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FedenJI --\\"iatinll Atiministration

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Airworthiness Direclives: Airbll$ ~,..Iodd A10{J S<:nt:S Airplall.:'s

.\GF:~CY: F.:ucral .'\\'iation Atlmillislralil1ll (FAA). 1)01'.

.-\CTI 0;'11; \\llic.: ()r p roposL'J nllel11aking, (;--:PR \1),

Sl:.\ll\lARY: WL' propose 10 adopt;1 11<:\\:lln\11r1hilli.'S:; dir<:l:II\L'i:\!Jl I'lf Ill:.: prI'Hiu<.:1

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In aeeor,blll:L' \\'ith design rcgul:llillll. lhc TIIS ..••.[lrill!l11ahk h06/,\111\;I\

st~lbilizo..:r:ll::tuawrllus a fails:ll'c tksign. Its upper auat:!llTl.:11I1\1Ill..:

<lo..:roplano.::tws two lond palhs. <lPrim:1r)' I.oad P:l1h (Pl.P) :llltl a SL'CLll1t!:Jry

Load Path IS!.!», which is lInly L'ngaged ill case lll'I)[ P 1~Il[lIr\' 1\\lluwlng

the lksign intent, cngag<:mo.::nl01'11l..::-SI.P k:;:Ids!Ll jam tho..:THS,-\,

indic:uing Ihl,,'i":lilure ,l!"chl,,' PLP.

TIlls ("lladll lOll uf PLP f;ulure dllring ;111ex(enJe-d p~'n .\.] ,If tim •...:f n.'1

JCIl,,'("!.:-d:lnd ..:,~rro.::ch:d. would IL";'.1\11 th~~nlpturc "fll;~' -J'II:->.-\\!)1]\'::'

;.lll;lI::"l1I11L'lll ~l)ld C<'>JlSCyU<:111 l"HS.·\ hh" of C<1111JllJnd. r~'~1I1til1~ 111 r<:dll\'L'd

c011lml or th~' :lo.::rlJpJanc.

Tesls clrricd OUI under lhe l(lnJ$·nl('<lst.r~'J during r(;p;~·so.::nt<!.tl\·c lli;;hts

hah' delllLlnstrated th:H, \\ht."n Ih~'SI.I' is .::ngag"d. il .1,10 ]],)1

sYSlo.::m:.ltil"all~ .Iam ,he THS_·\. In addition, l:l!:Joralory lo..:SI5h~'\L~ conti:TIlt."J

Illa! tll.: SLP wtll \)[':ly witllscmd IhL' 1(,'1.1"for a l11mlL'J p~'rhl,1"f1HnL'.

cOlluilioll as:

:IllUcorrecl an lI11:-.<l[i: .:ondiljon on an :t\"iati,lll product. TilL· \1(

FAA Form 1360·14,1 (6,89) OFFICIAL FILE COPY
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This condition ofPLP failure during an extended period of time, ifnot

detected and corrected, would lead to the rupture of the THSA upper

attac-hment and consequent THSA Joss o"fcommand, resulting in reducc-d

control of the aeroplane.

Tests carried out underthe loads-measured during representative flights

have demonstrated that, when fhe SLP is engaged, it does not

systematically jam the THSA. In addition. laboratory tests have confirmed

that the SlP will only withstand the loads for a limited period oftimc.

In <lccordunce with design regulation, (h~ THSA [trimmable horizontal

stabilizer actuator] has a failsafe design. illS upper attachment to the

aeroplane has two load paths, a Primary ~oad Path (PLP) and a Secondary

Load Path (SLP), which is only engaged in case of PLP failure. Following

the design intent, engagement of the SL~ leads to jam the THSA,

indicating the failure of the PLP _ I

condition as:

and correct an unsafe condition on an aviation product. The MeAt describes the unsa

information (MeAt) originated by an aviation authority of another country to identify

listed above. This proposed AD results from mandawry continuing airworthiness

ACTION: Notice of proposed rulemaking (NPRM).

IDockef No. FAA-2010-**±**~Directorate Identifier 2010-NM-076-AD]

14910-13

,

AGENCY: Federal Aviation Administration (F~L\A),DOT.

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Airworthiness Directives; Airbus Model A30q Senes Airplanes

RIN 2120-AA64

DEPARTMENT OF TR,,""SPORTATION

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the produc

Federal Aviation Administration

14 CFR Part 39

• • * * • * *

FAA Form 1360·14.1 (5-89)

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OFFICIAL FILE CO~Y

-(> U,S. GOVERl-oiIM:tiT PRltiTlNG OFF,CE, '995 ·769·2"