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 ISerialNo.

ADNumber Subieet

Effective

Date Due At Method of Complianee

Date of

Corunliance

Time at

Comnliance

Due at.

87-02-01 To prevent the possibilitY of

The tow hook inadvertentlY

Slipping out of the relsase

afin

oyzu87 < STows

Eal00I{t

sB sA-001 Drd. 10/03/86

Parts 38, 3C & Fig. 4,n/r#r f f o, s r/t?0,66

87-17-01 To prevemt the possibilitY of

The tow releasE assemblY

meating a jammed condition

Durins towine

08/19/88 <Next

Flight

Check for proper orm Per

sB-sA-005.1 Dtd. 01/3 1/88

Operational oheck Per Fig. 4r/t:/rr ffp, [ 6

tsl"tfn

fl- DL'01 i&,*,*'*'{- I v Y

/8*6;^*i^,*n*) M ntuL{q

tl -t'7 *ol $l**,c,,,*'*r{ 0. or(

{n fS*^ ,t Fr ?o "-V'?

r z/*fit

8 F -t'L -cr {..,^l f/ee,C /"-,t'1{' *

e€'e+ A 7't ,r'n

/uJP+*-t uv4

[aD 6.,*r,t*,,i " P

AF t?t,*Uo, ilf a,f ,, l,a o i{!'& 1i.rc s,P

ff/-oN, rol fcry doo'lt t^'S'F' /oollR- t,+lf * Q6Eyn *,rd

Af, tr";"r-vA

orhr/a tlrltpF.Y1 ll Dd, H{

*'7-u2^-ot

*7 -t1 'or

fv*t 1y'a*16

E+L<saa

t*re*fiO6t"^^E q*,0

/y'rtet u4 el

rel f/r /d y: \1 tll'/,\")

€l

SCHWE]ZER AIRCRAFT CORP.

ELMIR.AT EW YORK 3,1+9A?_

Form No. L-l+598

Dec. ft 972,

Rev" 5/ ,i; i Rev" TlT6

FAA AD NOIES: MFTIR'S SERVICE BULIETTI{S-E/IJIrru I\uIriD: IvLuUtt'U D-HI(vlUl5 IJULL!;'1II'IU I{ev. 121-tA n^a, /, l-la

auo lirnvr pr,arrs, R;;.' 7ii: i;;: drid

ftEX: 1i167 Rev. stB6

MODEL

FAA AD NOTES

NUMBER I SUBJECT

MIGR'S SERVICE BULIETIN I\,IF[I'S

IffiRSERVICE I,ETTER REV'

}II]MBER ST]BJECT

SGU 2-22

-24 u 2-22C

K, E9 EK

none

76-t3-

I1 fnternal

Rust

LO2-22-LOO

LO2-22-LOL

102'33-].

Hanrlling/wind cLamage to

short aileron push,,rod.

Internal Rust, (S/w's 98-2:B)

Fuse frame

[lL-102-3 Fire potential - fabric

cover aircraft

SGS I.

thru G

sGS 1-23

H and Hll

none

7L-t7

rud"d"e

rl Worn fin &

Li.nge

ro2-23 -r

l-i)z-23-2

Jamming of spoiler controls

Worn fin/rudd.er hinges

[:iL-102-7 Vertical surface flutter

SGS I.26,

& Model A

thru C

none Lt)z-26-L

LO2-26-2

L02-26-3

Loz-26-t+

L02-26-5

High release-operating loacl I

Failure in stamped. wheel flg

El-ev. cable routing at fin s

Seat back disengagement I

Failure, torque tube brgrs I

supp't I

I SL-lO2-3

F,:

Fire potential - fabric

cover

SGS

t-26D

L.263

Dt-26D,

none

L02-26-6

LOz-26-7

LDz-26-B

Mislocated rudder fairlead,

(S/N's 404 thru 409)

Iiwrr rudder hinge, swept

tail-

Stick-attach bolt should be

AN5-21 sL-102-14 Seat ajust vs. C.G. aft llmi

scs 2-32 none none si],-Io2-B Oversize main wing pins

I q:Jl 2

SCLII.^iEIZER AfRCRAFT CORP.

ErivrrRA, Mld RK L\9O2 Form No. f-hl98

Dec. ( L972

Rev. )t 6 ; nev. 7f7(

Rev. L2/76 Rev. 4/78

IIAA AD NOTES: MFtiR'S SERVICE BULIETINS

aNojirnvri LlrBrarvss Rev.

Rev.

],ETIERS

Rev. BlTB

Rev. 9l86

9177

t7177

1178

LO2-26-7

102-33-1

L02-33*2

toz-33-4

76-I3-

7 -23-7

Internal rust,

fuselage frame.

Attach Bolts,

I'in Spar

Lw'r rud.d.er hinge, swept

tail

Internal rust, Fuselage

frame (S/w's 1 thru 2OO)

Attach Bolts, Fin Spar

(S/N 1 Thru 507)

Removable Ballast Inst1.

sL-to2-1

sL-to2-2

sL-102-3

sr-ro2-h

sL-ro2-9

il,-102-L2

sL-102-13

sL-102-15

sL-102-16

sL- 102- tr" 7

sL-102-18

sl,-102-5

sL-102-6

rAA AD NOT$S

SUBJECT

MFGR'S SERVICE BULLETIN

none

NOTFI: The above information is valid. as of

MFCIR's SERVICE

scs 2-33,

A, AK

SGS l-31+, R

sGS r-3'

SGS 1_35A

SGS 1-35C

1-36

2-37

SGS

SUBJECT

Water in pitot-static syst.

Possible tow ring foul

Fire potentj-al-fabrt'e cover

Conversion to SGS 2-33A

Rel. control - Instrum. Pan

hline-S t ru E At Eachment

AilEron Security at Tie-dow

Sprlng Assy-Ratchet Lock Tr

Fuse. Fabric Separatlon

Aileron Bellcrank Corrosion

Tow Rel-ease Slot - Cracks

Retrofit - d.ive brake

control

Retrofit - trim control

FIap Flutter, S

2-35

Guard for canopy latch,

SlNrs 1-69

sL-102-I0

sL-102-1-1

none

2of2

(Da be )

*.@

\.-- PUBLICATIOI.I TNDE,X

FOR

SCHWEIZER

SAILPLANES

REVISION 1- TO PUBLICATION INDEX

NO. SSP.I.I ISSUED 1- JUNE 1988

INSERT APPLICABLE PAGE(s) INTO

PUBLICATION INDEX

SCITWETZER AIRCRA F'T CORP.

P.O. Box 147

Elmira, New York L4902

Publication No. SSP-I-1 ISSUED: 01June 1988

REVISED:01March 1989

SAILPLANE SERVICE BULLETIN INDEX

Number Subject Date S(iU

1-7 S(iU

2-8 SGU

2-L2

SGU

L-19

SGU

L-20

SGU

L.2L

SGS

2-22 li(is

t-23 S(iS

t-24 SGS

t-26 SGS

2-32

SGS

2-33

SGS

L-34

SGS

1-35

SGS

t-36

sA-004

sA-005.1

sA-006

Inspection of Elevator Pushrod 16 Jun 1987

Identification and Possible Replacement 31 Jan 1988

of Tow Release Arm

Installation of Seat Adjustment Bracket 01 Feb 1989

xx x xxxxxx

'ta

1\ x x xX

Index-3

Schweizer Aircraft Corp.

Post Office Box 147

Elmira, New York 14902

Bulletin No.5A-006

Date: 1 l,larch 1989

Page I of I

NOMEIELATUBE

Bracket

Spacer

Rivet

"lr)

PARTS LISTS

PART NO.

26245D-3

26245D-5

t1s26426AD4

PROCMURE

SUBJET: Replacanent of Seat Back Adjustrnent Bracket

I'IODELS AIEEC'IED: AII SGS L-26D and SGS I-26E

TIME OF COMPLIANCE: Sha11 be acconplished witfrin next 100 Hours of otrnration,

or within.I2 months of issue date of ttris bulletin

rfuichever occurs first.

PREFACE: Reports indicate that on the affected aircraft, the pilot's seat back

could inadvertently slide back during tow, when experiencing

turbulence or during certain flight attitudes where a negative g

condition may exist.

A neb, bracket, (PN26245D-3), and spacer | (^126245D-5), has been

designed to resolve this problen. This service bulletin lists

instructlons to install this improved seat back adjustrnent bracket.

This improved bracket should reduce the possibility of sudden seat

back movernent.

il l8?

QUANITY

Drill out rivets securing existing seat adjustment brackets. Rgnove brackets.

CLean up bracket mor:nt area removing any burrs and sharp edges.

Paint bracket mount areas with a ttrin coat of Zinc Chrcrnate or equivalent

prinuar to prevent corrosion.

Place the sprcer beficeen ttre inside fuselage wall and the lorarer edge of

bracket.

Mark tlre mount area and drill holes as per old bracket using a #36 drill

bit and secure wittr Cleco.

Install rivets (MS26425AD4) (5) places on each bracket ard spacer kit.

Paint exterior of rivet heads.

Record ccnrpliance wittr ttris servic-e bulletin in ttre aircraft log book.

SEAT ADJUSTN'ENT BRACKET

., .. i.-

NEtfU DESIGT.I 26245D-3 BRACKET

OLD DESIGN 26350D BRACKET

U.SDcportrn€nt

dTrmspefiotiffr

F*derdAYhtlom

&ffilrtastlan

EXRW&KTE{EF{ESS PXRECTXI'E

AVIATIOH ST&T.dOARO5 HATION&L FIELE OFFICE

P.0. EOX 26460

OKLAHOMA CITY, OKLAHOMA 73i25

eautioned thai EG PercE ruv oIEEatL an aircrafi to siieb an Airuorlhiae Diretiva appiieq ex*gi ir mundo*e vith ilx reguirereele of tl* furseril:inw Dimtive (FA.n 3$.31,

87*1?*01 qPill{EJ-FE8- .4IEC&&ET_--qqEE! Amendrnent. 3e*s 97 3 " Frnei

eopy of prre {ssued AugusL 18, LQET. &pplies e'.r

model-s {inelud.ing kit. bi"ri}e} gGU X*7 s SCS :-8 t?G*!ii e SGS :*i-}

(TG*3); SGU 1-1"98 SGTJ 1-AGF SGii 1*21"r SGU 2*?,2, 2*22&, e*22e ,

2*22eK,2*22F,.,2*22E.K; SSS L*23, l-*238u 3--'23f' 1-23D, t-238,

1-23F, 1*23G, 1-23H, L*23Hl5, SGS 1*?4; SGS l"*?6, 1*264, 1*258'

1*25e , 1-26D" l"*268r SGS 2*32; SGS 2*33 , 2*33F", ?*33AK;

SGS 1*34n L:34Rp SGS 1*35e; SGS 1*36 {SrnITE} gl"iders,

ecrtifieated in any eategsry.

eornpJ-ianee is required' prior L* tlge ns:ib fri"grhB aft-er tkre

ef fcefive dafe CIf this AE, unless &}ready aecCImplictied,

TCI ilrevene bhe possibiiity CIf th-e tci*; releace essenibiy

ereaLing a jammed e6ndibioa during towing and subseqt-lenL

faitrure of the eow lin* LQ release" w3:ieta eo-tlid res-t-liL 'rn a

foreed landingi, aeeomplish Lhc followings

(a) InspeeL the Low release insLallaLi-or: Bo deterrnirre tf

anlr of t.he following relcase arms are ir:stalled:

P/N 1"D21"7:L3, LD222:15, 18222*LV or 34017D-15"

NOTE: The above arrns cail be id"en"'j-fied by a lug which

i-s weLded orr the frone face of the releas€ arm aS shown in

FiEure 1 af Sehweizer Serviee Ei:"tletin (SB) NCI" SA*005"1, dated

.Tanuary 31, L988"

{b } Tow release in**rail.ations

release arms lj-stcd in {a} rrtust have

following manRer;

P/N 1D2L7-13 replaee wit.h 1D2l-7-09

P/N LD222-LS replaee with \D222*LL

P/N 1D222*L7 replace with LD222*L3

P/N 34017D-15 replace with 34017D-11"

(e) Perform the operaLional cheek in aceordance with

Figure 4 in Schweizer SB No" SA-001-"3, dated January 31, 1"988'

following relcase arm replacemenu"

{d} L}pran requese, &rl equivalent nneaRs of compliance with

the requiremenLs of Lhis AD rnay be approvcd. blr Lhe Manager, New

York Aireraft eerLifieabion CIffiee, Federai Aviab"ion

AdminisLrat lon {FAA} , New England Rcgien" 3"81" SouLh F"ranklin

Avenueu Roorn 202, Valley SLream, New York 11581.

Sekiweizer Aireraft eorporat.ion SB Ne's. SA-005"1, &nd

SA*001""3, both daLed January 3X, l"9EE" identified and deseribed

in thie doeumenL, are ineorpor"ated hcrein and made a part

hereof, pursuane to 5 U"S"e " 552 (a) (1) "

rshie h trave any of the

Lhe arnls reBlaced in the

87 -17"0 X

A11 persons af feeted by t.tris dj.reebive who have not already

reeeived these docuraent.s frCIm the manufaeburer may obLain

copies upon nequest from Sehweizer Aireraft ecrporat.ion, p"CI"

Box LeV, Elmira, New York 1"4902; t.elephone (60?) 739-3821_"

T?rese doeuments may also be examined at the Of f iee of Ltre

R.egional Counsel, Federal Aviation Admj.nistrat.ion, New England

Region, 12 New England Executive Park, BurlingLon,

Massaehuset.t.s 01"803, Room 311, Docket No" BT-ANE*2 g, between

the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday,

except federaL holidays.

This amendment, 39-5973, becomes effective on AugusL Lg,

1988r BS to all persons except those persons to whom it llras

made immediately ef fect.ive by ind.ividual priority letter

AD 87-17-01, issued. August. 18, 1987, which contained this

amendment.

FOR FURTHER TNFORMATTON CONBACT:

C. Ka11is, ANE-L73, New York Aircraft Certification Office,

Aircraft Certification Division, F€deraL Aviation

AdminisLration, New England Region, 181 South Franklin Avenue,

Room 2A2, Val1ey Stream, New York 11581; Lelephone

(s16) 793.-6428.

4910-r3

DEPARTMENT OF TI{ANSPORTATION

Federal Avlation Administration

14 CFR Part 39

IDocket Number B7-ANE-291 Amendment 39-59731

MrworEhiness Directi-ves; Schweizer Aircraft Corporation Glider Models

SGS and SGU Series.

AGENCY: Federal Aviation AdminiscraEion(FAA), DOT.

ACTION: Final rule.

SlrMltARY: This action publishes in the FEDERAL REGISTER and makes

effec[ive to all persons an amendment adopting a new airworthiness

direcEive (AD) which was previously made effecEive to all known U"S"

owners and operaEors of Schweizer Glider l"lodels SCS and SGU Series by

individual priority letters " Because typographleal errors occurred in

the part numbers (P/N) in prioricy lerrer AD 87-17*CI1, they are

corrected. The AD requires inspecEion, and replacemellt if neeessary, of

the tow*release arm in ehe tow-release system prior to ehe next ftright,

trnless already accomplished" The AD is needed [o pE€vent jammlng of, ehe

I-ow-rel-ease mechanlsm wl-lich couLd resul-t in failure of ttre Bo,w*line t,o

releaee fror*. the glider and result in an unsafe eondittort dur:i.ng land.ing"

DATES; Effective August 19, X9EE, to all persons sxcept those Eo qshom it

ruas nade imetediately effective by lndividuatr prio'riiy le!;eer Ail &7*17-01n

issued Augurst tr8, 1987, i.ihich con{:ained thls amendaenl"

Comp'l iance : Ae required 1n the boeiy of ttre Ail,

Ittcorporaeion by Reference : Approved by ehe Dlreeeor of, ti:e FELTEK{T,

AilDRESSES: Schwe"izer Aircraft Corporation Service Bulletin (SB)

No" SA*005.1, dated January 31, tr988, SB No. SA-001.3, dated

Jaouery 31, i988, and replacement parts specified in this AD may be

obtained f,-s"om Schweizer Aircraf e eor-poraEion, p"O* Box t4Z, Elmira,

New Yorir 149CI2; telephone (607) 739*3821"

Copies of SB No. SA-005.1 aad SB No, 5.{*001,3 are contained ia

ttre Rules Docket, Doeket No.87-ANE*2gr Office crf tlie Regional eounseJ-,

S'ederal- AviaLion Adminlscrationr 12 lJew Engl".ar:d Exeeuai.ve Park, Rc*m 3X.1 ,

EurlingEon, MassachuseLEs 01803, and rnay be examined b€Eween Lire nrours of

E:00 a"nn. and 4;3Cr p"n., Monday through Frielay, €xcept iederal holidays"

FoR FLIRT}{ER I},IF0R},IATI0N c0l{TAC?: e . Kallie, ANE*I73, New yorx<. Ajrerafe

Certification Office, Ai::cna.ft frert.if,icaEion Divi$ioe, Federal= Aviatton

Admi-nistraLlon, Ne*r Englarid- Division, LBl soueh Franklin AveRue,

Room 202 , val-Ley stream, New York 11581 ; telephone ( 516) vgt*6/+za"

SUPPi,EMENTARY rNF0Ri'{ATroN: on August 18, Lg87 o prioriry letter A&

87*i7*01, was iseued and made effective immediately to al-l krrown U"S.

or"rc.ers/operarors of eerl-a.j-n Schweizer Aircraft Corporation Gtr-ider Models

SGS and SGU Se::ies. AD action resr-rl-f,ed f rone cwo reporcs e trat ref l"eets

that cercain schrseizer tors:hoaks with release arms plNEs tDz1z*tr3,

La222*15, tr-n222*17 or 34017D-1.5 used os: Ehe above Schrretzen A"treraft

Corporation gliders, can create a jammlng eondiEion of etre tow*J-fne ring

dtlring towing, when an input by the glider piJ-ot eommands release of fae

tow*line. Sehrseizer Aireraft Corporation has issdled SB No, SA*005.1,

dated .Ianuary 3I, 1988, which eal-ls for inspeetion of the toqr*rel-ease

instal-lations, and replaeemene if neeessary with new parts" Faltrure to

release Lhe toi,*-line while towing one of these gtrlders may result in

an unsafe eondition during J_anding"

Since il was found that iunmediate correeeive act.lon was required,

noEice and publlc procedure thereon were impractieabLe and ccleerary eo

publie i-atercsr, and good cause existed to malec the ACI eff,eetive

imsed.iaeel-y by lnd,ivi.dual prir:rity leLf,er AD issued, August !g, lg&7, Eo

al--L knovun U"S. o*"ners and operators of eertain Sehwcizer gliders- Theee

ecndi-eions still exist, and the AD vr-leh typographieal correeElons to Ehe

p/Nts, is hereby published in rhe FEDERAT REGTSTER as an anendmenu

to SecEion 39.13 of Fart 39 of ehe Federal Aviation Regulations t,o ma[<e

iE effeceive as to all persons e

The regulations set f,orth in thie amendment are prouulgaeed pursuane

to the auttrority irr- the Federal- Avlation Act of lg5g, as aleLndeA (+g

{.i"S.C" 13C}1' S! gaq.}, which statuce is construed to Breempc seaee l-e1.r

regulating rhe saue subjeeE, Thus, ia aeeordanec with Exeeutive

*rd.er L26L2o ie f-e determined EhaE suah regul-acions do nat have

federalisnr imptr-ications warranti,ng the preparation of a Federaltem.

Assessmenf "

CONCTUSI0N: The FAA ha.s deterained Ehat Ehis reguXation ie an cmergenslr

regulation ttrat is noe eonsidered Eo be major under Exeeu€ive

0rder 1229L" rt is impraeeieable for Ehre ageney eo folLor* the proeedgree

of Exeeutlve Order 1229L with respeeE co t,his rulc stuce the rule musts be

issued innnediately co correee an unsafe conditton in airerafc. tr€ trae

been fr'rrther deeermined that this aeEion lnvolvcs a& ereergeney regulaef*re

under DoT Eegulatary Polieies and Proeedures (44 FR 11034; Febrgary 26,

x979) " rf this aetion i.s subsequently de8ermlned Eo irrvorve a

significafle/majer regulation, a ft::al regulaeory eval-uaEion or ana1ysis,

as appropriate, will be prepared and ptr-ae.ed ln the regulaEcry docleee

(otherwise, an evaluation or analysrs is noE required). a clpy of ie

when fi1ed, may be obiained by eoneaeting tbe p*rurrr. ide:r[lfied under Ehe

caption "FSR. FURTHER INFORMATION CCIt{TACT*.

List of $ubjeets ls 14 CFR parr 39:

Alr Tra.ns.po-rtation, Aircraf t, Aviation Safety, lncorporation by

Reference.

ADOPTION OI' ?I{E AUENDMENT

Accordingly, pursuant to the auBhorlty delegated to me, the Federal

Slrliatlqn Administraiion (fAA) amends Part 39 of the FcderaJ- Aviation

AdrnLnlstrdtion (fAB) as follows:

l. The authorlty ciEation for Part 39 continues to read as follows;

Authorityt 49 IJ.S,C. 1354(a) , Lt+2Lt and l4Z3; 49 U.S,.C, t06(e)

(Revlsed. Pub. L,. 97-449r Jaauary 12, 19S3); and l4 CFR 11,89.

2. By adding to Section 39,13 Ehe. follor*{ng new ainrorthLness

directive (AD):

-3-

ffi

\# HEAEffi GHNCY,fuERWtrRTEITNESS DTRECTIYtr

A\,IATION ST&HDARDS ilATIO],IAL FIELD OfrEE

F.0. Box 25082

oxrA+{ofifiA. elTl 0I{LAHOiIA 73125

A'UGUST 18, 1987

u.S Decb-rn"u*,'rt

of TranWtctm:

Fedsnd &v!s?lw

Fdr#tbgr€tfsft

This emergene )r pri.crity Ietter Ain*orthiness Diree tive (AD)

No. 87*1:*nt, -applieable {.o owRers enC eperators of certain

Sehvrei-ze:: aireraft e.)rp*ratien glieler Models SGS and SGU series

with tolu ::*l-ea.se insiatl.ations whie h use redesigned release

a:rrils u is ef f ee t j ve inuaedi-a.tely upon receipt" This prlority

Ieti:er Ail r= ::equired bceause the tcrs line coul-d f,aE1 to

release on g11r3-ers equipped with tor+ release instatrlat.ions

wSieii use r*designed release arms that l:ave an additional trug

wel-ded on the faee of the release arm. Tiris pr5-orJ-ty letter AD

requ-ires the inspeetion and replaeement, if rteeessary, of, the

t*:,i reiear-se ai:ui in the tov+ release system prior to the next

flight after reeeipt of this prierity letter AD, unless already

ae e ornplished.

pursuant to the authority of thre Federal Avj-ation Aet of 1958,

deleEated to me b-v t.he Adrninistrator u the following priority

l-ett6r AD j-s issr:ea and macie apptricable t.o a1i- of the following

nnodels of Schweizer Aircraft eorporation gliders (including kit.

built) eertifieated in any eategory: SGU L'7; SGS 2-8 (rG-2);

SGS 2*LZ (rG-3)r SGU 1:19; SGU 1-20; SGU 1-21; SGU 2'22t 2*22A,

2-22e, 2*2zeK, 2*228, 2-228K; SGS 1-23 , L*238, 1-23C, L-23Du

1*238u i-23P, 1*23G, 1*23Iln 1-23H15; SGS L-24; SGS l-26, 1-:6A,

1-268, 1--26eu 1*26D, 1-268; SGS 2*32; SGS 2*33, 2'33A,2-33AK;

ScS 1-34, 1-34R; SGS 1-35e; SGS 1-36 (spritei "

E7*17".01 SCHWEXE"ERa Fri-ority tretter issued August 18, 1987.

Applies to nr*Effi (ineluding kit built) SGU L*7; SGS 2*8

t-rb-zle sGS 2*12 (TG*3); scu 1-19; sGU l-*20; sGU 1*21;

"$G[] 2*22, 2*2?An Z*ZZ7 s 2.-22eKu 2*22F,0 2*228K; SGS L*23, 1*23]f-e

i--23fu 1-'23n, L*23Eu 1:23F, J,*23Gu l-*23H, 1-23H15; SGS L*2'4;

SGS 1*26 0 L*26&s 1-268 , L*26e o 1*26D , !*268; SGS 2*32;

SGS 2*330 2*334u 2*33AH; SGS 1*340 1*34R; SGS 1-35C; SGS 1-36

{Sprite} "

T}:j-s pr5-orlty let.i:er AD is ef f ee tive inrmedS-ate1y upon

ree eig:t "

eonrpli-anee is rcquired prior to the next fl"ight after the

ef,fee t j-ve date of .*:-hr j"s pricrity letter AD, unless alreadlr

ae e ompS,ishied "

To prerrent 1:h-e BCIssibility of L.he tow release assembJ-y

e reatS,ng a j a:mred e orrdition during towS.ng and subseguent

f ailure . of t.h-e i:ow line to release, whie h eould result. in a-

foreed landJ-ngs aeeonnplistr thre foJ-Iowing:

ia) Inspeet thre tow release insta.llation to determlne if

any of t3"le fol-1or^ij-:'lg relcase arms are installed a

PIN 1823.7*13 I LD222*15p LD222*L7 or 34017-13"

HE€E&GffiNCV,4JRWO&TE{ENESS DIRECT'WH

87*1 7-0 1

NorE: rhe above arms ean be identified by a lug which

i-s welded on the front faee of the retrease .o*' u" shbwn in

S'igure 1 of Sehweizer Servie e Bulletj.n (SAy SA-005, dated

June lu _1987"

(b) fow rclease instal-Iati"ons whieh have any of the release

arms Ij-sted in {a} must. }:ave tiae arrns replaced in the following

rnanRer;

plN 1D217* L 3 replae e wi-t!: lD-?l T-11

B/I$ lDZZ2-l"S replaee with LD-ZZZ*IL

P/N 1D222*17 replaee wirh LD-ZZZ*IZ

plN 34CI12-tg regrJ-aee with 34017D_11

Flgure 4 in sehweizer sB sA*00 ! "2, dated May L9, Lgg7,

foll-owing release arm replaeement,

^ upon request-e . &I1 equS"valent means of courpliance with the

requirernents of this prlority letter AD may be approved by the

Manager, New york Aireraft eertificatibn office, Federal

Aviatron Administration {r'aay , Irlew England negion, 1g1 south

Frankl-in Avenue, Room zaz, valIey stream, New york irsar.

Docurnents pertinent to this priority letter AD may be

obtained, upon request, from sehw-eizer aircraft corporat5.on,

P.o. Box 147, Ermira, N.y. L4gaz; telephone 607-i39:3g2L, or

may be examlned at the office of the Regional counsel, FAA, New

England Region , L2 New England Exee utive park, Burlirritorr,

Massaehi:setts 01803, Rules Eocket No" g7-ANB_29.

Federal Register publieation to follow"

_ This priority letter AD g7-17-ol issued August 1g, 1gg7, is

ef fee tive inmrediately upon recei-pt.

FCIR FURTHER TNF'ORMATION CONTACT:

censtantine KaI}is, FAAo 191 south Franklin Avenue _ Rar.rm ?n2

Va1treyStream,NewYork11581;te1ephone'i6-ii-iTiiz

7-: ., na3r4

----

Schweizer Aircraft Corp.

:Post Otfice Box 147

Eimira New York 14902

EULLETIN NO. SA-OOI.]T

DATE: ll January 1968

PAGE: I ol 13

Supersedes Servlce Bulletln

No. SA-001 .2, Dated 19 May 1.987

SUBJECT: oNE-TIr,rE INSPECTION OF TOW RELEASE ASSEMBLy; OArLy INSPECTIdN OF TOH

RELEASE ASSE}.IBLY: PILOTIS PREFLIGHT INSPECTION OF TOH RELEASE

ASSEI,TBLY; 100 HOUR INSPECTI0N OF TOl{ RELEASE ASSE!.iBLY.

AIRCRAFT AFFECTED: r AII the. followlng Schwelzer Sallplane

SGU 1.7

SGS 2.8 (TG.2)

scs 2-I2 (Tc-3)

SGU 1-19

SGU 1.20

SGU 1-2I

sGU 2-22, 2-22A, 2-22Cr 2-22CK, 2-2?2,

sGS 1-21, L-279t L-23C, l-230!- l-23e,

l-23H' l-23H15

sGS 1-24

scs 1-26' 1-?'iA, i-268'- l-26C' 1-260'

SGS 2-]2

SGS 2-31, 2-t34, z-rrA(

sGS 1-14, l-f4R

scs .1-l5c

ScS 1-16 (Sprlte)

Models:

. All Sehwelzer Sallplanes fleld retrofltted

lneorporate a tor release assenbly.

TII,IE OF COMPLIANCE: PART I:

? -??€K

t-23F, L-zrG,

I-25E

PART II:

PART III:

PART IV:

Shall be aceompllshed ofl E one-tlme basls

withln 30 days of lssue date of thls bulletln

or at next 100 hour lnspectlon, rhlchever

occurs flrst (unless already accompllshert ln

accorclance rlth Part III of SA-001.2, or

prlor revlslon).

Shal,l be accompllshed prlor to the flrst

fllgnt of each day.

Shal.1 be accompllsheo at each Pilotrs Pre-

fllght lnspectlon.

Shall. be accompllsned at each 100 hour in-

spection.

(

SERYICE BULLETIN SA-OOI.'T

OATE: 1l January 1988

PAGE 2 of l3

REFERENCE: Schrelzer Servlce Bulletln SA-005.I, jl January 1988

AC 45.13-1A

PREFACE! Fleld reports lndlcate that lt ls posslbl.e for the tor hooks on the

affected alrcraft to release durlng towing operatlons rlthout any

lnput from the sallplane plIot. Thorough analysls of thls sltua-

tlon has allored Schreizer Alrcraft Corp. (SAC) to attrlbute such

Lncldents to (l) lmproper comblnatlons ol. tor hooks and reJ.ease

arms, Q) lmproper lnstallatlon of the tor hook lnto the release

atmr or (r) excesslve rear o? thc tor hook or selrase arm.

Parts I through IV of thls Servlce Bulletln llst lnstructlons for a

one-tl,rne lnspectlon, a datly lnsgectlon, a Pllot's Prefllght Insgec-

tlon, and a 100 hour lnspectlon of the tor release assemblles used

on the affected alrcraft. It should be'noted that Part I of thls

bulletln need not be accomplished 1f Part III of Servlce Bul.letln

SA-001.() ras prevlously aecomptlshed, Any dlscrepancles observed

rhlle perfornlng the lnspectlon psoeedures ltsted ln thls bulletln

requlres tha atrcraft to be grounded until the sl,tuatlon i,s rc-

solved.

In additlon, slnce there ls always a posslblllty of laoroper re.-

lease of the tor hook, satlglane tor ogeratlons nust alrays be

perforned yhere these ls sufflcient al.rfleld avatlable to accommo-

date sueh occurrences. Premature rel.ease of the tor hook ftorn the

release arn should not result in damage to the alrcraft or !,nJury

of lts occupants, lf the lecovery ls executed propesly.

benr r - oilE-TnrE rr{spEcrrou 0F Tor RELEASE AssEr,rBLy.

PROCEOURE

NOTE

lrany dlfferent verslons (Part Numbers) of tor

hooks and release arms have been manufactured

for Schrel,zer Sallplanes. However, as specl-

fted th Table I of thls bulletln, only certaln

tor hooks/rclease arn comblnatlons are cornpatl-

ble rlth each model sallplane. Unacceptable

comblnatlons must be replaced.

Use Table 1 of this buLletln to determine lf an aeceptable tor hook and

release arm a!e installed.

. ! t .,.SERVICE BULLETIN SA.OOI.]r

. ,DATE: JI January 1988

PAGE , of I3

..,

TABLE 1. ACCEPTABLE TOW IIOOK / RELEASE ARM COMBINATIONS

Alrcraft Tow Ilook Standar*

Rcleasc Arm

Supcrsedlng/

Replacement

Releasc Arm

SGU1.7

scs 2-8 crG2)

scs 2-12 0C.3)

SGU1.19

sGUl-20

SGU1.21

SGU2-22 (AIl Eodcts)

(C.G.I{ook)

SGS 1-23 (Ali no&Is)

scs 1-24

sGS 1-26, A, B, q

& C.G.IIook

scs 1-26 q E

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

SGS 1-268(opr)

scs 2-32

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

(C.G.Ilook)

scs 2-33,2-33A"2:33AK

(opc) (CG.Ilook)

sGS 1-34,1-34R

scs 1-35C

SGS 1-35C (opr)

SC'S 1-36

R-200-9Aor 1A-218-1A

or 18-221-3

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

ot LB-?2L-3

R-200-9Aor 1A-218-1A

orLB-221-3

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

otLB-?2L-3

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

otLB-22L-3

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

orLB-22L-3

R-200-9Aor 1A-218-1A

or !8-221-3

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

or 18-221-3

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

or 18-221€

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

or 18-221-3

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

L*U.L

1o4i2A-1

18-221-1

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

LV232A-L

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

1A-218-1A ot !B-22t-L

L0232A-l

L0232A-t

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

LZB-L4L or 1B-217-1A

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

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

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

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

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

L>2D-7

t>zzz-l

tB-?J7-5

L>?a-L-

1B-217-1A

LB-2L7-5

34017D1

t>2?2-7

LE.-2t7-5

tB-2L7-5

t>217-9

L>2L7-9

LD2L7.9

tD2L7-9

LD2L7-9

L>2L7-9

t>2fi-9

lD21:t-9

LD|2L7-9

1>2fi-9

L>222-L3

L>222-Lt

1D217-11

t>222-tt

LD2t7-9

1D-217-11

3.1017D11

t>222-t3

1D,217-11

LD2L7-LL

$ERVICE BULLETIN SA.OO1.]I

pATE: fI January 1988

PAGE 4 of 13

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

t Figute 4. Excesslve rear of the tor hook

- step eould result ln lmproper engagement.

F!,gure 2 of tnls bulletln provldes lnspee-

tlon 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 re-

lease 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 speei-

fled 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 ACCOH-

. PLISHED TITHIN THE GUIOELINES ESTABLISHEO BY

AC 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 instru-

ment pancl to arrow the release asscmbly to close further.

. . ".SERVICE BULLETIN 5A.OOI .37

DATE: 3I January 1988

PAGE 5 of I]

'.I

i'. t

g. 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.

h. 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 re-

placed as an alternate to weldlng on slug.)

l. If length of release arm slot ls greater than 0.55 lnch, replace release

arn.

J. 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.

k. Repalr of replace unservlceable component(s), as reguired.

t. Record compllance wlth Part I of this Servlce Bulletln ln Alrcraft Log

Book.

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

PROCEOURE

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 re-

solved prlor to next fllght.

i. Perform a thorough vlsual lnspectlon of the tor release assenbly and -

assoctated components-ln accosdance rlth the dally lnspectlon rcqulre-

ments llstect In Table 2 of this bulfetln.

CAUT I ON

ALL AIRCRAFT REPAIR ANO REIORK }IUST 8E ACCOM-

PLISHEO IITHIN THE GUIOELINES SPECIFIEO IN AC

4r. lr.

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

next fllght.

1..

SERVICE SULLETIN SA.OOI.]T

DATE: ll January I988

PAGE 5 of l3

TABLE 2

DAILY ANO lOO-HOUR INSPECTIOI{

. 0a11y 100 Hour

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. X

Perforrn a release check for proper release

tenslon ln aecorrlance rlth Flguse 4.

Lubrlcate attach hardware for tor hook

and release atnr.

Lubrlcate gulde-tubes 1n rel,ease control,

rlth dry stlck type lubrlcant.

Insure that tow hook moves freely on plvot bo1t.

'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.

e. 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

and perfo8o necessary repalrs.

9. 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 com-

pletcly closed.

(r) If the release assembly has opened, even partlally, gsound atrcraft

and troubleshoot release assenrbly. Repalr or replace faul,ty conpo-

nent(s) as requlred.

'. -'' SERVrcE BULLETTN sA-oo1.3r

' DATE! ftr January 1988

PAGE 8 of ll

PART IY . IOO HOUR INSPECTION OF IOTI RELEASE ASSE},IBLY.

PROCEDURE

8. Perforrn a thorough lnspectlon of tor release assembly ln aecordance rlth

thc 100 hour lnspectlon requltements llsted ln Table 2.

CAUTION

ALL AIRCRAFT REPAIRS TIUST BE PERFORI{ED ITI

ACCORDANCE UITH AC .,.1'.

b. If rlefects are notect, repair or replace faulty conPonent(s).

c. Record co-npliance rlth Part lY of thls Servlce Bulletln ln Alrcra?t Log

8ook.

TEIGHT ANO BALANCE DATA

llelght and Balancc not affeeted.

SERVICE EULLETIN

OATE: )l January

PAGE 9 of ll

TOW HOOK

SA.OOI.'I

I 988

RELEASE

ARIll

TOW HOOK

STEP

VIEW A. PROPER ENGAGEMENT

HOOK FULLY ENGAGED

HOOK NOT FULLY ENGAGED

TOW HOOK TOW }iOOK STEP

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,€

DATE:' ,I

PAGE IO

BULLET I I'I

January

of ll

sA-001. lr

I 988

TOW HOOKSTEP

(NOTE 8)

A-A

TRAIGHT EDGE

0lt{cHEs f^x.

ALLoWAB LE IRREGU I.ARITY

IN SURFACE'X'

A (NOTES 2 AND 8)

SHOULDEB

NOTE 7

CORNEB WEAR

PERMISSIBLE

OTE

(NOTE s)

(NOTES 1 AHD 3'

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

.: SERVICE SULLETIN 5A.(]O1.fr

'DATE: f1 January t98B

. PAGE ll of tl

NOTES:

I. IF TEAR OCCURS ON SURFACE iYT IT },IUST BE POLISHED FLAT IIITHIN TOLER-

ANCES 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.

2. OII.IENSION TAT ON IO252A-I HOOK SHALL 8E .2I INCHES I,IIN. &, .28 INCH-

Es 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.

7. SURFACE 'Yi HUST REI,IAIN FLAT, SI,|OOTH, AND TITHIN TOLERANCES SHQHN

ON SHEET 1. (SEE ILLUSTRATION. )

4. 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.

6. H00K IIUST REHAIN FLAT IN THIS AREA FOR A l,lIN.0F.2I INCHES FROx

SHOULOER OF HOOK.

7. iEAR 0ursr0E 0F THE .21 HrN. FLAT AREA Is PERltrsSrBLE.

8. DII{ENSION'B'I{US;8E EQUAL TO DII,IENSION rAr, OR LESS THAN OI}rEN-

SION TAT BY NO HORE THAN.OI5 INCHES AND CANNOT 8E GREATER THAN

OII{ENSION. TAr.

9. ALL SURFACES EXCEPT SURFACE rxr HAY BE FILED TO OBTAIN REQUIREO

_ DII{ENSIoNS.

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

NOTE: 18-217-19 SLUG IS AVAILABLE FHOM scHWEIZER AIRCRAFT coBP.

0.125 X 0.5 X 1.0 4130N STEEL

T()Vr

crdD

l-(r)

N\ram

-ituc LT

Pfr

rraCm

O'{

FlH

l-l,

\OD

@cl cl

\rr

.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

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 1987

PAGE } of 5

SUBJECT: ONE-TIME lNSPECTION AND POSSIBLE REPLACEMENT OF TO}J RELEASE ARM

M6DELS AFFECTED: 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 1.7

SGS 2-8 (TG.2)

SGS 2-]2 (TG.')

SGU 1.I9

SGU 1-20

SGU 1-2}

sGU 2-22, ?-22A, 2-22C, 2-22CK, 2-22E, 2-22EK

sGS 1-2t, L-zrA, L-21C, L-7rD, 1-218, L-23F, L-23G, l-21H,

L-?1HL5

scs 1-24

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

SGS 2-32

SGS 2.]]

SGS 2-l], 2-33A, 2-134K

sGS 1-]4, 1-34R

SGS 1-]5C

SGS 1-]5 ( 5prite )

NOTE

In the text of this writing' the terms nGLIDERIT

and "SAILPLANEri are to be considered synonymous.

T IME OF COMPL 1 ANCE ;Must be eonrpleted prior to the next auto or winch tow

of any sailplane equipped with the affected release

arm.

Must be completed within 60 days on all sallplanes

equipped r*ith an affeeted release arm.

Affected release arms in spares inventory must not be

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.

PREF ACE :

SERVICE EULLETIN SA.OO5

DATEr 1. June 1987

PAGE 2 gf 1

PBOCEOUftE

I. 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: I

PAGE }

.lULLtr | lll Jn-eu/

June 1987

of 3

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

BULLETIN NO. 5A-OOi.2I

DATE: 19 May 1987

PAGE: I of 12

x Supersedes Service Bul letin

No. SA-001.1, Dated 2 Feb 1987

SUBJECT: SCHhIEIZER SAILPLANE TOH RELEASE' PROPER ATTACHHENT OF TOtl LINE'

INSPECTION, I.IAINTENANCE PROCEDURES AND REHORK OF TOH HOOK, 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)

scs 2-12 (TG-3)

SGU l-19

SGU t*20

SGU I_21

sGU 2-22, 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, l-26C, I-26D, t-258

sGS 2-32

5G5 2:33, 2-334, 2*33AK

5G5 l*34,1*34R

5G5 r-35C

SGS l-36 (Sprite)

NOTE

In the text of this

and "SAILPLANE" are

Synonymous.

writing, the terms "GLIDER"

to be considered

(I ) * Denotes a change.

BULLETIN NO. sA-001.2r

DATE:

PAGE:

19 Hay 1987

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 of 12

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

Part 2: Hust be completed prior to every fl ight of the aircraft

Part 3: Hust be completed wr'thin 30 days of this notice or at the next

100 hour inspeetion, whichever is first

Part 4: Must be cornpleted 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 out-

I 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.

tl0TE

BULLETIN NO. SA.OOI.2r

DATE: 19 Hay 1987

PAGE: 4 of l?

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 of lZ

B. 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

If 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,

D. Perform complete inspection in accordance with ltem 4 of

this bul letin.

NOTE

Al I repairs must be conducted in accordance with

AC43. l3 by an authorized, I icensed mechanic.

NO:TE

If excessive or accelerated wear of the release

mechanism 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.

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 1987

PAGE: 6 of 12

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 I

ArlcflrrI T0l [00( 5Till)rf,0

Ptritst lni 5UPmSt0 lI0/fl EPutfitfl(I

ttLtl$ rnil

t-7s0u

scs 2-8 (rG-?)

s65 2-12 (rG-3)

sGU t-19

scu l-?0

56U t-il

sGU 2-e2 (lll .odels)

S€S l-?1 (lll lodrlsl

scs l-?1

5G5 l-26, l,0, C,

t C.G. Hook

scs r-?6 0, r

SGSl-250rt(tGtiool)

565 l-l6t (opt.)

scs ?-12

s€s 2-!3, t-33r, 2-33il

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

sGs t-!r, r-3fi

s6s l-l5c

SGS l-!sc (opt.)

sCS t-35

R-?00-9r o. ll-?18-ll

or lB-r2l-l

[-200-94 or ll-?18-ll

or l$-2el-!

l-200:lA or ll-?18-ll

or lB-221-3

t-200-91 or ll-218-lt

or l8-?ll-3

n-100-91 or ll-218-ll

or l8-2ll-3

fl-e00-91 or ll-?18-ll

or l8-?ll-3

R-?00-9t or ll-218-ll

or li-l2l-l

l-200-tl or ll-218-lt

or 18-221-3

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

or l8-??l-3

R-200-91 or ll-Zl8-ll

or ll-221-3

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

lt-2? t - I

102321-l

I 8-22 l- |

ll-218.1[ or l8-UI-l

t0l3?r- I

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

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

t023zt-l

l0u 3?r- |

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

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

128-lal or l8-?17-ll

B-200-l3r or l0-?17-lt

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

[-200-l2t or l8-217-ll

[-200-l2l or lt-2li-ll

n-200-l2t or lB-lll-lt

n-200-l2l or l8-2ll-lt

P-200-l2l or li-2ll-ll

t0-122-1

fi-222-l

t8-zl7-5

t0-It2-l

r8-2 I i-lr

tE-?17-5

310lI0-l

It-222-1

rB-2 I i-t

r 0-2 t?-5

t0-?lt-t

t0-2 r 7-9

r0-zl?-9

l0-2t7-,

l0-? l7-r

t0-?17-9

l!-il?-9

l0-2 t1-9

lB-l ti-t

l0-2 r 7-9

l0-222-13

t0-222-l r

lg-2 I 7-t I

r0-??2-t I

t0-2 I 7-9

t0-? lI-t I

3{0t l0- I I

ilF?22-lt

l0-21?-r r

t0-2 tI-l I

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 of 12

TABLE 2

DAILY AND IOO-HOUR INSPECTION

Dai ly 100 Hour

Visual Iy inspect release arm for damage, X X

cracks, deformation, and freedom of

npvement on pivot bolt.

Visually and physically inspect release X X

arm slot for excessive wear which would

al low the tow hook to engage beyond the

hook step. (See Figure I, Item C.)

Dimensional Iy measure the slot in the X

release arm to insure that it is within

the tolerance as shor.rn on Figure 3.

Visually inspect tow hook for damage, X X

cracks, deformation' and freedom of

rnovement on pivot bolt.

Visual Iy check tow hook to insure that X X

surface "x" and "y" of step as shown

in Figure 2 are flat, smooth and properly

engages release arm.

Dimensional Iy check tow hook to insure X

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 X X

condition and proper engagement of tow hook

Perform an operation check per Part 2, X X

Ferform a release check for proper release X

tension in aecordance with Figure 4.

Lubricate attaeh hardware for tow hook X

and release arm.

Lubricate suide-tubes in release eontrol X

with dry stick type lubricant.

Insure that tow hook rpves freely on pivot bolt. X X I

BULLETIN NO. 5A-OOI.2T

DATE: 19 t'lay 1987

PAGE: I of 12

TOW HOOK

FIGURE 1

pRopER HOOK-UP WITHtHOOK FULLy ENGAGED RELEASE ARM

HOOK

TOW

STEP

A. CORRECT HOOK.UP

TOW HOOK

q- INCORBECT HOOK-UP WITH HOOK NOT FULLY ENGAGED

TOW HOOK STEP

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 HOOK

TOW HOOKSTEP

RELEASE ARM

INCORRECT HOOK-UP I,VITH HooK EXTENDING

c. INCORRECT HOOK-UP THROUGH THE RELEASE ARM BEYOND THE STEP

-nuulErtN NO. SA-001.2*

DATE: 19 MaY l9B7

PAGE: 9 af 12

STRAIGHT EDGE

A-A .O6 INCHES MAX.

TO1JV HOOK STEP

ALLOWAB LE IRREGU LARITY

tN SU RFACE 'X"

(HOTE S}

A fiOTES 2AND 8}

DETAI L B

SHOULDER

t{oTE 7

CORNEH WEAR

PERMISSIBLE

OTE

(NOTE 5)

SU RFACE "X"

SU RFAEE "Y"

(NOTE 3}

f.ut MlN. FLAT AREA

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

BULLETIN NO. 5A-OOI.2*

DATE: 19 Hay t987

PAGE: l0 of l2

1, Ir HEAR 0CCURS ON SURFACE *y" IT IIUST BE POLISI{ED FLAT I{ITHIN TOLERANCES

PROVIDED IN FIGURE 2 (SHEET I}. IF TI.{E HOO( CAf{IIOT I{EET THESE REQIJIREB

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 1023?A-l H$OK St{ALl- BE .21 INCHES tllN. e "28 INCHES HAX.

DIHENSI0N "A" 0N tA-z18-1A, lB*2Zt*I, tB*zel-3, & R*A00-9A Hoott$ $HALL BE

.35 INCFIES t'IIN. &.SI INEHE$ NAX.

3" SURFACE NY" }IUST REHAIN FIAT, SHMTH, AI-IS HITHIN TOLERANCES SHOI{N ON

SHEET I " {SEE ILLU5TRATION. }

4" DIHENSIOH "C" CIH 10232A-l HOOK Sl.lALL BE 2.06 t.03 INCHES" DII{ENSION "er

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

5, DIF{Ei{SION "E" SHALL BE .31 t.CI3 IHCHES.

6. HOOK I,IUST REI.IAIN FLAT IN THIS AREA FOR A HIH. OF .2I INCHE$ FROI,i SHOI.JLDEE

OF HOOK.

7 " I,,EAR OUTSIDE 0F THE ,21 t{lN, FLAT AREA IS PERHISSIBLE"

8" OII.iET.ISION IIBII I.IUST BE EQUAL TO DII'IENSION *A", OR LESS THAN DIHENSIOI'I "A" SY

NO I{ORE THAN .OI5 INCHES AND CANNOT BE GREATER THAN DII.{ENSION "A'I.

NOTE: 18.217-19 SLUG IS AVAILABLE FROM SCHWEIZER AIRCRAFT CORP.

0.125 X 0.5 X t.O 4130N

TO@

6) -l fr

rrlmr- m

\o z_

o=o

-t0) a

\Ol

t\)

-l

F-"3s r.03 TNCHES ON ATRCRAFT EOUIPPED W|TH 10232A-1 TOW HOOK

I .ro .+.og INcHEs oN AtRcRAFT EeutPPED wtrH IA-2'!B-iA, 'NB-221-i,

i ty'z2t'l, oR R-2oo-sA Tow l'looKs

I ,____--+-,

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

.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

ABOVE OR HEPLACED WITH THE

UNIT PER TABLE 1

BE REWORKED AS SHOWN

PROPER SUPERSEDING

FIGU RE 3

REWORK OF RELEASE ARt\4_

]ATE: IY

PAGE: 12

l-16y

of 12

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

iltm*t**m::m

CAUTION

wlTH A .25 iiierrsE@P

ErncBaEI

SEALE

5TO20 LB" READTNG

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

Tneg-I

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

Tow HOo K-/"

^. lff 3:Jl.:?3t,I'l ?l':i"13 $[?B ;$T1 if"*+ffiHlxllH:.

RELEASI

TOW HOOK

,F ro w Hoo K * ^l-il :t 3 J lxi:ff "1ffJfi

y- I ?f t?i *H;l E L EAs E A R$'}r

RE.FE.R TCI FIGURE 1

Schweizer Aircraft Corp

Post Office Box 147

Elmira, New York 14902

BULLTTIN NO. 5A-OOI.I*

ACI 87- ot-ol

DATE:

PAGE:

2 Feb 1987

lof12

Supersedes Service Bul letin

No. 5A*001, Dated Oct. 3, 1986

SUBJECT: SCHlllE I ZER 5A I LPLANE T0l".l RELEASE , PR0PIR ATTACHMENT 0f' T0h'l L I NE ,

INSPECTION, T4AINTTNANCE PROCEDURES AND REWORK OF TO}I HOOK, RELEASE

ASSEMBLY AND RELEASE DAHPTR.

AFFECTED AIRCRAFT: AlI 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.

SGU I-7

sGS 2-8 (TG-Z)

SGS 2-12 (TG-3)

SGU l-19

sGU t-20

SGU I_2I

5GU 2-2?, Z.-22A, 2-22C, 2-22CK, 2-22E, 2-278K

SGS 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,

SGS 2-32

sGS 2-33, 2-33A,

sGS l-34, l-34R

SGS 1_35C

SGS 1-36 (Sprite)

NOTE

In the text of this

and "SAiLPLANE" are

synonymous.

1-268, t-25C. 1-26D, t-26E

2-33AK

writing, the terms "GLIDER"

to be considered

(l) - Denotes a change.

BULLETIN NO. SA-OOI. I*

DATE: 2 Feb 1987

PAGE: 2 of lZ

PREFACE I

NOTE

It is absolutelv necessary that all pilots and

Eround personnel received proper training with

respect to the subiect matter of this bul letin

prior to fl iSht.

Reports indicate that a possibi I ity exists that the sai lplane tow

hook may inadvertently release during tow without any input by the

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 mainten-

ance 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

uncommon 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

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 1987

PAGE: 3 of 12

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 SHOULD I.OLD THE RELEA$E KNOB

FOR 3 TO 5 SECONOS TO ALLOH ADEqUATE TII.{E FOR THE

TOI{ LINE TO CLEAR THE SAILPLANE AND I{ATCH FOR

VISUAL C0NFIRI'iATION 0F TOI'I LINE RELEASE.

* TIME OF COHPLI,ANCE:

Part l: Hust be completed prior to the first flieht of the aircraft each

day

Part 2r Hust be completed prior to every flight of the aircraft

Part 3: f'lust be completed within 30 days of this notice or at the next

100 hour inspection, whichever is first

Part 4; Must be completed at every 100 hour inspection

PROCEDURES:

Part i: Perform a daily visual inspection of the tow release assembly

and its components in accordance with Table 2 of this Service

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 out-

I 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. I*

DATE: Z Feb l9B7

P,AGE: 4 of 12

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:

A. 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. I*

DATE: 2 Feb 1987

PAGE: 5 of 12

B. 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

If 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.

D. Perform complete inspection in accordance with ltem 4 of

this bul letin.

NOTE

All repairs must be conducted in accordance with

AC43. l3 by an authorized, I icensed mechanic.

NOTE

If excessive or accelerated wear of the release

mechanism is evident a review and correction of

piloting practices and ground personnel 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.

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. I*

DATE: 2 Feb 1987

PAGE: 6 of l?

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 T()T tl00l( SITIoARD SUPIRSE0 I tlc 1 Rt PLACEIIEIIT

RTIEA5E ARII RELEAST ARII

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.

SGtl I-? R-200-94 or lA-218-ll

or l0-221-3 R-200-l2A or l8-217-lt l0-217-9 or l0-2lT-13

5G5 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

sGs 2-r2 {TG-3) R-200-9A or lA-218-lA

or lB-221-3 l28-l{l or lB-217-lr1 lD-217-9 or l0-21?-13

scu l-t9 R-200-9t or lA-218-lA

or l8:221-3 R-200-l2A or lB-211-lA l0-217-9 or l0-217-13

sGU t-20 R-200-9A or lA-218-lt

or l8-221-3 n-200-l2t or l0-217-lrt lD-217-9 or l0-217-13

sGlJ l-2r R-200-9A or tA-218-lA

or lB-221-3 R-200-l2A or lB-2li-lA l0-217-9 or l0-217-13

SGU 2-22 (ll! mdels) R-200-94 or ll-218-lt

or lB-221-3 R-200-l2A or l8-217-lA l0-217-9 or lD-ll7-13

SG5 I -23 (All rodels) R-200-9r or tt-218-ll

or IB-221-3 R-200-l2l or l8-217-lr1 lD-217-9 or l0-217-13

SGS t-2t P-200-91 or lt-218-lA

or l8-221-3 R-200-l2A or l8-21?-lA l0-217-9 or l0-2li-13

scs l-26, A, g, c,

t C.G. Hook

R-200-9A or lA-218-ll

or l8-221-3 R-200-l2A or lB-217-ll lD-217-9 or l0-217-13

sGs t-25 D, tlA-218-lA or l0-221-l t0-222-1 lD-222-13 or l0-?22-17

SGSI-250ti(CG}look) rB-22r-l n-222-l lg-722-ll or l0-222-15

sGS l-Z5E (opt.l 102324- I I B-2 r 7-5 lB-217-ll or l0-217-15

SGS 2.32 I8-22t-I t0-222-l lD-ZZ?-ll ot 10-222-15

sGs z-33, 2-331, 2-331t( lA-218-lA or lB-221-3 lB-2ti-lA lD-217-9 or l0-217-B

SGS 2-33, 2-331, 2-3341( (opt.) I 023 2r- Il8-2r7-5 lD-217-ll or l0-217-15

scs l-3t, l-3tR lA-218-lA or lB-221-l 310 I 70- |3r0 I 7D-r3

sGs t-35c lA-218-lA or l8-221-l t0-222-1 l0-222-13 or l0-222-li

SGS l-35C {opt.) I 02324- II B-2 I 7-5 l0-217-ll or l0-217-15

sGS t-36 I 0232t- IlB-2 l7-5 lD-211-ll or lD-217-15

BULLETIN NO. 5A_001. IX

DATE: 2 Feb 1987

P,AGE: 7 of 12

TABLE 2

DAILY AND lOO-HOUR INSPECTION

Dai ly 100 Hour

Visually inspect release arm for 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.

Visual ly inspect tow hook for damage,

cracks, deformation' and freedom of

rnovennent on p i vot bol t .

Visual ly 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.

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.

Perform a release check for proper release

tension in accordance with Figure 4.

Lubricate attach hardware for tow hook

and release arm.

Lubricate guide-tubes in release control

with dry stick type lubricant.

BULLETIN NO.

DATE: 2 Feb

PAGEr I of

sA-001.1*

t 987

PROPER HOOK.UP WITH HOOK FULLY ENGAGED RELEASE ARM

TOW HOOK

STEP

TOW HOOK

A. CORRECT HOOK-UP

FIGURE

TOW HOOK

1 INCORRECT HOOK-UP wlTH HOOK NOT FULLY ENGAGE

TOW HOOK STEP

RELEASE ARM

B. 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

TOW HOOK STEP

RELEASE ARM

INCOHRECT HOOK-UP WITH HOOK EXTENOING

c. INCORRECT HOOK-UP THROUGH THE RELEASE ANM BEYOND THE STEF

BULLET I N

DATI: ?

PAGEr 9

N0. 5A-0CI1.1'

Feb 1987

of 12

STBAIGHT EDGE

A-A 06 INCHES MAX.

TOW HOOK STEP

ALI-OWAB LE IFR EGU LA RITY

IN SU HFACE 'X'

A OIOTES 2 AXD 8)

DETAIL B

SHOULDER

TE7

CORNER WEAR

PERMISS!BLE

SU RFACE 'X'

SU RFACE 'Y"

(NOTE 3)

(NOTE

f.0, ltlN. FLAT AREA

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

BULLETIN NO. SA-OOi. i*

DATE: 2 Feb 1987

PAGE: 10 of 12

NOT ES:

l. IF I{EAR oCCURS ON SURFACE .,y" IT HUST BE POLISHED FLAT I{ITHIN TOLERANCES I

PROVIDED IN FIGURE 2 (SHEET 1). IF THE HOOK CANNOT I.IEET THESE REQUIRED I

DII{ENSIONS IT I.IUST BE REPLACED. UNDER NO CONDITIONS SHOULD SURFACE UX" BE

POLISHED OR I'IACHINED TO CHANGE ITS ANGLE.

2, DII{ENSION I'AI' OH IOESEA.I HOOK SHALL BE ,EI IHCHES HIN. &.28 INCHES I.IAX. I

DI|{ENSIoN "A" 0N lA-218-lA, LB-??t-t, 18-221-3, & R-200-9A H00K5 SHALL BE

.?5 INCHES I.1IN. &.3I INCHES },IAX.

3. SURFACE "Y" I{UST REI.IAIN FLAT, Si{OOTH, AND I{ITHIN TOLERANCES SHOI{N ON

SHEET I. (sEE ILLUSTRATION.)

4. DIIIENSION "C" ON 10232A-l HOOK SHALL BE 2.06 1.03 INCHES. DIilENSION "C" I

ON lA-218-lA, lB-221-1, lB-221-3, & R-200-9A SHALL BE 3.00 +.03 INCHES.

5. DIi{ENSIoN "0" SHALL BE .31 1.03 INCHES.

5. HooK MUST REMAIN FLAT IN THIS AREA FOR A I.IIN. OF .21 INCHES FROH SHOULDER

OF HOOK.

1. I{EAR OUTSIDE OF THE .21 }IIN. FLAT AREA IS PERHISSIBLE.

8. DII{ENSION "8" MUST BE EQUAL TO DII{ENSION'AO, OR LESS THAN DII,IENSION "A" BY

NO HORE THAN.OI5 INCHES ANO CANNOT BE GREATER THAN DII.IENSION ''AX.

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

NOTE: 1B-217-19 SLUG IS AVAILABLE FROM SCFIWEIZER AIRCRAFT CORP.

0.125 X 0.5 X 1.0 4130N

-o(:}w

c).{r

mmr rrl

--l

=Nlz -Yt Z

ooo

-ig a

-.l C)

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,

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

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

.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

ABOVE OR REPLACED WITH THE

UNIT PER TABLE 1

BE REWORKED AS SHOWN

PROPER SUPERSEDING

FIGU RE 3

REWAHK OF RELEASE Aru

BULLETIN NO. 5A-OOI. I*

DATE: 2 Feb 1987

PAGE: 12 of 12

FIGU RE 4

APPLY A 25 TO 30 LBS. PULL ON TOW BOPE

WHILE CONDUCTIHG RELEASE TENSION TEST

SCALE

CAUTION 5 TO 2O LB. READING

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.

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

RELEASE ARM

HOOK STEP

CHECK TO INSURE THAT THE HOOK

CANNOT PASS THROUGH THE

RELEASE ARM BEYOND THE STEP

OI{ THE HOOK

ELONGATION OF THE HOLE

IS NOT PERMITTED AND

}IOOK MUST BE REPLACED

MAX. HOLE DIA. .350

TOW 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 1

SERVICE BULLETIN SA.OO'

DATE: 25 March I987

PAGE 1 of 2

SUBJECT: AEROBATICS IN SCHI{EIZER SAILPLANE MODELS L I STED BELO'd "

MODELS ATFECTED:

seu 1-7

SGS 2.8 (TG?)

scs 2-12 (TC3)

Scu 1-19

SGU I-?O

SGU 1-2I

SGU 2-22, ?-?2A, 2-72C,

scs 1-2r, 1-218, \-?3C,

1-2rHI5

SGS 1-24

sGS 1-25, L-26A, I-?68,

SGS 2.}2

sGS 2-1,,2-31A, ?-31AK

SGS I-14, I-34R

5G5 1-]5, l-]5A, r-f5C

SGS 1 -16 (Sprite )

2-22CK, 2-22E,

l-23D, L-23E,

L-26C, L-26A,

2-22EK

l-21F, 1-zt?, l-23t1 ,

l-268

In the text of this

and 'I SA ILPLANEII are

NOTE

writlng, the terms HGLIDER"

to be considered synony(rous.

REFERENCE: Page 1-10

Page 5

Pages l-5

Page 5

Pages 1-7

Page 21

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

SERVICE BULLETITI SA-OO3

0ATE: 25 t{arch I967

PAGE 2 of 2

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 sail-

plane models affected by thls Servlce Bulletin, desplte any lan-

guage 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 varl-

ous levels of aerobatlcs are permltted, Sehweizer Aircraft Corpora-

tion 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 person-

al lnJury to the occupants of the alrcraft.

The 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. Howev-

err befsre performing splns in the aircraft, each pilot must re-

celve 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.

Schweizer Aircraft Corp.

Post Office Box 147

Elmira, New York 14902

SERVICE LETTER 5L.OO1

DATE: 1 June 1987

PAGE 1 OF I

T0: All owners and operators of Schwelzer Sa1lp1anes.

SUBJECT: ANNUAL DISASSEMBLY OF AIRCRAFT

MODELS AFFECTED: All Model SGS 1-2], SGS L*26t SGS 2-12, and sGS 1-,4

Schwelzer SailPlanes.

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

dlfficult o! even impossible without damage to the aircraft. For this

reason, Schweizer Aircraft Corp" suggests that the affected sailplanes

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.

U.SDeBrtrnent'

d}wrspcrffitrtr'

fsderd A*rkfir*t

ffi*rffim

AIRUTOATT{II{E$S PTRECTX\IH

avraTl0fl cT*HoAnp6 HATtOa{&t nrLB OrncE

P.&. EOX 26/lGO

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

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$ms "ff& -$& 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* d SE Air{.d*c [frx*iw (Sift Ijl].

6?*02*0f SCHWHIZER AIECRAFT eQqp-.: A!ftenelment 3q*551"2"

uttii*u- t" m:A luding kib buiiL), all

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

sGU '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

slipping CIut CIf Lhe

whic'h eould result

possih'iliLy af. the tow-hook inaorrertently

release*arm and releasinE Lhe tow-1ine,

in a foreeo landing, aceomPl ish the

following:

{ a i IdiLh in Lhe next 5 t.ow release ae tuat ions af ter {-*he

effeetive date of this ADo perforrn bhe follewing:

{ I } Inspeet the ior**re}ease installation for proper

part numbers, exe essive wear, and E:oss-ibtre^, rework or

rep:.ae€ment of parts in aeeordance wiLh ParL 3A, 38, and 3C in

Se[rweizer Servl6e Bulletin No. SA-0S1, dated Oetober 3, I986"

( Z ) per f orrn the CIEleraL ional e heck in ae e ordane e wit.h

Figure 4 j-:'g Schureizer Serviee BulleLin No" SA*0CI1, dated

L-rctober 3, 1986

{b} Thereafter, &L intervals noL to exeeed 100 hours

Linre*ir"r-serviec, aeeomptrish the sLeps in Part.38, and 3e, and

Fig'*re 4 in Sehweizer Service Eul"leLin No. SA*001, dabed

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 "

87-02-01 2

Upor:submissionofsubstanbj"atinqdababyan0wnerCIr

OperaEor t.hrough an -FAA maintenanes inspeeLor, the Manager ' t{eEr

york Aircraft tertification Offiee, may adjust the c*mpliane*

Lime specified in this AD'

schweizer serviee Bulletin t{o. sA-00}f daLed oetobef 3'

1985, ident ified and d"*.r ibed ln ttiis doeument, is

i;;";poraEed herein and made a part hereof Pursuane to 5 U'S'C'

552(a){r). Aii-p*r*uo= affected by this direeti"ve who have not

received Ehis ds-cumer,e from the manufaeturer may obtain eopies

upon request to schweizer Aireraft eorp.r P.o. Box L47o Elmira,

N;; yorfi 14902, Tetephone (60?) 739-382L" This document a]so

;;t be examined at the offiee of Lhe Regional Counsel, Federal

Aviation Admini.strationo New England Regionr-- Jz *New England

ExeeutiVe Park, BurlingLon, MassachuseLts 01803t Rules Docket

Number B5-ANE-;6 r- noom -gtt n' between the hours sf I :00 a 'm ' and

4:30 p.m" l{onday through Friday, exe ept Federal" holidays.

This amendment becomes effEcfive on January 2!, 1987'

FOR FI'RTHER INFORMATTON CONT.ACT:

C. Kal1is, New York Aireraft CertificaLion Office, Aireraft

Certification Division, 181 SouEh Franklin Avenue, Roorn 292?

Vattey Srream, N;; York 11581, Telephone (516) 79L-6428"

4E O-IL

EELARTTETjr OF- IffiI{SE ORTArtffi

F+deraf A+1 aEf orr Adnfn fstrarfon

14 gFP. Parr 39

[Docket No. 86-ANE-46; Amendment ?9-S5lZ

Alrworthlness Directlve6; Schweizer Alrcraft Corp. Model SGS and

Sffl Sertes GLiders

A6IICY: Federal Aviation Adninistrarion (fAA), DOT.

ACTION: F{nal rule.

s-taffiaRY: This amendment .adopts a new alrworthiness direetlve (AD)

whieh nequ-ires eertai.n sehr.'eizer Aircraft corp. torr-release

l"nseaLl-acions i"nstatri"ed on gltder blodels sGS and sGJ series to be

lnspeet.ed to aseert.aln t.hat the proper reLease arm has been uated lrlth

tiie tcn:hook on the aireraft. lnspeet.ion wilL inelude wear linuit

measureBenEs for deteria-{nlng if the hook and/or the release-ar6 can be

repaired or replaeed wlth Rew superseding parts. This AD is 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 in the body of the AD.

rncorporat.ion by Referenee - Approved by the Di.reetor of the

FEDEP"AL REGISTEB. on

ADDRISSES: The technical lnfornation (Service Bulletin ],io. SA-001)

and uodiflcation part s spec{fied in this AD may be 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 tfre= Re81onal'eormael, Pederal

Avlatton Adainlstrstlon, New 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, 1.81 South Frenklln Avenue, Room 202, Valley

Stream, New 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 on

schweLzer Alrcraft corp. Models sGU and $GS serLee gltders esn

lnadvertently release the eable durlng tCIwing v{thout any lnput t0 ghe

release ha*dle by the glider pilot. Sehweizer Aireraft florp" has

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

t,owi"ng sne 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

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

abovetypecertifieatedgliders"Thereforeresisbeingissuedlo

requireinspectlortandposclblerepairorreplaeementofthe

tor-release installaeion P&rts'

-2*

$g*ee s 6ttue6l*m cxl.6t6 Ehet requtree the lmmedlate adopt*on of

rltf,* regri"r-).a*1cn, trr. 1s detcredried thet nette* and publ,te proeedure &re

jLr*;r;'*rri*:abjte, 6rud g*cci exuae exlsEe f,os usktng ttrls anendment

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

eONeLUStrON: The FAA tras determlned that thls regulaEton 1s an

eeergeney regulatlon Ehat ls not eonstdered to be raaJor turder Exeeut.lve

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

proeedures of Ordcr 12291 rdfh respcct to thtrs rule since the rule nuct

-be lssued lmqediately to eorreet an unsafe eondltlon 1n alrcraft. It

hae beezl further deEermlned that thls aetion {nvolvcs an cElcrgcney

regulatton tmder DOT 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 may be obtalned by contacting the

person ldentifled r:nder the eapLlon *FOR 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-

j' , Thc auchclriry e 5"t g,E j-gn f or FarL 39 conLinues E'q: read as

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 a-j rr'dor*"trlneps

direerlve (AD):

.*4*

---.\'\___\-

TELEX NO. g324sg

t49o2 - (6ot) 739-382t

AIRCRAFT CORP. P. O. SOX t47 - ELi,ltRA, N. r.

July 27, 1984

Mr. Dave Wilke

Powe1l Aviation

jvianfield Airport

Manfield, IvlA'. 02048

Dear Mr. Wilke:

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 make sense.

I hope this data will solve your problem.

Silcerely yours,

SGIIIEIZER

/rs AIRCMFT CORP.

ern

cc: John Braun

{-dnnu,{L

Leslie E. ScJrweizer

Vice Pres - Engineering

"AT THE SOAN/NC CAPITAL OF AIAERICA"

Schweizer .A.ircraft

P. 0. Box 147

Elmira, llew York

Corporatlon

14902

December ]'8, L9?5

G BSC

'-5;f"t

been

the control-

stick

length of

further action

SETTVICE BIILIET]}{ NO. 102-26-8

SU&IECT: Inspeciion, of Control Stick Pivot BoIt

MODM,S AtrT"ECTffi: SGS 1*25D & E

smIAI No"'s AFFECTED: (o ltooel) 4oo tirru 48r

{m'l{odal) 5,0'g te;qp &i+e '

TII'{E Otr' COivFLIANCE; }/ithin 1O fiours Flight Time

It has been determined that an j:rcoruect length bolt has

insta]-].ed on some SGS 1-26D and E Mode1s at the attachmeni of

stick-yoke wel.dment to the aileron control- torque tube.

fhe corcegt. bo1t, as specified. on drawings, is AN6-21.

Iq$PffiIf(N: On ships having the (optional) aft floorboard

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

1, Scale-neasure the length of the bo1.t installed. If the

the bo1t, from beneath the head to the end, is 2.20 no

is required, other than a logbook eniry of compliarlcg.

2. Should the bolt be shorter than the 2.2O length - o

and

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.

c. 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 method

of repair.

.\-

SC$rlEfZqB AIfiCeAIT COBP.

SCIf'J/EIZEB AIF.CRA FT CGEi .Februar.y 11, 197L

I. O. Eox L4?

Eimi.ra, i'Iew I-ork I42frz

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

L'?ODELS /tFFECTES: SGS 1-?SB and C, ter. I.{r,,ts 28} tirru 399 whic}r have Swept-

baci: 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

SUEJECT: Eudder Hi_qqe,_l-crvj_r, 5tlachrygr:_i_ to. iin SI*I

,V/A

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 <l*fect in the bolt i"s:1:i was noted. V/hethe i: ti:is i:clt rvas the first tc

iail, ieaiir:g to the failure cf the scccnri, is nci irn:wn. iicwev:i', il r,,'as siat,.i .,ilrt L

r,:.:.;.1 1r-::;l;',1 :14 nci usC,l ;;::,-.!.--.-':ldli oi fir:-do; n x'i:ici: ii:lii, ila'o:r3 i;c:ri a Ci,t).i.'t,..- -

iacicr:, as f!-igi;+, lcais are veiy iol,l ol the se boits"

To assure that a similar i*.i1ure has no'u occured on slii.pr: in service -

Frefiigirt i::spe ct ti:.a aii'ciaIi to assure rhe i:ciis ar€ rn pla.ce.

Accompli.sh ihe following ai ihe first 1O0-hc,ur or Annual Inspection,

wh;.cheve r occurs first" Cne at a tirne, remove each AN3-?A irolt {ii:ese

bolts have a cne quarter inch long, 3/8 diamete r x . C90 rva1i, aluminurrr

i:ushing under the bolt head), Sclvent-elcaa anC inspect, especially ai ti:e

thread and shank i*lersection, for damageC threads or cracks. ivlagnctic

particle inspection is reeomraended, if avaiiabie. Crlherw'rse a magrrif-r"irg

gl.ass of 3.5X to 5X should he useC.

Heplace ihe bolts ,.r,iih new bolts, when:

a. Inspection equl.::',rent is not a.,raiiabie.

'D. Aircraft has be:n in service for mcye ihan either 200 ho,:rs, or

ihree ]'ears.

c. Inspectiorr revei..Ls a-n;'deftrct in the boit {s}.

Use a to::cue-va!ue of 20 tn 25 inch-pourrds when reinstail.ing the Lrolts, and insur*

t}:ei ti:e -husirings are tiansfe::'ed lo tiie new bolis.

EECO_I,Ii{E}i}ATIC}{; Since i"i::c*gusi ioads a::e usually much greate r than lligiri

loaris, it is sirongi1i rec+r,:rnenCed thai control chccks be

use i ciuli::1; aii r:*:,.i;is i'.i. L.c*iic';;i.

*hrff,*oilr,,

-.-L .,<Ail#'"

s+r;,ffil.,rr

5 1rt

ICH*:Ii: ;,1i;i{r,A;.r? .J'lr-.:..

Schweizer Aircraft

P. O, Box 147

Elnlra, Hew York

Corporatlon

L*gA2

198\'ICE BULLETiN UC. 1C2-26-6

Model Affected: SGS 1-26D

Serial No.'s Affected: 404 Ehrough

December 30, 1958

CBs C

n//rt i* )-tr A-

{+Ag

It has been established that several SGS 1-26D fuselage frames were

butlt +rith Ehe rudder cabLe fairlead bracket, R. il. r welded to the upper

cross member, P/N 26Hc01-14 at fuselage statian Lgt+.25, rather then to

the R. H. vertical rnenrber as per drawing

This put the f airl,earJ lo:atiorr approxirrately 1.0 high and 3/t, i1,-

board of irs proper location, This mislocetion raises the right hanci

rudder cable enough tc rub slightty on the u"per horizontal diagonel

tube, P/N 26t1CC1-13 located betr,reen the upper R. H. clusEer at Fuselage

Sta. 194.25 and the upDer L. H. cluster at Fuselage Sta. 215.0,

Correction of the rudder cable rubbing cn the llsted ships can be

corrected by the installation of a rudder cable guarc lnstalled per

Schweizer Drawlng i{o. 4636).

A standard hand-hoLe, r.,ith reiniorcing ring (F/N 1A903-1) and cover

(P/N 13913-1)r maY be lnstalted in R. H, fuselagr: fabric ar approximare

s tation 200.0 ; 'il. L. - 2.50, to f acll itate ins tal latlon of the guard.

MaEerials for this instal-iation will be furnlshed uoon request

without charge. l"Iai1 requests to Schweize_r Aircraft Corporation,

E. O. Box 14?, Elmira, New York 14902. Mention Service Bulletin tO2-26-6

and the effected shio serial number, or registration number, in your re-

ques t

This Service Bulletin should be accornnlished at the next 100-l-lour

Inspection or at t,he next Annual Inspection, whichever shaLl occur first.

S CH',.trIZEF. AIR.Cfi.AFT CC,R:OP,ATICN

ir./*^ d c-^d,

llilton A. Courtright,

meg

{uality Control Supv.

t"*

Schweizer Aircraft Corporation

P.0. Box 1lr7

Elnira, Ner.r York 1/r9OZ

August 20, 1965

We have a

Torque hrbe Bearing

SERVICE BUIIETTN N0. 102-26-5

Models S.G..S. 1-26, A, B, C

field report of

Bracket

r///t

&ps( l-rt[ L

While we believe this to

should be checked before flight by

spection. If any cracks are found,

afailure at the forr,rard Control

rxil. Effectlve aI No, 2 and up.

REr )-cft t36

be an isolated case, we feel that this point

all owners. It is readily accessible for in-

please advise us.

SCHIIIEIZER AIRCRAFT C0BPORATI 0[

h-/*,*ae*a4

l,lilton A. Courtright, /

Quality Control Supv.

-r' i _,, 'q.

.io

q ,{ " ::.r r uLi'IlGSetien

t :,?*fi August L7, L962

SEf '[ECE BULLETIN N0 ' 102-26-lr

scst 1-25 SEAT BACK

Ehore hese been oases reported where the seat back, whloh ls held

€t ttre "eottcn ond by alunlaum ollps, hes dlsengaged end moved baok sud*

dently" Thls ls hlsconcertlng to the pLlot ancl could oause loss of

eontroL ,:t, a crltlcal fllght condltLon"

It :* reeonnmended that us C routLne prefllght cheok that thls Beat

back br: rne*kecl to see that lt ls secure ln lts no:mol posltlon" If

tbe eltr-:*,2,5D-3Lr-4 are dLstortedo they should be renorkecl or replacedo

If th*:.r sre reuorked, oheck aarefully for creokso Arr alternate destgn

1s b* " lnvestlgated. and you w111 be advlsed If thls becomes aval1able"

A# . + ad.dltlonal preoautlon, EoCo0o 26-259 ls enclosedo InstalLatlon

of th:l" , 3"s opttonslp aad, we wlII furnlsh at no oharge the nocessary parts

5"f y{is1 request themo

Chlef Englneer

EI i

;

*:-'"'"

-l

cH,{}iGf,: r.enD A+ti6'fiu#Ljt?, r ro SEA,T &$ gb4hi,

MAKE FKCrd ,O4CI ECZ+-T3 ALC

(l) *,. h.l 5 A 5="116 -: I

eaq *t fi,* E

X}.R$:.-L- 6/,#

{,.3 ies}

SCF..g.\i{ {ffi,f*F) -

.31 tr.(TYp)

fl\-

\f/ ;

(3) Al.t qa AD4 Rrv [T S

lON A.1* Ar TACI-iMIF]T

ron ptrAr Br^,ai! - -

)r,

frlVf,"t- .,3

S{H}i'EiIEn Alrcfr AFr CSftP.

trFSS rr'{rHii|r.ds f}"lAfl{sfl CIRDgR

,JIV'I

::+#&q.4*it,ta,isj

f l^::.. t

,,r. i

tttt-H: *fl& -r ffi#r- T

cl(6 ETFTCTIYITY C,C}T FAnrs nrlr'c-TEo I€c9.5:*ir.L

8r w.ff*E CIRO POSTEB 7,"t*,gZ D,C. R. S[*'AL

*, 4.f. lq e,

/,{t*,4{!_ cfitcirn ,

i- :.'/ is;'l'J;T"t* t''o"t'*"n I

DSJG. HO. e'S i":- * i. -

tr a ts

t.'

3.25

ScHw[rzER AtRCRATT Conp., ELr*tRt, ru. Y.,

$exs"i-*e BB}}e#. $p*" . lQ?*t€

._TE-d*

' #*--}.;gful-E*-9

tr/fr els( l-A€ E

S c*adltloa bas b**a dlscorercd, *hlqh *oul,i!, €srlag exoasa*r* xeer *n tha

*6EIlgS-gA E}evstsr C*ntro3. Oabla at the 1A-lgS Fairlesd oa tbc Sf"x, Spale thtr*

x*er *lcnrld bs trduced by tbe loeattac of tes LA-IE8 fui"rlwd, $t X{'L*--Eo*$n tbls

s$ngLtlse tslsta oa aL.L ah3p* tn sld lealudt{i$ iibLp So. ?$"

&* acsdttloa notsd my b* ellxiseted by relocatl,oa of, th* L*-3.8S Salr*

lwil to lAiotc S.4S xc*o$tn6 to the attaebe€ sketcb.o &terietr klts for tble sek

*rs ava*-18b1* upor roqu?sto

e-AN 52 0-,034 - t6 $c fi€,r-ds

aAhJ 36"5 - I 03e F{u r5

9-q

K--l-.

S'+

#i- \\ f

s-Q

F\J

I"SO

eLp**&ffi.i4*p

ffix=aeffiffi

t*6rc!{-t, }o4}sLER .*4o u zYa I 3tle a4$r &Lc.

ira; rsaas:r*s$l the r:ccor:6:.ltshxent of thlE reloeatlos 3t t&a aar}le*t oon"

?'*rile$Gc aarl tbarough lnaSiecttca of tb€ are* as{ pertg fcr lsdlCatlca* of weer,

ilaets 8$ haur* atrtLL t&o rela*stlo* ls Esdaa

Sffiigl?.ffi AISe{ff C0APCEA?trffi{

*Htf?d*$

$&116& B" X+Clum

tiualltr Costrol. *rgomle*r

Jeaue.rg 5.p l$ffi

l$@lssh

SCHWEIZER AIRCRAFl CORP.. ELMTRA. N. Y.

S.$ig}-ce BuILStt n $o.,192-26-3

sGi I-?5. ;,. R. Cnfr t \/F

G BS{ t* d"e

/t few failures bave oecurred. tn the flel-d to the 1-26 Whoel Assenbly-*

26880lr Tlrle failure bas occured ln the stanrped flange at the ed.ge of the balt

heads. To el"i*dnata this conditlonr the fol1ow1ng procedure should be used.r ghle

is not a safety of fligbt lten, but lt rr:111 ellmlaate the posslbllity of a x,h*aL

failureo ?]re change ls belng lncorporated, ln new productlon t-25 sallplanes.

Fr*e.edr:jL*: Take ttre wheet aesembly cut of the ship and drl1l thnr the four }roles

p,t X tirat do not have bolts with a 5f16't dr111, insta}l an AN 5-dA bolt, AlfS4S

washer, and ${565-524 nut. ?hen renove the origlaal four bolts and relnstall with

3I'I945-4 isashere. $ote th.at all bolts vriLl be installed wlth the was]:er betwees

the nut end the wheel flange. (See sketeh b*loli) " The one .bolt next to the calve

stem does nqt h.ese room for the Ai.j945 rvaeher* On thls bolt use one of the exlst-

lug Ali960-516 wa*kers at JL.

AN gq,-+ {'

riTe are furnlshing tbe foJ.lowlng

4 AI{$-€'A, 7 Ai{94S*4, 4 Ai\365-5*

ltems to complete thlg modlflcatloa--

SCliiiJI.aIR AIRCRAS'T COiiF 0P*qTI 0S

(\ 'r\ l)

L-.--.4 'JC-{""w\* _ ^=

Srrest -ch'.'reizer --'

$h.ief, Engiaeer

'{{o t

O( )(

\_/

il$/aab.

ef' .t

&asc l-e{ E

I r-' Tl:cre are three altc::riate spring; us.ed 11 the l.BG to,'r r*Lease r.:3r::-fi1,trtr, .

ilc:i. field reports frorn o-.'iners, it q:ireaps ih,:::+ ere ceses of ul::''. -;:iv;-- '

:rtgh reS.oase operilting.Ioads. '..'e lave run te ste an& have dete:-:.::: :d. =--::

tire besi spring is ou"r No. Li,Ii.j-L sho',ai 6eLot':.

APPIWY

V/'RE

"IiLl 1-36rs shoriLd be 'equipped vriih thls spring. E:.e installe.ilc:: sl'io';i.l

be eheclied. by pu}iing on the :elease a?n ju;t belo',v iho iool: .:t:: cr c:d-1

sprlag scale. Tiris shoulcl reqr:ire fron 6-Ll ibs. pressu?e to:'eiease.

(See note oB page-

6-n# To Rrrctss

El:e force requlred at the release control shouli. be ncderate. C:"-ci: :,rcul:

ccftrol sj'Eten lf you t'eel ihe o-ieiattag io:ce j.s e:ic;ssive. ..:l lia:;:.c:ei

check *h,lch is used' ai ihe i'aeto:f is io ole:'ate the ri:Lease ';;h11e Loai'

is appllecl at tlro hook. &,i; 1s d,oue by q!;1]ylr;-: -?'r't?ssu)le rvith: i-a::3a

seren d,rlver ox sr.BII tar (see sketch). ?il-oi sho'uli b* ab19 to :cl'..'.ese

uader this cond.ttLon-ii.t wiLL, hcl':ever, take nore fo=co. ' 't

FTTASF

ls".

If ;*cu.!;ve anothar t1'pe of :.rTi:.r: in Tour shi3 than the 1

adf ise us arui l'ic ui}I slrip o:rr l:t no char;e .

l.a elier;ntc Telcase silst:::! '".-',-''.: cnble e n'1 pul1.c:''s ts iior.r

slnee we have hacl rectuest.i for ihis. . lirlte f c: ''ricc anC

please

6rra - .ah l6

L.l,r.i vu;.LD .

BcHwElzER AtncR*rr CoRP'. ELt\'llRA' N' Y"

ger"t'i.c;r 3u1.1e.Ltn 11'". to3-26t

J.* -:r.. ^/h

ScHwErzEP AIFICRAF? CONN*

2. fae us'e of adequate tort rings also affects tiic afcti' of ope'ration' lie

haVe a r-cport from one €troup uho experiencecl :i';e:3J' rclease irrllri" i::-

. vestiSation shoryed this to be ce.used by theul .11 a: ovsL riilg ".,rlch "'"c's

' oi=O "-Sed On D1l-L ty-Oe releasc. ;,'e recorincnci i;'r "ise Of a 2" 3;:":";:5

;;;; ;i 3-f4rr rorrnrl-i.od--prefcrably all.oy stccl-. ?;:ese are ave;lablc

, -,frc.m Scltr.:eizer jiircr-aft if iro,,. l'riiir to purciras': tEn. Sofi; ha=lcr: r1:5:

;iii ofons"tu and possibly cctl:;e jam:Li"ng cincl s--ould be avoid'ecl. L sll;--tilr

i:eavler ring sng i 2 to 2-L/2.0D lvill also vorl: an6 ean be iiaee of soii'-

er steel . g '.';

Thc release mechanisn ond rings are veiy inpo:i :lt to safeti'--cc ::ot use

. :;lekeshifts.' If 1'611 are rtsin,1 a verY strong to"; :rhle as on "':i::li'c'l' use

a safety link of'5/16" oT 1fB" sin;ie n':nilla;lle. (Use co:':'cc;:it^3s')

The onl1, other 1cror';n case of :cleaie jarr,in-1 c; : Gcl:i,'e1zer ic-': l-col<

. occurred vlhen a ere'.',rnan hooi:eo e s::nll l'"- l-i;' :n a !G-2 occi:' T':e

- uincir surte loej<ecl iha ring on the iiooic r'ak-:n-; -; i-rqlossibLe tc ::;1ease'

flie piloi reallzed that the linc had' not bcen-^' ieased and naie e' safe

J.andlng by spiraling do,:n around tire lvinch' .

In tire lnterest of all 1-26 cqvners' iYc app;.f.):r;+ pronl:t report:r'g of any

fpera'blng dlfflcqlty thst you encountert

ES/ach

Note:

tt. ' :

. j .-

The only condltion at which the hiSher release- arn pressu:e' is

d,esireable is in aero to;i in turbul-ent air srrch as in "';n-. e fIy-

ing r.rhere the glld.er r,iay overtake ine to-"; lins and cause inad.-

VAf-bent release. Ilne heavier sp:'i:r5s llay be Used' i-or sucll

conditlons as long as the operailng loais are satLsfacio:ir. If

tbe pupey.t3pe rlXease conirol is used., this vrill .be qriie sat-

ls factcry.

Eriles

chiof

c^1.,,^4-^s

Llv. rttu J. - El

grr(ra rrv vI

SGS 1 26 N33917 A D S 2016 01 23

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