ASK 21 Instructions For Continued Airworthness

User Manual: ASK-21 Instructions for Continued Airworthness

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nsH 2t

Flight Manual

lnstructions For Continued
Airworth iness
Repair Manual

ALEXANDER SCHLEICHER SEGELF'LUGZEUGBAU

D-36163 Poppenhausen (L.lasserkuppe) Germany

---

Phone 06658

890

AIRWORTHINESS

SCHLEICHER ASK2I
fhis Manual is FAA approved for U.S. registered
gliders and is required by FAA Type Certiflcate
Data Sheet No. c 4? EU 1.10,83

Resistrationt I. A.Z.I.G. B
Factory Serial Number: 2.1..9. .3. .7 .
Owner:

l-.

German edltion of Instructions for Continued Air,,/orthlness are-approved under S12(1)2 Luft Gerpo

Publ

ished:

l{arch

1.983

Approval of translation has been done by best knowledge and Judgement. In any case the original text

ln Gerhan language ls authoritative.

ASK

21 Maintenance

Manual

(us-version)

Record of Revisions

Rev

Page (s)

No.

Affected

TN
10

2,3, 43,

TN
33

Juw

09.03.84

18.03.84

Juw

16.05.84

08.06.84

Juw

08.06.84

23.06.84

Juw

03.11.87

23.11.87

Juw

04.05.92

19.10.92

Juw

26.04.99

Juw

25.07.O3

19.09.03

01.06.10

23.08.10

2,41
45d, 45e, 45f
Ml (alternative rim for main
wheel)

lssue: March 9,
Revision:

03.01.84

45, 45a,45b, 60

TN
29

20.12.83

2, 58, 59

corre
ction

Ref. /
Signature

2.49

'15

Date of
lnsertion

TN
14

Date of
Revision

1983

Pase

Instructlons For Contlnucd Alnrorthlness
Lower chord
= ar17 m
Airfoi1 Wortmann FX 71-L-L50,/30.

SCHLEICHER ASK

3rB4 ft

4186 sqft

Rudder

33 % of vertical tail unit chord
)
Alcd
= 0,45 mChord (middle)
= 0,33 m

1'08 ft

Horizontal tail unit
Span

Area

Aspect ratio

= 3,1 m = 10116 ft
= a,92 m2 - 2o,64 sqft
= 5'05

Elevator

= 0,576m2 =
30r1 % of horizontal tail unit chord

Area

6t 19

sqft

Airbra\es
Schempp-Hirth type, on upper wing on1y.
2^
Area
= 0,35 m- - 3177 sqft
Span
= 1,35 m = 4.43 tl
Heigh t
= 0113 m = 0,43 ft
W

eiqhts

Max all up weight
Empty weight, app.

Weight of non lift
producing parts

= 600 daN
= 370 daN

= 1320 1bs
= 814 lbs

= 410 daN = 902 lbs
Max wj-ng loading
= 33t4 daNm2 = 6184 lbssqft
Max load of occupants, luggage, etc. :
see load table in the Flight Manual.

March

1983

Instructlons For Contlnucd Alraorthlncss
II.

SCHLEICHER ASK

DESCRIPTION OF AIRCRAFT AND COMPONENTS

Ai rcra

21 is a two-seater midwing with T-tail, airbrakes,
fi-xed shock absorbing main wheel and a nose whee1.
The structure is made in a highly developped fiberglass
technology. On certain crilical areas carbon fibers are
The

A,SK

ed.

Winq

Double T spar made of fiberglass roving flanges and fiberglass cloth webs. The skin consists of a 9mm Conticell
core with fiberglass on both sides.
Easy wing assembly by longue and fork connection, fixed
by two 356 bo1ts. Two shear bolts at the fuselage which
fi-t the bushings in the wing center rib, absorb the shear
loads to the fuselage. The rear shear bolts are secured
by an automatic safety device.
Fuse I aqe

The fuselage is designed as a honeycomb (tubus core) construction throughout which means considerable increase of
strength compared to non sandwich she1Is.
2-piece canopy, forward hinged in front and rearward hinged
in back; adjustable back rests.
Tai I pL ane

T-tail consisting of the same construction as the wing.
Control Surfaces
Sandwich construction wi-th Rohacell foam core.
IfI.
III.1

DESCR]P?ION OF

A/C

ASSEMBLY

EQUIPMENT

CONTROL SYSTEMS
Genera_L

Except for the rudder which is operated by cables
March

1983

InEtructlns For [ontinud Airyorthinrrs Schhicher ASK

E-

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(l,

vtc
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idg..-

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Ed
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L:=
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March

1983

EM.

page 48

BALANCE

Instructions For Contlnucd Alrrorthlnegs

SCIILEICHER ASK

Weight, empty weight C.G. and payload have to be certified by an inspector on page 48 of the Fllght Manual and
on page 38 of the InstructiorFFor Continued Airworthlness.

VI.3

INSTALLATION OF BALLAST

THE TAIL

It may be necessary to install ballast in the tail in
order to get the empty welght C.G. within the permlsslble
range.
1.

The amount of the lead ballast which is required ls

establlshed eit,her by calculation or by a weight and
balance procedure.
2. Sultable cast lead plates are aval.Iable with the
company Schlelcher.
3. Remove the rudder.
4. By use of a knife remove the tailskid very carefully.
Grind off glue residues and other impurities.
From below drill a hole of 8 mm (0r3 in) in diameter:
centrically to the lead plate. The long slde of the
lead plate must be placed next to the vertical tail
unlt spar so that the plate will not turn.
6. Shorten the M8 screws, screw them on and safety with
a selflocking nut. Awasher must be added on each
side.
7. Reglue the rubber skid with contact cement.
8. After the hardenlng smooth the tail.skid/fuselage gap
and tape it in order to prevent the peeling off or
catching of long grass.
9. Refit the rudder and safety duly with castellated nut
and cotter pi.n.

March

1983

Instructio*s For Continued Airuorihiness Schleicher ASK
Instafiotion

baltast

2't

in the toit

Wosher O9,t+ 125-1,5
locking

Screv

nut

I'18

lnstructions For Continued Ainvorthiness

VI.4 WEIGHTS

ASK 21

TAILHEAVY STATIC BALANCE OF

CONTROL SURFACES

After repairs or repaintings the weight of the control
surfaces and their tailheavy static balance must be
checked. For this job the control surfaces have to be
removed. For the determination of the tailheavy static
balance M = P " r the control surfaces must be seated
in the fulcrum with as little friction as possible. lf necessary, suspend them in their bearings with thread.
To measure P at the trailing edge it is best to use a
spring balance of 1 kg scale to which a small piece of
tape is attached. lf necessary, a letter balance will do,
too.
lf weights or tailheavy static balance moments are not
within the approved tolerances, you should contact the
company Schleicher.

Tolerances in weight and tailheavy static balance of
control surfaces and tolerances in play (backlash) of
control systems (controls fixed):

3.15-4.1/6,95-9,04

ailheavy static balanct Tolerance in play
(backlash)
tolerance
Deoree/mm/in
cm*ko / in*lbs
17 ,1 - 22.3 t 14.84 - 19.35
0.672"/3.88/0.15
1 3.9 - 18.4 / 12.06 - 15.96
a.g2 l 2.84 t0.11

2.85 -3,75 t6.28 - 8.27

17.4 - 22.91 15,10 - 19.87

Weight tolerance
kg / lbs
Rudder
Elevator
Aileron

1.75-2.59/3.86-5.71

March 9, 1983
Correction: 26.04.1999 / Juw

0.8M'/3.01/0.12

Instructions
Taitheavy

fur

Continued Airuorthiness Schteicher ASK

stotic batonce

meosurement

controts.

= P- r (&N.cm )

Oeterminotion

of P

by use of o spring klonce or a lefier bo[once .

Instructions For Continued Airworthiness Schteicher ASK

V:1.

CHECK I,ISTS

Ple

ltieht Ckt

1.
2.

lhi.rr

pbs

safetr.ed

Rear }firg attachmnt ptns:
the piD

eD$€ed

3. lkizsrtal tail udt
4. Elevator $shrod

the safety ioclr nisibie alove

pins safetied ? I3 the slEjng retamer

ccffrected ? Safetied T:itb a

smw dip

this is not aplicable fc Eliders fitdch us€ tbe autcoatic
el€vatc cwectien !

5. Ailerm pslrcds
Do

conn€cted ? Saretied ritb a slrim clip ?
mt forget tle sight csrtrol throt8h the ac!€ss hole

ccn€r

6. .lirba]re trlsirrds cqmected ? Saietied rith a sgj-w clip ?
Do rpt iorget the sidrt ourtroi tlrrcrrgh tb aacess hole
7.

ccroer !

drcck

for foreign objects

lt!€oql$ I
Ilitl alf. UIII&IEn qtd*rel€ase jairts G ulst be ahle to
t.rd tb brr !d!d by feeury ttu(r[h th slot jr tb hll
sntet. .lxt tb gQer f,lq[ffit d tb satetv l"* bf lllsh.
r.u it cn to dce !

Prc

lble trf fuI

1,
2.
3.
45.
6.
7.

Paractlute ccnmtei to harrless
Sale* harness fasteued ?

Ai*rales locked ?
nria neutral

llti"Eter

curr€ct1y set ?
C&cpies closed ard l6}ed
Eor

? Rear Cancpy I I
flidlts vith mly file occlsant rmve the rear

badr

rest I I
8. I€are yos tes l& tle pedal toe-straps I flelEri flatterr
tbe stres ! Htg€r of jamiry the p€dals :

1lHrlo.20 tlated october 15, i987

Instructions Por Contlnucd Alrrorthlncss
VIIl.

SCHLEICHER ASK

PER]ODICAL INSPECTJONS

fhe following maintenance checks have to be caried
out periodically, however, imperatively at the latest
annually :
1. Check the whole glider - outside and inside where
accessible - for cracks, holes, dents and brhite
spots in the fiberglass.
2. The attachment hinges and pins must be checked for
corrosion, tool marks and play. If the front shear
pins of the wing,/fuselage junctlon show too much
Iateral play due to ground loopings, thin metal
washers must be added on these pins. The spar plns
must show some play, otherwise the wings possibly
cannot be rlgged at a1l with different temperatures.
Besides here the bearing pressure is so low that
there is no danger of wearout.
On the other hand the rear pins of the wing/fuselage
junction require more attentlon. In the case of
play (backlash) at these pins they have to be replaced in time agalnst oversize pins. The play at
these pins always should be within the tolerances
H7

/ s6.

preventive nalntenance will increase eonslderably
the service life of all plns and fittings. Always
clean and relubricate the plns prior to every rigging. Do not misalign the pins t
Check aI1 metal parts for corroslon and, if necessary, repaint them. As primlng a zlnc-chromate prime
has to be used.
Make sure that there i.s no play in the wing/fuselage
attachment and in the tail unitlfuselage attachments
(see also above polnt 2).

Good

ljarch 9, 1983

Instructions For Continued Airuorthiness Schleicher ASK

I+5

Check tbat there is no play in the fuselage/ring aDd fuselage/tailplane connections (see also above Point 2.!.

The corditioD

The controls. iucluding the airbrakes, ilust be subjected to
aa op€rational test. and their control deflections nea-

of all accessible beari.ngs. fittings, joints,
stops in the control linlages, and especi.ally the control
cables anA tosing hook cables, nust be checkecl.
The plastic tubes inside the S-shaped rudder pedal tubes
nust be checled for proper and tight fit !
sured.

7. If any

coDtrol

is not

its entire range of
is to be established and e1i-

free-novinq over

novenent, then the cause
ninated.

8. Tbe condition of the nain landing Eear and tailskid (foam
skitl rith vear plate or pneunatic tailrheel respectivel.y)
incLudiDg tire, brake liniags, and rubber shock absorber
Bust be checked. See also that there is sufficient brate
fluid i-n the tark.
9. The toving hooks nust be inspected according to the nanufacturer's "operati.ons and maintenance instructions".
10.

11.

(pitot antl statie pressure ports)
the tusel.age, including their flexible lines, are to
checked for b}octages and leaks.

The pressure openingis

Condition and function

- if

on
be

app1i.cable. naxj.[um permissible

operational tine - of all instrunents, VBF-Iransceiver
unit, and other equipnent are to b€ checked :

ritrg bendiag frequency is to be neasured and conpared
trith the stated value in the latest inspection report. For
this test the fuselage $ust be ri.gidly supported oB tro supports, in oriler to obtaiD conparable values; for the position of the supDorts see the Survey Draring on page 29.

L2. Tbe

13. Check that the equipnent aDd iDstrunentation are in accordance rith the Equiphent Inventory (Section XIV, AP?ENDIX of

this nanual).

14. lfter repairs or alterations to the equipnent the ner enpty
reight and tbe C.G. positloD are to be found by calculation
or yeighing, and are to be recoraleal in a sunnary of
lleights.
Til-ilo.20 dated October 16,

1987

lnstructions

fur

Continued Airuorthiness Schleicher ASK 21

,+5 a

SecuriBg

Past experj.ence shoreii that the quick-release connectors in
the airbrale, aileron anal particularly in the el"evator coatrol 1i[kages were incorrectly asseu]Led or that their as-

senbly ras even cospletely forgotten (as of serial no.
21205 the arrcraft was then supplied rith an autonatic elevator connection). A sticler (fig.1) fixed to the fin and
the access hole cover, serve to renind the pilot of the cor-

rect assenbly. All quich-release connectors nust be secured
in addj.tiou by raeans of a spring clip (Fig.2), flitb the o1der type of connectors the check hole nust be drilled to approx. 1,2 nn g for this purpose.
Fig. I

Fig. ?

* Spri.ng clip no.50030?71 can be ordered fron Alexander
Schleicher or fron the coepany A.$trth, P,o.Box L26L, D-713,8
Kflnzelsau.

(?hi.s

part is also identical rith the foRD bralre securing

spring clip).

Tl{-!{o.20 dated October 16. 198?

lnstructions For Continued Airworthiness Schleicher ASK 21

2. Inspection
As experience accumulated in Australia has shown, the condition
of the L'HoTELLIER quick-release connectors must be checked on
every annual inspection of the aircraft, especially when it has
been operated freguently and from sandy airfields.
(o

must not exceed O.15 mm
inl; check this by using a wire

of the above diameter!

causrng

greatest

found

and

must

mm (0.O04 inl.

The tight seat ol
ed as loose ball
the thread

the
ends

the

smallest diameters B to
not differ by more than

ball ends inside the fittings must be checkare likely to break under bending loads in

area.

Gap generated by an unscrewed and
rectly refitted ball end or owing to
loading / wear out of the lever part.

incorover-

NOTE: The Technical Note "Technical Data No. 1M.10.01A, lssue
01i89", by the manufacturer L'HOTELLIER must be observedt

TN24 dated 04.O5.92 (Juw)

45b

lnstructions For Continued Airworthiness Schleicher ASK 21
lnspecting the taoino of the conilol surrace gaps

For aerodynamic reasons the control surface gaps between wing and
aileron and between stabilizer and elevator respectively are
taped where the control surface hinges are located.

Should this adhesive tape come off or be damaged, this may lead
Therefore the sealing adhesive tape must be inspected
in regular intervals and where necessary replaced.

to flutter!

lf the adhesive tape needs to be removed for maintenance, or repair purposes, or because of aging please observe the following:
as a replacement you must use onlv the Tesa tape no.46451, white,
25 or 38 mm wide, made by Beiersdorf AG, Hamburg.

Where other types

adhesive

have been repeatedly reported!

tape have been used, flutter

cases

Where a plastic fairing tape (elastic lipseal) has been fixed at
the control surface gaps, you have to observe MAINTENANCE INSTRUCTION C,

TN24 dated 04.05.92 (Juw)

45c

lnstructions For Continued Airworthiness

vilr.1

Schleicher ASK

45d

INSPECTION PROGRAM TO EXTEND SERVICE LIFE
lntroduction
Fatigue tests on GRP/CFRP wings and GRP/CFRP wing
spars have shown that a service life expectancy of at
least 18000 hours may be achieved for these components. However, as this test program did not examine an
entire aircraft made of CFRP and GRP, this service life of
18000 hours can be achieved only if the long-term airworthiness of each individual glider is demonstrated in a
special multi-stage inspection program (over and above
the mandatory annual C of A inspections).
Time Limits

1st Stage:
When the sailplane has reached a service life of 3000
and 6000 hours respectively, tests must be carried out in
accordance with the lnspection Program for the ASK 21,
lssue 2 dated 28.04.92, as laid down by Messrs. Schleicher.
lf the results of these tests are positive, or if any defects
discovered have been correctly repaired, the service life
of the sailplane will be increased after the 6000 hours-

inspection by 3000 hours, i.e. to a total of 9000 hours.

2nd Stage:
When a service life of 9000 flight hours has been
reached the above lnspection Program must be repeated. lf the results are again positive, or any defects
found have been correctly repaired, the service life may
be increased to a totalof 12000 flying hours.

Rev.Nr.
TN

/ Date

SiS.

Author

Date

25.07.03 Juw

Kaiser

March 83

lnstructions For Continued Ainrrrorthiness

Schleicher ASK

45e

3rd Stage:
Before reaching a service life of 12000 flight hours an
inspection in accordance with TN no.29 must be accomplished. Depending on the results of this inspection, as
well as on the history of the aircraft and the evidence of
the percentage of aerobatics being below 12.5 o/o as
compared to the totalflight time, Messrs. Schleicher will
decide on a release to service for up to 15000 hours.

The lnspection Program must then again be repeated
and on the condition that the results are again positive, or
any defects found have been correctly repaired, the aircraft may be approved for increase of service life up to
18000 hours.
It will be decided at a later date whether an extension of
service life beyond 18000 hours may become possible. A
research program which is intended to clear the preconditions of this aim, has already been started with the
BMVBW (Federal Ministry of Transport).

lnspection Proqram
Please contact SCHLEICHER in order to obtain the lnspection Program for the ASK 21, lssue 2
dated 28.04.92, or any later issue effective.

The inspections must be carried out only by the manufacturer, or by an appropriately licensed aircraft repairer.
The results of the inspections must be entered into the
lnspection Program which is at the same time the report
of findings, where each item must be annotated with a
comprehensive comment, as laid down.
lf the inspections were carried out by a licensed aircraft
repairer, a copy of the filled in lnspection Program (report
of findings) which must be signed by the inspector, must
be returned to SCHLEICHER for the purpose of evaluation.

Rev.Nr.
TN

/ Date

Sig.

25.07.03 Juw

Author
Kaiser

Date
March 83

lnstructions For Continued Airworthiness

Schleicher ASK

45f

On receipt and examination of such lnspection Program
Report SCHLEICHER will issue an "Acknowledgement of
Receipt" and send this back to the operator of the sailplane. Only on receipt of this "Acknowledgement" the inspector may certify the extension of the service life as
laid down in the lnspection Program, into the logbook and
the relevant sailplane's inspections papers.

The need for annual Certificate of Ainarorthiness inspections and overhauls (for German registered gliders $ 27
(1) LuftGerPO applies*' is not affected by this rule.
*)

Rev.Nr.
TN

/ Date

LuftGerPO = Aeronautical Products Examination Order

Sig.

25.07.03 Juw

Author
Kaiser

Date
March 83

fnstructlons For Contlnucd Alrvorthlness

SCHLEICHER ASK

l+6

Special Checks
After rouoh landinos :
Check the landing gear suspension mount at the front
maln bulkhead I
Check the wheel fork for deformation; gear box ll
Check the control shaft above the wheel for deformation!
Make sure that the rubber buffers have not come over
the support discs !
Check spar tongue and fork for whlte areas I
Check the wing connections at the fuseJ.age t
Check the cross tube at the front main bulkhead for compresslon deformations I
Determlne wing bending oscillation frequency and compare
the value with that of the last inspection report. In
case of dlfferences by more than 5 % contact the SchLeicher
factory. (See survey drawing on page
of the Instructions For Continued Airworthiness for jack up points).

After oround looos :
Inspect the fuselage tall cone at the transltlon to the
fin and also the attachment of the horizontal tai.l unlt
to the fin !
Check wlng connections at the fuselage t
lnspect horizontal shear web in the fuselage (between
front and rear main bulkhead) t

March

9, i983

Instructlons For Contlnued Airyorthlne8s
rx.

LUBRICA?]ON

SCHLEICHER ASK

SCHEME

Bearings : the slotted-sealed ball bearings are fi1led
with a longlasting grease and are capped off. So 1t ls
unnecessary to regrease thls bearing. The 14C6 self-aligning bearings in the pushrods and in the duraluminum rocker arms are also greased and covered with felt
seals so that they likewise do not need any regreasing
for a long period of time. The same applies to the ball
bearings of the pushrod guides.
The grease nipples at the controlstick and at the landing gear rocker arm should be lubricated at least annua11y.

The grease nipples of the control systems are accesslble
from the top when the seat cushions are removed. The
rear seat has to be removed in order to reach the grease

nipples of the landing gear rocker

arm.

?he canopy locks and especially the emergency Jettisoning device in the front cockpit have to be kept well lu-

bricated.

Dirty tow releases are cleaned best wlth compressed air,
brush and through movement of the kinematics. ?hen regrease them with a spray oll or some slmilar agent.

March

198:1

Inshuctions For Continued Airrrorthines Schleicher

LUBRICATION SCHEME

@ Cnoo and lubrirch lu rrery rigr4"
@ 0irort.mble ond tubricotr on onnuol inpclton.

Instructions For [ontinued Ainrorthiness Schleicher ASK

PLACARDS AND MARKINGS

1,
2.
3,
4,
5,
6,
7.
B,
g,
10.
11.

Data placard wlth welght & balance dataJ
one placard each for the front and rear seat on the

rlght cockplt wall.
Flre-proof type plate;
0n the risht at the spar tunnel bottom.
Piacard statlng the approved Alrworthlness Categoryr
on the front lnstrument panel ,
Max. baggage compartment loadlng;
one placard each left and rlsht on the rear cockplt
wail close t0 the baggage compartment openlng,
Placard on the rear lnstrument panel .
Placard for "Pre take off check";
0n the underslde of the front lnstrument panel cover so
that the placard is vistble when the canopy ls open.
Placard on left side of top of fln;
Note: Thls piacard is cancelled if your giider features
the automatic elevator c0nnectl0n.
Placard ln the access hole cover
Placard for tlre pressure nose wheel: 2,0 bar.
Placard for tlre pressure maln wheel; 2,7 bar.
Ai rspeed indlcator marklng .
G-meter marklng.

December

24,

1983

f N no.1'l

Instructions For [ontinued Airxorthiness Schleicher ASK

Setting of plocords

0ecember ?0.

1983

TN no

Instructions For Continued Airnorthiness Schleicher ASK

For talll.{heel option only

PLACARDS AND MARKINGS

1.
2,
3,
4,

Data piacard with weight & balance datar
one placard each for the front and rear seat on the

rlght cockplt |,lall.
FIre-proof type plate;
0n the right at the spar tunnel bottom,
Placard stating the approved Alrworthlness Category;
on the front lnstrument panel.

10.

l'lax, baggage compartment loadlngJ
one placard each left and rlsht on the rear cockplt
wall close to the baggage compartment 0pening.
Placard on the rear lnstrument panel.
Placard for "Pre take off check";
on the underslde of the front lnstrument panel cover so
that the placard ls vlslble when the canopy is open.
Placard on left slde of top of fin;
Note: Thls placard 1s cancelled lf your gllder features
the automatlc elevator connectlon,
Placard ln the access hole cover !
Placard for tlre pressure nose wheel t
2,0 bar,
Placard for tlre pressure main wheel: 2,7 bar,
Airspeed lndicator marking.

G-meter marking,

5,
6,
7,
8.
9,
.

12,

Placard

December

for ttre

20,

1983

pressure

tall wheel:

2,5 bar,

TN n0.11

Instructions For [ontinued Airworihiness Schteicher ASK

Setiing

December

plocords

20,

1983

TN n0.11

Instructkns For Continued Airvorthiness Schteicher ASK

Segelftugzeugbau A. &,hlekhcr

Modcl

*rp,l

DATA PI-ACARA

Aprond fu:

oir
oir
Itax. m@ruvcring spccd
tlox ocro lou specd
l,loxvinch lounch sp*d
thx. slrtd

lihx. spocd

@nlr,u so n

no.

lor

fZttEril-Ft
| 200 kn/hl
Vp Lte0 tl4la)

colm

rough

WEIaHT

AND

seat
Mox. poyload front seal
llax. pylood reor seot
Boggoge in vitryrots

l,lin pyload lronl

Takc

i; f lso ir/i1
iw 17fi kz7A
BALANCE

?ff

kg
mox. 2

xlo

kg
kg

(lteck

'
Cootrals cosy to qarotc
2. Airbokcs tocked ?
1.

h llto cenler psilion ?
l.furochutc orrd sdfety harness

3.him

fostaned

5.Altimeter odjusted to field
or to zero ?
6Rodio "ON"ond odjusted to
proper lrequency ?
7 Eoth canopics locked

heigh

Instructions For Continued Airuorthiness Schleicher ASK

Attentian

Energency fuitout !

Pull back both canopy sidr-/oclts and push
canopy upwords.

bl Undo sofety horncss.
c ) 6ot up and bail oul.
d) Wilh manuol chulc seize releose grip
pull out enlirely al ter | -3 sec.

and

A. Sc hleicher

6af Mnhqrsrn
Hodel

Srnal no.'
nagisttotion

ASK 2,
21 XXX

,lode in llrbst Gcrnany

For equipmcnt witlwut
g-mctcr ond bottom strap.

For quipment with

g-ileler ond battom strop.

Instructbns For Continued Airuorthiness Schleicher ASK

Airspeed indicqtor cotor codes
43-9? kts / 506reen orc

112

nph
97

- 151 kts / 112- 174 mph

Yellow arc

6round, mat-btack
Color odes and tetter
tuminous point.
0

-meter cotor codes
o) Positive range
Yelton

2
o

Negative range

orc frcm +

Instructions For Continued Airuorthiness Schteicher ASK

!, i!*i

Instructions For Contlnucd Allorthlness
XT.

SCHLEICHER ASK

REPATRS

principle repairs must only be made by the manufacturer or by a certified (licensed) technical aviation
facility.
For exceptions see repair manual. In case of doubt contact the manufacturer !

xIr.

MODIFICATTONS

Minor modification
A modification to the aircraft which has no influence
on its airworthiness and is feasable by using standard
working methods, may be done without prior notification
to the Civil Aviation Authority,if
it is done in accor' ri
dance with a technical note !ssued.rp $tu,e'tivil
Aviation

Authority.

-L...1,.'
--",
:

I
r

:f'
or modi f ication
A modification to the aircra{t--whi'ch-has .l-, inflr.n..
on 1ts airworthiness or requires a change of the operation instructions or of the operation limitations or is
not feasable by using standard working methods, must on1y be done by a certified (licensed) technical aviation
facility. The major modification must only be done in
accordance with technical documentations which were subject of a supplementary type-approval under the test regulations for aircraft.
A supplementary type-approval is not necessary, if the
major modification is restricted to only some single
units. Prior to the carrying out of the major modification
the proof of the airworthiness must be furnished in accordance with the test regulations for aircraft.
Ma i

March

L983

InstructLons For Contlnued Alrlrorthlnegs

XIII.

SCHLEICHER ASK

DESCRIPTION OF SYMBOLIC PLACARDS

Rudder pedals adjustment: grey

knob on RH slde of the console.

To adJust pedals backwards:
Take your feet off the pedals and pull pedals backwards;
then let go the grey knob and load the pedals in order

to lock

them.

To adjust pedals forwards:
Pu1l grey knob and push pedals forwards with your heels;
then let go the grey knob and load the pedals in order

to lock

them.

Airbrakes! blue lever in the LH
arm rest; pu1l to extend airbrakes.
G

Trim: noseheavy.

Trim: tailheavy.

L:a\

Tow

release: ye1Iow knob LH below

canopy frame.

OPEN

Hove

froat canopy;
rbite levers LH and R[

canopy frane backxards.

of front cedopy!
knob to the left
rith
red
fLat
Pusb lever
EMERGENCY

t{ay 29,1984

JETTISONING

no.

Inatructions For Contlnucd Alrworthiness

OPEN

rear

SCHLEICHER ASK

catropy

anVor

EMERGENCY

JATTISONING:

Hove rcd lcvsrs tH and RE oa caaopy

fraoe backrards.

Ventllatlon

Prior lo loke

off check

proper engogemenl

the
the

locks! torvord:{ocked

May 25''t984

this placard must be fitteC in
the front and rear cockpit in
fulL view of the pil-ot.

EN no.15

Instructions For [ontinued Airworthiness Schteicher ASK

XIV

IPPEI]DTX

XIV.1 Equipnent Liat

llinlouq couioacut
1. Alrapcod indicetor
kl^
r. Ylatcr cv 6005 50
p - ,5o
b. tuL Ps oE
)Ja k;a/h

2.
r.
b.
cr
,.

Altirtrr
Iltrt* 4 EX 6
Yiatcr { FGE 10
WL U-12 S
Sefoty hunctr
Gadrtagcr Bagu v-Br/1

Schusu IJ-C/V

Bonr I-B./V front
Bogu I-A./V rear

Additional ainiaun cqulpuaat for aerobatlca

G-actcr

BA ??A L

Addltional EiriEu! rquipocnt for cloud flyiE8 :
tura & bank lndicator Apparatebau Sauting YZ*4O2/
,1.

Colpaaa
-

LudolPh 9K 5

Luitol3b

w,
?7,L

Bs-1

*1r/KJ

circ r
Dlttrl $e 1r/25
Dittrl ?so 16/2,
Dtttcl fSG 40 S

VIIP- t rauac

r.
b.
c.
d.
..
f.

Brcl,cr

2@8/25

^R eOO9./e5
Bcel,qr AR
lviosic Dittrl AIR

Tt{-No.20 dated october 16, 198?

72O

lnstructions For Gontinued Airworthiness SCHLEICHER ASK

XIV APPENDIX

XlV.l

Equipment List

Minimum eouipment

1. Airspeed indicator

a. Winter GW 6005
b. PZL
PS 08
c. winter 6 FMS 4
d. Winter 6 FMS 421
e. Winter 6 FMS 5

Winter
Winter

50 to 350 km/h
50 to 350 km/tr
50 to 300 km/h
0 to 300 kmlh
50 to 300 kmlh
50 to 300 km/h
50 to 300 km/h

7 FMS 4
7 FMS 5

2. Altimeter
a. Winter 4 HM 6
b. Winter 4 FGH 10
W-12 s
b. PZL
d. Winter 4 FGH 20
3.
a.

Safety harness

Schroth

G-meter

BM470-2

d.
e.

G-meter
G-Meter

BJ 10 - 2

Gadringer

Bagu V-B/1
Schugu ll-CA/
Bogu l-Blr' vome
Bogu l-Aly' hinten

BM 770 L

G-Meter

510

GM510-2

Additional minimum equioment tor cloud flvinq
Turn & bank indicator Apparatebau Gauting WZ - 44431

Compass Ludolph
Ludolph
PZL
PZL

FK 5
FK 16
BS.1

B131KJ

VHF - transceiver

Dittel
Dittel
c. Dittel
d. Becker
e. Becker
f. Avionik Dittel
g. Dittel
a.
b.

FSG 15/25
FSG 16/25
FSG 40 S
AR 2008/25
AR 2009/25
ATR 720
FSG 71 M

March 9, 1983
Correction: 08.07.2003 / Juw

ASK 21
Maintenance lnstruction
Wheel-Rim Tost Penta, lssue

Blatt

1 vonl

Subject

Alternative rim for main wheel

Applicability:

ASK 21, TCDS EASA.A.221,
variants ASK 21 and ASK21Mi, all serial numbers

Reason:

The rim Tost Penta 125

Alexander Schleicher
GmbH & Co.
Segelflugzeugbau

D - 36163 Poppenhausen

- 1/i' can be installed instead of the rim specified in the

Maintenance Manual (Cleveland 40-788)

Action:

For every rim model there is an appropriate set ot space bushings, which are threaded onto

the axle on both sides of the wheel. Vvhenever the rim models are exchanged, the space
bushings have to be replaced, too. Furthermore, a tyre tube with short valve must be used.
The brake calliper retains unchanged.

Material:

For the Tost-rim:
Part no

Pcs

Denomination

210.21.0027

Space bushings for Tost Penta 12S1%'
(Left: I = 37; Right: I = 31)

210.21.0028

Clamp washerfor Tost Penta 125-17;'
Tyre tube with short valve

Part no

Pcs

210.21.0006
210.21.0007

Space ring f. main wheel (u35110 - 10)

Tyre tube with short valve

Clamp washer f. main wheel (O40110,1

210.21.0008

Notes:

Denomination

Space bushing leftf. main wheel (l = 29)
Space bushing right f. main wheel (l = 30)

210.21.OOO5

none

Poppenhausen, 01.06.10

Alexander Schleicher
GmbH & Co.

i.A

M-e;

(M. Greiner)

DOEIil{Srf IEA

l 10.01
Rev:B
No

EO8.A

.NSTRUGTIONS FOR THE MAINTENAI\ICE
L'HOTSLLIEH BALL AND ST,\TIVEL JOINTS

EI5:BORISI'S DU DOAN@|!!

nEv.

oI"E

OE.}E? DB

11/85

02le6

cteatl-otr of dorunerrt
Bspreacntatl.oa of 1 .rrivsl
Adruactioa of Rtg.l illd E.lE.2

01189

o? 192

0.3194

$e $ISE A

JOUR.

of functlon of c8147
UldrtitrE follor.irg DEI229-EH
IrpdattGg

EED.

aElx..

8EAP.

BE
BE
BE

lLrD
l{.tD

JI'B

t{Jb

ru8

llrD
XJD

LtsEE DES D8stltrt8f,rtts

B.E.

B.C

0.a. r.c

Q.C. C.B

0R. +1 EX.
1 BX.

TRODUGIlOt{

1 Ef,.

IruisL'HOTEI,LEBS.A.
93, acorre Chirles De Csullc.- 94170 BOIS COLOMBES
Tdl.(1X2.42. 13.94 T6hx. 61 r l53F IJIOTAIR TeEcopic (t)47.60'0?.0?

mtfGftL'B

fouaElh tElrl*r.iltr

1 EI(.

JI{B

Jr,t8
d

ne#.

DOCU}{EHT THA
lils : 1O. 01

cs{PoExlror uo

nrsrBggtrrgr{s ron r8E uellmB|escE

EO8-A

LrBOlggttJIEB BilLrr eI[D Sf$IEIJ ifo$fllt

EoemaEuE

PACE

rND.

Ptct

IIID.

FA@

INB,.

tIa

sox

PICE
2

I}ID.

?tcr

r$D,

sUHirrI!

1 - FrEIEtf,!fiE xf,D 6A!ig!r

2 - BE*IODICET

r{A$*IEEAI|CE frSAf,lrellONs

CTa1EX

:.T. FREE I'OIIEilEN:8 OT EEE EAiiL U*AO lrBE AOUBIilC
2,3. Elr.& SPIEBICXTf r'lEaSUBElsN:t {S.G fig. 2}
2.3. BII.&'IEERETD gEECf,
2.{. afitVllt q[SIritr CEEqf,
2.5" r{Eif,s[ilrl.ErlI Or 18! tacrES IollEB ?eEt Pro.rEq[rEf, lf,uEE
IFsEtI8ar oF Exr'S{IVEL oll El8 EHtiL (si. fig. l}
2.5. 6 T TE I,Iffi BEII{EEI DEJTVE RO' IITD 8TTl'EE.
2.?. $|r!rg, a58I .OPEneEIOtt CEECX

RED.

IrubUEOTELLIERE A.
93, evaruc ehedes Ds Grullc ' 92!7O BOIS COLOMBES
T6t.f lN2.4l. 13.94 Tdler 6Il l53F IJIOTAIE: fd&opic{l}4''69'07'$?
ffigL

lffl*.*Gl,

;8E

DAJE I (BlS4

PAGETSOM MD.:E

DOCTI!{E}I!' IUil
l{e ! 10. 01

rlr8rBuclroHs roB lEE uBIUTErrnNcE

LtEOTEIif,fER BA!Ir BHD AWMII ifOfNEA.

E08-A

tha rotrtio[ 6f thr trr'lvel iaoEad the ba!,l firat tre iiaap r*lth rs!i..tl,ng sticngh,
dqc to 6l,Br-6u!n !ric!ton8, Co,rrcqucnlly lt l. ltrartdetory t6 lubricits the
'reLv.l/brll rE y. Thls lulttficatloa
ioust bE alon€ rftBr cleaaing a,ad bef,or€
.r..Ebly, wLth a non col.d catgulating Ercrsa.
8E !

'-'

purto.e {general u6e} t
Spfly containing ollt ctraiched ]rlth Elllcon. (recomEndsd for
exlto*ed to.smd ar 6gher abreslv. Eaterlals,.
ESSO

Bs6€mb1l.si

ft lE mandrtory to eellfy, .ftBr eg6h ert€nblyr th€ correct locrEion of, thc.bal.l,
in the errlvel. lo do Eo, a locetlon hole l,r drilled Ln the lockca. t{hTn tbB
a€Eeilbtry l,s good, th6 hole fturt bG visible e,ld rnuBt a[eble to lnsaat tha pi.r -Er
r€f, &'E 140-31, or othEr d.vl-ceE, llnhed to the. locher only.

PERIODICTL CEECE

Durlng the anDual visit oJ' $g later than every 50O Slight hauss. it ir $e€6.rsery
to verJ,fy balla aad gl,iqrls as followa. !

2.1, reEr Mo r.E&! or GEs BlI.Ii r*to rEE roustlte
- Clreck that th€ bal}, ursvr f,6€ 6! frletlon lFlnt.
- Check th€ alr€uler d:lr]1.c@n!.
- Check that tlrare lg no crack" at tlre bage €f, tbc b81l
2.2. BBIIL s?EEfi,lstlt

HET!IaBEI{3!U!

(s.. fig. ,}

varlrt-i.on betw6a)l eeveral nr.e€u?e. of the ball dl,an€etr rrtlEt not
0,1 m.
tblE check aLE iB to detaet en alrnordsl'ball rycer.
Th€

2.3. BM.I, EBABD

€xeeed

CEECX

Eo th!6td darurE6 l"e acceptablc. Dt ritrg rer66embl,y ehE EEllar lruat b€
.FGrfEctly !6t on itc baEe. It la eand.toly to trtx thc ball ln p6siti('n wltb

an rdeqlratE loclLng devl,c€.

2.4.
N6

SWrEEr.

Vlflrl,r

eEECS

defornatlon or pennlag fn ball location or l,a the loc,riag doyico scat,ir

acceptable.

2.5. lrEtstR8$Em or rE rocxEe. Lol{EB ERtu[ t8otEcrlots er:ssf, agsElilBLt or lEl
A$MI. Ol( tE Eer& (sE! .tiE. 1)
thi. proj€ctlon Eust be hiqher tban 2 fttr.
the aj.tt ot thlE requirrment is to v€rlfy tbe efflciercy

of the eutonrstic

takB uI, claara$ce

Louis L'IIOTELLIER. S.A,
93, avenueClrartesDo Gaulh -92?70 BOIS COLOMBES
Tgl-(1112-"12. 13.94 T€le* 6l I 153F LIIOf,AIR Tdldeopic (Ila?.60.07.e7

fiorurErr

muEEr!

tflrf5g

RED. : BE
.FAGE r I

DAIE

r 0X/9,4

IHD. r E
*tnoblE $r{,{fii:BnE rrB

BOCIIHET{tr TIIJI

No:10.01

2..6. eEcE oF

IIIST'RUCTTO}Tq I,OB

TNE UAISAE}IANCE
SUXVEI) irort{ts8

EO8.A

[reor8r,LrER Bn!I, ]fiD
EEE

lIilE aEElEEr DBIVE aoD aND SrvIgEEr

In the ca6. o! aI} .dlr3tabls. swlval, r€rLfy th.t tlte }ink betweatr
B(ivsf and drlve, rod is ttght and Droperly Eecurid by 8a r'lequ4te
lecking dalIj.ee"
2.?, SffiVEr. ASav OFBEffrrOr

CEE(X

seat or IsskBr : no clan?log, diro to oxlidatiot sr otier reaton,
aeerptsble.

i.E

If aft6f the6e ve?ifis6tion3. ,one of the sboYs ahtsek i.{ oue of tolstanEG? it Ir
nrrldatory to r€plac6 both ball and suj:vsl'
ne+erlhelsss it ig. r6saosl6'nded Co t€9lace thlg 8ss€dlbllr every 10 yeara or av6ry
3OO0 fligbt hoqrs.
IMPORTf,ItrI

Any dsfection paru5 may be returned to Ets I.eult l'tfOIELLfER for letdmical

inve€tigat.ion.

rrc.1

FTG.

H-Bl
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ASK 21 Instructions For Continued Airworthness

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