### Federal Register /Vol. 65, No. 191/ Monday, October 2, 2000/ Rules and Regulations 58641

39.13 (Amended] 2. Section 3fL13 is amended 

### by adding the following new (lirworthiness directive:
2000-20-01 Turbomeca: i\mendment 39- 11912.Docket2000-NE-I1-AD. Applicability: This ADis applicable to Tllrbomec3Arrie1] A,-I A1.-1 A2.-1 n. -1 C.-1 C1.-] C2.-1 D.-1 D1,-l K.-1 K], -1 S,and-1 51 turboshah engines,Th~se engines areinstalled 011, fJ1J1 notlimiled to, th~fullowinghelicopt~r,:

Not" 1;This airworthiness dil'ective (AD] applies toeach engineid"ntified in Lile preceding appticability provision, regardless ofwhether itha5been modified, allered, or repOlired in thearea~ubjecttolhe requirements ofthis AD_ Forsngines that havebeenmodified, altered_orrepairHdso thatthejlsrform3nceoftbe requiremp,nl~of this ADis affected,theowner/operator mllst requesLapproval foranalternalive meulO_d uf comp!iallCfl

inaccord3nce with paragraph (hl ofthis AD.Thel'Oqlwst should include an Rsse~smentofthe(llleClofth~modification. atimntion. Orrepair onthe unsafecondit.ion addressed bythis AD;and, ifl.neunsafe condition has notbeen eliminated, the requestshould include specifir.proposed action~toaddress it. Compliance Required3Sindic~ted. unless accomplished previously. Topl'eventgasgeneratorrearhearing failure,which ~ouldre!;ultillall uncommand.edengine shutdown, dothe following: Required Aclion [a)Within 38deygfromtheeffeclivedate ofthis AD,ingtallachip detectorwith alectnmic warning onther~arb~aj'ingoil return Sr"L~rn

inaccordance withTurbomeca 5e)'\'iceHullelin(SB)No_292728163. Revision 1,daled.Apl'il3, 1995,paragraph 2, jmlruction~ forincol'poration.
Alternative Methods ofComptianc~ (b)Analternative method ofcompliallce or adjustment ofthecompliance time lhat provide~anacceptable lev~lof,afety maybe u,,,d ifapproved bythe Manager.Engine CorlificationOfl'ice(ECO),OpemlOr,;shall submit theirreq,wsts lhroughanappropriatt! FAAPrincipal Maintenance iaspector, who m~yadd commerllsand then send ittnthe Maiwger. ECO_ Nllt" 2:Infol'mationconcel'ningthe existence ofapproved sll.ernalivemulhods of compliantHwitb Lhig

~irworthine:;~directive, C:ommenters wishing the Fl\A to acknowledge receipt oftheir comments submitted in response to Ulis nOtIce must submit a self-addressed. stamped postcard on which the following statement is made: "Comments to Docht Number 2000- NE-11-AD," The postcard ,vill be date-stamped and returned to the r:ommenter. Regulatory Impact

The I'egulatiolls adopted herein will not have asubstantial direct effect on the States, on the relationship between the l\~tional government and the States,

or on the distribution ofpower and responsibilities among the various levels ofgovernment. TheJ'eJ'ore. in accordance with Executive Ortler 13132, il is determined thut this final rule docs not haVE!

sutTicient federalism implicatiollS to wasrant the preparation ofaFederalisn'l Asse~smE)nl, Accordingly, the FAA has not conslJltfld witb stat,,,authorities prior to publication or this proposed rule. The FAA has determined that this I'cgtJ1ation is at] emel'gency regulation. Ihal must he issued immediately to correct illlunsafe condition in aircraft and is not ()"significant regul(ltory <lctiou" under ExecutiVE!Order 12866. It has bBcn determined ful'ther thaI this action involves an.emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034. February 26. 1979), Ifit is determined that this emergeucy regulation otherwise wuuld be 8ignificanl under DOT Regulatory Policies 'lnd Procedures, IIfinal regulatory evaluation will bc prepared 3nd placed ill the Rules Docket. Acopy ofit. iffiled. Illay be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

List ofSubjects in 14 eFR Pat1 :19

Air transportation, Aircraft, Aviation s()!oly. Incorp0l'ation by reference. Safety Adoption ofthe Amendment Accordingly. pUfsuant to the authority delegated to me by the Administ.ralor. the Federal Aviation Administration ,lillcnds part39 ofTitle
101 ofthe Code ofFederal RegulaLions (14 eFR part 3~l)as follo",'"s:

PART 39-AIRWORTHINESS DIRECTIVES

1 The aUlhority citation for part 39 continues Loread as follows: Authority; 49U,S.c. 106(g1.40113,44701 EUl'oCOplf!1' AS 356 C. Eurocopler
AS 356 N2. E:llrocopter AS 350 D. Sikorsky S76A, S[korsky 57DC. EurocoplHr

AS 355 Cl. Eurocoptel' AS 350 H,
Eurocopt~r As 550 112, Sikol'sky
76A+. Eurucopter

c\S 350 HI\ Eurecopter AS 350 B2N Augu~ta A109K2 S[korsky 76A++ ifany. maybeobtained fromtheManager.

ECO. Spedal FlightPermits [c)Special flightpermits maybeiSS1Wd in accordance with §§21.197and 21.][18oftllc Fedffal Avi"tion Regulations (14CFR2] -t87 and21.199)toopHratethe aircrHftLO a lociltioJlwhere therequirements ofthis AD
canbt!a{;Lompll~h~d. tncorporation byReference (d)The actions required bythi8AD~hntl bf'performed inaccordance wiLhTurhomecu Ser'.,'iC9 IJul1etinNo. ZgZ720153.Revision 1. dated April :J, 1996.Thi81ncorpor~lion by reference wasapproved bytheDireclor01" the Federal Registerinac~ordanc~,vith 5U_S_c. 552(a)and 1 CFI{purl51.Copie, mayb<l obtain~d fromTurnomeca, li4~11IJordes Cud •• x,Fralll:e;telepllone 3359 125000:ffix 3J59 5:'11512,Copiesmaybe iIl~peLledat lheFAA,NewEnglundRegion,Oftleeoftlte RegionalCounsel. 12NewEnglandExeclIlive Park,Burlington, MA:orattheOffke ofthe Federal Register,BOO North Capitol Slr~d, NW,Suite 700,Washinglon. DC.
EffectiveDate (nlThis amendment becomcs effective011 October 17.2000. Issued inBurlington. Mas~achllSf'lIs, On Sp,plember21, 2000,
Mark C. Fulmer, Actirlg Marmger, Enginl' ond Propeller Direetoralv. AiTem!1 C,nU/i(;(J!iun SiIIlIice, JFRDoc.00-24900 Filed/3-29-00: B:45 ~rn]

BilliNG CODE4910_13--P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration



### 14CFRPart 39
[Docket No. 2000-NM-14G-AD; Amendment 39-11910; AD 2000-19-09J

RIN2nO-AA64

Airworthiness DIrectives; Boeing Model 767Series Airplanes Powered by Rolls-Royce RB211 Series Engines
AGENCY;

Federal Aviation Administralion, DOT ACTION: Final ntle: request for conunents.

SUMMARY:

This amendment adopts a
new airworthiness directive (AD)that is applicable to certain Boeing Model 767 S0ries ()irp13nes powered 

### hy l{olls-l{oyce RE211 series engines_ This action requires modiflcCltion of tbe nacelle strut and wing structure, This action is nccessary to prevonl [()tiguecracking in primary strut structure and consequent reduced structural integrity ofthe strut. This action is intended to address the identified unsafe conditi[)n. DATES: Effective Octoher 17. 2000,

### 58642 Federal Register! Vol. 65, No. 191! Monday, October 2, 2000! Rules and Regulations

The incorporation by reference of certain publications listed iu the regulations is approved by the Director ofthe Federal Register as ofOctober 17, 2000. The incorporation 

### by refel'once of BOllingService Bulletin 767-57-0053, Revision 2. dilted September 23,1999,

as listed in the regulations. was approved previously by the Director of the Federal Register as ofJuly 24, 2000 (65 FR 3784:1,junA lH. 20(0). Comments for inclusion in tbe Rules Docket must be received on orbefore December 1, 2000. ADDRESSES:

Submit comments in triplicate to tbe Federal Aviation Administration (FAA), Transport l\irplane Directorate, ANM-114, Attention: Rules Docket No. 20oo-.-NM140-I\D, 16U1Lind Avenue, SW., Renton, VI/ashington 98055--4056. Comments may be inspectfld at this locMion between !l:OO a.m, and 3:00 p.m., Monday through Friday, except Federal holiday~. COlllments mny be submitted via fax to (425) 227-1232. COL1Hnentg

may also he sent via the Internet using the following address: ganm-i'1fl,:omment@faa.gov.Comments sent via fax or the Internet must conloin "Docket No. 2000-NM-140-AD" in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must he formatted ill Microsoft Word 97 [or Windows or ASCI! text The service information referenced in this AD may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattlc, vVashington 98124-2207. This infurmation m<lvbe examined at tbe FAA. Tl'ansport Airplane Directorate, 1601 Lind Avenue, SW" RentoIl, V\,'a~hinstoll; or at the Office of tbe Fflderal Register, BOO North Capitol Street NVV.,suile 700, Washington, DC. FORFURTHER

INFORMATION

CONTACT: James Rehrl, Aerospace Engineer, Airframe Branch. ANM-120S, FAA, Seattle Aircraft Certific;}tion Office, 1601 Lind Avenue. SW., Renton. Washington 98055-4056; telephone (425) 227-2783: fax (425) 227-1181. SUPPl.EMENTARY

tNFORMATION:

The FAA ha~ received reporls indil.:ating that tlle airplane llHlllul'<lcturerhas accomplished astructural reassessment ofthe damage tolerance capobilities of the Boeing Model 767 series airplanes powered by Rolls-Royce RB211 series engines. This reassessment indicat.es that the ilctllal operalionalloads applied to the nacelle strut and wing structure

me higher than the flnalyticalloads that

were used during the initial design. Subsequent analy~is and service history. which includes numerous reports of fatigue cracking on certain strut und wing structure, indicate that fatigue cracking Cilnocc;ur OilthAprimary strnt structure before an airplane rco-ches its design service objective of20 years or 50,000 flight cycles, Analysis also indicates that such cracking. ifit were to OCCtlt,would grow at a much gnwter rate than originally expected. Fatigue cracking in primary strut structure would result in reduced structural integrity ofthe strut Explaniltion ofRdevanl Service Information Boeing recently developed a modification ofthe stl'ut-to-wing attachmenl structme installed on Boeing Model 767 series airphllles powered by Rolls-Royce RB211 series engines, This modification 8ignifkantly impl'oves the lOild-carrying capability and durability ofthe strut-to-wing attachments. Such improvement also will substantially reduce the possibility off<ltigue cracking and corrosion developing in the attachments. The FAA has reviewed and approved Boeing Service Bulletin 7l17-54-UO$Z. dated October 211,1999, which describes procedures for modification ofthe nacelle strut and wing structure. The modification consists ofthe following actions:

o Detailed visual inspections for migration ofthe midspar, upper spar. and lower spar fitting bushings and the strut side link fitting bearings ofthe strut.
o Installation ofnew tension bolts in the aft pitch load fitting and a new side link fitting ofthe wing.
o Inspection and rework ofthe side 10<ld fittings ofthe wing and rework of the fonvard pitch load fitting ofthe wing.

o Rr.placement oftnflUYoftile significantload.bearing components of the strut-to-Wing attachment 

### (e.g., rnidspar fuse pins, side links, side link fuse pin8, diagonal brace, and dii'.gonal brace fuse pins) with improved components. The service bulletin contains a formula for calculating an option<ll compliance threshnld forthe specified modificotion. This formula is intended to be used as an alternative to the 20- year calendar threshold specified in the service bulletin. In additiun, Table 2ofthe service bulletin identifies six related service bulletin modifications that must be accomplished before or at tile same time

as the modification in Boeing Service Bulletin 767-54-0082:

o 

### Boeing Service Bulletin ir;i-29- 005i:The FAA hflSreviewed and approved Boeing Service Bulletin 767- 29-0057, dated December 16, 1993, which desr.;ribes procedures for modification oft.he electrical wiring support ofthe alternating current motor pump of the m;;in hydraulk power system. The modification involves installing new hand clamps and indexstraps, and rmcertain <lirplanes, new wire support brackets on the strut bulkhead,

o GOCiil!] 

### Service BulleUn 767-5'1- 0059: The FAA has reviewed and approved Boeing Servke Bulletin 767- 54-0059, dated Julv 28, 1994, which describes procedu;es for removing the midspar hlse pin~, performing repelili.ve detailed visual inspections for cracked

orbroken sedant or migration or rot;}tion ofthE;midspar attachment fitting bushings, and accomplishing follow-on corrective actions (including replacing the bushings], it'necessary.

o Boeing Service 131l1Jelin76i-54- 0069: The FAA bas mviewed and approved Boeing Service Bulletin 767- 54-0069, Revision 1, dated lanuarv 29, 1998. which describes pror.edures~for rework ofthe side load fitting and tension f<lsteners, <IS applicable, and mplacoment ofmidspal' fuse pins with

new. higher-strength mid spar fusp pins. The rework involves increasing the size ofthe tension bolts ofthe inboard <Iud outboard side load fittings. The replacement also involvos installing
new, higher-stwngtb bolts and radius fillers in the side load fittings and backup support struchne, and inst<llling higher-stl'ength fasteners common to the front spar and rib number 8rib post

o 

### Boeing Service Builetin 767-54- 0083: The FAA has reviewed and approved Boeing Service Bulletin 767- 54-008:1. dated Septem ber 17, 199B, \vhicl1 desnibes procedmes for rc;placement ofthe upper link assembly with a new, improved assembly that will increase the strength and durability ot'the upper link inslallation, Thu! service bulletin also describes procedmes for modificution oflbe wire support brackets attached to the tIpper link.

o HoeingService Bulletin i67-54- 0088:Tbe FAA has reviewed <lnd approved Boeing Service Bulletin 767- 54-0088, Revision 1, datt,d July 29, 1999. which describes procedures for replacement ofthe upper link fuse pin 'and aft pin with new, improved pins thut will increase the strength and durability ofthe upper link installation.

~ Boc;ing SeNice Bulletin i67-57- 0053, RevfBion 1, dated October:i1, 1990:The FAA h<lspreviously issued AD 2000-12-17, amend menI39-11795 (65 FR37843, JUne 19, 2000), vl'hich r2quires repetitive inspoctions to detect fatigue cracki ng ofthe pitcl1IO<ld fitling

### federal Register/Vol. 55, No. 19l/Monday, October 2, :WOO/Rules and Regulations 58643

lugs oj'tbe wing front spar, and rework, ifnecessary, in accordance with Boeing Service Bulletin 767-57-0053, Revi~ion 2, dated Septembel' 23,1999. "NOTE 2" oftbat 1\0 states that inspections and rework accomplished prior to July 24, 2000 (the effective date ofAD 2000-12- 17) under Boeing Service Bulletin 767- 57-005:'1. dMed June 27, 1995, or Revision 1, dated October 31, 1996, are ~cceptable for compliR!lce with thRt AD. Explanation of Requirements ofthe Rule Since un unsufe condition has been identilied that is likely to exist or develop on other airplanes oIthe same type design, this AD is being issued tb prevent fatigue cracking in primary ~tI'l1t structure ;md consequent reduced structural integrity of the strut. This AD l'equires accomplishment ofthe actions specified in the service bulletins described previously, except as discussed below.
Differences Between Service Bulletin and This AD Boeing Service Bulletin 767-54-0082 recommends accompli~hment of the ilctions in BOl1ingSel'vice Bulletin 767- 57-0053, Revision '1,priur to or concurrently 1,\'illlthe actiOns ill Boeing Service Bulletin 767-54-0082. However, as uiscussed alJOve. the FAA has pHwiollsly issued AD 2000-12-17 to require Boeing Service Bulletin 767- 57-0053, Revision 2. Therefore, paragnlp!l (b) ofthis AD requires accomplishment ofBoeing Service BLllletin 767-57-0053, Revision 2, insteild of Revision 1. However, as specified in "Note 2"' ofthis AD, Revision 1 is ilcceptable for compliance with this requirement.
Cost Impact None ofthe airplanes affected by this action are on the U.S. Register. All airplanes included in the applicability ofthis rule currently ilft1operilted by non·U.S. operators under rordgn registry; therefore. they are not directly affected by this AD action. However, the FAA considers lhM this rule is necessary to ensure that the unsare condition is addressed in the event that any of these subject airplanes are imported and placed on the U.S. Register in t11efuture. The following are costs associated with lhis AD that would apply ifan affected airplane is imported and placf:!d

on the u.s. Register in the future:

• lt woulrl require apPl'Oxim,'\teJy :114 work hours to accomplish the actions described in Boeing Service Bulletin 767-54-0082, at an average labor rate of $60 pel' \Nark hour. Tllf) manufacturer has committed previousl y to its customers thaI it will bear the cost of replacement parts. As a result, the c:ost ofthose parts is not attribtltableto this AD. Based on these figures, the cost impact ofthis action would be $18,840 per airplane.

G 

## nwould t~ke approximately 16 work hours per airplane to accomplish the adions described in Boeing Service Bulletin 767-29-{]057, at all ilverage lahor rate oj $60 per \Nork hour. Rilquired parts would be provided ;:Itno cost by the airplane mallLlfactur9l". Based on these ligures, the cost impact ofthis <lction would be $960 per airplane.

G It would take approximately 6 work homs per airplane to accomplish the [lctions described in Boeing Service Bulletin 767-54-0059. at an average lahor rato of$60 per work hour. Required parts would be provided at no cost by the alrplane manufacturer. Based on these figures, the cost impact of this action would be $350 per airplane.

o Itwould take approximately 212 work hours per airplanElto accomplish lhe ~ctiOI1Sdescribed in Baaing Service Bulletin 767-53-0069, Re\'ision 1. at an average labor rate of$60 per wqrk hour. Required parts would be provided at no cost by Ule airplane manufadursr. Based on these figures. the cost impact of this action would be $12,720 per airpl[lne.

G It would take ilpPl'OxLmately 1 work hour per airplane to accomplish Ule actions described in Boeing Service Bulletin 767-54-0083, at an average labor rate of$60 per work hour. Required parts would be provided at no cost hy Lheairpl:Jne manufacturer. Based on these figures, the cosl impact ofthis action would be $60 pel' airplane.

" It would take approximately 4 work hours per airplane to accomplish the actions described in Boeing Servil:e Bulletin 767-54-0088. Revision 1. at an average labor rate of$60 per work hour. Required parts would be provided at no cost by the ilirplane manufacturer. Based on these figures, the cost impacl of this action would be S240 per airplane.

~ Itwould take approximately 5 work hours per airplane to accomplish the actions described in Boeing Service Bulletin 767-57-0053, Revi~ion 2, at an average labor rate of $60 per work hour. Based on these figures, tbe cost impact of these actions would be $300 per airplflne. Because the aclion~ described in this service bulletin are already required by another AD action, this requirement adds no ne1,\'costs for affected oper!ltors. Determination of Rule's Effective Date

Since this AD action does not affect any airplane that is currently on the U.S. register. it hilS no adverse economic impact and imposes no additional burden on any person. Therefore, prior notice and pllblic procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register.
Commenls Invited Although this action is in the form of

afinal rule ilnd was not preceded by notice and opportunity for publiC comment. comments are invited on tlus rule. Tnterested persons are invited to C'Jmml)n! on lhis rule by submitting such written data, views, or arguments

as they may desire. CommuniCJtions shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES.All communications received on or before the closing dute for comments will be considered, und this rule may be amended in light orthe C'Jmments received. Factual information that supporls the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness ofthe AD action and determining whether additional rulemakiug action would be needed. Submit comments using the following format:

g Orgilnize comments issue-by-issue. For example, discuss ilrequost to change the compliance time and a request to change the service bulletin reference as two separate issues.

G For ellch issue, state whal spf!dt'ic change to the AD is being requested.

~ Include jllstiflcation [e.g., reasons or data) for each request. Comments are specilically invited 011 the overJU regulatory. economic, enviromnental, [lnd elHlrgy aspe(.1s of the rule that might suggest a need to modHy the rule. All comment~ submitted will be available, both before and after the closing date for commenls, in (he Rules Docket for examination by interested persons. A report that summarizes each FAA-public cont~ct concerned with the substance oftllis I\D will br. nled in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their commell ts submitted in response to this rule must submit a self-addressed, slamped postcard on which the follO\ving statement is made: "Comments to Docket Number 2000-NM-140-AD." The postcard will be d<ltestamped and returned to the commenter.

### 58644 Federal Register/Vol. 65, No. 191/Monday, October 2, 2000/Rules and Regulations

Regulatory Impact

The regulations adopted herein will
not have a substantial diroct sHect on the Slates, on the relationship between Lhe lHltional Government and the States.

or on the di.<;tribulion of Dower and responsibilities among tl;c various levels of government. Therefore, it is determined that this final rule does not have federalism implications under ExecutivlJ Order 13132. For the reasons discussed above, I certify that tJ1is action (1) is not a 'significant regulatory action" under Executive Order 12866; (2) is not a "significant mle" under DOT Regulatory Policies and Procedures (44 FR 11034. February 26, HI79); and (3) will not have a significant economic impact, positive or negative. on a substantialn umber of small entities under tile oriteria of the Regulatory Flexibility Act. A final evaJuation has been prepared for this action and it is contained in the Rules Docket. A copy of it m<lYhe obtained from the Rules Docket al the location provided under tJ18 enplioll AODRESSES.
List ofSubjects in 14 eFR Part 39

Air transportation. Aircraft, Aviatian safety, .lJ1corporation by reference, Safety, Adoption ol"lhe Amentlment
Accordingly, pnrS[Jant to UlC autbority delegated to me by the Administrator, the Federal Aviation Administration amends pnrl 39 of the Federal Aviation Regulatiotls (l4 CFR part 39) as follows:

PART 39-AIRWORTHINESS DIRECTIVES

1 The anthority citation for part 39 conlinues to read as follows: Authority: ')9 u.s.e. 10li(g), 40113. 4'1-701.
§39.13 [Amended]
2. Seclion 39.13 is amended by edding the following new airworthiness directive: 2000_19_09 Boeing: Amendment 39-11910. Dockel 200Q-NM-1~0-AD. IlppJir;abihty.· Model 767 series airplanes power"d by Rolls·Royce RB211 series engines. line numbers 1 through 663 indusive. cf!rlific~ted in an)' G~legory
Note 1: This AD applies lOea~h airplane identillecl ill thHpreceding ~pplicabjJjly pJ'ovi,iun, regardles" ofwhether it h~s bflen modified. allered, or repaired ill the area subject lOthe requjrements of lhis AD. For ,tirplanes lh~t have been modified, allered. or repaired so lhat lhe performance of tl", reqtFi['~menls of lhis AD is ~ffected. lbe owner/oper;ltrJr JlJlIsl request "pproval for ~n ullemaliv~ melllotl of compliance in sccordonce wilh p~r~graph [d) ofthis AD. The J'eqllBst SllOUlJ include an nssussmenl af the ~Ifect ofthe modiJication. alteratiou. or repair on lhB wlsafe condilion addressed by this AD; and, if the unsafe condilion has !Jol been eliminated, the requAsl should include specific prOj.losed f.ctions lo addres, it. Compliance: Required U$indicated, unlilss accomplished previously, To prevent faligue crocking in pri.mary strut slrLlclme and consequent reduced ~truclllral inlegrity of the slnll, aCGomplish \h~ following'

Modifications (a) At the later ofthe times specified in paragraph (aJ(1J or (a)(2) nfthis AD, modify tIle nacelle strut and wing strUClure on both lho left ~nclright sideo of the airplane. in accordance wilh Boeing Service Bulletin 767-54-0082, dated October 28, 1999: (t) Prior to the accmnullll.ion of J7 .500 total Dight cycles, or wllhin 20 years sinc(l the dale of manufacture, whichever occurs first. Use DE the optlouallhl'Bshold formula describ"d in Figurel ofthe service buJlelin is an acceptable alternative to the 2Q'year thresbotd, provided lhallhe rldd-itional critoria specified In the service bulletin arB met; or (2) Within 3,000 flight cycles dft~r the effecliv" dnl" of this AD. (b) Prior to or concllrrenlJy wilh th" ilccompUshment of lJw modification of thil nacelle Strllt and wing structure roquirod by puragraj.lh (ol oftbis AD, as specified in paragrapb 1.D

.. Table 2, "Prior or COllLllfrent Service Bulletins," Onpag" 3 ofBoein,g Service Bulletin 76j-54-I}082. dated October 28,1999. accomplish the aClions specified in the following service butletins; Boeing Service Bulletin 767-29-0057. daled December 16, It.J!l:l:Boeing Sel'vice BulIfltin 767-54-0059. dated July 28. 1994; Boeing Service Bulletin 7b7-501-1}06>i, !{Avision 1. dated January 29, 1998; Boeing Servic(l Bulletin 7fi7-5·1-o083, daled September 17. 199B; Boeing Service Bullelin 767-54--{J08S, Revision 1. dated July 29, 1999; nnd Boeing ServicR BlIllotin 767-57-0053. Hevision 2. dated SeptembBr 23, 1999 Nole 2: AD 2ilOO-12-17, arnondment ~gt1795, require8 accompli,hmenl of Boeing Service Bulletin 7(j7-~7-0053, Revision 2. dated S~pt0mber 23.1999. However. inspeclions and rework occol1lplished in accordallce with Boeing Service Bulletin 767-S7-005J, da!Hd Juno 27. 1996, 01 Revi~icm 1, d"lsd October 31, 1991i, are acceplable for compli~nce witb the applicable oction required by paragrapb (b) of this AD.
R"p"ir (c]lf any dmnage to airplane struclme;s found dllring tbe accomplishment ofallY modification required by paragl'aph fa) or (bJ uUhis AD, and the applicoblo service bul!etiJJ "pecifies to contact Boeing for appropriate aclion, lJwn prior to furlher flight, repair in accordance wilh J melhod appro" •• J by lhe Managnr, Suatlle Aircraft Certification Office (I',CO), F/I.A_For a repair me_lJlOdto be "pproved by the Manager, Sealtle I\.CO. as reqllirer! by lhis paragraph, the M8nuger's appwl'alletlel' JIlllst 'j.lecifically rnference ll,is AD. Alternative Melhods ofCompliance (d) An allernati\'~ m"lhod ofcomplianco Or acljustmenl ofthe comj.lli"nce time that providus an occ;eptable level of safety may be used ifapproved by the Manager, Seattle ACO. Operators shall submitlheir request" tbrough an. appropriate FAA I'rincij.lal MBintilnanCll tnspector, who may add
comments and then send il to the Manoger, S",atlJo ACO,
NDle 3: lnformotion concerning lhe existence ofapproved slternJtive methods of compliance with Ihis AD, Ifau)', may be obtained from the Seattle ACO,
Spedal Flight Permits
tel SpAcialllight p"'Illits may be i:;sucd in accordance with soctions 21.H17R.nd 21.19S ofthe FedBral Aviation Hegll1ations (1~ CFH 21_197 and 21.199J l()operat8tho airplnnH lO

a loc.ation where the mquircmonl:; of lhis AD

can be accomplisher! ["corpDration hy Reference (0 EXC"pl as provided by paragraph [c] M this AD, the aClions shall be dono in accordanco with BOHing_ Sen'ice Bulletin 7B7-~4--D082. d'Jted Oclober 21;,-I 9S9: Boeing Service .BIlIlBlin 767-29-00~7, d"led December 15, 1S9J: 130eing Service Bullel in 757-S4-{lOS9. daled July 21;, 1994: Boeing Service Blillelin 7li7-54-00f;9, Kevision 1, dilled ["Tluary 29, '1!.I9s: Boeilli; ServiCA Ilulletin 767-54-0083, daled September 17, 1998; Boeing Service Bllll(lliIl 767-54-0088, KevisiQn 1. daled July 29. H198; ond LJoeing Sen'ice BullBtin 767-57--D053. Revision 2, dated September 23, 1999: as applicahle. (1] The incorporalion by reference of Bo"ing Service Bulletin 757-54-0082, doted October 28, E199; Boeing Service Bulletin 767-29-0057, dated Decemher 16. l!j\J:J: Boeing Service Bulletin 767-54-0059. dated Jltly 23, 1994; Boeing Sel'vlc~ IhlilHlin 757- .~'I----{l069.

R~"ision L d,Hed [alt1i~r)' 29. Hl'lS; Boeing Service Bulletin 767-54-0083, d~\ed SsptBmber 17, 19911;and Boeing ServicA Bulletin 767-501-0088, Revision 1. dnlAd July 29, 19S9: is al'provBrI by LILe Dircclor of lJw Federal RegistBf. in accord~ncl' witll 5 U,S,c. 552(a) and 1 eFR part 51. (2) The i.ncoJ'poration by reference of Boeing Servicl' Bulletin 767-57-0053. Revi"ioll 2. dated S"ptmnbol" 23. 1D99. was approved previously by the Djre~lor ollh" Federal Register as ofJuly 24. 2000 (65 FR 37843, June 19. 2000). (;l] Copies may be oblained from Boeing Commercial Airplane Grollp. P.O. Box 3707, Sliallle, Washington 98124-2207. COj.liesINl)' b" il'lsP~CI~d althe FAA. Transport Airplane Directorote, 1601 Lind Avenue, sw_.r'"nlolJ. Vlia,hinglon; or ~llhe Office oft),o Federal Register. eon NOrlJl Capitol Slreet. NW" suile 700. W3shington. DC.

Elfeclive Dale (g] This am\i-ndment becomes effective on Ortolmr 17, 2000.

### Federal Register/VoL 65, No, 191/Monrlay. October 2. 2000/Rules and Regulations 58645

lssued in RHnlnll, Wa~hinglon, On September 21. 200n, Dnnald I., Riggin. Actin!) M(JJJ(Jg"r, 1'ran.'por/ Airpl(lnn Dime/om/e,fliu:ro// CL'rlifjGrltiol1 Snvic".
IFH DOG.00-24751 I·'iled 'l-20-DO: 8:45 ami

BILliNG CODE 4910_n_p

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39
IDocket No. 200Q-NE-38-AO; Amendment 39-11913: AD 2000-20-02)

RIN 212Q-AA64

Airworthiness Directives; General Electric Company CF6-50 Series Turbofan Engines

AGENCY:

Federal AviatiOll Administration, DOT. ACTION:FLnal rule: requllst for comments.

SUMMARY:

This amendment adopts a
new airworthiness directive (AD) that is applicable to General Eledric Compauy (GE) CF6-50 series turbofan engines, This action requires inspection of the low pressure turhille nozzle lock assenlblies, ilnd replacement of the borescope plug with a new design plug. This amendment is prompted by three lll1conWilled engine failures, The actions specified in this AD are inlended to detect loose or missing LPT nozzle lock a~sembly studs Ihat could lead to failure of the locks and subsequent uncontained failure oftho engine.
OATES:Efi'ective October 17, ZOOO. The incorp0l'iltion by reference of cert"in publications listed in the rule is approved 

### by the Director ollhe Federal Register as ofOctober 17, 2000. Comments 1'01'

inclusion In LheRules Docket must be rer.eived on or before December 1, ZOOO, ADDRESSES:Submit comments in triplicate to the Feder;]l Aviation Administration (FAA), New England Region, Office ofthe Regional Counsel, Attention: Ruies Docket No. ZOOO-NE38-.'\D. 12 New England Executive Park. Burlington, MA OlB03-5299, Comments may also be sent via the InterrH)t using the following address: "9-aneadr.omment@faa.gov
.,Comments sent via the Internet must contain the docket number in the subject line. The servicp, information referenced in this AD mav be obtained rrom Ceneml Electric COl~pany via Lockhued Miutin Technology Sf!I'\'icf!s. 10525 Che~ter Road, Suite C, Cincinnati, OIJio 45215, telephone (513) 572-8400, fax (513) 672-8422. This information may be examined at lhe FAA. New England Rpgion, Office ofthe Regional Counsel, 12 New England Executivp Park, Burl ington, MA; or at tbe Office or the Federal Register. 800 North C"pitol Street, NW" suite 700, Washington. DC.
FORFURTHER

tNFORMATION

CONTACT: K"ren Curtis, Aorospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299: telephone: (781)238-7192,

rax: (781) 238-7199.
SUPPLEMENTARY

INFORMATION:

On .'\pril 25, 2000, a DC10-3D experienced an uncontained engine failure during takeoff, Ground inspection found uncontainment ofthe low pressmc turbine (LPT) case, airplane dal:'lage. and ingpstion damage to the other two engines. An investigation revealed that thb' failure ofstage 2LPT nozzle lock agSemblies made orWaspalloy material resulted in the uncontained failure of all stage 2 nozzle segments, Since that time, there have been two

more uncontained engine failures, on September 5,2000, and September 7, 2000, that have been attributed to the railure ofWasp alloy stage 2LPT nozzle lock assembly studs.
Before these three events, there had been two uncontained failures of stage 2LPT nozzle lor.k assemblies made or Rene 41 material. Olle failure was in April 1£101which was contained within the cowl with no damage to the airplane, and one in 1996 that also penetrated the cowl and resulted in mi.nor dmn"ge to the airplane, There

was also aile unscheduled engine removal (UER) for hroken Rene 41 nozzle lock assembly studs in 1997 and two UER's for broken Waspalloy assemblies: one in January 1999, and

one in December 1999.
Loose or mIssing LPT nozzle lock assembly studs could lead to I'ailure of the locks and subsequent uncontained failure ofthe engine,
Manufacturer's Service Information

Tho FAA has reviewed and approvad the todmical contents or GEAlerl Service Bulletin (ASB] CF6-50 72- A1196. dated Septeillber 15, 2000, that describes procedures for replacing the existing stage ZLPT uOl.zle borescope plug, part nUlTlber (PIN) 9022M63G13, wilh borescope plug 

### PIN 2083M99P01. This new plug provides an additional antirotation feature for the nozzle segments in the event of failure of Ihe nozzle lor.ks, Inlerim Aclion Requirements orThis 

### AD
Since an unsafe condition hilS been identified Lhatis likely to exist 01' develop on olher GE CF6-50 series turbo ran engilles ofthe same type design, this AD is being issued as an interim acHon to detect loose or missing LPT nozzle lock assembly studs that could lead to failure ofthc lock assemblies. and subsequent uncontained fflUme ot' tlle engine. Tl1is AD requires:

" Initial and repetitive inspections of the lock assemblies ror loose or missing studs.

'" Replacement ofall ofthe stage 2 LPT lock assemblies with new assemblies berore further Hight ifa loose

or missing stud i~found.

" Installation ofborcscope plugP/N 2083M99P01. This nm'! borescope plug is designed to prevent rotation ofthe stage 2 LPT nozzlt ifthe nozzle lock assemblies fail.

" Inspection ofthe area surrounding the borescope plug for evidence of buckling or cracks whenever the nozzle lock studs are inspected.

" Replacement of the LPT stator Cllse assembly with a sp.rviceable part before further flight irany buckling or cracks

are found. The borcscope plug must be replaced

as specified in ASB CF6-50 i2-Al1iJ(:i,
lmmediale Adoption ofThis i\D
Since a situation exists that requires the immediate adoption ofthis regulation, it is found that notice and opportunity for prior puhlic comment hAreon arc impracticable, and that good

cause exists for making this amendment effective in less than ;JOdays.
Comments Invited Although this action is in the form of

a final rule that involves requirements E.ffecling flight safety and, thus. \I\.'1IS not preceded by notice and an opportunity for public comment, commenls are invited on this rule. Interested persons
are invited to comment on thi, rule by snbmitting such written data, views. or arguments as they may desire. Communications should identify the Rules Docket number and be submitted ill triplicate to the address specil'ied under the caption ADDRESSES.All communications receivHd on or before tlw dosing date for comments will be considered. and this rule lllay be amended in light ofthe comments received. Far.tual information that supports the r,ommenter's ideas and suggestiolls is extremely helpful in evaluating the effectiveneS5 of the AD action and determining whether