cntena of the Regulatory FlexIbIJrty Act A final evaluatron has been prepared for this acbon and It Is contained In the Rules Docket A copy of rt may be obtained from the Rules Docket at the location provtded under the capbon ·ADDRESSES "

List of SubJects In 14 CFR Part 39 AJr transportation, Aircraft, Aviation safety, Incorporation by reference, Safety

Adoption of the Amendment Accordingly, pursuant to the authonty delegated to me by the Administrator the Federal Avtatron AdminIstratIon amends part 39 of the Federal AvIatIon Regulations (14 CFR part 39) as follows

PART 39·AIRWORTHINESS DIRECTIVES 1 The authonty crtatron for part 39 continues to read as follows Authonty 49 USC App 1354(a) 1421 and 1423, 49 USC 106(g), and 14 CFR 11 89

§ 39 13 - [Amended] 2 Section 3913 is amended by adding the following new airworthiness d1rectrve

""Regulatory Information

ff,WILLAND, INC Amendment 39-9207 Docket 94-NM·127.P.D ~phcabilrty Model DHC-8-102, ·103, and .,05 sanes airplanes, serial numbers 3 through 369 inclusive, and Model DHC-8-301, ·311, and .314 senes airplanes, serial numbers 100 through 370 InclusIve, certificated 1n any categO!)'

NOTE 1 This AD applies to each airplane li.JentIfiad in the preceding applIcabIllty provision, regardless of whether 1\ has been modrfied, altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD !s affected, the owner/operator must use the authority provided m paragraph (e) to request approval from the FAA This approval may address either no action, 1f the current conflgura~on eliminates the unsafe condtbon, or different actions necessaiy to address the unsafe oondibon descnbed In this AD Such a request should Include an assessment of the effect of the changed conllgurabon on the unsafe condIhon addressed by this AD In no case does the presence of any modification, alteration, or repair remove any airplane from the appllcabIlrty of this AD

Compliance Required as Indicated, unless accomplished previously

To prevent engine llameout following a lightning stnke, accomplish the following

(a) Wrthin 45 days after the effective date of this AD, perform a visual InspectIon of Iha mounting clamps and "breakout 1unct1ons• In the metal overtra1d to venfy the integnty of the shield grounds for the cab!e harness of the electronic engine control (EEC), m accordance with de HavIlland Sef\llce Bulletin S B 8·73·18 (for Model DHC-8-100 senes airplanes), or S B 8-73-19 (for Model DHC.S-300 senes airplanes), both dated April 29, 1994, as applicable If any discrepancy Is found, prior to further fhght, correct the discrepancy In accordance with the applicable servtce bulletrn

{b) Within 45 days after the effective date of this AD, perform an electncal resistance measurement of Class A and Class B shield grounds In accordance with de HavIlland Service Bulletin S B 8-73·18 (for Model DHC-S.100 sanes airplanes), or S B 8-73·19 (for Model DHC.S-300 sanes airplanes), both dated Apnl 29, 1994, as applicable

(1) For Class A shIekl grounds If the e!ecllical resistance exceeds the value speafied In the service bulletin, within 50 flight hours after perfonmng the resistance measurement, repair

In accordance with the apphcable service bullebn

(2) For Class B shield grounds If the electrical resistance exceeds the value specified In the service bulletin, within 180 days after performing the resistance measurement repair In accordance with the applicable service bulletin

(c) For Model OHC-8-102, ·103, and ·106 senes airplanes on which an 1ntenm shield ground Is installed in accordance with paragraphs 19 and 93 of the Accomphshmenl lnstruct1oos or de Havdland Ser,,ice Bulletrn S B 8-73-18, dated Apnl 29, 1994 Within one year after the effective date of thts AD, restOfe the atrplane to the Post•Mod1ficatron 8/0772 conllgurabon In accordance with paragraph 161 of the Accomplishment Instructions of that service bulletrn

(d) For Model DHC-8-301, -311, and .314 sen es airplanes on which en intenm sh1e!d ground Is installed 111 accordance with paragraphs 19 and 112 or the Accomplishment lnstructrons of de Havilland Service Bulletin SB 8-73-19, dated Apnl 29, 1994 Within one year after the effective date of this AD, restore the airplane to the Post--ModIflcallon 810772 configuration in accordance with paragraph 200 of the Accomplishment lnstruc!:Jons of that service bulletin

(e) An alternative method of compliance or ad1ustment of the compliance time that provides an acceptable level of safety may be used 1f approved by the Manager, New Yori<. Alrcra1'1 Certification Office (ACO) ANE-170, FAA, Engine and Propeller Directorate Operators shall submit their requests through an appropnate FAA Pnnc1pal Maintenance Inspector, who may add comments and then send It to the Manager New Yori<. ACO

NOTE 2 lnformatron concerning the existence of approved alternative methods of compliance with this AD, If any, may be obtained from the New Yori<. ACO

(f) Special flight permits may be Issued In accordance with seci!ons 21197 and 21199 of the Federal Aviation Regulations (14 CFR 21 197 and 21 199) to operate the airplane to a location where the requirements of this AD can be accomplished

(g) The inspections, measurement, repair, and restorabon shall be done In accordance with de Hav1l1and Service Bullebn S B 8-73-18 (for Model DHC-8-100 senes airplanes), or de Hav1!1and s B 8-73-19 (for Model DHC..8·300 senes a\rplanes), both dated Apnl 29, 1994 This Incorpora!Ion by reference was approved by the Director of the Federal Register in accordance with 5 U S C 552(a) and 1 CFR part 51 Coples may be obtained from Bombardier Inc , Bombardier Regional Aircraft D1V1s1on, Garratt Boulevard, Downsvlew, Ontario, Canada M3K 1Y5 Copies may be mspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW, Renton, Washington, or at FAA, Engine and Propeller Directorate, New York Aircraft Cerbficabon Office, 10 Frith Street, Third Floor, Valley Stream, New York, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC

(h) This amendment becomes effective on May 30, 1995

,..Footer Information

,..Comments

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(I""""·-~ Administration

Airworthiness Directive

• Federal Register Information

•Header Information DEPARTMENT OF TRANSPORTATION

Federal Aviabon Adm1rnstratlon

14 CFR Part 39

Docket No 94-NM-127-AD, Amendment 39-9207. AD 95-09-o4

Allworth1nesa 01recbves, de Hav1Uand Model OHC-8-100 end-300 Serles Airplanes PDI' Copy Of Avall,bl•)

•Preamble Information AGENCY Federal Aviation AdmmIstratlon, DOT

ACTION Final rule

SUMMARY This amendment adopts a new airworthiness directive (AD), applicable to certain de HavIlland Model DHC-8-100 and -300 senes airplanes, that requires an mspectlon to verify the integrity of the shield grounds for the cable harness of the electronic engine control (EEC), and correction of any discrepancy Th,s amendment also requires measurement of the electncal resistance of certain shield grounds, and repair, rf necessary This amendment Is prompted by a report of an engine flameout after a llghtrung stnke, due to several shields for the cable harness of the EEC not being property grounded to the airfi"ame The acbons speafied by this AD are ll'llended to prevent engine ftameout due to insufficient protecbon of the EEC

DATES Effective May 30, 1995 The incorporaUon by reference of certain pubffcatlons listed m the regulabons Is approved by the Director of the Federal Register as or May 30, 1995

ADDRESSES The service lnfonnallon referenced In this AD may be obtained from Bombardier Inc, Bombardier Reg10nal Aircraft Division, Garratt Boulevard, Downsview, Ontano, Canada M3K 1Y5 This Information may be examined at the Federal AvIabon Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW, Renton, Washington, or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York, or at the Office of the Federal Register, 800 North Capltol Street, rm, surte 700, Washington, DC

ltGLHome

FOR FURTHER INFORMATION CONTACT Richard Fiesel, Aerospace Engineer, Propulsion Branch, ANE-174, FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Vallay Stream, New York 11581, telephone (516) 256-7504, fax {516) 568-2716

SUPPLEMENTARY INFORMATION A proposal to amend part 39 of the Federal Avlaflon Regulabons (14 CFR part 39) lo Include an airworthiness dlrectrve (AD) that IS applicable to certam de Havllland Model DHC-8-100 and -300 series airplanes, was pubUshed in the Federal Register on September 21, 1994 (59 FR 48408) That actton proposed to require a visual inspecUon to venfy the lntegnty of the shield grounds for the cable ha mess of the EEC, and correction of any discrepancy That acflon also proposed to require measurement of the electrical resistance of certain shield grounds, and repair, If necessary

Interested persons have been afforded an opportunity to parbcipate rn the making of this amendment Due consideraflon has been g1Ven to the comments received

One commenter requests that the proposed 45-day compliance lime In paragraph (b) of the proposed AD be extended to perrmt operators to schedule the proposed acflons according to Iha size of their Individual fleets and, specifically, to allow up to 165 days for a fleet-wide Inspection The commenter bases this request on the following factors

1 The commenter stales that, to accomphsh the proposed measurement requirement, the use of a low resistance ohm meter (micro-ohm) Is necessary The commenter has only one low reslSlance ohm meter to perform the measurement of an the airplanes m Its fleet Wrth only one mlCnH>hm meter available, the commenter coukl Inspect only a l1mlled number of ltS fleet of alrplanes dunng its regularly scheduled maintenance visits, and would not be able to accomplish the proposed inspecflons within the proposed 45-day compliance time Further, the commenter does not believe It should have to purchase or otherwise obtain add1t1onal units to sallsfy the requirements of the proposed AD

2 The commenter states that the actiol'IS specified ln the service bulletin could not be accomplished m less than 25 hours and, that based on the amount ofbme evadable for a scheduled maintenance vleil, up to 4 vlelts may be required to complete the Inspection Tha commenter Is concerned about these addrtional expenses that would be associated with this aotion

The FAA does not concur with the commenter's request to extend the compnance time In developing an appropriate compliance bme for this action, the FAA considered not only the degree of urgency associated wllh addressing the subject unsafe condlbon, but the normal maintenance schedules for timely accomplishment of the acbons required by the final rule for all affected airplanes to continue to operate Wllhout compr0m1Smg safety In cons1deraflon of these items, the FAA has delerrrnned that the 45-day complrance lime represents an average maintenance Interval for the affected fleet, during which Ume the required lnspecflons, measurement, reparr, end restorallon can reasonably be accomplished and an acceptable level of safety can be maintained However, under the provisions or paragraph (e) of the final Nie, the FAA may approve requests for adJustments to the compliance Hme If data are submitted lo substanllate that such an adjustment would provide an acceptable level of safety

As for the commenter's concern regarding the expenses associated Wllh accompfishmg the requirements of thlS AD, the FAA recognizes that the obilgabon to maintain aircraft in an airworthy condrt1on is vital, but somellmes expensive Because AD's require specific actions (such as testing wllh special equrpment) to address specdic unsafe condrtions as required In this rule, they appear lo Impose costs that would not otherwise be borne by operators AttrlbuUng those costs solely tc the Issuance of this AO Is unrealistic because, In the Interest of maintaining safe aircraft, prudent operators would accomplish the required actions in a timely manner even If they were not required to do so by the AD

One commenter requests that a certain procedure for repalnng frayed or broken harnesses be referenced In the proposed Nie as an acceptable means of repair The commenter slates that accomplishment of this repair procedure may be necessary In the course of performing the required Inspections The commenter notes Iha! thrs repair procedure IS not Included in any service bulletin or manual

The FAA does not concur The FM does not consider It appropriate to include varloos provisions In an AD apphcable toe sfngle operator Paragraph (e) of this AD provides for the approval of allernabve methods of compliance to address these types of umque circumstances

As a result of recent communications with the Air Transport AssocleUon (ATA) or Amen ca, the FAA has learned that, In general, some operators mey misunderstand the legal effect of AD's on airplanes that are ldenbfied in the appOcablllty provision of the AD, but that have been altered or repaired In the area addressed by the AD The FAA points out that eU airplanes ldenbfied In the appilcabI]Ity provision of an AD are legally subJect to the AD If an alrpler'IEI has been altered or repaired in the affected area m such a way as lo affect compliance wllh the AD, the owner or operator IS required to obtam FAA approval for an alternative method of complance with the AD, In accordance wllh the paragraph of each AD that provides for such approvals A note has been included rn this nollce to clarify this long--stanchng requirement

The FAA has recently reviewed the figures It has used over the past several years In oalculalmg the economic impact of AD actIvrty ln order to account for various 1nflallonary costs In the etrline Industry, the FAA has determined that It Is necessary lo increase the labor rate used rn these calculahons from $55 per work hour to $60 per work hour The economic Impact information, below, has been reVISed to reftect this Increase m the specified hourty labor rate

After careful review of the available data, Including the comments noted above, the FAA has determined that air safety and the pubftc interest require the adoption of the rule as proposed

The FAA estimates that 141 a11planes of U S registry will be affected by this AD, that II will lake approximately 16 work. hours per airplane to accomp1lsh the required actrons, and that the average labor rate Is $60 per work hour Based on these figures, the total cost Impact of the AD on U S operators 1s estimated to be $135,360, or $960 per airplane

The total cost impact figure discussed above Is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions m the future If this AD were not adopted

The regulallons adopted herein wia not have substanbal direct effects on the Stales, on Iha retabonshIp between Iha neflonal government and the States, or on the dIstnbullon of power and responslbllllles among the various levels of govemment Therefore, m accordance with Execuflve Order 12612, It Is determined that this final rule does not have sufficient federalism Imphcations to warrant the preparallon of a Federalism Assessment

For the reasons d1Scussed above, I certify that this action (1) IS not a •significant regulatory action" under Execubve Order 12866, (2) Is not a •s1gn1ficant rule" under DOT Regulatory Pol1e1es and Procedures (44 FR 11034, Febniary 26, 1979), and (3) will not have a sigrnficant economic Impact, pos1hve or negabve, on e substanllal number of small enbtles under the

RECORD OF AtRFRAME

AIRWORTHINESS DIRECTIVES IA/DJ, SERVICE BULLETINS (S/Bl, DATE A / D, 1/8, 1 / t. MODI D.TAILI OP-

DHC - 8-314, S/N , 554

_ 1-------- -- -- -- -- --1 1---- -- --- --- -- ----1

PACI l OP '

N('( AIRWORTHINESS OiR!:CTlVES DATIW PRIOR TO SERIES JOO CERTIPICATt ON, FEB!UJAAY 14, 198' HAVE BEEN

I~CORPORATED INTO THE BASlC BUILD OF 111£ AIRCRAFT - , ______ , ______________________________ _ _ ICF- BS-06 RJ .,/ I

I I H[ NIHIZE THB PROBABILITY" OF LOSS OP POWER INDUCED BY LIGHTHIHO S1'RlK!: - AlitCRAP'i' 001 'fflRU US OHLY

- NOT APPL1CABLE BY AlRCRAn' SERI,lj. NUMBER

- '--- - ----,~'--------------'------- - ------- ------ ICF- 87-07 Rl 7 '

I (S/8 8• 11 - 14) U\VATOR't AND PASSBNCER DOOR t>.BELS • A IRt'RA.FT 003 THRU 402 ONLY - NOT APPLlCABL.£ BY

AIRCRAFT SERIAL HlMDER - 1 _ _ _ ____ , ___ _______ ___ _ _ __________ ___________ _

_ !CF-88-15 I I ,/ I

$TARTER CENERATOR. SBA.LINC • P/N 23081• 0069, S/N 99060 lNSTALLE.0 ON LJI ENGINE S/N PC3•AR0028 AND

S/N YOOlO IMSTAJ..LEO ON RH BNOINB: S/N PCE- AA0029 - NOT A.PPLICASLE BY Pi\RT Nt.lt(BER INSTALLED

- , '- ------------------------- --- --ICF- 89-01 Rl / I I I _ ___________________ _ ____ ___ ___ _ _

ENGINE PJRE EXTINGUISHING SYSTEH - HOO 8/lll6 INCOAPOR.AT£D

IC.F-19-0l ./ I FATIGUE PAU.IJRE ON FLAP TRACK FAIL SAFE STRJU>S - AIRCRAPT 001 nmu 119 ONLY - NOT APPLICJ.81,£ BY

I I AJRCR.APT S ERIAL NUMBBR

'-- --- -'-------------------- - - ---------- -ICF-89 - 03 ./ I MAIN LANDING C£AR UPLOCX AC"ItlATOR - MOO 8/10,a INC'MPOR>,orao I I _______________ ___ _ _ _______ _____ _

ICF-9'-09 R4 ./ ASYl+lETRIC FLAP DEPLOYMENT - AIRCRAFT 003 Ti<Ra 2Sll ONLY • NOT APPLICABLE av -'L'lCRAFT SERI.AL Nt.NBERI

- --- --- ----- ---- --------- --- ------ ---' IMPROVED tu - PLIGHT RESTA.RT CAPMILITY - A~PLISHSI> ON ZNGI N& S/N'S PCE-AR.0028 AND PCB-AK0029 I

:_ _ __ ~I I ,Y- --.,..,..-1 c.:- -u -1, )-,.-s-PECT--POR--I- .... -ECR-!TY--o,-_,-1-. -.-.-L-BE_O_A_ I_.-.. -.-_,-_oo-LE_R_MOUNT __ I_NG_WGS _ ___ A_I_RCRA--FT-1-00_THR_ U_ 2l_l_ON_L_Y ___ I ~-\""-

I NOT AP?LlCADLF. BY A.IRCRAFT SEiUAL NIMDER I

--- --- -'---- --- --- -------- - - ---- -------------' ----1 &NS-.:."RE •BE.LOW CLIO&s.LO?B• WARHI~ JS AVA!t.A8L£ W1fEll OPBRATit.G Wini no: MLS • AIRCRAFT 001 n<RU I ----.,/J 178 OtlLY - ~ APPLICABLE BY AIRCRMT SERIAL NUMBER )

- - - ---' ,----ICP-90-21 (•4£1,, IM.PROVED PUEL PIMP A.~ COVER l'N'iTALLEO ON 8-'«.JN.i!: S/N'S PCE - AR0028 AHO PC£•AROCJ29 j ___ _

'-- - - --'- --- ----------- --- --------------' ICF-,0-2 , f --ro MAINTAIN HITERCONPAR1M8NTl!L V£N'Tl~ - AI/l'CRAPT 116 THRO 1 88 ONLY - NOT APPLICABLS BY AIRCRAFT j ----

1 I I SERIAL :<I.MBER I ----1 I I JCf' - 91-0i P.! / I OXYG!rn LINE rNSPECTJON J\ND RECTIFlO.TlON - MOD 8/1142 INCORPORATED I ----_ _ _ _ _ _ I _ ___ ___ ___ _____ _ ______ ____ _ ___ ____ I

jCF-91- 15 R2 JI ~100 DRY DAY INSPE~ION - AIRCAAFT 202 fflRU 288 ONLY - HOT 1tPPLlCABL£ BY AIP.CRAF":' S&RtM. Nlt".BER \

------' ,----1 MAtlf u.NOING GEAR tNSPECTIOH - BOLTS TORQUE CHECK REOUIREO I\T IHTERVA!..S NOT txCEEDlNO 500 PLICHTS ) ----

v, PLIGHTS - MODS 8/1830 ANO 8/2049 I NC0.R PORAT&D • AIRCRAFT 003 fflRU 400 ONLY - HOT APPLICABLE BY J

I AIRCRAFT SERIAL NIJ,C9£R

---- ---'----------- - - ------------- - -------- --ICP-92- 03 R2 _ I I c,-I/J I

TO Rt;OOCE POTENTIAL ANO ENSURE OOtlTAl~NT OF AN ICC F IRE - COMPLlED MITH ON BNO IHE S/N ' S

PCE- AR0021 A.NO PCE-AR.0029 l ______ , _ _ __________________ ____________ _

:CP-91 - JJ Rl / : TO ALERT CREW OP INTF!itNA.L £NO~NE PIRES • AJil:CPAPT 100 lllRU 29~ O!fl.Y - !'f0'T APPL!CAS!..! SY A!!'!.C!'..AF'!'

SERIAL N1MBER

'-- --- -'--------- - ------------------- --- -ICF 92 - 06 R2 J TO ALERT CREW OF INTERNAL 8.NGlNE FIRES - AIRCRAf'T 100 TtlRU 296 ONLY - YO'!' APPLICABLE 9!' AIRCRAFT

I v, SERlM. N\NDER

'- - --- - - --- - ----- - ------ - ---- --- ------- --- - --ICP-91- 34 I/ FLAP LOAD OISTRIBt.rrlOH - AlRCRAPT 001 THRU 216 ONLY • ~ APPLICABLE BY AIRCRAFT SERIAL truHSER

,----

SPECIAL INSPECTIONS !SIil AND MODIFICATIONS IMODSI

WOflK 01111 INIP. CT I ON ..... .,o,u••o IIONATUPI&

DHC-8 - 31 4 , S/N: 5 54 PAGE 2 OF' 6

L IC &NC• NUMalEPI

ICF-92•09 / I TO PRCVENT LOSS OF THB HYDRAUL IC SYSTEMS DOWNSTREAM OF THE OIJAHTITY LJMITINC VALVES •

----- f I AIRCRAFT 003 n<RU 321 ONLY - NOT >.PPLlCABLE BY AIRCRAFT SERIM. N1MB£R

----- '------'----------------------- -----------ICF-'2- 12 VJ LOW PRESSURE F'UEL SWITCH ADAPTER/SNUDBER INSPECT ION • MOD 8/1208 JNCORPORATED

---- , '- - - --- ---------------------- ------- ICF•92-l4 f TO DETECT ANO CORRECT FAILURE OF THE EHGINB REA.::t l«XJNT" STRUT - AlRCRArr 003 THR.U JlO CtiLY -

,/ I NOT APPLICABLE BY AI RCRAFT SERIAL NlMIER

I TO PR6VF.N'T FAILURE OP THE N.L.O. UPPER DRAG STRtrr TRUNNION FJTTJHGS - MOOS 8/1880 MD 8/2139

vi INCORPORATED - AD AGAlNST AIRCRAFT 003 THRU US ONLY - NOT APPLICABLE Bl' A.l RCRAFT SERIAL N\.MJER

----- -'----------------- -------------------- ICP-92-20 I TO PREVENT LOOSENINC AND CORRODING OP tliE O. C. FEEDER CABLES - MOO 3/1970 INC'ORPCRATEO DUR I NG

VJ ....UPACJVRE

------ '---------------- --------------- -------- ICP·9l-0l Rl ,.--1 TO PREVE?IT OVER..'i&ATINO OP THE PSU CIRCUIT 90AR.D OR CONNECTORS • AIRCRAFT 001 fflRU 369 ON LY •

I I NOT APPLl CABLE BY AJ RCRAFT SER I AL N\HlER • HOO 8/l 9SO INCORPORATSD ----- , _______ , ___________________________________ _ _____ fcF-93-os kl I TO DETECT POSSIBLB STRUCTUJOJ.. 0£GlADATJON OF THB HORlzotr'I'AL STABILU£R ATTACHHE:N'I' BOLTS

I v' I AI RCRA:-""'T 100 ntRU H2 ONLY - NOT APPLICABLE B'i AlRCRAFT S ERIAL NUmCR

----- '-------- ----- -------- ------ ---- ------- )C?-93-20

I 1

,/ I

INCO!UUi'.CT OPERATION OF THE PSEU AND ASSOCIATED SYSTtH.S • IHSTALLA.TIOH OP WHEL£.'f STROBE: POWER

SUPPLY - AIRCRAFT 003 TH.RU 214 OOLY - MOO 8 /1271 INCORPORATED - NOT APPUCABLE 9"1' Al RCRAFT SERIM. __ r_f"'_,__ I

--~ '--- --- ------- --- --- --- --------- - --- - - - -........

f CP-'3-ll DC ELECTRICAL LOM) DISTRIBUTION - REPLACENEtff OF HARDWARE -~T FJREW'-1.L TERMINAL BLOCK AND BAT'l'ER':'

----- I v i SHU!rr - AIRCRAFT 003 TKRU 362 ON"~Y - MOO 0/19 .. INroftfOO,\T£0 - NOi' APPSI CA!lLE BY AIRCltAPT SERIAL

----- I I NUMB~R

I _ _ __ I......:'------ --- --- --- --- ---- ---------------- jCP-'4-01 I HICH PReSSU'U: nmBINE (HPT I DISK U M FA ILUH - HOT APPLICASLE BY DISK PART N\1-mER INSTALLED

L--

I c Ad,, f ON ENGINE SERIAL NUMBERS PCE-AR0021 ANO PCE-AR0029

'------ ---------- - --- - --- --------------icr -,t - 08 Rl I TO PREVENT CORJl:OSION - REPt.ACE BUCK PIIJil TH.£:;tM,\L INstn..ATION lfJni AN4C AJ,Lt41NIZ~O CSI LVE'R I PI U4

/ J INSULAT!ON BLANKETS - AIRCRAFT 001 THRU 310 ONLY • ~CT AF-PL:CAAt.B BY AlRCi\A.r-,, SERIAL N\.NSER •

I J10DS 8 / 20 04, 8 /2006 AND 8/200i INCORPORATED

INSPECTION TO VZRIFY THE INTF.CRlT! OP TtlE ENGINE e:otn'ROL CABLE HARNESS SH I EW GROUNDS •

,/ Al RCRAPT 100 fflRU l70 ONLY - NOT .\Pi,lt.ICABLE BY 1.IRC'RAFT SERIAL Nt.11aER

1Cf'• 94 •l0 Rl NACELLE FUEL LEAKS - AIRCRAFT 003 THRU 369 ONLY • NOT A~P'-lCA.B;.E BY AIRCRAFT SEiUAL NtN!ER -

~ I MODS 1/1126, 8/1815, 8/1887 AND 8/1966 INCORPORAnD

- - ----'------- - --------- -------- -------- -ICP- 9-1 -11 / I TO PREV2tn' NUIS M CE TRIPPING$ OF 7HB 5-AHP CIRCUIT BREAKER - AIRCRAFT 100 THRU HO ON.LY -

ICF - 9/J-22 Rl

ICP-94 -25 Rt

I I I CF-94 -26 Rl

I

I :(QT APPL I CABLE BY AIRCRAPT SE'RIM. MMS£R

/, AHETEX/ WESTON BATTBRY T£MPBRA11JR£ MONITOR FAILUR2 - AIRC'RAr-r' OOJ 114RU 389 ONLY - !Cr A.PPL I CABL.£

I BY A1RCRAPT SERIAi', Nt148£'R

I

I /I

I

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CORROSION DUE TO INSTALLAT ION OF BLACK P I LM THERMAL INSULA.TJON BLANKETS • A.IRCRAPT 003 ~RU 381

OHLY - MOT A?Pt.ID.91..e BY AI RCRAFT SERIAL NU186'R

CORROSION DUE TO BLACK PILM THERMAL INSULATION BLANKETS - A.tRCRAFT 003 THRU 370 ONLY -

MOT' APPLICA9t.a BY AIRCRAFT SERIAL m.M3ER - HOD 8/2127 INCORPORATED