### Federal Register! Vol. 68, No. 19! Wednesday. January 29, 2003! Rules and Regulations

."Tle~ specified in paragraphs (CHll(i)and (c](l](ii) ofthis AD. 0] Within 12,000flightcycles or42 month~ after doing th~ [eplaC~nlentpp.r paragraph (a) ofthis AD. whichever is first. (il) Withi[] 12 mouths afterthe effective dat~ ofthis AD. (2] For all other airplanes: Within 12,000 flight crcle~ or42 mflnthsafterthe effective date urthis AD,whichever is fi[i;l. (eI) For airplJnes having actuators with rou end assemblies PINs 65--44760-28and 5H73'185-9; Ifmaintenance fec:ordsshow that the assefllblLus

Oilthe airplan" wereneve. cbanged. orwereexchang"rlwith arod end assembly directly acquired fromBoeingur Parker Hannifin. and werenot part-marked by vihm-"ngraving or other part markings t.hiJ.l penlllmtll111<'

,;urface,this i,;considered acceplablv forcompliance with the actions specified io paragraph (~)ofthis AD.

COITeclive Aaion le) Ifvibro-engravingi5fmmdduring the inspection required byparagraph (c)ofthis AD;B.p.fol'e

further f1ighl,reworkorreplace the affecl~drod end with anew rod end, as applicable, pertimWorklnslluclions of Boeing AlertService Bulletin 737--27 A1243, dat~d July26, 2001, excluding Evaluation Form.

Part fllStailation [lJAltp.r the effe~tivedllt('ofthis AD,no persoll shall inst1l11

OllJllY~irplane ,t rod eud having vibro·e[]graving,orether part markings thal penetrate lhe ~Llrface, unless tbat part has been reworked as required hy this AD.

illternoti"e Methods o[CompliQflCC [gIU)An alternative metbod ofcompliance

or adjustment ofthe compliance time that provides an acceptable levelofsafety may be us~d ifllpproved bythe MmIag~r,Seattle Aircraft Cf,rtificationOffice(ACO).FAA. Operators shall submit their reqllests through

an appropriate FAr\ Principal Maintenance Inspector, who mllYadd comments and then s~nd it to the Manager. $eallll' ACO, (2)Alternative methods ofcompliance, llpprov~dpr~viou.>ly

in accordance with AD 2.000-02-03, amendment 39-11521, are appruvlld as aitelllalive lll~thods of compliance wiU,paragraph (a]ofthis AD. Note 3: [nfomlalion GOl'lc~rning the "xisl[!nc~ofappwv~d lllternat1vemethods of compliance with this .".0,ifany, may he ohtailled fromlhe S~nttl\!,\CO.

Special Flight Permits (h] Special flight permit, maybe issued in aGcordauceWiUl

sections 21.197 and 21.199 ofthe Federal Aviation Regulation>(14eFR 21.197 and 21.199) to operate the airplane to

~lor-alionwh"re the reqllirem~nts ofthis AD

can be a(:comp1ish~d.
Jncorporalioll by Reference
(i] Unless olherwise specified inthis AD, the actions shall be dOllein acc-ordancewith Boeing AlertService Bulletin 737-27AI211, dated November 19,1998, BoeingAlert Servi~eBnlletin 737-27A1211.Revi~ion 1, dated December9. 1999.or Boei.ng Alert Servfc~Bulletin /37-27AI211, Revision 2, dated December21. 2000,including Information Nutice 737-27A1211lN 03, dated July26,2001. excluding Evaillalion Form; and BoeingAlert Service Bulletin 737- 271\J243, dated July26, 2001, excluding Evaluation Form~asapplicable. (1)The incorporation byreference of BoeiligA[~rtServiceBoll~liil737-27A1243, dated July 26,2001, excluding Evaluation Form; and BoeingAl~rtService Bulletin n7- 27A1211,Revision~, dat'ld December21, 2000,including InformationNolice 737- 27A1211 [N03, dated July :W. 2001. excluding Evaluation Form: is approved by the Dirm:torofthe Fedeml Registerin accordance with

~U.S.G.552(a)~nd 1 CFR

1-'1I1t51. (2)The incorporation byreference of Bb~ingAlert Service Bulletin 737-27A1211, dated November 19, 1988: and BoeingAlert Servi(:eBulletin 737<!7A121l, Revision 1, dated December9, 1999;was approved previously by th~Directorofthe Federal R~gi,;ter as ofFebruary 29,2000 (65FR3801. ]alluary 25,2000). (3)Copies may beobtailled ff()mB(lsing Commercial Airplane Group, p.o. Box 3707, Seatlle. Washington 98124-2207. Copi~smay b~inspe(;llldatthe FA,\, Tran,port Airplane Dire~torate, 1601 LilldAvenue, SW.,Reilton, Washington; orat the Officeofthe Federal Register,eoo North Capitol Street. NW

.. Suite 700, Washington, DC.
f.ffecti"" Dale (j) This amendment becOllleseffectiveall March 5. 2003.
Issned in Renton. Washington. 011 January 22.2003. Vi L.Lipski, Manager, Tmnsporl Ai"plane Directomlr, Aircraft Certificrltion Service. IFRDoc,0.3-1832Filed 1-2.8-{)3:8:45 amI

BILLING CODE 4910_13--fl

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration



### 14 CFR Part 39
(Docket No. z002-NM-308-AD; AmGndment 39-13026; AD2003-{)3...(12]

RIN 2120-AA64

Airworthiness Directives; Boeing Model 767 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT. ACTION: Final rule; request for comments,

SUMMARY:

This amendment supersedes

an existing airworthiness directive (ADJ, applicable to all Boeing Model 7li7 seriss airplanss, that currellIly requires repetitive detailed a(ld eddy curre(lt inspections to detect cracks of certain midspar fuse pins, and replacemsnt of any cracked mirlspar fuse pin with a
new fuse pin, Thisamenrlment reduces certain compliance times for certain inspections, expands the detailed and eddy CutTent inspections, and limits the applicability in the existing AD. This amendment also pwvides for optional terminating action, which ends \he repetitive inspections. The actions specified in this AD are intended to prevent loss ofilie strut and engine due
to corrosion damage and cracking of both fuse pins on the same strut. This action is intended to address the identified unsafe condition. DATES: Effective February 13, 2003. The incorporation by reference of a certain publication, as listed in \hs regulations, is approved by the Director ofthe Federal Register as ofFebruary 13, 2003, The incorporation by refsrence of Boeing Alert Service Bulletin 767- 54A0062. dated April 14, 1904, as listed in the regulations, was approved proviously by the Director oftlIe Federal Registsr as ofJuue 10, 1994 (59 FR 27229, May 26, 1994). Comments for inclusion in the Rules Docket must be received on ur before March 31. 20U3. ADDRESSES:

Submil comments in triplicate to the Federal Aviation Administration [FAA), Trall$port Airplane Directorate, ANM-l14, Attention: Rules Docket No. 2U02-NM308-AD, 1601 Lind Avenue, SW., Renton, Washingtoll 98055--4056, Comments may be inspected at this location between 9 a.m. and :3p.m., Monday through friday, except F'ederal holidays. Comments may be submitted via fax to [425) 2"0-1232. Comments may also be sent via the Intel11et using the following address: 9-anm

### iarcomment@jaa.gov. Comm<Jnts sent via fax or the Internet musl conlain "Docket No. 20U2-NM-308-AD" in tbe subject line and need not be submitted ill triplicate. Comment,; senl via lhe Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text. The service information referenced in this AD may be obtained fcom Boeing Commercial Airplans Group, PO Bux 3707, Seattle, Washington 98124-2207. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW" Renton, Washington; or at the Office of the Fedsral Rsgister. 80a North Capito! Stroet, NW" suile 700, Washington, DC, FORFURTHER

INFORMATION

CONTACT: Suzanne Masterson, Aerospace Engil1eer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1501 Lind Avenue, SW., Renton, Washington ,18055-4056; telephons (425) 227-2772: fax (425) 2:.<7-1181.

### Federal Register/Vol. 68, No. 19/Wedncsday, January 29, 2003/Rules and Regulations 4375

SUPPl£MENTARY INFORMATION: On May 18, 1994. the FAA issued AD 94-11-02, amendment 39-8918 (59 FR 27229, June 10.1994), applicable to all Boeing Model 767 series airplanes. to require repetitive detailed visual and eddy
current inspections to detect cracks of certain midspar fuse pins, and replacement of any cracked midspar fuse pin with a new fuse pin. That actinn was prompted by reports of longitudinal fatigue cracks on certain midspar fuse pins installed on Boeing Model 767 series airplanes. The actions required by that AD are intended to prevent loss ofthe strut and engine due
to cracking ofboth fuse pins on the

same strut.
A<:tio!ls Since Issuance ofPrevious Rule
Since the issuance ofAD \)4-11-02,

an operator has reporled a fractured outboard midspar fuse pin [part number [PIN) 311T3102-1) ofthe left engine pylon, which was found during a scheduled maintenaflce visit. The fuse pin also bad corrosion on the pin and within the hore. The airphme had accumulated 9,456 tolal flight cydes, and 38,911 totill flight bours. Tbe initial inspoction for airplanes with midspar fuse pins having PIN 311T3102-1, as required by AD 94-11-02, begins prior to the accumulation of 15,000 tolal landings on the fuse pin. or within 90 days after tbe effective dale ofthe existing AD, whichever occurs later. In light ofthis information, the FAA finds it necessary to reduce tbe complianC1l time for the initial inspection for airplanes with midspar fuse pins. This AD illso includes inspecting for corrosion ofthe midspar fuse pins, in addition to cracks, and limits the applicability in the existing AD. J':xplanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin 767- 54All062, Revision 5, dated November 11,2002 (Boeing .'\Iert Service Bulletin 767-54A0062. dated April 14, 1994, \Vas referenced in the existing AD for accomplishment of the actions specified). Revision 5 of the service bulletin reduces certain compliance times, references certain ilctions specified in related service bulletins that would eliminate the need for Ihe repetitive inspections, and clarifies certain procedures. Revision 5 describes procedures for repetitive detailed and eddy current inspections for cracks and corrosion of certain midspar fuse pins, and replacement of any cracked midspar fuse pin with a new fuse pin. The service bulletin also describes procedures for a magnetic particle inspection to verify cracks iftbe fuse pins are removed from the strut. Accomplishment ofIhe actions specified in the service bulletin is intended to adequately address the identified unsafe condition.

Related ADs
This AD provides iln optional terminating action fOtthe repetitive inspections by accomplishment ofthe modification ofthe nacelle strut and wing structure required by tbe following ADs: AD 2000-1\)-09, amendment 39- 1HIlO (65 FR 58641, October 17, 2000), which is applicable to certain Boeing Model 767 series airplanes powered by Rolls-Royce RB211 series engines; AD 2001-02-07, amendment 39- 12091 (66 FR 8085, March 5, 2000, which is applicilble to certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines; and AD 2001-06-12. amendment 39- 12159 (66 FR 17492, May 7, 2001}, which is applicable to certain Boeing Mode! 767 series airplanes powered by General Electric engines. All the previous ADs require prior or concurrent accomplishment ofthe following service bulletins, which are specified in Service Bulletin 767- 54A0062, Revision 5. as the appropriate

sources of service information for accomplishment of the rework of the side load fitting and tension fasteners,

as applicable. and replacement of midspar fuse pins or modification ofthe nacelle strut ilnd wing structure. Doing either oftbese actions would eliminate the need for the repetitive inspections specified in Service Bulletin 767- 54A0062, Revision 5.

•• Boeing Service Bulletin 767-54- 0069, Revision], dilled January 29, 1998, describes procedures for rework of the side load fitting and tension fasteners, ilSapplicable. and replacement of midspar fuse pins with
new, higber-strength midspar fuse pins. The rework involves increasing the size ofthe tension bolts of the inboard and outboard side load fittings. The replacement also involves installing
new, higher-strength bolts and radius fillers in the side load fittings and backup support structure, and insta!Jing bigher-stren.gth fasteners common to the front spar and rih number 8 rib post.

• Boeing Service Bulletin 767-54- 0080, dated October 7, 1999, describes procedures for modification of the nacelle strut and wing structure. The modification consists of replacing many ofthe significant load-bearing components ofthe strut [e.g., the side link fittings ilssemblics, the midspar fittings. the side load fittings, certilin fuse bolt assemblies) with improved components.

• Boeing Service Bulletin 767-54- 0081, daled July 29, 1999, describes procedures for modification ofthe nilceHe strut and wing structure. The modification consists of replacing many ofthe significant load-bearing components of the strut and wing (e.g

.. the side link fittings, the midspar fittings, the side load fittings, certilin fuse pin assemblies) with improved components.

• Boeing Service Bulletin 767-54- 0082, dated October 28, 1999. describes prucadures for modification oftbe Dilcelle strut and wing structure. The modification consists ofreplacing many ofthe signiGcant load-bearing componenl~ ofthe strut-ta-wing attachment [e,g

.. midspar fuse pins. side links, side link fuse pins, diagoll<ll br<lce,and diagonal brace fuse pins) with improved components. Explanation of Require men Is of Rule
Since an unsafe condition has been identified that is likely 10exist or develop on other airplanes of this silme type design, this AD supersedes AD 94- 11-02 to continue to require repetit.ive detailed and eddy current inspections to detect cracks of certilin midspar fuse pins. and replacement of any cracked midspar fuse pin with iInew fuse pin. This AD reduces certain cornpliauce limes for certain inspections. expiluds C1lrtilindetililed and eddy curreDl inspections. ilnd limits the applicability in the existing AD,
Difference Between This AD and Service Bulletin Boeing Alert Service Bulletin 767- 54AOUGz,Revision 5, specifies that all HI;tioTls for which the Hoeing 767 Airpl<Jllc Maintenance Manuill (AMM) is specified as the appropriate sourOl of service information for work instructions may instead be dOlle according to an "operiltor's equivalent procedure." However. this AD requires that engine removill ilnd support. when any fuse pin is removed from a strut, must be accomplisbed per the procedures specified the ilpplicable section of the AMM. An "operator's equivalent procedure" may be used only if approved as an alternati~'e method of compliance per paragmph (0)(1) of this AD. Explanation of Change Made to Existing Requirements

The FAA has cbanged all references
to a "detailed visual inspection" in the existing AD to "detailed inspection" ill this AD. Additionally, a note has been

### 4376 Federal Register/Vol. 68, No. 19/Wednesday, January 29, 2003/Rules and Regulations

added to this AD to defille that inspection,

Determination of Rule's Effective Date

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon arc impracticable, and that good

cause exists for making this amendment effective in less than 30 days.

Comments Invited Although this action is in the form of

a final rule that involves requirements affecting flight safety aod. thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons

are invited to comment on this rule by submitting such wrillen data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received 011or before the dosing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas alld suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemakiug action would be needed. 

### Submit comments using thefollowing format:

~ Organize comments issue-by-issue. For example. discuss a request to r:hange Lile compliance time and a request to 

### Ghunge the servke bulletin reference as lwu separate issues.

~ ror each issue. state what specific ch'lIlge to the AD is being requested.

~ Include justification (e.g., reasons or data) for eat:h rcqu8s!' Cumments are specifically invited on the overall regulatory. eculJomic, environmental. and energy aspel;:ts of the rule that might suggest a need to modify the rule, AU comments submitted will be available. botb beforf! and after the closing date for I;:omments, in the Rules Docket for examination by interested per suns. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response tu this rule must submit a self·addressed, stamped postcard on which the following
statement is made: "Comments to Docket Number 2002-NM-308-AD," The postcard will be date stamped and returned to the commeuter. Regulatory Impact
The regulations adopted herein will not have a substantial direct effect on the States. on the relationship between the national Government and the States,

or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26. 1979). Ifit is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed. may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

Usl of Su.bjects in 14 CFR Parl 39
Air transportation. Aircraft, Aviation safety, Incorporation by reference. Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, tbe Federal Avilltion Administratlon amends part ~9 orthe Federal Aviatiun Regulations (14 CFR part 39) 85 follows:

PART 39-AIRWORTHINESS DIRECTlVES

t. The authority citation for part 39 continues to read as follows: Authority: 49 U.s.c. 10B[g).4Ul1J, 44701.

§39.13 IAmendedi
2. Section 39,13 is amended hy removing amendment 39-8918 (59 FR 27229, June 10. 1994), and by adding a
new airworthiness directive (AD). amendment 39-13026. to read as follows:
2003-03-02 Boeing: Amendment 39-13026. Docket 2002---NM-308-AD. Supersedes AD 94-11-02, Amendment 39--8918. Applfcability: Model 767-200. -300. and -300F series airplanes, as listed in Boeing Alerl Service Hul1etin 757-54A006Z. Revision 5. daled November II, 200Z: certificated in any category. Nole 1: This ADapplies to each airplane identified in the preceding applicability pro"isioD, regarrlless ofwhether ithas been modified. altered. or repaired in the area subject to the requirements ofthis AD. for airplanes that have beeDmodified, altered, ur repaired so that th" performance ofthe requirements ofthis ADis affaded. the owner/opmator must request approval for an alternative method ofcompliance in accordance with pamgrnph [0)[11ofthis AD_ The request should include an assessment oj the effl.'Ct

ofthe modification. alteration. or repair on the unsafe condition addressed by this AD: and, ifthe unsafe coodition has not been eliminated. the request snould include specific proposed actions to address iL Compliance; Required as indicated. unless accomplished previously. To pre.•. ent loss ofthe strut and engine du" to corrosion damage and cracking ofboth fusu pius on the same strut, accomplish the following:

Restatement ofRequirements ofAD 9'1-11- 0' Repetilive Inspections [a)For airplanes having midspar fuse piDS, part number (PIN) 3111'3102-1: Perform a detailed inspection and an eddy o:;urrenl inspection 10detect cracks ofthe midspar fuse pins, in accordance with SOlOing Alert Service Bulletin 767-54Ae062. dated April 14,199'1; or Boeing Alerl Service Bulletin 767--..'>4,0.0062.

Revision 5. datad November 11.2002; at the time specified in paragraph (a)(l). (all2). (al{3].or (a](4)ofthis AD. as applic~ble. Repeat these inspectiuns lhereafiur at inturvals nollo exceed 3,000 landings until accomplishment ofthe initial inspectiOllS specified iDparagraph (h]llf lhis AD. Note 2: Fo" the purposes ufthis AD. a detailed iUiipectiuDis defined as; ··Ao inlensive visual examination ofa specific stru~lural area, system, installation, or assembly to detect damage. failure. or inegularily. Availclble lighting is normally supplemented with a direcl source ofgood lighiing at intensity deemed appropriate by lhe inspeclor,lnsptldion aids such as mirror, magnifying lUllses,ete" may be used. Surfac!: cleaniug and elaborate aco:;esS procedures may be required," (I) l'·orairplanes having midspar fuse pins that have accumulated 18.000 or more total landings as ofJune 10. 1994 {theeffective Mle ofAD 94-11-02. amendment 39-8916}, accomplish the inspections within 60 days after June to, 1994. [2) For airplanes having midspar fuse pins that have accumulated lS.000 or more lola! landings. but less than ]8,000 total landings.

as ofJune 10, 1994. accomplish the inspllctions within 90 days afler June 10. 1994.

### federal Register/Vol. 68, No. 19/Wedncsday, January 29, 2003/Rulcs and Regulations 4377

(3) For airplaues having midspar fuse pins that bave accumulated 10,000 or more total landin[:s, but less thall 15,000 total landings,

as of June 10, 1994, accomplish the inspections within 120 days afier June 10, 1994, (4) For airplanes having midspar fuse pins that have accumulated less than 10,000 total landings as of Tune lO, 19[14, accomplish the inspections prior 10the acr;umwation of 10,000 lotal laudings on the fuse pin. or within 120 day" after June 10,1994, whichever o(:curs later. (b) ['or airplanes havillg a midspar htse pin, PIN 3111'3102-2 or 31lT2102-1, Prior to the accumulation of 15,000 total landings Oll the f,,se pin, Drwithin ~o day~ after June 10, HHH, whi~he"er occu,s later, perform a d~taiJed illSpe~tion and an erldy Cllrrent inspection to detect ~rack:; on the midspar fuse pins, in accordance wilh Bodng Alert Service Bulletin 767-54A0062, dated April 14,18'014: or Boeing Alert Service Bulletiu 767-54A0062, Revision 5, dated November 11, 20U2. Repeat these illspectiolls thereafter
at intervals not to exo.;eed 3,UUOlanding, until accomplishment of paragraph [h) of this AD.
Replacerrwnll1lupulili"'c Inspeclions (cJ Ifany crack i, found during an insper:lion required by pamgraph [a) or (b) of this AD, prior to further !light, replace the cracked midspar fuse pin with a new fuse pin, in accordance with BOBing Alert Service Bulletin 7(;7-54A0062, dated April 14, 1994;

or Boeing Alert Servic~ Bull~lin 767- 54A0062, Revision 5, dated November 11, 2002. Thereafter. perform the detailed and eddy current inspectiom specified in paragraph taJ or (b) of this AD, as applicable,

on the new [llse pin at the time specill~d in paragrapb (c)(lJ or (cJ(2) of this AD. (1) For airplanes having midspar fuse pins, PIN 3111":n02-1: Perform the initial inspection of the new fu~p.pin prior to the accumulation of 10,000 total landing, on the tICWfuse pill. Repeat the inspection thereaft"r at interva.ls not to exceed 3,00U landings until accomplishm,;ut of paragraph (jJ of this AD. (2) Fur airplan~s having midspar fuso pillS, PINs 3111"3102-2 and 311'1'2102-1: Psrform th~ initial inspection of ths new fuse pin prior to the accumulation uf 15,UOll tutal Imldings on the new fuse pin. Repeat the illspaction thereafter at interval~ unt to cxc~?d 3,000 larldiIlgs until ac(;ompli~hment of paragraph 

### 0] of this AD.

F"se Pin Removal [dJ When any [use pin is rcmoved from a strol equipped witb a Gencrai Electric engine, tbe engine must be removed in accordauce with procedures describBd in the Boeing 767 Maintenance Manual. subject 71::- 00--0:':: or supported in accordance with H method approved by the Manager, Seattle Air~raft Certification Office (ACO], FAA, Transport Airplane Directorate. (eJ Wh~n any fuse pin is removed from a ~trut equipped wilh a Pratt & Whitney engine, tIle engine mu~t be removed lu accordance with procedllms described ill the Boeing 767 Maint(mancc Ma.llual, subjed 71- 00-02: or ~upported in a~cordance with procedures described in the Boeing 767 Maintenance Manual. subject 54-51-02, Temporary Revisions ('1'R),dated April 22, 19'014;or supported in accordance with a method approved by the Manager, Seattle ACo. (fl When any fuse pin is removed from a strut equipped with a Rolls-Royce engine. the engine must be removed in accDrdance with proc(\dure~ described in the Boeing 767 MBintenan~e Manual, subject 71-00-02: or supported ill accordance with procedures descrilJed in the Bueing 757 Maint"nance Manual, subject 54-51-02; or supported in accordance with a method approv"d by the Manager. Seattle ACO. [g) Any mid~par fu~e pin, PIN :u1T3102- 1, 311 1'31U2-2, or 3111'2102-1, that h~s been removed from the strut and inspected for cracks using the 100 percent magnetic perticle inspection tel:hnique described in Boeing A1<n1Service Bu.lletin 767-54A0062, dated April 14, 1994; or Bueing Nert Service Bulletin 767-54A0062, Revision 5, dated Novamber 11. 2002: mav be reinst~lJed 00 the ~trut pruvided th~t the fuse pin is fuund
to be crack·free during the magnetic particle inspection, P,ior to the accumulation of 3,UOOtotal landings after reinstallation of the fuse pin, the fuse pin must be inspected in a.ccordance with the [equirements of paragraph (a), {h], or (h) of thi, AD, as applicable.

New Re<juiremont.-i oftMs AD

Jni/ill! and Rtpetilive [n"peclions (h) For airplan",; having midspar fuse pins, PINs ;1111'3102-1, 3111'3102-2, 3111'3102-::1, 311nl02--4, 3111'2102-1 or 3111'2102-2: Du

a dutlliled inspp-ctiou Bnd an eddy curreat inspectiun for cracks and corrosion per Bueing Alert Service Bulletin 767-54AUOt;2. Revision 5, dated November 11, t002, Do the inspections at the later of the times specified in paragraphs (h](1) and [h){2) of this AD. Repeat tho inspectiuns at lea:;t every 3.000 landings or 5 years, whichever is first. A~complishment of the initial inspections in this paragraph ends the mp"titive inspections required by paragraphs (a] ~nd (b) ufthis AD, (1) Before the accwnulation uf 5.UUOtotal landings on the fuse pin or within

~ years
atter fus!l pin imtallatioll, whichever is first. (2) Wilhin 30 days aftBr th" effective date oftltis AD.

Corrective Adion (iJ If any crack or corrosion i5 fuund during
any i.nspection required by paragraph [h) of this AD, before further flight. do the actiuns required by paragraph (ill1) or (i)(2) of lhis !\D, as applicable. per Boeing Al"rt Service Bulletin 767-54A0062, Revision 5, dated November 11, 2002. [1) Ifany crack is found, replace the midspar fus\' pin with a lleW I'use pin, (2) II'any corrosion is found, repair the mid,par I'use pin or replace with a new fuse pin.
Reperili.,o In8pucliOll8 (jJ For airplan"" identified in paragraph (h) of this AD, After the imtal1atiun of a oaw midspar fusa pin, inspect tb~ n(\w fuse piu
per paragraph (h) of lhis AD befOIB the accumulation of 5,000 total landings 011the fuse pin or within 5 years, whi~hevor is l'irsl. Repeat the illspections at leasl every 3,000 landings ur 5 years, whichever is thst Accomplishment of this paragraph ends the repetitive inspectious required by paragraph (c) of this AD.
Optional TerminMing Action [k) For all airplanes: Accomplishment of the rework or the side ioad fitting and lension fllsteners, as applicable, and replacement of midspar fw;~ pins per Boeing Service Bulletin 767-54-005'01, dated October 9, 1997: Revision 1, dated January 29, }998: or Revision 2, dated August 31. 2000; ends the rapetitive inspeclions required by tbis AD. (I) Modificatiun of the uacelle strut ami wing structure as l'equil'ed by AD :OOOO-1!J09, amendmenl 39-11910 (al-'pl i~able to certain Boeing Model 767 smies airplanes powered by Rolls-Royce RBtll s"r;.cs ungines); AD 2001-02-07, amendmenl39- 12091 [Bppli~able to certain Boeing Model 767 series airplanes puwered by Pratt & Whitney engines]: or AU 2001-ofi-12, amendment 39-12159 (appUcable to ~ertaill Boeing Model 7[;7 series airplanes powered by General Electric eugines]; as applicabln; ends the repetitive inspections required by this AD,

### 4378 federal Register/Vol. 68, No. 19/Wedncsday, January 29, 2003/Rulcs and Regulations

"Oper%r's EquivoJrml Procedure" (m)Though BoeingAlertServiceBulletin 767-54A0ll62,Re..-ision 5. datedNovember II, 2002. specifies !.hat

an "op1lralor's equivalent proced=e" maybeused foraU actions forwhich !.heBoeing767Airplane Maint"nance Manual (Ami) is specified as the appropriate soun::e

ofservice information: Engineremoval and support. when any ruse pin is removed froma strut must bedone according to the applicahle section oftbe Boeing767Airplane MaintenanceManual. as specifilld inthe servicebulletio.

Actions Done pcr Previously Issued Service In/ormation (n)Ins[Juctiollsaad replacemunts done bururuthe effectiveualE: ofthis ADper DoeingAlert ServiceBulletin 7fi7-54A0052, Revision 1, dated May11, 1994:Rovision2, dated December21. 1894:Revision3. uatlld June 15. 1995;orRevision4..datedMay 7, 1998;are accepla!>lu

forcompliant:" with the appliCilhleactions specified inthis AD.
A!lernoti"e Methodsa/Compliance (0)(1):\n alternative method ofcompliance

oradjustment ofthe complianclltime that provides an acceptablelevelofsafety maybe used ifapproved b),theManager,Seattle ACO.Operdtorsshall submittheir requests through an appropriate FAAPrincipal Maintenan<;;e

Inspector. who mayadd comments and then send itto theManager, Seattle ACO. (Z)Alternative methods ofcomplian<;;e, approved previou:>ly

in accordancewith AD 94-11-oZ. anJelldment39-8918, are approved as alternative methods of compliauet! with the applicable actions specified in this AD. Not" 3: lnformatiouconcerning the existence ofapproved alternative methods of compliance with this AD,ifany. maybe oOlai.lled

fromthe SeatllllACO.

Spc(:iol Flighl Permits (p)Special night permits lllaybeisslludin accordance with sections 21.1!J7and 21.1[J[J elf theFederal Aviation Regulations [14CVR 21.197 and 21.199)to operale the airplalle to

It 10\:ation

where the requiromentsoftbis AD

can be accomplished.
In(:orporotion by Hefarenct: (q)Unlessotherwise provided in this AD. the actions shall be done in accordance with BoeingAlert Servic" Bulletin 767-54A0062, dated April 14, 1994:and BoeingAlert Servtet!Bulletin 767-S4A006Z.Revisioo5. d.:ltedNovember11, 2002. (1)The incorpmation byreferenceof BoeingAlert ServiceBulletin 767-54Al1062, Revision5. dated November 11,2002. is approv"d bythe mrector oftheFederal RE:gister in accordance with 5 U.S.C.552(a) and 1 C'''Rpart Sl. (2)The incnrporation byrererenceof BoeingAlert ServiceBulletin 767-54AOQ62. dated April 14, 1994.wasapproved previously by !.heDirectorofthe Fed=<! Re:gister as ofJune 10.1994 (59fR 27229, May 26, 1994). {3)Copiesmaybeobtained fromBoeing CommercialAirplaneGroup, POBox3707. Seattle. WlIShington

98124-2207. Copiesmay beinspected atthe fAA, Transport Airplane Directorate. 1601LindAvenue, SW.,Rentnn, Washington; oratthe Officeofthe Fede.-al Register.BOO

North CapitolStreet, NW.,suite 700.Washington,DC.
Effective Dolfi (r)This amendment becom\lS effectiveon February 13,2003.
issued in RentnTI,

Wa~hington.onJanuary ZZ,Z003. ViL. Lipski, Manager. Transport Airplan", Directorote. Aircroft Certification Service. lFRDoc.03-1827 Filud 1-211·-03~ 8'45 ami

81UING CODE 4910_13..J'

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39
[DocketNo.2001-NM-34O-AD;Amendment 39-13030; AD2003-03-06]

RJN212o--AA64

Airworthil1ess Directives; Airbus Model A330 and A340 Series Airplanes
AGENCY;

Federal Aviation Administration, DOT. AcnON; Final rule.

SUMMARY:

This amendment supersedes all existing airworthiness directive (AD). applicable to r:ertain Airbus Model A330 and A340 ~edes airplanes, that currently requires a onu-time inspection ofthe rail release pins and parachute pins of the escape slidelraft pack assembly for correct installation, and corrective actions. iflie(,:~ssary. This amendmenl adds a requirement to modify the escape slidos/slide rafu Oll tho passenger, crew, and emergency exit doors. The ~ctions specified by this AD

are intended 10prevent improper deployment ofthe escape slide/raft and blockage ofthe door in the event of au emergency evacuation. This action is intended to address the identified uusafe condition. OATES; Effective March 5, 2003. The incorporation by reference of Airbus Service Bulletin A33Q-25-3126, dated August 7. 2001; and Airbus Service Bulletin A34Q-Z5--4152, dated August 7. 2001; 

### as listed in the regulations, is approved by the Director ofthe Federal Register as ofMarch 5, 2003.
The incorporation by reference of Airbus Industrie Service Bulletin A33D25-3086, including Appendix 01, Revision 01. dated June 11. 1999; and Airbus I.ndustrie Service BuHetin A340- 25-4115, including Appeudix 01. Revision 0t. dated June 11, 1999; as listed in the regulations. was approved previously by the Director ofthe Federal Register as ofNovember 26, 1999 (64 F'R 56963, October 22, 19£W).
ADDRESSES:

The service informatIon referenced in this AD Illav be obtailled from Airbus Industrie, I Rand Point M~urice Bdlonte, 31707 Blagnac Cedex. F'rance. This informalion may be examined at the federal Avialion Administration (FAA). Transport Airplane Directorate, Rules Docket. 1601 Lind Avenue. SW., Renton. Washington; or at the Office ofthe federal Register. 800 North Capitol Street, NW,. suite 700, Washington. DC.

FOR FURTHER

INFORMATION

cotrrACT; Dan Rodina, Aerospa~ Engineer. International Branch, ANM-116. FAA, Transport Airplane Directorate. 1601 Lind Avenue. SW., Renton. Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-1149.

SUPPLEMENTARY

INFORMAnON:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 99-22-07, amendment 39-11385 (64 FR 56953, October 22,1999), which is applicable 10Gurtain Airbus Model A330 cllldA340 series airplanes, was publlshed in tbe Federal Regisler on September 13, 2002 [67 FR 579B2). The action proposed to continue to require a one-time inspectioll ofthe rail release pins and parachute pins ofthe escape slide/raft pack assembly for correct installation, and corn

..

octlve actions, ifnecessary. The action also proposed to require modification ofthe escape slides/slide rafts on the passenger, crew, and emergency exit doors.

Comments

Interested persons have been afforded

an opportunity to participate in the making of this amendment. Due consideration has been given to the
comments received.