triggers the ChargIng lever which depresses the cemera shu tter releese.

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part 9A General equipment Supplement 1: PKS 12 Patin directional control

(Effective July 1944)

Issued September 1944

G~nerel

01

equipment. PKS 12 Petln directional control

A. General The Potln dlrectlone) control Is used fa molnteln e required flight course by supplying eutometlc steer_ In 9 Inputs to the rudder.

This facilitates both f lying In bad weather conditions and penetration of con t I nuous cloud cover.

The sol e control device provided for the pilot is the turn switch IV601 mounted on the control column.

The swl tch comprises both a blpoler tumbler swl tch to engage end dlsengege the eutometlc pilot system, end e five position rete_of_turn switch which c om_ prl ses a centre 'null' pOSition end two t urn rete positions each to right end left. These turn rat e positions permit the Initletlon of 0 turn at either of two predetermined turning rotes, 1C1 /sec or ~/sec.

The elevator and ailerons ere operated In the normel menner.

B. Methad of aperation

Is ectlveted when the turn switch

Is operated, to

turn

onto

the elr-erllft

direct Ion which

compass course

Is Indicated

b~

After the pIlot moves the fur-n switch to contact 1 or 2, the co U,.. 5 e motor will change the CotTll8SS

course et e turning rete of either 10 /sec or 2O/sec.

When the steering mechenlsm Is disengaged, the rotetJon speed of the compess course Indlcetor'" !through e wetlkenlng of the magnetic field wit h I n the course motor! Is increased t o 50/sec. By mtlnuelly t urning Hie elrcraff onto the desired heeding befor@ engeglng the eu tome t i c pilot, the

eircrtlft c

tI

n be brought to the desired course In e

shorter time.

1 n 5 t e I led In the steering reley Is e moving call unit, with five electrlcelly sepereted coils, I'fhlch pesses through the field of e permanent megnet. The various direction sensors creete electricel currents of specific strengths and directions which eet on given calls; the strength end dlreet I on of the s e currents ere trensmltted to the steering unit IKBI. In the steering unit IKB) ere conteined the steering

,,

V46

.. v v

,~, ,, ....

cl<cul' .... , oun"l.,. 00. ? ~'9"""

,,

•

1• • , , _ . , con.. "

co."

"Io "; ~u ' or

~ ••• I ..... (;0<.,.')

Fu.o l o~.

F• •• I .....

.. • ~ c-r .. """' ''''-

•

1

• '0 O_

o

•

.. 06

"

$

P•• I" .... '"'0,/,0,1 0... , ~ ..... ' .. c........ " ., .0g. lI-. GI.,,,"., ...

lng "~U "' or ulo. c_on ' ''''' In In.' ..... OI po.ol l V 60 'u.n owllch (Con'rol . ,I c " ~ ...

V Hl ' . . nd."._,

desIred

e reference stripe.

Operetlon of the turn switch IV60) engages the course motor tK12) which Is connected to the base of the repeater COll1)ass (V46 I by a flexible cable, torque converter end spindle sheft. The course motor

1I 1 ~h!

ell

• 10

' Su I ....... 6-8' ,unc.lon •• • I"",Uon co un l ' ~ ••• rI. g u.l . "onor G ', on .' ~ '

~

~

la."I 'h"~

la-H>

unl '

Gen@rel @qulpm@ntl PKS 12 Patln dlr@ctlonel control

and mixing units for the systeml 11 The d~lng circuit, 21 The steering relaYJ and, 3) Th@ oscl I latlng trensformer.

The dampl ng circuit is fltt@d wl th a matching c i r c u i t In which the voltage gen@reted by a divergence from horizontal flight Is matched by en equel and opposlh voltage g@nerated by the circuit.

The oscllletlng transformer has en IIC frequency of 50Hz __ Input to one of the coils In both the position Integral Ion unit and the steering unit, so that slight vibrations will not, through slippage or jamming, cause seizure.

The dsnplng reguletor IK141 Includes en air Intake pipe In which the movement of the shaft operates en e I e c t r Ice I trensmlsslon line which relates the deflection of the rudder to the elrcreft speed. Thus at greeter speeds the required rudder def lectlon Is less then at lower speeds.

As only en everege course

Is maintained by the steering un I t , small deviations from the required course cause only very weak currents which will not result In operetlon of the steering unit.

The I eonard transformer IK101 Is till DC_DC transformer, end Is excited by the steering contro I current produced by the steering reley. The current Is then pessed to the armeture of the DC motor In the rudder drive {K161.

The rudder d r 1 v e also contelns en e I @ct r I ca 1 coupling, opereted from the eutometlc pi lot @ngaglng swItch IV60l, wh I c h connects the geer drive to the rudder ae t u a tin 9 lever. Wh@n the rudder drive is dlsengeged, however, the rudder Is relees@d.

Within the Impedence casing IK41 Is located an 8dJusteble resistor to control the edjustment re t e of the actuetlng spindle on the course molor IK121.

Addltlonelly, two releys ere provided, which When the autometic pilot Is uncoupled Idisengeg@dl, ceuse e weekenlng In the field of the course motor IK12J, thus perm I t I I n 9 e higher adjustment rete of the ac t u a tin 9 spindle end thereby the compass cours@ indicator.

02

D. (Luft) T. 2190

A-a

For Official Use Only!

• - • Aircraft Handbook

Part 9A General equipment

(Effective July 1944)

Issued September 1944

01

General equ ipment

I. Instrument panels and consoles 1. Instrument panels 28

30

32

17 45

15

46

14

_ - 47 49 50

10 - - 1 - 9-

-

8- -

51

-

-f

52 53

6--

54

5- --"

5

4 -~

56

,,

3--

57 58

2

9 60

,• •• •• .••

... .." ...""

..

•. "

.."

"

~

67 ,

••

"

...

66

65

64

- -,,,_ .

• -

63

.. ..-.." -.

-_ . ,'- < -• • • '.'- -....... -•• .,. ..... . ....... '" ..••.. ,-,"'-.

"- ..

-••--......--•" "_ " •

~

"

o'

"

,

,

,

,..,~._ ... _ _ ........ h.1 --.~" •• ,toO .~

,,-

<-0, .,i .. ...

"fi_ •

•

Fig ,

61

62

Cockp l t Interi or

~

~

.."""" ......." .. "

---

General equipment

"I ne Instrument penels comprise 15 meln pl!lnel (Fig. 21 and an auxll hry panel (Fig. 31. In the aree above these panels are positioned addltionel Instruments and the Instrument glare cover. A third Instrument panel, situated between the 15uxI1115ry panel emd the floor, serves as the armament penel.

The auxlllery Instrument penel bese plate Is e loed Deerlng component of the fuselege end Is secured to It Ilnstrument bulkheed!.

? 1 •• , , _ •• ,

, " " '''' ' .1 ,1 .. ,,, 2 ) • ) 6

Alr .p." In~I •• ' " " " l l l d . , ~ ... I ....

V.r ll •• 1 _ .. 1""luh.. ~ . p . . l ... . _ ...

s...p".".r9*'" p, ••• ur .

~'"!I"

& ' 1101 Iv', ""'r "9" 9 UgM . ""k.' • '0 ~v"" " _.'In~ poln lO

....... _,.

12 EI ..... leo l I ••••

Fig. 21 Meln Instrument penel

•

, ••• , .no 011 pr ... v," 9O'V9' . . ..... 11 .... 11.n In.I •• I ...

2 CII ......... , . " g.ug. ~ ~ " .. ... _M . ) >•• 1 co.to.to goog.

6 Boo • • , •••• " •• _.1 polnlO ? [ •• • ,,1<0 1 I ....

'''0<'

Fig. 31 Auxiliary Instrument pllnel

2. Instrument consoles The left end right instrument consoles contain operetlng controls end clrcult breekers. The left con sol e contelns the engine primer p~ end the bettery master swItch, ea well es the controls and monitoring Instru_nts for the undercerrlage. the lendIng fleps ond the stebllizer IncldenceJ the r I gh t console, all alrcreft electrlcel system

02

c I r cui t breekers, the engine sterter sw'tch, tne flllre gun dillllunltlon IInd the aircraft clock. The electrical system circuit breekers ere protected by sprlngw I oeded covers end des I gnated by neme plates neer the covers.

In more recently produced IIlrcraft the two groups of circuit breekers ere consolldeted Into one.

03

Generel equi pmen t

•

•

•

11. Powerplant mOnltormg Instruments 1. Supercharger pressure gauge

2. RPM gauge

The supercherger pressure geuge 11 , 381 Is mounted on the right side of t he meln Inst r ument panel, Instrument ra ngel 0 , 6 _1, 9 etl! IB .5_25.5 psi t,

The RPM geuge (1,401 Is positioned on the right side of the meln Instrument

For

Meesu reme nt ren gel 600-3600 rpm,

the rou t ing of the Instrument meosu r lng line see

pen e I .

The engine !!nd the

gauge ere connec t ed by e flexible c ebl e.

Fi g, 4,

An 011

extrector (5, 31 Is buil t Into the flexIb le C.!I b 1 e neer Its point of ettechment to the engine.

Any 01 I thet

has

p enetrll te d the

cable

Is extracted

e t this poin t cnd ellowed to drop Info the en g i n e c~ artment •

,

~".<_"' 001., of Ih. 'VO"C""'I"

1. '''0 <-.nd

_ , uul

.... ,_ 'no" ....." •..,.,

~

6

.r ... v', Iln ,

.r ••'u" _ ...... I"g ""

~"." C ""'9" 1 ...... . " ' ... , ,., " _

:

u'"

$""'C""'9"

('g'"

pru,u,"

_,I1'g "'I

loug"

7 ~, •.,.ot '.,.. u'"': 0' Bu""'"

'n, .... '"

FIg. 41 Sup ercharger IndIcator system

I Atl OC _", .0'", of '''' _"ur_o ' 00'" ~

., .. 1.,. co."

,. , •• '"I ' "

0" ''''K'"" •} "p,. g""" , Ay"" .,. 1., ,,_" , ••n. 1 6 ,..1, ' " ,'r~"' .0."

I t'I'"

~u"I'"g

" '9

FIg. 51 Engine RPM measurement sys tem

Generol equipment

3. Fuel and 011 pressure gauge

4. Oil temperature gauge

The due I pressure gouge 11.201 Is mounted on the near left side of the ouxlllery InstrlJ'Tlent ponel.

The feed pressure of the PInPS Is Indlcoted In Kg/sq cm.

Th I s Instrument 11 .. 231 Is positioned In the n eer left side of the euxlllory Instrument pene I, end provides en Indlcotlon of oil tM1'erefure. The unit consists of en eledrlcol probe 17,1 I on d on Indlcetor 17,21, end uses the 24 volt elrcreft electrlcel system. Indlcotlon rongel 0-130'C 132_266·FI.

0- 3,0 Kg/sq cm 10- 42.6 psll 0-15,0 Kg/sq cm (0-213.0 psi'

Fuel pressure renge 011 pressure ronge

The operot I ng Ilml ts ere morked by Indlcetor 'Ines.

, l

, (\«,.k.,

O l ' ~_

h.' ,_ ho' ........... ........ lIon 0 11 pr •••u" 11.0 •• .... 1I1.r , 1.... _ . ,

, 'I~ . ,.r."~ ' ,.~. , 6 '.0 1 o~_ p....... ~.ui.

1 £.~I n o ~n'lni rl.,

."

l Oll

~ol.' 'o ,~,

Fig. 61 Fuel and oil pressure meosurement system

'_or.'~"

' _o" 'u" ,oug.

p._

) A. , II1 ... , ' . . .. _ M po.o ' • 0 1' " •• 'ro- <001 •• 1 0 . . In ~ Sopor. "'" 001., ,0 6 !ngloo . ooror " ' _ ' ,

1 eOI'" 8

Fig. 71 011

~ I 'I'"

.~

_".!lnq . I og 1•••• _ .,

c" •• 'o

t~eroture

meosuring circuit

Gene~ol

05

equipment

5. Fuel contents gauge

6. Mechanical airscrew pitch indicator

The e 1 e c t r I c a I fuel contents gouge, 11.361 end 18,11, Is positioned on the neor right side of the !luxllll!ry Instrument ponel (8,2)~ It Is possible to Indlvlduelly meesure, In Ilter-s7 the con tents of eClch mo ln f u el h nk .

The unit, (1,371 and 19,11, serves t o Indicate t he p I I c h of the adjustable alrsc rew. In d I c 11 t Ion Irrpulses ere fed from the pitCh con trol un It 19,2 ) via a flexible cllble 19,31. The propeller blade p itCh Indic a ti on Is given in hours and minutes.

The unit

For operati o n IInd malntenenc e of the appropriate publlcetlons.

consists

of e fuel contents probe with low

level warning attachments In bot h the rear 18,31 end forwerd 18,41 hnks, Md tm Indicator unit 18,11.

Indicator lights 18,51 ere positioned In the

Instrument bulkhead. The lower, white light, acting es lenk 5wl tchover- warning, 111umlnetes when rear

the unit

consult

From time t o time e xsnlne the ceb le attachment point s f or good seating, to prevent line d o!lmage due to chafing.

hmk contents hove dropped t o 10 Lt,.. 12.2 gall, the up per, red light, provides return to b8se warning, lllumlnlltlng when 80 Llr 117.6 gill) rerM l n In the f orward fuel tllnk. P lllte Inscription' 20 m In ut e s remain ing at econom ical cruise.

A gauge selector switch (8 ,6) enables the Indicator un I t t o be swl t c hed 10 measure the con tents of the f orward or rear tan k .

Operating power I 24 volts.

•

.'

, ' "cl> lodlco'or 2 Krdr o. " c_. ' oc,rl c .I,<n con,.ol """ , " .. Ib'.

<o~I*

• Separ." on 001., , on .... ,.n... , ~

A.""'..,., ,•• ,.._., ..... ,

Fig. 9; Alrscrew pit c h Indi c etor

, ' ••' .<.,••,.

~."g.

2 .... 111 .. , 1., '. _ _ ' .... ,

, R.... ''''' COII' o' " " •••• ,," ' '''' l on l ...... ,.~ • '''''''......... <on .o. U ., ••• _ I'. ' '''' , • •• , _ nl.~ , 'nolc o'or o ' •• ' ; •• g.

II~M O

11 ... I• •• , . .... In~'

" '. c'''' .. lten

Fig. 8. Fuel tank contents clrcul t

06

General equipment

•

•

•

Ill. Flight monitor and navigation Instruments 1. Pressure altimeter

Measurement I l ml tsl 'descent' and 'climb'

The unit, 11,1 9 ) and (1 0,1 I, Is positi o ned on t h • left s i de of t he main I nstrumen t pa nel 11 0,2 1.

Meas uri ng ra nge s 0- 10 km 10-32810 ft l .

3 000...0-3 000 m! s 2000-0-5000 m/ s

19840-0- 9840 fp sl 16560-0-16 400 fp sl

The bo ttom fi gure Is the maximum value o f the older Indi c at ors.

4. Artificial horizon Locat ion of the unit 11, 281 1 c entre main I nstrume n t panel. It I nd icates the positi on of the alr c r a f I r e lati ve t o the na t ural horizon, and t he turn sp e e d a nd s peed of r o tati on of the airc raft a bo ut I I s verti c al axis.

For detailed I nstruc ti ons concer n in g the I nspec ti on , I nstallation, oper at ion , s erv icing, and ma in te nanc e o f the unit s ee D.I Lu fllT.54 05 .

5. Remote compass system

, '<O ..y, •• ", ... ..,

.... ,. 'n""••ss"' y....•' ••••• , •,., ~

~ '. "c ~

9 ~ ' . .. .. d ' <><11 <0' '''

9 O,. oml c .1 • •""Y" 10 RI . ,""

o ., 10' ,y" " " ~ e..' ''' '' , ...... 111", 100"_ . ' ••••• ," . ,v.rI 'c.' .,n. ".'.ot .. " A lr ~

".,

'y" .... ,

'1' 0 ' ~ 11 • • " .9- ' 0 0 ' n .... II"" pol •• OI !!,,,.'I. , . .... ch_or O ",".~

y,.

The s y s t em comp r-i ses t he mas ter c~er s s a nd the pllof' s repeerter c omp ass . The merster c ompass 11 1 ,1 1 Is l ocat e d In the rear f uselergeJ the repeat er c omp a s s 111,21, I n the near ri ght s ide of the main I nstr ume n t pernel.

I. " 0.' . ' . 100 •• ,. ...

I ln.

Fig. 10 1 Fl I ght mo nit o r In s tr ume n t c ir cu its

2. Airspeed indicator The airs peed I n d i c at o r .. 11,241 and pos iti oned on the left side of the me ln pan el "0, 2 1.

11 0 , 8 1, Is I ns tr ument

It Is connected t o bo th the static air pr essure line 11 0 ,3 1 a nd t o the dynsnlc erlr pressur e line 110 .. 91; the two li nes tire r outed ptlra 1 1el t o one a no ther.

When the pit o t tube heater Is swit c hed on, e letti c ed Indlcet or loc ated on the left side o f the merln I nstrument penel Is Illumi nated.

..

3. Vertical speed indicator The Indicat or, 11,3 31 a nd 110 , 7 1, Is pos iti oned I n the c e n tre of the mer l n Instrument panel 11 0 ,2 1 a nd i s c o nnec ted to the s tat ic a i r pressure line (1 0 , 3 1.

The differential pres sure lank ' 10 ,131 Is sec ured by two c I amp s beneath the decking In fr on t of t he windsc reen [10,141, and Is c onnec ted t o the vertl c erl speed I ndIcator by an air line.

, .... ,or 0_'" 1) "... 1'0 ". ,"P"'" ' '''...... . '''0''"",",, , ••• 01 • ~19""

""'....1.. 1...

""It

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7 r. "~ <"",.,,'"" A I~h '

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Fi g . 11, Remo te comp ass s ys t em

07

General equipment

6. Stabilizer incidence indicator ThIs system consists of Ihe steblllzer Incidence reley unit [12,11 end Indicator , 12,21, The 5

Ind i cator 113,7) IInd the act uation switch (13,6) er-e

l oc ated In the left Instrument console .

The Incidence relay unit 113,11 Is positioned In the right side of the vertlcel ste.b ilizer end is

connected to the triangular stress frMle 113,51 by e push

rod

(13,41 . The

stllb l l l ze,..

Incidence

!!

Is

Indlc et ed as + or _ (Fig. 141.

@

*~ 6

,, ,'

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1

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c." ,•• " ..... , '''''.0' ' 9 "'v"""" •• 11 <' o v .. . . <o.d.~. " . (, •• 1,,~le .. or

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• , . .... 11< ...

Fig. 131 Stabilizer trim system

• 1

. ... -! ~.C--cC'""--­ ,,;.: _,::;;.... 6

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, I ncl.,.,< ",., u. It 1 InOl e o' ...

•

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6

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Fig, 121 Sttlbllizer trim sys tem

•

Trim system Ind ication The shlblllzer null setting .!Ind limit settings .!Ire m.!lrked on the shblllzer f.!llrlng and left cover pl.!lte {Fig . 14 1, and on the Indicator IFlg . 151.

The st.!lblllzer null settIng Is m.!lrked on the s t.!lb I I i z er folrln g 114,2), In the centre of the overl.!lp, by 0 red stripe which Is extended for 50 mm onto the cover plate .

It Is .!Innotaled - Anzelgeger'6t 0" In red letters 1 0 mm high.

At the st.!lblllzer maximum neg.!ltlve setting, .!I stripe, 25 rrm long, Is m.!lrked on the cover p I .!I t e, .!Ind denoted by .!I _ Imlnusl .

A s I m I l.!Ir stripe Is marked ot the stabil iz er moxlmum posItIve setting.

I1 Is Indicated by .!I + Iplus).

, . . . . ,.0... ' ••• "," .., " ' rin g OOno "

1 .... , " ...

J t . .. , .,., .

• ~"" " '" 1.<;1 ... . <0 ro ... v.l.

~

!rl . ngv' ", ., .... [. _

o ~ " olll ". 1< 11. _la< , E'oo ")e" , •••• " nil

" T."

FIg. 141 T.!Ii l unit trim components

These registration left side only.

m.!lrks

.!Ire pl.!lced on the fusel.!lge

Durl ng Inspection of the st.!l blllzer trim system ensure that the reglstr.!ltlon morks on the Indic.!ltor and on the cover pl.!lle .!Ire In .!Igreement ,

08

Generel equipment

, SlO."''''

,.c, ..... ,... ,.. ,...

1 ~ . 11 , . " . _ " ' ..... ~I .

l 51 • • 11, ..... ,,,,,1' • • 00

n ••• " ... .

Fig. 151 Indlcetor

7. Aircraft clock Posltlonl on tne dgnt Instrument console !1 p 511.

IV. Oxygen system A. Description The syslem consis ts of Ihr'"ee two liter'" li ght steel spher'"iclll bottles "6 , BI, e r egulator'" uni t 11 6 ,1' wi th oxygen hose 11 6 ,2 1, high pr'"essure lines 11 6 ,31 wi Ih pressure gau ge 116, 5 1, en oxygen flow monl t or (16,-4 1, and e flow valve "6 ,61.

Tne oxygen boff les ere mounted et the bllse of the rlldio compertment lequlpment bllyt beh i nd Bul kheed 9; two are on Ihe f use l eg e dght side __ fecin g I h e equipmenl bay eccess door __ and Ihe third is on Ihe lell side beneelh the equipment bey door. As II slIfety meesure, the three boffles ere divided Inlo two seperete systems by Ihe Instelllltion of lo u r non _ret urn velves. A non_return vlllve Is bu i It In t o the f i ller l i ne, between the externlll connection and the first oxygen bott le. The r'" e g u III tor unit is pos illoned behind the p l lol's seat on Ihe d ght side fnr'l\eJ the pressur'"e glluge p oxygen flow monitor and flow vlllve ere on the lIuxlller'"y Ins tr'"ument pllnel r'"i ght s ide.

After the flow ve lve i s opened p the oxygen flr'"st flows to the regullltor unit. The emer'"gency pressur'"e bulton on the reguletor cen be lIct uated by Ihe ri ght elbow of the pi lot.

B. Inspection Inspect the oxygen s ys tem for proper'" operll ll on, satisfactory condition and secure mountlng. See O.IL uftl 1205 .

• A• .,.,' . .... ",,11

1 .....

l

.'V> ......... ,' n..

• " .. -.. 1, ...

• , . ........ ~ .... t·

, '1.,. •• ,•• ' h . ... . . 1 " " ... , .1• •

•• ..c ••,." •••• ,, •• "

". ~ . , .~o ,

11) ~ • • , " " . , •• , , _ , •• no'

Fig, 161 Aircrefl oxygen system

Short test Open the valve, reed the pressure, close the velve, In 20 minutes, the system pressure '1 50 et'ul must not fall by more than l a lIt'U.

G@nerel equipment

09

V. Rescue and safety equipment 1. First aid kit The fkst

e tube end con, from that position, be fired, rhe required ommun I t I on Is cerrled within the right

old Idt Is posltlcnN within the r I 91'1 t

Instrument conso le 11,581.

side of the reol" fuselogl! between Bulkheads 9 end 10, end Is eccl!sslb le from the outside,

3. Seat straps and parachute

2. Flare gun The flere gun Is locoted In the r"ight side of Instrument bulkheed 11,451.

the There it Is inseded In

The pil o t's seef Is Du tfltted with lap IInd shoulde,.. slreps, with Intogrel Quick_releosl! mechanism , The pi lot is provided with 0 beck perechute end 0 0 n e_

men dinghy pec k.

VI. Windscreen cleaning The sprey t ubes 117,9 .!. 101 lire so pos! tloned that when the stop cock Is opened, fuel expelled through

the sme ll ho l es In the tubes, wi 11 be blown retl,..,ard by the slipstream to clean the three glass panels.

'V

I ' ~. I ""0"" 1 Fw. ' . ' • • , 1 I ' .. 1 " • •

• -. 1_ ~

~ O"i'

I••• 11ft. ~""v" , ov9'

1"", ~ ,1

••,. 1

.... . ltl .,., , ,, ' ' __ , ' . ... .

6 " " U" " •• lOn .......... 11... I.v", I " " "'00' _ _""1 i r _

e 'v.' Ii • ...

•

, $0>'"

'0

~ .. ,

,~

. . .. .

Dur i ng f I I gh', 011 on the front end side window penels cen drestl c ally reduce visIon thr ough them, These panels can be cleered by spre ylng fuel over them. The required fuel Is drawn 'rem the fuel pressure gauge feed line 117,11. Just before the line enters the gouge 117,21, e tube brenches off 8nd runs be tween the ml!lln Instrument penel 117,41 end the 8u:ll:lllory Instrument penel 117,51, to I!I stop cock 117, 6 1 on the windscreen moun tI ng frame 117 , 71.

D. (Luft) T. 2190 A-8

For Official Use Only!

Aircraft Handbook

Part 98 Radio installation

(Effective July 1944)

Issued September 1944

01

Red' 0 Instellatlon

,

•

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Foch-Wulf Aviation Corporation

-=~~=-~B:'.~m:.~"~_

_P_.~'~'_'

_____________

Top Secret Observe appropriate security regulations

Technic&l description No. 284

Fw 190 A-8 Fighter

Prepared by:

, 30.11. 44 Sta/Bu .

File N, ,~, .

~----.-

-------'

Foclle-WIII' Aylotion Corporation Br.men

Technical description No. 2B4

Fw 190 A-8 Fighter

Poo.' 1

Data sheet Mission type:

Single-seat fighter (Fighter-bomber)

Construction:

Single engine, low wing, cantilever construction with electrically retr&ct&ble undercarriage.

Structural strength :

For Fw 190A-8/R2 on fighter operations, at G = 4450 kg (9812.2 Ib), safe 'G' factor n = 6,0 A On fighter-bomber operations, at G = 4775 kg (10.528.9 Ib). n ~ 5.5 A

Powerplant:

BMW 801 D (F 600). from about July 1944 BMW 801 TU

Dimensions:

Wing are8 Span Aspect ratio Length Max. height Main wheels Tail wheel

Normal flying weight:

F

~

18.3 sq m

2b~10.5 m

b /F ~ 6.0 L ~ 8.95 m H ~ 3.15 m 700 Il x 175 mm 350 Il x 135 mm or 380 Il x 150 mm

(197 sq ft) (34 ' 5.4") ( 29 ' 4.4") (10' 4.0")

Fighter operations

G ~ 4400 - 4450 kg (9702 - 9812.2 Ib)

Fighter-borr.ber operations

G ~ 4775 kg (10.528.9 Ib)

Airframe weight:

1225 kg (2701.1 Ib). composed of 55.8% Dural; 36.6% Steel; 4.3% Rubber and plastic; 3.3% Wood

Armament:

Fw 190 A-8:

2 MG 131 in fus.lage with 475 rpg 2 MG 151 in wing-roots with 250 rpg .2 MG 151 in outer win gs with 140 rpg

Fw 190 A-8/R2:

2 MK 108 with 55 rpg replace the outboard MG 1515

Fw 190 A-8/R3:

2 MK 103 with 35 rpg (beneath the wings) replace the outboard MG 15ls

Engine armour BMW 801 D (F 600) Thickness 6.5/5.5 mm; Weight 78.0 kg (171.9 Ib)

Amour:

Engine annour BMW B01 TU Thickness 10.0/6.0 mm; Weight 106.0 kg (233.7 Ib)

Cockpit armour rmour weight

i-----"fFii=' 27.11.44

Stii/Bu.

N,

60.0 kg (132.3 Ib) 136 or 166 kg (299.8 or 366.0 Ib)

p,..:...-- J,..;,_I..I..!._'路~-"r .

__J....

I _I-I_ _ _ _ _ _ _ _ __

Foc:ke路Wulf Aviation Corporotion Bre",en

Technical description No. 284 Fw 190 A-a Fighter

Equipment:

Fu G 16 ZY;

Fuel l oa.d:

Normal: 525 1 (115.5 gal) Additional fuselage tank: 115 1 (25.3 gal) Drop tank: 300 1 (66.2 gal)

Fu G 25&;

R.vi l6b

_ _ _ _ _ _ ,...-_ _ _ """"" r 27.11.44

Sta:/Bu.

File

N,

./

tnued ~---'r--

I

I

_____________

Focke路Wylr A'tiotion Corporotion Bremen

Technical description No. 284 Fw

190 A-8 Fighter

Pau:

..2.:;...____

Design modifications The Fw 190 A-8 is the latest production version of the Fw 190 series and include5 a number of changes in armament, navigation equipment, range capabilities, etc. designed to meet the demands of modern air warfare.

These modifications include: Fuselage auxiliary tank; Based- on the requirement to increase aircraft range without degrading its aerodynamic efficiency, provision has been made for the mounting of a protected fuel tank within the rear fuselage.

After August - September 1944 all A-8 aircraft will be delivered with the auxiliary tank fitted. If required, instead of the 115 Ltr (25.3 gal) fuel tank, an unprotected Methanol-water (MW 50) tank of either 115 Ltr (25.3 gal) or 140 Ltr (30.8 gal) capacity, or a GM 1 tank of 85 Ltr

(18.7 gal) capacity, can be installed. At the present time, however, it is planned that the standard A-8 will be produced only with the auxiliary fuel tank.

Radio compartment: Fitting of the auxiliary fuel tank has required the relocation of the Fu G 16 radio installation from Bulkhead 8 to the area behind the pilot's seat. An access door built into the fuselage right side provides easy access to the compartment.

Fu G 16 ZY: Fu G 16 Z'f radio equipment will be installed in place of the earlier Fu G 16 Z. This set is like the Fu G 16 Z, but has, in addition, the E-type range measuring circuitry. In the interim, Fu G 16 ZE is being fitted; it is eqUivalent to the Fu G 16 zy except for its lack of homing

capability .

Forward placement of ETC SOl: Fitting of the additional fu s elage tank has necessitated shifting the ETC 501 (Part no. 8-190 . 861) forward about 200 mm (7.9 in). Starting with the Fw 190 A-8 series, only the forward mounted ETC 501 (Part no. 8-190.8861) is to be installed. This will be replaced, at a later date, by the aerodynamically and functionally superior ETC 504.

Vertical speed indicator: To improve flight monitoring, a Vertical Speed Indicator will be built into the centre of the main instrument panel .

Camera installation: Starting in June 1944, provision will be made for the installation of a BSK 16 gun camera (Part no. 8-190 . 8061). The gun camera provides confirmation of gunnery results. powerplant: Commencing in July 1944, the BMW 801 02 (F 600) will be replaced by the B楼.W 801 TU. This engine i s an intermediate step between the BEW 801 D2 (F 600) and the later, more powerful, BMW 801 T5 or TH. Oue to delays encountered in readying the BMW 801 F fOT s ervice, the

28.11.44

Sta!Bu .

A

Fockl-Wulf Aviation Cor poration

Technical de s cription No. 284 Fw 190 A-8 Fighter

Br • .".n

PaQ.=

4

BMW 801 D wil l, as a temporary measure, be fitted with certain drive components of the BMW 801 TS/TH; in addition, it will also receive t he heavier 10 mm/6 mm annoured nose rings . The BMW 801 TU will be delivered as a complete replacement unit; it is fully interchangeable with the BMW 801 D2 (F 600) . Wit h the TS/ TH engine installed, the Fw 190 A-8 is redesignated Fw 190 A-9.

Increas ed emergency power: Commencing in July 1944, all Fw 190 A-8 aircraft will be fitted with the 'emergency power unit'. By overriding the supercharger boost re gulator, this system increases the boost p res sure , on takeoff and emergency power, at the low supercharger setting, from 1,42 ata to 1,58 ata ," and at the high supercharger setting, from 1,42 ata to 1,65 ata.

The res ulting increas e in maximum horizontal speed is about 22 km/h (13.6 mph) at the low setting, and about 25 km/h (15.5 mph) at the high setting. Due to the danger of engine overheating, thi s system must not be us ed for more than 10 minutes at a time.

The fitting of a GMl unit in place o f t he additio nal f us el a ge f uel t ank is bas ically feasible; but, in the Fw 190 A-8 series is not no rmally done. It can be used at altitudes above 8 km (26, 250 ft) and s p eed increas e of about 58 km/ h (36. 0 mph ) at climb and combat gives po·.... e r.

Gm ins tallation :

•

Armament: The no rrnal a n r,an:ent o f t he Fw 190 A-8 co ns ists o f: 2 1,:G 1 31 in the upper cowl ing wit h 47 5 rpg 2 VG 1 51 i n the wing-root s with 250 rpg 2 VG 1 51 in the outer wings wi t h 140 rpg This anc.ament ha s been stan da rd commen cing wit h t he Fw• 190 A- 7. Attachment points for a WGR 21 weapons unit beneath each outer Wl.ng panel are provided on the A- 8 .

An armament modification currently in production i s the: Fw 190 A-8(R2 wi th MK 108s in the outer wing panels with 55 rpg (replacing the outboard I<G 151s) • >s the: modification currently in preparation Another armament Fw 190 A-8/ R3 with 2 MK 10 3s beneath the outer wing panels with 35 rpg (replacing the outboard MG 151s)

Fw 120 A-8LRll Bad weather fighter: A portion of the A-8 produc t ion se r ies will, commencing in September 1944 ~ be out fitted as bad weather fighters and will be allocated the deSignation Fw 190 A- 8/ Rll . Additional equipment will comprise:

28 . 11. 44

Sta/Bu.

.I!:.

N"

FII •

•

IlIu·.!EL

Foch-Wulf Awlotion Corporation

Bru,.n

Technical description No. 284

Fw 190 A-8 Fighter

Pao.=

5

1.) PKS Course steering unit, with rudder drive installed 1n the rear

fuselage.

2.) Window heating: The front and left windscreen panels will be electrically heated.

3.) Fu G 125 radio range approach system.

Due to the rearward shirt of the Centre of gravity caused by the weight of the steering unit, all Fw 190 A-8/Rll aircraft will be equipped with the heavier 8¥.W 801 TU engine.

The following modifications are, at this time, in the planning stage: 0 A-8 R with increased cockpit annour for use by the Stunnstaffeln lAttack squadrons), with the following armament: 2 MG 131 and 4 MG 151 as per the standard. Fw 190 A-B. Fw 190 A-B/RS also with increased annour, but with 2 MK lOBs in the outer wings a5 per the Fw 190 A-a/H2.

Fw 1

•

28.11.44 5ta!Bu.

•

L -=-

Focke·Wulf A'f'ialion Corpontion Sr.me"

The Fw 190

Technical desc ription No. 284 Fw

A-a

190 A-8 Fighter

Pate'

poss e ss es the fol l owing armour variation s :

190 A-8 with BMW 801 02 Fw

Sub-type

190 A-8 with BMW 801 TU Fw

d

G

d

.£

..!.

.£

(mm)

(kg)

(mm)

(kg)

(mm)

(kg )

53.3 52,4

10,0 6,0 15,0 4,0

53,3 52,4 16 , 0

SO , O

l.

Oil coo ler amour

6,5

34,7

2.

Oil tank armour

5,5

43,5

10,0 6,0

3· 4.

Windsc reen mounting unit

-

-

-

-

-

-

5.

6.

Windscreen

SO , O

14,6

SO,O

14, 6

Wind5creen side panels

-

7.

8.

Triangular panels

Ho ri zontal. panel

-

4, 0 8,0

13,5 18 , 2

-

5, 0 5,0 20 ,0 20 , 0

5,9 7,9 20 , 0 21,0

-

4,0

9, 0

-

Seat armour

8, 0

18 , 2

8,0

18 , 2

Back armour

5,0 5,0

5,9

5,0

5,9

7,9 13,0

5,0 12, 0

7,9 13, 0

-

ll .

Head armour

13·

30 , 0

-

Panels on Bulkhe ad 5

12.

-

9,0 14,6 8,0

-

9.

10.

1 2,0

MK 108 ammunition p rotection

Total wei ght

-

front

top

&

,tom.

0

r

137, 8

armour

190 A- 8/RS ( At tack fi ghter) Fw

131 3.8 lb

-

165,3 . 5 1b

248 , 8 548 . 6

For Attack fighter sub-types of the Fw 190 A-9, the wei ght of armour is further increas ed.

/1

28 .11.44 Sta/Bu.

F~~-::::tM

'

II

Focb·Wutf

Avla.IOft Corporation

.,.",e.

Fw 190A-B armour

Pate: 7

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Focb~WI&I'

Technical

Avlotioft ~

(o"or.'ion

d.~criptlon

No. 284

Fw 190 A-8 Fighter

8"",."

Po,.' ""8

Weight distributlen Fuselage Undercarriage Control surfaces Flight controls Wing assembly Powe",lant Standard equipment Pennanenc accesso ries Additional acces so ries Paint

345,2 kg 258,3 120,8 " 32,3 " 475,0 , 1661,3 248,1 " 27,4 " 319,3 " 2,0 "

761. 2 lb 569.5 " 266.4 " 71.2 " 1047.4 " 3663.2 547.1 " 60.4 " 704.1 " 4.4 "

, ,

Fw 190 A-8 empty wei ght

3489, 7 -

,

3490 kg

100 , 0 kg

7694.8 -

7695.4 lb

Pilot, parachute, flying gear Normal fuel 525 1 Auxiliary ruel tank 115 1 Lubricants Ammunition for MG 131 (2x475 rpg) Ammunition for MG 151 (2x250 rpg) Ammunition for KG 151 (2xl40 rpg)

410,0 90,0 50,0 77,0 110,0 64,0

Useful load

901 ,0 kg

220 .5 lb 904.0 " 198.4 , 110,2 " 169.8 , 242.6 " 141.1 " 1986.6 lb

Empty weight

3490,0 kg

7695.4 lb

4391,0 -

1. Fw 190 A-8 flying weight

" " " " " "

~ I.OO

kg

9682. 2 - 9702.0 lb

============~===== ===~===== = ~=== ================

Removal of 2 MG 1515 and ammunition 2 MK 108 with 55 rpg

2. Fw 190 A-8/R2 flying wei ght ==~==========a=====

Removal

ot

2 MK 108s

2 MK 103 with 35 rpg

-176,5 kg 240,0

-389.21b 529 .2 "

,

4454,5 -

4450 kg

9822.2 - 9812. 2 lb

__ === ============ ====== ====== - 240 ,0 kg -529.2 lb , 460,0 " 1014.3

3. Fw 190 A-8/R3 flying weight

4674,5 - 4675 kg

10307.3-10308·41b

=~========--======-===============-~========--=~

-1014.3 lb 133.8 " 1102 .5 "

-460,0 kg 60,7 , 500 ,0 "

Removal of 2 MK 1030 ETC 501 carrier (8861) SC 500 bomb

4775,2

4. Fighter-bomber flying weight

~4775

==s=========_===== __ ======= __

kg

10529.3 - 10528.9 1b

~======d_==========

Installation of the BMW 801 TU engine increases the aircraft weight by about 35 kg (77.2 1b ) .

Stii/Bo

8.9.44

F~:

, •

I

Fod...·wut' Avlatioft Corporotio"

Range

8r.",."

a Endurance Calculations 4365 kg (9625 Ib)

--

Stgtus:

•

FIlI.lag.

"'"" 2x MG 1)1 2x NGroot.

151 each 475 rds. each 250 rds.

Armament Carrl.r Disposable load Fuellood

Engine sp.ed

TOP SECRET

640 Ltr (141 Gal)

•

Supercharger pr,ssure

500 kg

Outer wing.

2x MG 151

each 140 rd s .

(1102 1b)

Fuel consumption

oto

km

9

Po,.:

Takeoff weight, Disposable load' Fuel load,

Altitude

Fw 190A-8 Fighter

Aveloge

speed km/h

Flight distance

Flight endurance

km

h

0,)

984 2,0

6562 ),0

984)

5,0 16405

7,0 22967 Notes: j) Consumption from BMW specifications + 12.!i% reser"

2) "'rag. speed :: arithmetic overaq. of (Hltbound and inbound 'eq,

3) Endurance includes climb and descent tImes 4) Ranqe calculated wilhout deductions for lactical requirem.nt,! Ittc/udu climb and descent di,tanc ..

....;.;..----

Deduction. hOIf#! be.n made for warmup. taxi. takeoff, climb, descent, oversltoot and reserves

0.,. 23.12.43

CompMd by

Foch-Wuff

Fw 190A-8

Range a Endurance Calculations

Aviation Corporation

Fighter

8r.m."

4480 kg (9866 Ib) WR21 640 Ltr (141 Gal)

Takeoff weight, Disposable load' Fuel load'

Stqtus:

Fu••log.

Armament

2x MG 131

Dlsposoble lood Fuel load

WR21 500 kg

Supercharger

Engine .p.ld

km

(ft)

rpm

Ovter w'n,.

2x WR 21

each 475 rds. each 250 rds.

Carrier

AlHtud.

WIn,-root.

2x MG 151

TOP SECRET

pressure

(1102 1b)

Fu.1 consumption

(psi)

Amage

speed

Fli9h1

Flight

dittonCI

endurancI

km

h

km/h

0 ,3 984 2,0

6562 3,0 9843 5,0

16405

7,0 22967 Notes: IJ Consumption from BMW specificotions ...

2) Anroge speed = orithmetic ovl!!roge of

t2.5% reserve OtItbound ond inbound legs

3) Endurance includes climb and desce.n t times 4) Rang. colculated without deduction, for tactical requirement.!

Inc~des

climb and descent di,tortc ..

----

Deduetion' hOve beM mode 'or warmup, lold, takeoff, climb, descem, aVl!!rshoot and reserves

0."

23.12.43

Foch-Wulf

Range a Endurance Calculations

A'f'ia,jon

Corporotion Br• ..,.n

Stgtus:

Ovtt, win"

2x KG 1 31 2x MG 151 ea ch 475 r ds . each 250 r ds .

2x fiG 151

each 140 r ds .

Carrier

ETG 501

Disposable lood Fuellood

300 1 (66 , 2 gal ) drop tank 734 kg (1 618 l b)

Engine speed •

rpm

km

Win, root.

F"..IoV·

Armament

Supercharger

Fuel

pressure

consumption·

ota

Fighter

4683 kg (l0326Ib) TOP SEeR 300 Ltr (66.2 Gal) drop tank 940 Ltr (207 Gal)

Takeoff weight' Disposable load' Fuel/oad'

Altitude

Fw 190A-8

(ps;)

AI/ernge speed km/ h

Flighl

Flighl

,nduranc.

distanc.

h

km

1

0, 3 984 2, 0 6562 3, 0 9843

B80 616 2000

Bo 10

474 795

5, 0 16405

Notes: /} Consumption from BMW specifications + 12.!5 % reserve 2) iweroqe speed :: arithmetic overOllfl of outbound cnd inbound lev.

3) Endurance includes climb and descent times

4) Rongfl calculoted without deductions for tocticol ,equir,"'e"t.! Includes climb ond descent di.tOllc ••

Deductions hove been mode for wormup. lO1(i, takeoff, climb, descen" overshoot and reserves Dot,

23.12. 43

Compiled by

""",e,,,,,

=----

L " ~

Focke-Wvlf Aviation

Range

Corporation

8r,m'"

Fw 190A-8 F-B

a Endurance Calculations

Po,.'

4923 kg (10855 Ib) SC500 640 Ltr (141 Gal)

Takeoff weight, Disposable load' Fuel load,

•

TaP SECRET

•

•

/

12

( )

Io,.

2x MG 131

stg'us: Armament

2x HG 151 each 475 rds. each 250 rds.

Carrier

ETe 501

DIsposable load Fuel load

se 500 500 kg

Supercharger Altitude km

Engine sp.ed

(ft)

'pm ~o

0,3 984

2100 2000 2300 2100 2000

2,0 6562 3,0 9843 5,0 16405

I

WIIt9-roof.

Fu••

~

2100 2000 ~o

2100 2000

pressure

ala 1 20 1 10 1~

1,20 1 10 1,05 1,20 1 10 1 05 120 1 10 1 05

Out., wIn,.

2x HG 151

each 140 rds.

(1102 1b)

Fu.' consumption

/we·ooe speed

Flighl

Flight

.nduranc.

distanc.

(psi)

kg/h

(lb/h)

km/h

(mph)

h

km

170 1 1,,9 17,0 15,61 14,91 17,0 15 14 9 17,0

360 22 205 370 240 215 350 240 215 360

795 496 452 816

485 4 410 515 470 450 510 470 455 540

301 267 255 320 292 280 317 292 282 335 --1l1 295

1,20 1 91 2 10 1,21 1, 79

575 82> 860 590 815 870 610 805 860 630

A

~~ 1 215

529 474 772 529 474 795 ~

~o

474

475

2 ,00 1,28

1 78 1,96 1,29 1 1 94

~

8 75

(tml••)

357

~ 535 366 506 546 379 500 5'35 391 ..2).6 544

Notes: IJ Consumption from BMW specification... 12.5% reservtl 2J Aver091 spud = arithmetic averao, of outbound and inbound "0'

3) Endurance includes climb and descent times 4J Rang, co/culated without deduction. for tactical require"',nt,! Includes climb and descent dj,tone •• Deductions hove been made for warmllp. taXi, tolleoft, climb, descent, overshoot ond reserves

Dale

23.12.43

Compiled by ~

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ff.tJ~#

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