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

."Tle~specified in paragraphs (CHll(i)and

(c](l](ii) of this AD.

0] Within 12,000 flight cycles or 42 month~

after doing th~ [eplaC~nlentpp.rparagraph (a)

of this AD. whichever is first.

(il) Withi[] 12 mouths after the effective

dat~ of this AD.

(2] For all other airplanes: Within 12,000

flight crcle~ or 42 mflnths after the effective

date ur this AD,whichever is fi[i;l.

(eI) For airplJnes having actuators with rou

end assemblies PINs 65--44760-28and 5H73'185-9; If maintenance fec:ordsshow that

the assefllblLusOilthe airplan" were neve.

cbanged. or were exchang"rl with a rod end

assembly directly acquired from Boeing ur

Parker Hannifin. and were not part-marked

by vihm-"ngraving or other part markings

t.hiJ.lpenlllmtll111<' ,;urface,this i,;considered

acceplablv for compliance with the actions

specified io paragraph (~)of this AD.

COITeclive Aaion

le) If vibro-engraving i5 fmmd during the

inspection required by paragraph (c) of this

AD;B.p.fol'efurther f1ighl,rework or replace

the affecl~d rod end with a new rod end, as

applicable, per tim Work lnslluclions of

Boeing Alert Service Bulletin 737--27A1243,

dat~d July 26, 2001, excluding Evaluation

Form.

Part fllStailation

[lJAltp.rthe effe~tivedllt('of this AD, no

persoll shall inst1l11OllJllY~irplane ,t rod eud

having vibro·e[]graving,or ether 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 of compliance

or adjustment of the compliance time that

provides an acceptable level of safety may be

us~d if llpproved by the 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 of compliance,

llpprov~d pr~viou.>lyin accordance with AD

2.000-02-03, amendment 39-11521, are

appruvlld as aitelllalive lll~thods of

compliance wiU, paragraph (a] of this AD.

Note 3: [nfomlalion GOl'lc~rningthe

"xisl[!nc~of appwv~d lllternat1vemethods of

compliance with this .".0, if any, may he

ohtailled from lhe S~nttl\!,\CO.

Special Flight Permits

(h] Special flight permit, may be issued in

aGcordauceWiUlsections 21.197 and 21.199

of the Federal Aviation Regulation>(14 eFR

21.197 and 21.199) to operate the airplane to

~ lor-alion wh"re the reqllirem~nts of this AD

can be a(:comp1ish~d.

Jncorporalioll by Reference

(i] Unless olherwise specified in this AD,

the actions shall be dOllein acc-ordancewith

Boeing Alert Service Bulletin 737-27AI211,

dated November 19,1998, Boeing Alert

Servi~e Bnlletin 737-27A1211. Revi~ion 1,

dated December 9. 1999. or Boei.ngAlert

Servfc~ Bulletin /37-27AI211, Revision 2,

dated December21. 2000, including

Information Nutice 737-27A1211lN 03,

dated July 26, 2001. excluding Evaillalion

Form; and BoeingAlert Service Bulletin 737-

271\J243, dated July 26, 2001, excluding

Evaluation Form~as applicable.

(1)The incorporation by reference of

BoeiligA[~rtService Boll~liil 737-27A1243,

dated July 26, 2001, excluding Evaluation

Form; and BoeingAl~rt Service Bulletin n7-

27A1211,Revision~, dat'ld December 21,

2000, including Information Nolice 737-

27A1211 [N03, dated July :W. 2001.

excluding Evaluation Form: is approved by

the Dirm:torof the Fedeml Registerin

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

1-'1I1t51.

(2)The incorporation by reference of

Bb~ingAlert Service Bulletin 737-27A1211,

dated November 19, 1988: and Boeing Alert

Servi(:eBulletin 737<!7A121l, Revision 1,

dated December 9, 1999; was approved

previously by th~ Director of the Federal

R~gi,;teras of February 29, 2000 (65 FR3801.

]alluary 25, 2000).

(3)Copies may be obtailled ff()mB(lsing

Commercial Airplane Group, p.o. Box 3707,

Seatlle. Washington 98124-2207. Copi~s may

b~ inspe(;llldat the FA,\, Tran,port Airplane

Dire~torate, 1601 Lilld Avenue, SW., Reilton,

Washington; or at the Office of the Federal

Register, eoo North Capitol Street. NW.. Suite

700, Washington, DC.

f.ffecti"" Dale

(j) This amendment becOllleseffective all

March 5. 2003.

Issned in Renton. Washington. 011January

22.2003.

Vi L. Lipski,

Manager, Tmnsporl Ai"plane Directomlr,

Aircraft Certificrltion Service.

IFRDoc, 0.3-1832 Filed 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

of the Federal Register as of February

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-anmiarcomment@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,

FORFURTHERINFORMATIONCONTACT:

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 of the strut and engine due

to cracking of both fuse pins on the

same strut.

A<:tio!ls Since Issuance of Previous Rule

Since the issuance of AD \)4-11-02,

an operator has reporled a fractured

outboard midspar fuse pin [part number

[PIN) 311T3102-1) of the 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 of the

existing AD, whichever occurs later. In

light of this 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 of the 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 of Ihe actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition.

Related ADs

This AD provides iln optional

terminating action fOt the repetitive

inspections by accomplishment of the

modification of the 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 of the

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 of the

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

of the 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

of the 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 of the

nilceHe strut and wing structure. The

modification consists of replacing many

of the 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

of the signiGcant load-bearing

componenl~ of the 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 10 exist 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 iI new 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;tioTlsfor 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 the following

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). If it 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 AD applies to each airplane

identified in the preceding applicability

pro"isioD, regarrlless of whether it has been

modified. altered. or repaired in the area

subject to the requirements of this AD. for

airplanes that have beeD modified, altered, ur

repaired so that th" performance of the

requirements of this AD is affaded. the

owner/opmator must request approval for an

alternative method of compliance in

accordance with pamgrnph [0)[11of this AD_

The request should include an assessment oj

the effl.'Ctof the modification. alteration. or

repair on the unsafe condition addressed by

this AD: and, if the 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 of the strut and engine du"

to corrosion damage and cracking of both

fusu pius on the same strut, accomplish the

following:

Restatement of Requirements of AD 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 of the midspar

fuse pins, in accordance with SOlOingAlert

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) of this AD. as

applic~ble. Repeat these inspectiuns

lhereafiur at inturvals nollo exceed 3,000

landings until accomplishment of the initial

inspectiOllS specified iDparagraph (h]llf lhis

AD.

Note 2: Fo" the purposes uf this 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 of good

lighiing at intensity deemed appropriate by

lhe inspeclor,lnsptldion aids such as mirror,

magnifying lUllses, ete" may be used. Surfac!:

cleaniug and elaborate aco:;esSprocedures

may be required,"

(I) l'·or airplanes having midspar fuse pins

that have accumulated 18.000 or more total

landings as of June 10. 1994 {the effective

Mle of AD 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 of June 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 10 the 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, Dr within ~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 Ins peclions

(cJ If any 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) If any 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 BoeingAlert Service Bulletin

767-54A0ll62, Re..-ision5. dated November

II, 2002.specifies !.hatan "op1lralor's

equivalent proced=e" may be used for aU

actions for which !.heBoeing 767Airplane

Maint"nance Manual (Ami) is specified as

the appropriate soun::eofservice information:

Engine removal and support. when any ruse

pin is removed froma strut must be done

according to the applicahle section of tbe

Boeing 767 Airplane Maintenance Manual. as

specifilld in the service bulletio.

Actions Done pcr Previously Issued Service

In/ormation

(n) Ins[Juctiollsaad replacemunts done

bururu the effective ualE:of this ADper

DoeingAlert Service Bulletin 7fi7-54A0052,

Revision 1, dated May 11, 1994:Rovision 2,

dated December21. 1894:Revision 3. uatlld

June 15. 1995; or Revision 4..dated May 7,

1998; are accepla!>lufor compliant:" with the

appliCilhleactions specified in this AD.

A!lernoti"e Methods a/Compliance

(0)(1):\n alternative method of compliance

or adjustment of the compliancll time that

provides an acceptable level ofsafety may be

used if approved b), the Manager,Seattle

ACO.Operdtorsshall submit their requests

through an appropriate FAAPrincipal

Maintenan<;;eInspector. who may add

comments and then send it to the Manager,

Seattle ACO.

(Z)Alternative methods of complian<;;e,

approved previou:>lyin accordance with AD

94-11-oZ. anJelldment39-8918, are

approved as alternative methods of

compliauet! with the applicable actions

specified in this AD.

Not" 3: lnformatiou concerning the

existence of approved alternative methods of

compliance with this AD,if any. may be

oOlai.lledfrom the SeatllllACO.

Spc(:iol Flighl Permits

(p) Special night permits lllay be issllud in

accordance with sections 21.1!J7and 21.1[J[J

elfthe Federal Aviation Regulations[14CVR

21.197 and 21.199)to operale the airplalle to

It 10\:ationwhere the requiroments oftbis AD

can be accomplished.

In(:orporotion by Hefarenct:

(q) Unless otherwise 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.Revisioo 5.

d.:ltedNovember 11, 2002.

(1)The incorpmation by reference of

Boeing Alert Service Bulletin 767-54Al1062,

Revision 5. dated November 11, 2002. is

approv"d by the mrector of the Federal

RE:gisterin accordance with 5 U.S.C.552(a)

and 1 C'''Rpart Sl.

(2)The incnrporation by rererence of

BoeingAlert Service Bulletin 767-54AOQ62.

dated April 14, 1994. was approved

previously by !.heDirector of the Fed=<!

Re:gisteras ofJune 10.1994 (59 fR 27229,

May 26, 1994).

{3)Copies may be obtained from Boeing

Commercial Airplane Group, PO Box3707.

Seattle. WlIShington98124-2207. Copiesmay

be inspected at the fAA, Transport Airplane

Directorate. 1601Lind Avenue, SW.,Rentnn,

Washington; or at the Office of the Fede.-al

Register.BOONorth Capitol Street, NW.,suite

700.Washington, DC.

Effective Dolfi

(r)This amendment becom\lSeffective on

February 13, 2003.

issued in RentnTI,Wa~hington.on January

ZZ,Z003.

Vi L. 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

[Docket No. 2001-NM-34O-AD;Amendment

39-13030; AD 2003-03-06]

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

of the 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 of the escape slide/raft and

blockage of the 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

of the Federal Register as of March 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 0 t. dated June 11, 1999; as

listed in the regulations. was approved

previously by the Director of the Federal

Register as of November 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 of the

federal Register. 800 North Capitol

Street, NW,. suite 700, Washington. DC.

FORFURTHERINFORMATIONcotrrACT; 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.

SUPPLEMENTARYINFORMAnON: 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 cllld A340

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 of the rail release pins and

parachute pins of the escape slide/raft

pack assembly for correct installation,

and corn ..octlve actions, if necessary. The

action also proposed to require

modification of the 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.