SGS 1 26 N33917 A D S 2016 01 23

User Manual: SGS 1-26 N33917 A-D s 2016-01-23

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AD COMPLIANCE
Ar-^-^oI\,f-La {/-<

lVfndpl I-)*

No. Al

SerialNo.

€l
Date

Effective
Date

Subieet

ADNumber

To prevent the possibilitY of
The tow hook inadvertentlY
Slipping out of the relsase

87-02-01

oyzu87

To prevemt the possibilitY

Method of Complianee

sB sA-001 Drd. 10/03/86
Parts 38, 3C & Fig. 4

Eal00I{t

afin
87-17-01

Due At
< STows

08/19/88

217-9

scs 2-8 crG2)

R-200-9A or 1A-218-1A

R-200-12A or 1B-217-1A

L>2L7-9

scs 2-12 0C.3)

R-200-9Aor 1A-218-1A
orLB-221-3

LZB-L4L or 1B-217-1A

LD2L7.9

SGU1.19

R-200-9A or 1A-218-tA

R-200-12A otLB-ZL7-1A

tD2L7-9

R-200-12A or 1B-217-1A

LD2L7-9

R-200-9A or 1A-218-1A'

R-200-12A or 1B-217-1A

L>2L7-9

SGU2-22 (AIl Eodcts)
(C.G.I{ook)

R-200-9Aor 1A-218-1A
or !8-221-3

R-200-12A or 1B-217-1A

t>2fi-9

(Ali no&Is)

R-200-9A or 1A-218-1A
or 18-221-3

R-200-12A or 1B-217.1A

lD21:t-9

R-200-9A or 1A-218-1A
or 18-221€

R-200-12A or 1B-217-1A

LD|2L7-9

R-200-9A or 1A-218-1A
or 18-221-3

R-200-12A

1>2fi-9

1A-218-1Aor LB-ZZL-L

L>2D-7

L>222-L3

L*U.L

t>zzz-l

L>222-Lt

1o4i2A-1

tB-?J7-5

1D217-11

scs 2-32

18-221-1

L>?a-L-

t>222-tt

scs 2-33,2-33A,2-33AK

1A-218-1A or 18-221-3

1B-217-1A

LD2t7-9

scs 2-33,2-33A"2:33AK
(opc) (CG.Ilook)

LV232A-L

LB-2L7-5

1D-217-11

sGS 1-34,1-34R

1A-218-1A or 18-221-1

34017D1

3.1017D11

scs

1A-218-1A ot

!B-22t-L

t>2?2-7

t>222-t3

L0232A-l

LE.-2t7-5

1D,217-11

L0232A-t

tB-2L7-5

LD2L7-LL

ot LB-?2L-3

otLB-?2L-3

sGUl-20

R-200-9A or 1A-218-1A

otLB-22L-3
SGU1.21

orLB-22L-3

SGS 1-23
I

scs

1-24

sGS 1-26, A, B,

& C.G.IIook

scs

1-26

sGS 1-26 D & E (C.c. Ilook)
SGS

1-268(opr)

(C.G.Ilook)

1-35C

SGS 1-35C
SC'S 1-36

(opr)

1B-217-1A

$ERVICE BULLETIN SA.OO1.]I

pATE:
PAGE

fI January

4 of

1988

CAUTION

THE 10232A.1 TOf, HOOK IS PHYSICALLY SI{ALLER
THA}I THE OTHER TOT HOOKS. FIELO RETROFIT TO
THE 10232A-1 TOT HOOK REQUIRES IHSTALLATION OF
A IA-217-I1 RELEASE ARM AT A LOCATION FURTHER
FORHARO ON THE AIRCRAFT. BE SURE TO CONTACT
SAC FOR INSTALLATION INSTRUCTIOIIS BEFORE FIELD
RETROFITTING SAILPLANE TO INCORPORATE IO2'2A-I
Tof, H00K.

Replaee tor hook and/or release arm as requi,red to obta!,n an accaptable
comblnatron (as specl,fied ln Table l) for salJ.prane ln questlon.
NOTE

r Proper

engageoent of the tor hook lnto the
rel.ease arn 1s shorn tn F.l,gure l, vler A and
Figute 4. Excesslve rear of the tor hook
step eould result ln lmproper engagement.
F!,gure 2 of tnls bulletln provldes lnspeetlon data and reat limlts for the tor hook.
Tor hooks rhlch do not neet the speclfled
ll.nits nust elther be rerorked to obtaln
dlnensl,ons (as speclfled ln Flgure 2) or
replaced.
r If tor hook ls able to sllde lnto the release arn, beyond the tow hook step, as
shorn by Flgure I, Vler C, the rel,ease aro
must elther be rerorked wlth a slug as speeifled Ln Flgure 3, or replaced.

Inspect tor hook for rear ln accordance rith Figure Z oi tnts bulletln.
CAUTION

ALL AIRCRAFT REPAIRS ANO REHORK }IUST BE ACCOHPLISHED TITHIN THE GUIOELINES ESTABLISHEO BY
AC

d.
g.

4'J'.

rf tor hook dlmenslons are not rlthln rlmlts speclfled ln Flgure 2,
elther rerork the tor hook to obtaln dlmenslons (as speclfied ln Flgure
2], or replace lt ulth a ner or serviceable, used tow hook.
Engege tor hook into release e!m. Ensure that the tor hook lngages
properly as shown ln Flgure 1, VLew A.
rf tor hook ls unable to cornpletely engage (shorn by Flgure l, vler B),
shorten the rubber uumpet stop between the release knob and the instrument pancl to arrow the release asscmbly to close further.

".SERVICE BULLETIN 5A.OOI .37

DATE:
PAGE

3I January

1988

5 of I]

g.
h.
l.
J.
k.
t.

If tor hook ls able to travel too far lnboard as shoun ln F1gure I'
Yler C, dlsengage tor hook from release alm and neasure the length of
the release arn slot.
If dlmenslon ts less than 0.56 lneh, rework release arm by reldlng on
1B-2I7-19 slug at locatlon shown in Flgure 3. (Release alm nay be replaced as an alternate to weldlng on slug.)
If length of release arm slot ls greater than 0.55 lnch, replace release
arn.
Perform a thorough Lnspectlon of the tow hook lnstallatlon ln accotdance
rlth the I00 hour !.nspectlon requlrements listed ln Table 2 of thls
bul Ie t 1n.

Repalr of replace unservlceable component(s), as reguired.
wlth Part I of this Servlce Bulletln ln Alrcraft

Record compllance

Log

Book.

PART

II - DAITY INSPECTION OF TOII RELEASE ASSET{BLY.
PROCEOURE

'.I

i'.

t
NOTE

The folJ,oulng lnspectlon does not requl!e any
dlsassembly of the allc!aft or release assem-

bly. Horever, 1f any defects are noted durlng.
the lnspectlonl the problem(s) must be resolved prlor to next fllght.

Perform a thorough vlsual lnspectlon of the tor release assenbly and assoctated components-ln accosdance rlth the dally lnspectlon rcqulrements llstect In Table 2 of this bulfetln.
CAUT I ON

ALL AIRCRAFT REPAIR ANO REIORK }IUST 8E ACCOMPLISHEO IITHIN THE GUIOELINES SPECIFIEO IN AC

4r.

1..

lr.

If any defects ale noted, repair or replace faulty component(s) prlor to
next fllght.

SERVICE SULLETIN SA.OOI.]T

DATE:
PAGE

ll January

I988

5 of l3

TABLE 2

DAILY ANO lOO-HOUR INSPECTIOI{

0a11y

Vlsually lnspect release arm for damage,
cracks, deformatlon, and freedom of
moveoent on plvot bolt.

Vlsually and physlcally lnspect release
arm slot for excesslve rear whlch would
al,lor the tor hook to engage beyond the
hook step. (See Flgure I, Item C.)

Dlmenslona1ly measure the slot ln the
release arm to lnsure that lt 1s rl,thln
the toJ.erance as shorn on Flgure 3.

Vlsually lnspect tor hook for

danager

eracks, deformatlon, and freedom of
movenent on plvot bolt.

Vlsually check tou hook to lnsure that
surface nxi and 'y" of step as shorn
ln Flgure 2 ate fJ.at, smooth and properly
engages relsase arm.

glmenslonally check tor hook to lnsure
that aI1 dlnenslons a8e rlthln tolcra-nces
ln accordance rlth Flgure 2 and for
elongatlon of attach hole ln accordance
rlth Flgure 4.
Inspect release darnpet for general
condltlon and proper engagement of tor hook.
Perform an operatl,on check per Part

III.

Perforrn a release check for proper release
tenslon ln aecorrlance rlth Flguse 4.

Lubrlcate attach hardware for tor
and release atnr.

hook

Lubrlcate gulde-tubes 1n rel,ease control,
rlth dry stlck type lubrlcant.
Insure that tow hook moves freely on plvot bo1t.

100 Hour

'SERVICE SULLETIN 5A.(]O1 . fI

DATE: 31 January I988
PAGE

7 of l]

PART

III . PILOTIS

PREFLIGHT INSPECTION OF TOl{ RELEASE ASSEMBLY.
PROCEOURE
NOTE

r Flgure I shows plopes attachment of the tow
hook lnto the reLease arm. Note that the
step of the tow hook should seat agalnst the
release arm. The tow hook step must fully
engage the release arm to allow the release
assembly to functlon properly. The tor hook
must not be allowed to extend through the
release arm beyond the.step on the hook as
shovn ln Figure 1, Vlev C.
r The tor rope must not be aJ.lored to rrap
around the release arm or any part of the
sallpiane. It must extend, unobstructed,
dlrectly forrard from the sallplane to the
tor vehlcle.

..\

Attach tor llne to tow hook and apply tensl,on on the llne ln dlrectlon

of tor.
b. t{lth tenslon on tor llne, pull the release control on the lnstrument
. panel and check for proper release of tow llne.
c. If tou 11ne does not rel,ease properly, troubleshoot tov release assembly
9.

and perfo8o necessary repalrs.
Reattach tor Ilne to tou hook and check for posltlve retentlon of tor
llnc as foll,ors z
(I) Apply. a nodarate tug on the dor tlne 1n the dlrectlon of tor.
(2) Inspect the release sssembly to ensure that lt has remalned completcly closed.
(r) If the release assembly has opened, even partlally, gsound atrcraft
and troubleshoot release assenrbly. Repalr or replace faul,ty conponent(s) as requlred.

-''

SERVrcE BULLETTN sA-oo1.3r

DATE!
PAGE

ftr January

1988

8 of ll

PART

IY .

IOO HOUR INSPECTION OF IOTI RELEASE ASSE},IBLY.

PROCEDURE

Perforrn a thorough lnspectlon of tor release assembly ln aecordance
thc 100 hour lnspectlon requltements llsted ln Table 2.

rlth

CAUTION

ALL AIRCRAFT REPAIRS TIUST BE PERFORI{ED
ACCORDANCE UITH AC .,.1'.

b.
c.

ITI

If rlefects are notect, repair or replace faulty conPonent(s).
Record co-npliance rlth Part lY of thls Servlce Bulletln ln Alrcra?t
8ook.
TEIGHT ANO BALANCE DATA

llelght and Balancc not affeeted.

Log

SERVICE EULLETIN SA.OOI.'I

OATE:
PAGE

January I 988

9 of ll

HOOK FULLY ENGAGED

RELEASE
ARIll

TOW HOOK
STEP

TOW HOOK

VIEW A. PROPER ENGAGEMENT
HOOK NOT FULLY ENGAGED

TOW }iOOK STEP

TOW HOOK

LEASE ARM

VIEW B. IMPROPER ENGAGEMENT
NOTE:
IF TOW }IOOK IS ABLE

TO SLIDE.
THROUGH RELEASE ABm,
BEYOND THE TOW HOOK
STEP, THE RELEASE ARM
MUST EITHER BE FETYORKED
IN ACCORDAI{CE wlTTI
3, oR BEPLACEO.

TOW HOOK STEF

TOW HOOK
BELEASE ARM

VIEW C. IMPROPER ENGAGEMENT
FIGURE 1. ENGAGEMENT OF TOW HOOK INTO RELEASE ARM

SERVIC,€ BULLET I

DATE:'

PAGE IO

I'I

sA-001.

January I 988

of ll

TRAIGHT EDGE

(NOTES 1 AHD

A-A

0lt{cHEs

f^x.

ALLoWAB LE IRREGU I.ARITY

IN SURFACE'X'

TOW HOOKSTEP

(NOTE 8)
E

A (NOTES 2 AND 8)

SHOULDEB

NOTE 7
CORNEB WEAR
PERMISSIBLE
OTE

(NOTE s)

FIGUHE 2. TOW HOOK INSPECTTON AND BEWORK (SHEET 1 OF 2)

SERVICE SULLETIN 5A.(]O1.fr

'DATE:

.
,t

PAGE

f1 January t98B

ll of tl

NOTES:

TEAR OCCURS ON SURFACE iYT IT },IUST BE POLISHED FLAT IIITHIN TOLERANCES PROVIOED IN FIGURE 2 (SHEET 1). IF THE HooK cANNoT HEET
THESE REQUIREO DIHENSIONS IT I'IUST BE REPLACEO. UNOER NO CONOITIONS
SHOULD SURFACE TXi BE POLISHEO OR T,IACHINEO TO CHANGE ITS ANGLE.

OII.IENSION TAT ON

'Yi HUST REI,IAIN FLAT, SI,|OOTH, AND TITHIN TOLERANCES SHQHN
1. (SEE ILLUSTRATION. )
OIHENSION rcr ON 1O2l2A-1, HOOK SHALL BE 2.05 i.03 INCHES. DIttEt{sr0N 'Cr 0N 1A-2I8-1A' lB-221-tr lB-221-f, & R-200-9A SHALL BE r.0o
+.0f INCHES.
DIIIENSION r0. SHALL BE .Jl +.0f INCHES.

IO252A-I HOOK SHALL 8E .2I INCHES I,IIN. &, .28 INCHEs MAx. OrHENsr0N rAr 0N lA-218-tAr lB-221-1, la-zzL-r, & R-200-9A
HOOKS SHALL BE .25 INCHES MIN. & .]1 INCHES MAX.

SURFACE

ON SHEET

4.
).
6.

H00K IIUST REHAIN FLAT
SHOULOER OF HOOK.

iEAR 0ursr0E 0F THE

DII{ENSION'B'I{US;8E

FIGURE

.21 HrN.

FLAT AREA

INCHES FROx

PERltrsSrBLE.

EQUAL TO DII,IENSION rAr, OR LESS THAN OI}rENSION TAT BY NO HORE THAN.OI5 INCHES AND CANNOT 8E GREATER THAN
OII{ENSION.

9.
_

IN THIS AREA FOR A l,lIN.0F.2I

TAr.

ALL SURFACES EXCEPT SURFACE

rxr

HAY BE FILED TO OBTAIN REQUIREO

DII{ENSIoNS.

TOW HOOK INSPECTION AND REWORK (SHEET 2 OF 2)

T()Vr
crdD
NOTE: 18-217-19 SLUG IS AVAILABLE FHOM scHWEIZER AIRCRAFT coBP.
0.125 X 0.5 X 1.0 4130N STEEL

.35

I.O3

INCHES ON AIRCRAFT EOUIPPED WITH 10232A-1 TOW HOOK

.40 .+.o3 tNcHES ON ATRCRAFT EOUtppED WITH 1A-218-1A, 18-221-1,
18-221-3, OR R-2oo-gA TOW HOOKS

l-(r)
N\ram
,o@
-ituc
LT
Pfr
rraCm
O'{
FlH
l-l,
\OD
6l
@cl

cl
lr
a

\rr
+

1B-217-1s SLUG (WELD AS

SHOWNT

.og
.o9
IF THIS DIMENSION IS
.66 INCHES OR GREATER PRIOR TO
BEWORK THE RELEASE MAY NOT BE
REWORKEDAND MUST BE REPLAC

NOTE: ALL TOW RELEASE ARMS MUST BE REWORKED AS SHOWN
ABOVE OR REPLACED WITH THE PhOPER SUPERSEDING ARM
AS SPECIFIED IH TABLE 1.

FIGURE

3. REWORK OF RELEASE ARM

SERVICE BULLETiN 5A.OO5

DATE: I June
PAGE

} of

1987

L
SUBJECT: ONE-TIME lNSPECTION AND POSSIBLE
M6DELS AFFECTED:

REPLACEMENT OF TO}J RELEASE ARM

All 5chweizer manufactured and kit bullt Schwelzer gliders
and sailplane models Listed belo,w. All Serial numbers of
each model. Also affected are all sailpLanes retrofitted
wlth a Schweizer tow hsok installetion.

sGU
sGS

2-22, ?-22A, 2-22C, 2-22CK, 2-22E, 2-22EK
1-2t, L-zrA, L-21C, L-7rD, 1-218, L-23F, L-23G, l-21H,

scs

L-?1HL5
1-24

1-25, 1-25A, 7-258, l-26C, L-26O, l-26E

SGS 2-32
SGS 2.]]
SGS 2-l],

2-33A, 2-134K

1-]4,

1-34R
sGS
1-]5C
SGS
SGS 1-]5 ( 5prite

)

NOTE

In the text of this writing' the terms nGLIDERIT
and "SAILPLANEri are to be considered synonymous.
IME OF COMPL

Must be eonrpleted prior to the next auto or winch tow
of any sailplane equipped with the affected release

ANCE ;

arm.
2. Must be completed
3"

PREF ACE :

SGU 1.7
SGS 2-8 (TG.2)
SGS 2-]2 (TG.')
SGU 1.I9
SGU 1-20
SGU 1-2}

sGS

within 60 days on all sallplanes
equipped r*ith an affeeted release arm.
Affected release arms in spares inventory must not
installed on sailplanes and are to be returned to
Schxelzer Aircraft for warranty replacement.

Reports indicate the possibillty that the tou line eould fail to
release properly from Schweizer sallplanes equipped with a new tor
release arm part number 10217-11, 1D222-L5, 1O222-L7, or 34017-L3.
The posstbllity of this incident occuring greatly increases during
auta and wineh to,l operatlons or duri.ng an ove!run of the tow
]ine" This Bulletin requires replacement of the affected tow

release arms with a new

arm.

SERVICE EULLETIN SA.OO5

DATEr 1. June 1987
PAGE

2 gf

PBOCEOUftE

Inspect release arm for lug welded on front, belor tow hook slot as shorn
ln Flgure 1. Any affected release arm must be removed and replaced
rlthln the time of compllanee stated on thls Bulletln. Return affeeted
release arms to Schrelzer Alrcraft rlthin 90 days of the date of thls
notlce for free rarranty reBlacement. Contact Sehweizer $ailplane
Product Support Depat'tment for exehange informatlon. Arms received after
90 days wiIl not be given warranty consideratlon.

Upon rept.acement of release armr F€rform an operatlons check and maintaln
periodlc and plefllght inspectlons in aecordance with the procedures
outlined 1n Schwetzer Bulletln SA-081.2.

Racord Compllanee

ntth this Notlce in the aircraft log book.

. 5LRV IUE

DATE:
PAGE

.lULLtr

I June

} of

| lll

Jn-eu/

1987

ANY RELEASE ARM WITH THIS LUG WELDED ON FRONT
SURFACE AS SHOWN MUST BE REPLACED.

RELEASE ARMS WITH THIS LUG WELDED ON THE INSIDE AS SHOWN ARE NOT
AFFECTED BY THIS BULLETIN.

FIGURE

1. RELEASE

ARM

B
BULLETIN NO. 5A-OOi.2I

DATE: 19 May 1987
PAGE:

I of

x Supersedes Service

Bul

letin

No. SA-001.1, Dated 2 Feb

1987

PROPER ATTACHHENT OF TOtl LINE'
INSPECTION, I.IAINTENANCE PROCEDURES AND REHORK OF TOH HOOK, RELEASE

SUBJECT: SCHhIEIZER SAILPLANE TOH RELEASE'
ASSEMBIY AND RETEASE DAI4PER"
AFFECTED

AIRCRAFT: AI I Schweizer manufaetured and Kit bui lt Schweizer gl fders
and sai lplane models I isted below. Al I Serial numbers of
each model. Also affected are all sailplanes retrofitted
with a Schweizer tow hook instal lation.
SGU t-7
SGS 2-B (TG-z)

2*22A, Z-22C, 2*2ZCK, 2*228, 2-22EK

scs l-23,1-238, l-23C, l-230, l-23E, l:23F, l*23G, l-23H,
l*23H15
5G5 L-24
$G5 1-25, l*26A, t*268,
sGS 2-32
5G5 2:33, 2-334, 2*33AK
5G5 l*34,1*34R
5G5 r-35C
SGS

l-26C, I-26D, t-258

l-36 (Sprite)

NOTE

In the text of this writing, the terms

and "SAILPLANE" are
Synonymous.

(I ) *

Denotes

change.

T
I

scs 2-12 (TG-3)
SGU l-19
SGU t*20
SGU I_21
sGU 2-22,

be considered

"GLIDER"

BULLETIN NO. sA-001.2r
DATE:

19 Hay 1987

PAGE:

2oflZ
NOTE

It is absolutely necessary that alI pilots and
ground personnel reeeived proper training with
respect to the subjeet matter of this bul letin
prior to fl ight.

PREFACE: Reports indicate that a possibility exists that the sailplane tow
hook may inadvertently release during tow without any input by the

sailplane

pilot

on the tow release control.

This Service Bulletin I ists possible causes, precautions, rn6intenance
practiceso inspection and correetive action to be taken in order to
minimize this situation.
NOTE

An inedvertent release e&n oeeur due to various
eonditions such as improper hookups, towing
equipment fai lures, as wel I as irnproper mainten*
aRce practices. Aison the tow hook is of, the
overriding type sa that the tow Iine will release
if overrun due to pi lot error or unden eonditions
r.rhich could leave the tow line attaehed to the
sai trplane without the pf Iot's kmowledqe.
NOTE

As compl ianee with this br"rl letin could not
completely eliminate the possibiIity of an
inadvertent release due to pilot error, rope
breakn or abort of tow, any sailpiane operation
must be carried out so that there is sufficient
airfield avaiIable to acconmodate these not
uneofirrlon situat.ions. Aiso, proper pi lot
instrurtion in dealing with these situations is
an essential part of all pilot training
programs" In any event a premature release and
properly executed recovery Broeedure should in no
way result in damage to the aireraft or injury to
any of its occupants or ground personnel "

BULLETIN NO. SA-OOI.2I

DATE: 19 May 1987
PAGE: 3

tl0TE

Excessive tow release wear caR result during all
tow operatieins when the tow I ine is released
under ful I touring pressure. This should not be
done since proper piloting practice requires
easing off the tow I ine pressure before releasing.
CAUTION

AT RELEASE THE PILOT SHOULD }IOLD THE RELEASE KHOB
FOR 3 TO 5 SECONDS TO ALLOI{ ADEQUATE TI}IE FOR THE
TO}I LINE TO CLEAR THE SAILPLANE AND I{ATCH FOR
VISUAL CONFIRTIATTON OF TOI{ L1NE RELEASE.

TII.IE OF COI{PLIANCE:

Part l:

l{ust be completed prior to the

f,irst fl ight of the aircraft

each

dav

prior to every fl ight of the aircraft

Part 2:

Hust be completed

Part 3:

Hust be completed wr'thin 30 days of this notice or
100 hour inspeetion, whichever is first

Part 4:

Must be cornpleted

at the next

at every 100 hour inspection

PROCEOURES:

Part ll

Perform a daily visual inspection of the tow release assembly
and its components in accordance with Tabl e ? of this Service
Bul

letin.

}€TE

This inspection does not require disassembly of
the aircraft or release assembly. However, if a
component fails to pass the inspection as outI ined' the aircraft must be removed frorn service
and receive proper maintenance procedures to
correct the problem prior to fr.rrther f I ight of
the aircraft.

BULLETIN NO. SA.OOI.2r

DATE: 19 Hay 1987
PAGE: 4

Part 2:

A release check is to be made by the pi lot prior to takeoff. To
accomplish this have the ground personnel attach the tow Iine to
the tow hook and apply a I ight pul I on the i ine in the direction
of tow. The pi lot should then pul I thc release control to check
for proper release of the tow line. After reattachment of the
tow line to the saf lplane, a check should be rnade for positive
attachment of the teiw line to the sai lplane by applving a
npderate jerk on the tow i ine in the direetion of the tow. The
release assernbly should then be inspected to insure that it hras
rernained eompietely elosed. If the release is found to be
opened, even partially, inspeetion and rnaintenance procedures
must be perf,orrned to eorreet th* problem prior to eontinuing

with operation of the aireraft.
NOTE

Figure I shows the positions for the tow hook and
release arm when eorreetly hcloked-un. Note that
the step of the tow hook should be tight against
the release arm assembly" The tow hook step must
ful ly enqage the release arm to al Iow the release
assembly tn work properly. The tow hook must not
be allowed to extend through the release arrn
beyond the step on the hook since this ereates a
condition whieh defeats the design of the release
and inereases the possibility of an inadvertent
re I ease

FIOTE

The tow rope rnust not be al lowed to wnap around
the release arm or any part of the sailpiane" trt
must extend, unobstruetcd" direetly forward from
the sai lplane to the tow vehiele,

Part 3:

A. Several tow release arms and hooks have been manufactured
for use on Schweizen gl iders. Table I I ists the proper
hook/release combinations for eaeh model sai lplane. Each
aircraft must be inspected to insure that it is equipped
with the proper tow hook and release 6rm as indicated in
Table l.

BULLETIN NO. SA-OOI.2T

DATE: 19 May 1987
PAGE: 5

Hear of the tow hook step wi I I cause improper engagement of
the hook and release. The tow hook must be inspected in
accordance with Figure 2. Any tow hook which does not meet
the minimum specified dimensions, after inspection and/or
rework, as I isted in Figure 2 must be replaced.

NOTE

Tow hook must engage release arm in accordance
with Figure tA A Figure 4. If hook is able to
pass through release arm beyond step as shown in
Figure lC, release arm and/or hook must be
reworked with slug or replaced.
t{OTE

tow hook fails to engage completely as shown
in Figure tB, check release control rigging,

Shortening the rubber bumper stop between the
release knob and instrument panel will allow the
release assembly tcr close further.

C. All

tow release arms must be reworked in accordance with
Figure 3 or replaced with a new superseding Schweizer
release arm as listed in Table 1. If the release arm wear
exceeds the dimensions given in Figure 3, rework is NOT
al lowed and replacement

is MANDATORY,

Perform complete inspection
bul letin.

this

accordance

with ltem 4 of

NOTE

I repairs

AC43.

must be conducted in accordance with
I icensed mechanic.

l3 by an authorized,

NO:TE

or accelerated wear of the release
is evident a review and correction of
piloting practices and ground perssnnel tow line
attachment procedures is in order.
Part 4: Conduct inspection of tow release at 100 hour intervals in
accordance with Table 2 and Figure 4 of this bul letin.
excessive

mechanism

Record compliance with Part 3 and keep a copy of this Service Bulletin in
the Aircraft Log Book. tf'a flight manual or pilot's handbook is provided
with the aircraft, a eopy of this notice should be kept with that manual
until incorporated into the text.

BULLETIN NO. SA-OOI.2*

DATE: 19 Hay
PAGE: 6

1987

Aircraft Heisht

and Balance not affected.

The operational checks, rework and inspection procedures given in this
Bul letin comply with Feder:al Avietion Regulations and are FAA approved.
IrEtt
ArlcflrrI

s0u

t-7

T0l [00(

R-?00-9r

o. ll-?18-ll

5Till)rf,0

5UPmSt0

lI0/fl EPutfitfl(I

ttLtl$

Ptritst lni
t-?00-tzt or l0-?li-ll

t0-?lt-t

n-100-l2l or l[-217-lA

t0-2 r 7-9

128-lal or l8-?17-ll

r0-zl?-9

rnil

or lB-r2l-l
scs 2-8 (rG-?)

[-200-94

or ll-?18-ll

or l$-2el-!
l-200:lA or ll-?18-ll

s65 2-12 (rG-3)

or
sGU

lB-221-3

t-200-91 or ll-218-lt

t-19

B-200-l3r

or l0-?17-lt

l0-2t7-,

or l8-?ll-3
scu l-?0

n-100-91

or ll-218-ll
or l8-2ll-3

t-?00-l?l or l0-2li-lr

l0-?

56U

t-il

fl-e00-91

or ll-?18-ll
or l8-?ll-3

[-200-l2t or l8-217-ll

t0-?17-9

sGU

2-e2

(lll

.odels)

or ll-218-ll

[-200-l2l or

lt-2li-ll

l!-il?-9

l-200-tl or ll-218-lt

n-200-l2t or

lB-lll-lt

l0-2 t1-9

l-?00-91 or lt-?18-ll
or l8-??l-3

n-200-l2l or

l8-2ll-lt

lB-l

or ll-Zl8-ll

P-200-l2l or

li-2ll-ll

l0-2 r 7-9

R-?00-9t

or
S€S

l-?1

(lll

lodrlsl

or
scs l-?1

5G5

l-26,

l,0,

C.G. Hook

scs r-?6 0,

SGSl-250rt(tGtiool)
565

l-l6t

(opt.)

l7-r

li-l2l-l
18-221-3

R-200-91

ti-t

ll-221-3

ll-218-ll or l8-2Ul-l

t0-122-1

l0-222-13

lt-2? t - I

fi-222-l

t0-222-l r

102321-l

t8-zl7-5

lg-2 I 7-t I

t0-It2-l

r0-??2-t I

scs ?-12

s€s 2-!3, t-33r, 2-33il

ll-218.1[ or l8-UI-l

r8-2

8-22

i-lr

t0-2 I 7-9

SGS

?-!!, 2-33r, 2-3i*[ (oet,)

t0l3?r- I

tE-?17-5

t0-?

sGs

t-!r, r-3fi

U-210-lt sr l8-2el-l

310lI0-l

3{0t l0- I I

ll-2lE-tl or lE-??l-l

It-222-1

ilF?22-lt

t023zt-l

rB-2

s6s l-l5c
SGS

l-!sc (opt.)

sCS t-35

l0u 3?r-

i-t

0-2 t?-5

lI-t

l0-21?-r
t0-2

tI-l

CAUTION

INSTALLATION OF THE SHALL TOr{ H0S( #t0232A-1 AND APPROPRIATE RELEASE ARH
REQUIRES RELOCATION OF THE RELEASE ARH ON THE AIRCRAFT. CONTACT SCHI{EIZER
AIRCRAFT FOR THE INSTALLATION DRAI{ING REQUIRED FOR YOUR AIRCRAFT TO INSURE
PROPER INSTALLATION.

BULLETIN NO. SA-OOI.2r

DATE: 19 l|lay 1987
PAGEr 1

TABLE 2
DAILY AND IOO-HOUR INSPECTION

ly
X

Dai

Visual

Iy inspect release arm for damage,

cracks, deformation, and freedom of
npvement on pivot bolt.

Visually and physically inspect release

arm slot for excessive wear which would
al low the tow hook to engage beyond the
hook

step.

(See Figure

Dimensional Iy measure
release arm to insure

the tolerance as

Item C.)

the slot in the

that it is within

shor.rn

100 Hour

on Figure 3.

Visually inspect tow hook for damage,
cracks, deformation' and freedom of
rnovement on pivot bolt.

Iy check tow hook to insure that
surface "x" and "y" of step as shown
in Figure 2 are flat, smooth and properly

Visual

engages release arm.

Dimensional Iy check tow hook to insure
that al I dimensions are within tolerances
in accordance with Figure 2 and for
elongation of attach hole in accordance
with Figure 4.

Inspect releese damper for general
condition and proper engagement of tow hook

2,
check for proper release

Perform an operation check per Part

Ferform a release

tension in aecordance with
Lubricate attaeh hardware
and release arm.

X
X

Figure 4.

for tow hook

Lubricate suide-tubes in release
with dry stick type lubricant.

eontrol

Insure that tow hook rpves freely on pivot

bolt.

BULLETIN NO. 5A-OOI.2T

DATE: 19 t'lay
PAGE:

I of

1987

FIGURE

pRopER HOOK-UP WITHtHOOK FULLy ENGAGED

RELEASE ARM

TOW HOOK
STEP

TOW HOOK

A. CORRECT HOOK.UP
q-

INCORBECT HOOK-UP WITH HOOK NOT FULLY ENGAGED

TOW HOOK STEP
TOW HOOK

RELEASE ARM

B. INCORRECT HOOK-UP
IF TOW HOOK CAN D(TEND THROUGH THE TOW RELEASE ARM AS SHOWN,
RELEASE ARM AND POSSTBLY TOW HOOK MUST BE REPLACED.

TOW HOOKSTEP
TOW HOOK

RELEASE ARM

INCORRECT HOOK-UP

INCORRECT HOOK-UP I,VITH HooK EXTENDING
THROUGH THE RELEASE ARM BEYOND THE STEP

-nuulErtN

NO. SA-001.2*

DATE: 19 MaY l9B7
PAGE: 9

SU RFACE "X"

STRAIGHT EDGE

A-A

SU RFAEE "Y"

.O6 INCHES MAX.
ALLOWAB LE IRREGU LARITY
tN SU RFACE 'X"

(NOTE 3}

TO1JV

HOOK STEP

(HOTE S}

fiOTES 2 AND 8}

DETAI

f.ut

SHOULDER

MlN. FLAT AREA

t{oTE

CORNEH WEAR
PERMISSIBLE
OTE
D

(NOTE 5)

FIGURE

2. TOW HOOK INSPECTION AND REWORK (SHEET 1 OF 2)

BULLETIN NO. 5A-OOI.2*

DATE: 19 Hay t987
PAGE:

l0 of

1, Ir

*y"
I}.

IT IIUST BE POLISI{ED FLAT I{ITHIN TOLERANCES
HEAR 0CCURS ON SURFACE
(SHEET
IF TI.{E HOO( CAf{IIOT I{EET THESE REQIJIREB
PROVIDED IN FIGURE
DII{ENSIONS IT I,II.'5T BE REPIACED. UNDER }*O CONDITIONS SHOULD SURTACE "X" BE
POLISHEN OR }IACHIHED TO CHANGE ITS ANGLE.

2" Dll{Etlslot{'A'ON
DIHENSI0N

.35

3"
4"
5,
6.

1023?A-l H$OK St{ALl- BE .21 INCHES tllN. e "28 INCHES HAX.
"A" 0N tA-z18-1A, lB*2Zt*I, tB*zel-3, & R*A00-9A Hoott$ $HALL BE

INCFIES

t'IIN.

INEHE$ NAX.

NY" }IUST REHAIN FIAT, SHMTH, AI-IS HITHIN
SHEET I " {SEE ILLU5TRATION. }
SURFACE

DIHENSIOH

"C"

CIH

10232A-l

HOOK Sl.lALL

BE 2.06

TOLERANCES SHOI{N ON

t.03

INCHES" DII{ENSION "er

lA-el8-iA, tB-Zzt*l, tB*azt*3, & R-aOO*gA SHAi_L BE 3,00 +"03

DIF{Ei{SION

"E"

SHALL BE

HOOK I,IUST REI.IAIN

OF HOOK.
7

&.SI

I,,EAR OUTSIDE

.31 t.CI3

IHCHES.

FLAT IN THIS AREA FOR A HIH. OF

.2I

INCHE$ FROI,i

SHOI.JLDEE

0F THE ,21 t{lN, FLAT AREA IS PERHISSIBLE"

IIBII I.IUST BE EQUAL TO DII'IENSION *A", OR LESS THAN DIHENSIOI'I
NO I{ORE THAN .OI5 INCHES AND CANNOT BE GREATER THAN DII.{ENSION "A'I.

OII.iET.ISION

"A"

TO@
6)
-l

rrlmr-

NOTE: 18.217-19 SLUG IS AVAILABLE FROM SCHWEIZER AIRCRAFT CORP.
0.125 X 0.5 X t.O 4130N

-l

F-"3s r.03

TNCHES ON ATRCRAFT EOUIPPED W|TH

o=o
-t0)

I
i

.ro .+.og INcHEs oN AtRcRAFT EeutPPED wtrH IA-2'!B-iA, 'NB-221-i,
ty'z2t'l, oR R-2oo-sA Tow l'looKs

rl
I

t\)

\Ol
@o

z
a

10232A-1 TOW HOOK

fr
m

,____--+-,

1B-217-19 SLUG (WELD AS SI.IOWN)

.o9
.o9
IF THIS DIMENSION IS
"66 INCHES OH GREATER PRIOR TO
REWORK THE RELEASE MUST NOT BE
REWORKEDAND MUST BE REPLACED

NOTICE.".ALL TOW RELEASE ARMS MUST BE REWORKED AS SHOWN
ABOVE OR HEPLACED WITH THE PROPER SUPERSEDING
UNIT PER TABLE 1

FIGU

REWORK OF RELEASE ARt\4_

]ATE:

l-16y

PAGE:

$,fi

i:j"'-"H;$?*'^:""#-HI-1"J'1

iltm*t**m::m
SEALE

5TO20 LB"

READTNG

CAUTION

ff"X-ff'f"''i'-tl5iffi

wlTH A .25
ErncBaEI iiierrsE@P

Tneg-I

ry!

RELEASI

d--"#i#.;ip;trt,--.
TOW HOOK

Tow

lff

HOo

K-/"

$[?B
3:Jl.:?3t,I'l ?l':i"13

;$T1

if"*+ffiHlxllH:.
E

,F ro

Hoo K *

^l-il :t

lxi:ff "1ffJfi

y- I

FIGURE
RE.FE.R TCI

?f t?i *H;l

EAs E

A R$'}r

Schweizer Aircraft Corp
Post Office Box 147
Elmira, New York 14902

ACI 87- ot-ol
B

BULLTTIN NO. 5A-OOI.I*
DATE:

2 Feb 1987

PAGE:

lof12

Supersedes Service Bul letin
No. 5A*001, Dated Oct. 3, 1986
SUBJECT:

LPLANE T0l".l RELEASE , PR0PIR ATTACHMENT 0f' T0h'l L I NE ,
INSPECTION, T4AINTTNANCE PROCEDURES AND REWORK OF TO}I HOOK, RELEASE

SCHlllE I ZER 5A I

ASSEMBLY AND RELEASE DAHPTR.

AFFECTED

AIRCRAFT:

Schweizer manufactured and Kit buiit Schweizer gllders
and sailplane models listed below. All Serial numbers of
each model. Also affected are all sailplanes retrofitted
with a Schweizer tow hook installation.

AlI

SGU

I-7

5GU

2-2?, Z.-22A, 2-22C, 2-22CK, 2-22E, 2-278K
1-23, l-238, l-23C, 1-23D, l-23E, 1-23F, 1-23G, l-23H,

l-23H15
SGS I_24
SGS t-26, l-26A, 1-268,
SGS 2-32
sGS 2-33, 2-33A, 2-33AK
sGS l-34, l-34R
SGS 1_35C
SGS 1-36 (Sprite)

t-25C. 1-26D, t-26E

NOTE

In the text of this writing, the terms
and "SAiLPLANE" are
synonymous.

(l) -

Denotes

change.

T
I

sGS 2-8 (TG-Z)
SGS 2-12 (TG-3)
SGU l-19
sGU t-20
SGU I_2I
SGS

be considered

"GLIDER"

BULLETIN NO. SA-OOI.

DATE: 2 Feb
PAGE: 2

1987

lZ
NOTE

necessary that all pilots and
personnel
received proper training with
Eround
respect to the subiect matter of this bul letin
prior to fl iSht.

It is absolutelv

PREFACE I

that a possibi I ity exists that the sai lplane tow
hook may inadvertently release during tow without any input by the

Reports indicate

sailplane

pilot

on the tow release control.

This Service Bulletin lists possible causes, precautions, maintenance
practices, inspection and corrective action to be taken in order to
minimize this situation.
i{OTE

An inadvertent release can occur due to various
conditions such as improper hookups, towing
equipment fai luresr ES w€l I as improper maintenance practices. Also, the tow hook is of the
overriding type so that the tow line will release
if overrun due to pilot error or under conditions
which could leave the tow I ine attached to the
sai lplane without the pi lot's knowledge'
N0TE

As compliance with this bulletin could not
completely el iminate the possibi I ity of an
inadvertent release due to pilot error' rope
breakr or abort of tow, any sai lplane operation
must be carried out so that there is sufficient
airfield avai lable to acconrnodate these not

situations. Also, proper pilot
instruction in dealins with these situations is
an essential part of al I pi lot training
programs. In any event a premature release and
uncommon

properly executed recovery procedure should in no
way result in damage to the aircraft or injury to
any of its occupants or ground personnel.

'.'

BULLETINNO.SA-OO1.I*

DATE: 2 Feb
PAGE: 3

1987

IWTE

Excessive tow release wear can result during all
tow operations when the tow line is released
under ful I towing preseure. This should not be
done since proper piloting practice requires
easing off the tow I ine pressure before releasing.
CAUTION

AT RELEASE THE PILOT
FOR

SHOULD I.OLD THE RELEA$E KNOB
SECONOS TO ALLOH ADEqUATE TII.{E FOR THE

TOI{ LINE TO CLEAR THE SAILPLANE AND I{ATCH
VISUAL C0NFIRI'iATION 0F TOI'I LINE RELEASE.

FOR

TIME OF COHPLI,ANCE:

Part l:

Hust be completed

prior to the first flieht of the aircraft

each

day

2r
Part 3:

Hust be completed

Part 4;

Must be completed

Part

prior to every flight of the aircraft

f'lust be completed within 30 days of this notice
100 hour inspection, whichever is first

or at the

at every 100 hour inspection

PROCEDURES:

Part i:

Perform a daily visual inspection of the tow release assembly
its components in accordance with Table 2 of this Service

and
Bul

letin.

NOTE

This inspection does not require disassembly of
the aircraft or release assembly. However, if a
component fai ls to pass the inspection as outI ined, the aircraft must be removed from service
and receive proper rnaintenance procedures to
correct the problem prior to further fl ight of
the aircraft.

()

BULLETIN NO. SA-OOI.

DATE: Z Feb l9B7
P,AGE: 4

Part 2:

A release check is to be rnade by the pilot prior to takeoff. To
accomplish this have the ground personnel attach the tow line to
the tow hook and apply a light pull on the line in the direction
of tow. The pilot should then pull the release control to check
for proper release of the tow I ine. After reattachment of the
tow line to the sailplane, a check shouid be rnade for pasitive
attachment of the tow line to the sailplane by applying a
moderate jerk on the tow line in the direction of the tow. The
release assembly should then be inspected to insure that it has
remained completely closed. If the release is found to be
openedr €VBrl partially, inspection and maintenance proeedures
must be performed to correct the problem prior to continuing
with operation of the aircraft.
NOTE

Figure I shows the positions for the tow hook and
release arm when correctly hooked-up. Note that
the step of the tow hook should be tight against
the release arm assembly. The tow hook step must
fully engage the release arm to allow the release
assembly to work properly. The tow hook must not
be allowed to extend through the release arm
beyond the step on the hook since this creates a
condition which defeats the design of the release
and increases the possibility of an inadvertent
re I ease.
NOTE

The tow rope must not be al lowed to wrap around
the release arm or any part of the sailplane. It
must extend, unobstructed, directly forward from

the sailplane to the tow vehicle.

Part 3:

Several tow release arms and hooks have been manufactured
for use on Schweizer gl iders. Table I I ists the proper
hook/release combinations for each model sailplane. Each
aircraft must be inspected to insure that it is equipped
with the proper tow hook and release arm as indicated in
Table l.

BULLETIN NO. SA-OOi.

DATE: 2 Feb
PAGE: 5

1987

Wear of the tow hook step wi I 1 cause improper engagement of
the hook and release, The tow hook must be inspected in
accordance with Figure 2. Any tow hook which does not meet
the minimum specified dimensions, after inspection andlor

rework, as

listed in Figure 2 must be replaced.
NOTE

Tow hook must engage release arm in accordance
with Figure IA & Figure 4. If hook is able to

pass through release arm beyond step as shown in
Figure lC, release arm andlor hook must be
reworked with slug or replaced.
NOTE

tow hook fails to engage completely as shown
in Figure 18, check release control rigging,
Shortening the rubber bumper stop between the

release knob and instrument panel will allow the
release assembly to close further.

C. AlI

tow release arms must be reworked in accordance with
Figure 3 or replaced with a new superseding Schweizer
reiease arm as listed in Table l. If the release arm wear
exceeds the dimensions given in Figure 3, rework is NCIT
al lowed and replacement is i'IANDAT0RY.

Perform complete inspection
bul letin.

this

accordance

with ltem 4 of

NOTE

All repairs must be conducted in accordance with
AC43.

l3 by an authorized,

I icensed mechanic.

NOTE

or accelerated wear of the release
is evident a review and correction of

excessive

mechanism

piloting practices and ground personnel tow line
attachment procedures is in order.

Part

Conduct inspection of tow release at 100 hour intervals in
accordance with Table 2 and Figure 4 of this bul letin.

Record compliance with Part 3 and keep a copy of this Service Bulletin in
the Aircraft Log Book. If a fl ight manual or pi lot's handbook is provided
with the aircraft, a copy of this notice shouid be kept with that manual
until incorporated into the text.

BULLETIN NO. 5A-001.

DATE: 2 Feb
PAGE: 6

1987

Aircraft $leight and Ealance not affected'
The operational checks, rework and inspection procedures Elven in this
BuIIetin comply with Federal Aviation Regulatir:ns and ate FAA approved.

TAELE I

AIRCNIFT

SITIoARD
ARII

T()T tl00l(

RTIEA5E

SUPIRSE0 I tlc 1 Rt PLACEIIEIIT
RELEAST ARII

or l0-2lT-13

or lA-218-ll

R-200-l2A

or l8-217-lt

l0-217-9

2-8 (IG-z)

R-200-94 or lA-218-lA
or lB-221-3

R-200-l2A

or lB-2tl-lA

l0-2lt-9 or

l0-21?-13

2-r2

R-200-9A or lA-218-lA
or lB-221-3

l28-l{l or

lD-217-9

l0-21?-13

scu l-t9

R-200-9t or lA-218-lA
or l8:221-3

R-200-l2A

lB-211-lA

l0-217-9

l0-217-13

sGU t-20

R-200-9A or
or l8-221-3

n-200-l2t or l0-217-lrt

lD-217-9

l0-217-13

SGtl

I-?

5G5

sGs

R-200-94

sGlJ

l-2r

SGU

2-22

SG5 I

SGS

-23

{TG-3)

(ll! mdels)
(All

rodels)

t-2t

C.G.

sGs

lA-218-lt

Hook

t-25 D,

SGSI-250ti(CG}look)

lB-217-lr1

R-200-9A or tA-218-lA
lB-221-3

R-200-l2A

or lB-2li-lA

l0-217-9 or l0-217-13

R-200-94 or
or lB-221-3

ll-218-lt

R-200-l2A

l8-217-lA

l0-217-9

or lD-ll7-13

or tt-218-ll

R-200-l2l

l8-217-lr1

lD-217-9

scs l-26, A, g, c,

l0-221-3

R-200-9r

l0-217-13

IB-221-3

P-200-91 or
or l8-221-3

lt-218-lA

R-200-l2A

or l8-21?-lA

l0-217-9 or l0-2li-13

R-200-9A or
l8-221-3

lA-218-ll

R-200-l2A

or lB-217-ll

lD-217-9

l0-217-13

lA-218-lA or l0-221-l

t0-222-1

lD-222-13

l0-?22-17

rB-22r-l

n-222-l

lg-722-ll or

l0-222-15

sGS

l-Z5E (opt.l

102324- I

B-2 r 7-5

lB-217-ll or l0-217-15

SGS

2.32

I8-22t-I

t0-222-l

sGs

z-33, 2-331,

lA-218-lA or lB-221-3

lB-2ti-lA

SGS

2-33, 2-331, 2-3341( (opt.)

I 023

l8-2r7-5

ot 10-222-15
lD-217-9 or l0-217-B
lD-217-ll or l0-217-15

scs

l-3t,

lA-218-lA

lB-221-l

310 I 70- |

3r0 I 7D-r3

lA-218-lA

or l8-221-l

t0-222-1

l0-222-13

2-331t(

l-3tR

sGs t-35c
SGS

l-35C {opt.)

sGS t-36

2r-

B-2 I 7-5

02324- I

0232t- I

lB-2 l7-5

lD-ZZ?-ll

or l0-222-li

l0-217-ll or

l0-217-15

lD-211-ll or lD-217-15

CAUT ION

INSTALLATlON OF THE SMALL TOI.I HOOK IILO232A.L AND APPROPRIATE RELEASE ARM
REQUIRES RELOCATION OF THE RELEASE ARM ON THE AIRCRAFT. CONTACT.SCHIIElZER
AIRCRAFT FOR THE INSTALLATIOI.J DRAI{ING REQUIHED FOR YOUR AIRCRAFT TO INSURE
PROPER INSTALLATION.

BULLETIN NO. 5A_001. IX

DATE: 2 Feb
P,AGE: 7

1987

TABLE 2

DAILY AND lOO-HOUR INSPECTION
Dai

Visually inspect release arm for

100 Hour

damage'

cracks, deformation' and freedom of
npvement on pivot bolt.

Visually and Fhysically inspect release
arm slot for excessive wear which would
al low the tow hook to engage beyond the
hook step. (See Figure I' Item C.)
Dimensional ly measure the slot in the
release arm to insure that it is within
the toierance as shown on Figure 3.

inspect tow hook for damage,
and freedom of
deformation'
cracks,
p
t.
i
vot
bol
on
rnovennent
Visual

check tow hook to insure that
surface "x" and nyrr of step as shown
in Figure 2 are f lat, srnooth and properly
engages release arm.

Visual

Dimensional Iy check tow hook to insure
that al I dimensions are within tolerances
in accordance with Figure 2 and for
elongation of attach hole in accordance
with Figure 4.

Inspect release damper for general
condition and proper engagement of tot+ hook.
Perforrn an operation check

per Item 2.

a release check for proper release
tension in accordance with Figure 4.
Perform

Lubricate attach hardware for tow

hook

and release arm.

Lubricate guide-tubes in release control
with dry stick type lubricant.

BULLETIN NO. sA-001.1*

DATE: 2
PAGEr

Feb

I of

987

FIGURE

PROPER HOOK.UP WITH HOOK FULLY ENGAGED

RELEASE ARM

TOW HOOK
STEP

TOW HOOK

CORRECT HOOK-UP
1

INCORRECT HOOK-UP wlTH HOOK NOT FULLY ENGAGE

TOW HOOK STEP
TOW HOOK

RELEASE ARM

INCORRECT HOOK-UP

IF TOW HOOK CAN EXTEND THROUGH THE TOW RELEASE ARM AS SHOWN,
RELEASE ARM AND POSSIBLY TOW HOOK MUST BE REPLACED.

TOW HOOK STEP
TOW HOOK

RELEASE ARM

INCORRECT HOOK-UP

INCOHRECT HOOK-UP WITH HOOK EXTENOING
THROUGH THE RELEASE ANM BEYOND THE STEF

BULLET I N

N0. 5A-0CI1.1'

DATI:

Feb

PAGEr

1987

SU RFACE

'X'
STBAIGHT EDGE

A-A

SU RFACE 'Y"

(NOTE 3)

06 INCHES MAX.

ALI-OWAB LE IFR EGU LA RITY

TOW HOOK STEP

SU HFACE

A OIOTES

'X'

2 AXD 8)

DETAIL

c
(NOTE

f.0,

ltlN. FLAT AREA

SHOULDER

TE7
CORNER WEAR
PERMISS!BLE

FIGURE

2. TOW HOOK INSPECTION AND REWORK (SHEET 1 OF 2I

BULLETIN NO. SA-OOi.

DATE: 2 Feb
PAGE: 10

1987
12

NOT ES:

l. IF I{EAR oCCURS ON SURFACE .,y" IT HUST BE POLISHED FLAT I{ITHIN TOLERANCES I
I
PROVIDED IN FIGURE 2 (SHEET 1). IF THE HOOK CANNOT I.IEET THESE REQUIRED
UX"
DII{ENSIONS IT I.IUST BE REPLACED. UNDER NO CONDITIONS SHOULD SURFACE
POLISHED OR I'IACHINED TO CHANGE ITS ANGLE.

I'AI' OH IOESEA.I HOOK SHALL BE ,EI IHCHES HIN. &.28 INCHES I.IAX.
DI|{ENSIoN "A" 0N lA-218-lA, LB-??t-t, 18-221-3, & R-200-9A H00K5 SHALL BE
DII{ENSION

.?5

INCHES I.1IN.

SURFACE

SHEET

&.3I

INCHES },IAX.

"Y"

I{UST REI.IAIN FLAT, Si{OOTH, AND I{ITHIN
(sEE ILLUSTRATION.)

TOLERANCES SHOI{N ON

DIIIENSION "C" ON 10232A-l HOOK SHALL BE 2.06 1.03 INCHES. DIilENSION "C"
ON lA-218-lA, lB-221-1, lB-221-3, & R-200-9A SHALL BE 3.00 +.03 INCHES.

5.
5.

DIi{ENSIoN

"0"

SHALL BE

.31 1.03

I{EAR OUTSIDE OF THE

DII{ENSION
NO HORE

FIGURE

"8"

FLAT AREA

.21

INCHES FROH SHOULDER

IS PERHISSIBLE.

BE EQUAL TO DII{ENSION'AO, OR LESS THAN DII,IENSION
INCHES ANO CANNOT BE GREATER THAN DII.IENSION ''AX.

MUST

THAN.OI5

.21 }IIN.

INCHES.

HooK MUST REMAIN FLAT IN THIS AREA FOR A I.IIN. OF
OF HOOK.

"A"

TOW HOOK INSPECTION AND REWORK (SHEET 2 OF 2I

-o(:}w
c).{r
mmr
NOTE: 1B-217-19 SLUG IS AVAILABLE FROM SCFIWEIZER AIRCRAFT CORP.
0.125 X 0.5 X 1.0 4130N

-Yt

=Nlz
ooo
-ig

l--.SS c.OS INCHES ON AIRCRAFT EOUIPPED WITH tO232A-1 TOW l-tOOK
.40 }.03 INCHES ON AIBCRAFT EQUIPPED WITH 1A-218.1A,18-221-1,

rrl
--l

@t
-.l

18-221-3, OR R*200-9A TOW HOOKS

1B-217-19 SLUG (WELD AS SHOWN)

.o9
.o9
IF THIS DIMENSION IS
.66 INCHES OR GREATER PRIOR TO
REWORK THE RELEASE MUST NOT BE
REWORKEDAND MUST BE REPLACED

NOTICE...ALL TOW RELEASE ARMS MUST BE REWORKED AS SHOWN
ABOVE OR REPLACED WITH THE PROPER SUPERSEDING
UNIT PER TABLE 1

FIGU

RE 3

REWAHK OF RELEASE

Aru

BULLETIN NO. 5A-OOI.

DATE: 2 Feb
PAGE: 12

FIGU RE 4

1987
12

APPLY A 25 TO 30 LBS. PULL ON TOW BOPE
WHILE CONDUCTIHG RELEASE TENSION TEST

A 5 TO 20 POUND PULL
ON THE SCALE MUST RELEASE THE
TOW HOOK IF THIS CANNOT BE MET
MAINTENANCE OF THE TOW RELEASE
IS REOUIRED PHIOH TO FLIGHT

SCALE

5 TO 2O LB. READING

CAUTION

SCHWEIZER TOW RELEASES ARE DESIGNED TO OPERATE
WITH A .31 INCH DIA. TOW RING. CHECK WITH SCHWEIZER
AIRCRAFT ENGINEERING DEPARTMENT FOR WRITTEN APPROVAL
PRI)B TO yStNG ANY ATTACHMENT DEVTCE OTHER THAN THE
SPECIFIED .3I INCH DIA. TOW RING.

ELONGATION OF THE HOLE
IS NOT PERMITTED AND
}IOOK MUST BE REPLACED

MAX. HOLE DIA. .350

RELEASE ARM

HOOK STEP

TOW HOOK

CHECK TO INSURE THAT THE HOOK
CANNOT PASS THROUGH THE
RELEASE ARM BEYOND THE STEP
OI{ THE HOOK

ANY ROUGH EDGES MUST BE POLISHED SMOOTH
AND BLENDED WITH EXISTING CONTOUB

IF TOW HOOK CAN EXTEND THROUGH THE TOW RELEASE ARM, RELEASE ARM
AND POSSIBLY TOW HOOK MUST BE REPLACED.
REFER TO FIGURE

SERVICE BULLETIN SA.OO'

DATE: 25 March I987
PAGE

1 of

L
L

SUBJECT: AEROBATICS IN SCHI{EIZER SAILPLANE
MODELS ATFECTED:

MODELS L I STED BELO'd

seu 1-7

2.8 (TG?)
scs 2-12 (TC3)
SGS

Scu 1-19
SGU I-?O
SGU
SGU

1-2I

2-22, ?-?2A, 2-72C, 2-22CK, 2-22E, 2-22EK
scs 1-2r, 1-218, \-?3C, l-23D, L-23E, l-21F, 1-zt?,

l-23t1 ,

1-2rHI5
SGS 1-24

sGS

1-25, L-26A, I-?68, L-26C, L-26A, l-268

SGS

2.}2

SGS

sGS 2-1,,2-31A, ?-31AK
SGS I-14, I-34R
5G5 1-]5, l-]5A, r-f5C

-16 (Sprite )

NOTE

In the text of this writlng, the terms
and
REFERENCE:

'I SA

ILPLANEII are

HGLIDER"

to be considered synony(rous.

2-12 Flight-Erectlon-Maintenanee Manual
2-22 Flight-Erection-Malntenance Manual
2-r1 FIight-Erection-Maintenanee Manual
1-25 Flight-Ereetion-Maintenance Manual
1-!4 Fllght-Erection-Malntenance !4anua1
I-35 r'Spriter Pl1ot's Operating Manual

Page 1-10
Page 5
Pages l-5
Page 5
Pages 1-7
Page 21

SERVICE BULLETITI SA-OO3

0ATE: 25 t{arch I967
PAGE

2 of

NO-I,E

For the purposes of thls Service Bulletin,
areobatic fltght ineans an lntentlonal manueuver
involvlng an abrupt change in an alrcraftrs
sttltude, an abnormal attitude, or abnormal
acceleratlon, not necessary for normal flight.
(Refer to FAR 91.71 for further lnformatlon.)

PREFAcE:SchreizerA1rcraftCorporationthat
serobatlcs of any kind be performed in any of the Sehweizer sailplane models affected by thls Servlce Bulletin, desplte any language to the contrary ln any of the Fltght-Erection and l,lalntenanee
Manuals or Pilot's 0peratlng Manua] referenced helein.
Although there ls language ln the refereneed publlcatlons that varlous levels of aerobatlcs are permltted, Sehweizer Aircraft Corporation RECOMMENDS that N0 TYPE of aerobattcs be performed in these
model sallplanes slnee 1n doing so, the struetural deslgn levels of
the sallplane eouLd be exceeded, uhlch may result Ln serious personal lnJury to the occupants of the alrcraft.

only exception to this recommendatlon is spins when performed
rlthln the guldelines of, and as approved ln, the Fllght Manual or
PiIot's Operating Handbook for the aircraft being operated. Howeverr befsre performing splns in the aircraft, each pilot must recelve complete lnstructlons and tralning as to the proper execution
of thls rnaneuver, as well as the characteristics of the aircraft
durlng the spln and recovery therefrom.
The

Schweizer Aircraft Corp.
Post Office Box 147
Elmira, New York 14902

SERVICE LETTER 5L.OO1

DATE:
PAGE

1 June 1987

1 OF I

E
T0: All owners and operators of Schwelzer Sa1lp1anes.
SUBJECT: ANNUAL DISASSEMBLY OF
MODELS

AFFECTED:

All Model

SGS

AIRCRAFT

1-2],

SGS

L*26t

SGS

T
T

2-12, and sGS 1-,4

Schwelzer SailPlanes.

E
H

Reports indicate that failure to disassemble the sub.Ject sailplanes
perlodically (removal of wings and stab) eould result in corrosion
buildup on the attach flttings and hardware, making disassembly
For this
dlfficult o! even impossible without damage to the aircraft.
sailplanes
affected
the
that
reason, Schweizer Aircraft Corp" suggests
be disassembled at each 12-month calendar interval. After
disassembly, inspect the wing ancj stab attachment fittings and
trunnions f,sr eorroslon. Cleanup light corrosion with abrasive paper
and ripe surfaees with a elean, soft, lint-free c1oth. Apply light
grease to all attaching fittings and parts, Ensure that all attaching
parts are free of dirt, grit, and contamination, prior to reassembly.
Failure to eornply with thls servlce Letter could lead to a
difficult-to-disassernble condition.

AIRUTOATT{II{E$S PTRECTX\IH
U.SDeBrtrnent'

avraTl0fl cT*HoAnp6 HATtOa{&t nrLB OrncE

d}wrspcrffitrtr'
fsderd A*rkfir*t

P.&. EOX

26/lGO

o{tr}+of{A e;T-r, #{L*H{ni* y}!ag

ffi*rffim

11r follo*inp {i*st}"ire Oiretie im.d ia the FaSral Av&te* A&dr&r*ioo h eede s{dr d* pm*dor a{ fcdrC Avir{hn f.Sshdeq ft r ff, *pfr" * * .f*"fi
md'] oJ *ns+ @r lw.& indkrte m mv br_ tl* !c?i{*n d ffiffi. n&.rcrlerr Ohedrq *frrt e.iab; rJcay. ftay n qrrhr$ms
-$& b.-"dii*'sibtin* yo m
.s$ts*d lL&! m Fff*r rur ogsf,lr I Bircnat i4 *i** e &irmedilg Etirotiw ryfLr qs# l* mdrnei y*I 6x mdiire* "ff&
d SE Air{.d*c [frx*iw (Sift Ijl].

A!ftenelment 3q*551"2"
6?*02*0f SCHWHIZER AIECRAFT eQqp-.:
luding kib buiiL), all
uttii*u- t" m:A
serial numbers eertifieated in any category, and all modetrs
listed below:

SGU 1-7
SGS 2-8 (TG*z}
SGS 2-L2 (TG*3)

scu

1*19

SGU 1- 20
sGU t-21

'2-22, 2'22A'i 2'22C, 2*22CKt 2-228, 2-228K
sGS L-23, r-z:g, I:23C, L*23D1 1-238, L-23F,
1-23G r L-23H, 1-23Ht5
scs L-24
sGS l-26, 1*264 t L*268, L*26Cn I-26D' L-268
SGS 2*32
sGS 2*33 I 2*33h8 2*33AH
sGS I*34, l-*34R
5GS 1-35e
SGS 1-35 {sprite}
eompliance i= reEuired as indieated unlcss already
*ce0mp1 ished
To preveR*r the possih'iliLy af. the tow-hook inaorrertently
Lhe tow-1ine,
slipping CIut CIf Lhe release*arm and releasinEaceomPl
ish the
landing,
whic'h eould result in a foreeo
following:
IdiLh in Lhe next 5 t.ow release ae tuat ions af ter {-*he
{ai
effeetive date of this ADo perforrn bhe follewing:
Inspeet the ior**re}ease installation for proper
{I }
or
part numbers, exe essive wear, and E:oss-ibtre^, rework
3C
and
in
38,
3A,
ParL
rep:.ae€ment of parts in aeeordance wiLh
I986"
3,
Oetober
dated
Se[rweizer Servl6e Bulletin No. SA-0S1,
per f orrn the CIEleraL ional e heck in ae e ordane e wit.h
(Z)
j-:'g
Schureizer Serviee BulleLin No" SA*0CI1, dated
Figure 4
L-rctober 3, 1986
100 hours
{b} Thereafter, &L intervals noL to exeeedand
3e, and
Part.38,
in
sLeps
Linre*ir"r-serviec, aeeomptrish the
dabed
SA*001,
No.
Eul"leLin
Fig'*re 4 in Sehweizer Service
tlctober 3, 1946"
Upon reque-et- u an equ:"valent means 6f compliance with bhe
requir*ments of, |his AD rnay be epprslveC by ti:e Manager, New
Y*:rlk Aire raf t e er{:if icaLton fif'f ie e, Aire raf t e erLif ie ation
Ei.rris:i-r:n, Federal- AviaLi,rn- AdrninisLraLion, I'lew England Regiont
i&1 Sout-h Franklin F.venue ' Room 2A2, r/al-1ey Stream, New York
11581, Telephorie ( 516 ) 79L* 6680
sGU

87-02-01 2
Upor:submissionofsubstanbj"atinqdababyan0wnerCIr
the Manager ' t{eEr
OperaEor t.hrough an -FAA maintenanes inspeeLor,
york Aircraft tertification Offiee, may adjust the c*mpliane*
Lime specified in this AD'
daLed oetobef 3'
schweizer serviee Bulletin t{o. sA-00}f
is
ibed ln ttiis doeument,
1985, ident ified and d"*.r
5
U'S'C'
to
part
hereof
Pursuane
i;;";poraEed herein and made a by this direeti"ve
who have not
552(a){r). Aii-p*r*uo= affected manufaeturer may obtain
eopies
received Ehis ds-cumer,e from the eorp.r P.o. Box L47o Elmira,
upon request to schweizer Aireraft
739-382L" This document a]so
N;; yorfi 14902, Tetephone (60?)
Lhe Regional Counsel, Federal
;;t be examined at the offiee of
England Regionr-- Jz *New England
Aviation Admini.strationo NewMassachuseLts
01803t Rules Docket
ExeeutiVe Park, BurlingLon,
-gtt
n' between the hours sf I :00 a 'm ' and
Number B5-ANE-;6 r- noom
holidays.
4:30 p.m" l{onday through Friday, exe ept Federal"
2!, 1987'
January
on
effEcfive
This amendment becomes
FOR FI'RTHER INFORMATTON CONT.ACT:

Office, Aireraft
C. Kal1is, New York Aireraft CertificaLion Avenue,
Roorn 292?
Franklin
SouEh
Certification Division, 181
(516)
79L-6428"
Telephone
Vattey Srream, N;; York 11581,

O-IL

EELARTTETjr OF- IffiI{SE ORTArtffi

F+deraf

gFP.

A+1 aEf

orr Adnfn

fstrarfon

Parr 39

[Docket No. 86-ANE-46;

Amendment

?9-S5lZ

Alrworthlness Directlve6; Schweizer Alrcraft Corp. Model
Sffl Sertes GLiders

A6IICY: Federal Aviation Adninistrarion (fAA),

SGS and

DOT.

ACTION: F{nal rule.
s-taffiaRY: This amendment .adopts a new alrworthiness

whieh nequ-ires eertai.n sehr.'eizer
l"nseaLl-acions i"nstatri"ed on
lnspeet.ed

direetlve

(AD)

Aircraft corp. torr-release

gltder blodels sGS and sGJ series to

aseert.aln t.hat the proper reLease arm has been uated

tiie tcn:hook

on the

measureBenEs

for

lrlth

aireraft. lnspeet.ion wilL inelude wear linuit

deteria-{nlng

repaired or replaeed wlth

if the hook and/or the release-ar6

Rew superseding

parts. This

can be

needed to

prevent the posslbility of an inadvertent top-hook release during

towing operatlons, resulting ln a forced landlng.
DATES:

Effective

January 21, i9g7.

compliance sehedule

As prescribed

rncorporat.ion by Referenee

in the

body

of the AD.

Approved by the Di.reetor

the

FEDEP"AL REGISTEB. on

ADDRISSES: The technical

and

lnfornation (Service Bulletin ],io.

uodiflcation part s spec{fied in this

AD may be

SA-001)

obtalned from

sehseizer Alrcraft corp., P. 0. Box 147, ELfl'lr€r Neu York

.Ll+9A2,

Teiephone (60i) 73}4AZL" A eopy of the technltial note ,.s coitalned ln

the Rules Doeket No" 86-ANE*46, 0fftce of
Avlatton Adainlstrstlon,

New

tfre=

Re81onal'eormael, Pederal

England Regi.on, 12 tleu England Exeeuti"ve

Park, trurltngton, Massaehusctte

01E03'

FOR FURTi{ER INFOR}IATION COI'ITACT:

e. KaI11e, New York Alreraft certlf,leatlsn offtce, atreraft
Certiftcatlon Divlelon,
Stream,

New

1.81 South

Frenklln Avenue,

Room

202, Valley

York 11"581, Telephone (516) 79L'6{428'

SUPPLEI,IENTARY

INFORIIATI0Ii: Reports have been receivcd

that

the

schwelzer R-200, 1A-218, Lb-221, and 10232A-1 totrhoeks r'rsed
schweLzer

Alrcraft corp.

Models sGU and $GS serLee

gltders

esn

lnadvertently release the eable durlng tCIwing v{thout any lnput t0
release ha*dle by the glider pilot. Sehweizer Aireraft florp" has

ghe

issued Servtrce Bgllerf.n No" SA-0010 dated Oetober 3, 1986, whi*h calls
for inspeetion of the tow*release Lnstallatlonsn md p*ssible r*pai':: or
replaeement r{'lt.h nery parts. PremaEure release

of th* eable whiLe

of ttrese gliders e€y result Ln a foreed landing. The FA'A"
has examined the available lnfsrmation related to the lssuaqee of ehe
.above servLce bulLetin and has determined that the eoadition addressed
t,owi"ng sne

by Schweizerts bulletin is m unsafe condit,ion tl1at may exlsE on the

abovetypecertifieatedgliders"Thereforeresisbeingissuedlo
requireinspectlortandposclblerepairorreplaeementofthe
tor-release installaeion P&rts'
-2*

$g*ee

rltf,*

s 6ttue6l*m cxl.6t6 Ehet requtree the

regri"r-).a*1cn, trr.

jLr*;r;'*rri*:abjte,

6rud

lmmedlate adopt*on of

1s detcredried thet nette* and publ,te proeedure &re

g*cci exuae exlsEe f,os usktng

*ff,seri.ve i"ir less than 30 daYs-

anendment

eONeLUStrON: The FAA tras determlned

eeergeney regulatlon Ehat

ttrls

that thls regulaEton 1s an

ls not eonstdered to be raaJor turder

Exeeut.lve

Order L229L" trt ls lmpraettreable for the ageney ts fotrlou the
proeedures

of Ordcr

12291

-be lssued lmqediately

rdfh respcct to thtrs rule since the rule

to eorreet an unsafe eondltlon 1n alrcraft.

hae beezl further deEermlned

regulatton tmder

DOT

nuct

that thls aetion {nvolvcs an cElcrgcney

Regulatory PolleiEs andjProeedures (44 fR 11034;

Felrruary 26, L9?9)" trf thls aeEion 1s subscquently determlned to
trnvolve a slgniflcant/najor regulatien, a flnal regulatory evaluatlon

or analysls, as approprlate, r.rLl] be prepared and placed ln the
regulatory docket (otherwise, an evaluation or analysls Ls not
required)" A copy of lt,

when

flledn

person ldentifled r:nder the eapLlon

may

*FOR

be obtalned by contacting the

FURT1IER INFORI'IATION

CONTACT".

LLst of, Subjeets in 14 CFR Part 39:

Alr Transportation, Aireraft, Avlation Safety, sld Incorporation
by Reference.
ADOPTIO}i OF T:{E

A}1E1{D}TE]'IT

Aecordingly, pursrrant to the authority delegated to me, the
Federat Aviation Adrnj.ntrstration (fAA) amends Part 39 of the Federatr

Aviation Regulatlons (FAR) as follovs:

-3-

, Thc auchclriry e 5"t g,E j-gn f or FarL 39 conLinues

E'q:

read

follqrws:

Ar,r.rirorlry: 49 u"g"e. 1354(a), t&21, ffid t&23;49 tT"S.C. te5(c;]
(Revtsed Pu'n " L. gv*t+49, January x-2, 1983)l end I.4 fFR ti.&s"
Z.

E3r

adding eo

See

t{on 39,13 thc fc,J-howing Reid

direerlve (AD):

.*4*

a-j

rr'dor*"trlneps

---.\'\___\-

TELEX NO. g324sg
AIRCRAFT CORP.

P. O. SOX

t47 -

ELi,ltRA, N. r.

July 27,

t49o2 - (6ot) 739-382t
1984

Mr.

Dave Wilke
Powe1l Aviation

jvianfield Airport
Manfield, IvlA'. 02048
Dear Mr. Wilke:
nF

As per our telecon of last week about the 1-26E lvlodel aircraft
which the MIT Soaring Club or^n:s, we recoilrnend using the next size bolt
and hardware in the attachment of the rear spar plate to the machjned
rear spar fitting to renove the play at the T.E. of the wing.

This would imrolve increasing the bolt from an ANS to an AN6. The
bolt also should be brought up to .373 - .375 for the 268415-1 fitting,
268439-L friction plate and the 268416-1 fitting. A new Alt{5 bolt and
a 7/32 wal1 bushing rnade from 4150N heat-treated to 125,000 psi can be
used in lieu of the oversize bolt but from a cost point of view, it does

not usually

hope

make sense.

this

data

will

solve your problem.

Silcerely yours,
SGIIIEIZER AIRCMFT CORP.

/rs

{-dnnu,{L

Leslie E. ScJrweizer
Vice Pres - Engineering
ern

cc:

John Braun

"AT THE SOAN/NC CAPITAL OF AIAERICA"

.{
Schweizer .A.ircraft Corporatlon
P. 0. Box 147
Elmira, llew York 14902

December

SETTVICE

]'8,

L9?5

BIILIET]}{ NO. 102-26-8

SU&IECT: Inspeciion, of Control Stick Pivot BoIt
MODM,S

AtrT"ECTffi:

SGS 1*25D

G BSC

smIAI No"'s AFFECTED: (o ltooel) 4oo tirru 48r
{m'l{odal)
TII'{E

Otr'

COivFLIANCE;

has been determined

insta]-].ed on some

stick-yoke

fhe

SGS

wel.dment

}/ithin

5,0'g te;qp &i+e

fiours Flight Time

that an j:rcoruect length bolt

1-26D and E Mode1s

has been

at the attachmeni of the control-

to the aileron control- torque tube.

corcegt. bo1t, as specified. on drawings,

Iq$PffiIf(N:

'-5;f"t

AN6-21.

ships having the (optional) aft floorboard

and

stick

boot, it will be necessary to renove tlr-is.

Scale-neasure the length

of the bo1.t installed. If the length of

the bo1t, from beneath the head to the end, is 2.20

is required, other than a logbook eniry of
2.

further action

compliarlcg.

Should the

bolt be shorter than the 2.2O length -

Remove

the bolt.

Reinsta1l the yoke on the torque tube using arl AN5-21 bolt

Q"za 1ong, with 1-9/l-5 grip) using (a)

gNgSo-616 wastiers under

the nut a:rd safeiy. Replace stick boot, as applicable.

Check

the side-play at the top of the control stick.

If t/gtt or less, the installation i.s satisfactory"
If greater than L/8", contact

Schweizer

Aircrafi Corp. for

of repair.
SC$rlEfZqB AIfiCeAIT COBP.

.\-

method

SCIf'J/EIZEB AIF.CRA FT CGEi
I. O. Eox L4?
I42frz
Eimi.ra, i'Iew I-ork

Februar.y 11, 197L

SflElr'ICE SULLE?I$ h1C. 1.02*25-?
L'?ODELS

/tFFECTES:

ter.

I.{r,,ts 28} tirru 399 whic}r have Sweptbaci: irertical Taii Sui:face q
SGS 1-2eD, Cer, l.jo,ts 400 tirru 4?5
SCS 2-33 a;:* 2-33A. Ser. lio.'s l" thru 196
,V/A
SGS 1-?SB and

SUEJECT: Eudder Hi_qqe,_l-crvj_r,

5tlachrygr:_i_ to.

iin SI*I

G8S(

/-x6 tr

A report from the fieid has been rece i.red indicating failure af both Ai"{3-?A bolts
attachi:ig the iower rudder hirge io the fin spar. Tiris repori rvas from one aircrait
odi'"
Cne bolt only, of the t'*o wi,ich failed, rvas fourrd and, undar a 50X rnagniiicaticn.
an aFparent
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