, , . CUSTOMIZED MAINTENANCE PROGRAM AIRWORTHINESS LIMITATIONS LIST Dash 8 Series 300 - Wing IIB Flap SIN FI 530 DOT Approved tyrolean ~ Threshold Repeat Task # Ale SIN IFIt [Fit Task Description DH Ref Remarks Hours] Hours] Ii 8-57-3314 N/A 40.000 20.000 Insp for repair of RD # 8-57-3314 This task applicable for chafing on upper wing skin of the LH inboard flap inboard nap upper SIN FI530 skin VO-CMPI A WL-8/300 Authority: TE Issued by: TE 4 1"1530.DO(, 2-FI53D Revision # 16 Page 1of 1 Sep 01,2008
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DOT Approved Dash 8Series 300- Wing IIBFlap SIN · CUSTOMIZED MAINTENANCE PROGRAM AIRWORTHINESS LIMITATIONS LIST Dash 8Series 300- Wing IIBFlap SIN FI 530 DOT Approved tyrolean ~
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, ,
. CUSTOMIZED MAINTENANCE PROGRAMAIRWORTHINESS LIMITATIONS LISTDash 8 Series 300 - Wing IIB Flap SIN FI 530
DOT Approvedtyrolean
~Threshold Repeat
Task # Ale SIN IFIt [Fit Task Description DH Ref RemarksHours] Hours]
Ii 8-57-3314 N/A 40.000 20.000 Insp for repair of RD # 8-57-3314 This taskapplicable for
chafing on upper wingskin of the LH inboard flap
inboard nap upper SIN FI530
skin
VO-CMPI AWL-8/300Authority: TEIssued by: TE
4 1"1530.DO(, 2-FI53D
Revision # 16Page 1 of 1
Sep 01,2008
BOMBARDIERPREPARED: IB
CHECKED
DATE: May'06
RD8-57-3314SECT 1PAGE 1lSSU]l; 1
The following pages detail a Permanent Repair for Chafing on the Upper Skin ofthe LH Inboard Flap Upper Skin, 85750051, at Yw 79.0 Forward of Stringer 2,Damage is as reported in Temporary RD8-57-J312 .. Blended damage is left as is andall external repair' doubler installed ..
This repair is void if there is any damage to underlying structure.
This repair will require a special inspection as defined on Page 2. Thisinspection must be incorporated into the operators approved maintenanceprogram,
This Repairis detailed in: RD8-57~3314 Section 1
-- Approx Repair Location
Pages 1 Iss..!2 Iss.13 Iss.14 Iss.I5 Iss.1
RDISSUE 1 Title:Permanent Repair for Chafing on.-----1the Upper Skin of the LH InboardFlap Upper Skin, 85750051, atYw 79.0 Forward of Stringer 2.
DA.TE 4/May/06-----r---------+--------~DRA WN Ian BumsAPPROVED
STRESS
DAD# tOb REPORT NUMBE~
RD8-57-3314
DArE
APPLICABILITY
DHC-8-300
SIN 527LH Inboard Flap,85750002·011.SIN: FI-S30
BSS)' 91.E 9l)'IZ8-j lOO/eOO d 218-1
PREPARED: I B RD8-57-3314CHECKED BOMBARDIER SECT 1
PAGE 3DATE: May'06 ISStJ"E 1
.....-BLENDED AREA FROM RDB-57-3312LEAVE AS IS - DO NOT CUTOUT.
Yw87.35 DO NOT INSTALL RIVETS THROUGH Yw74.35I BLENDED AREA. .
Ir:;:h+ ~,'" , --Jr-II II 1~11II II II II)1+1\ )I+I!
STR 1 .=============================== ===:===================.:::1+ L'+l --_- __ -:..":..":=,.-:...-:::.:::.-:.. -:::......::.;-=.:::.~~-=--=.:~"":.."::..--::~:::::.::-+ ('+"'I/?~/ ~--:..---,--1--;-=-=------------ ':\-T--r I'\. '-I- I / <: I+ I (\ I I ( FW D \ I I,I! 'I \, II'1+11 t ---_ 11+1'I , I( :_k. _k _lL_ _IL _IL I ,I11+11 7j 71 71 71 7]"- :1+11i i+ II ~ liB _k _k ___k _k. _k I: i iII I I, 71- 7J 7): 7j 7J"- II+ I iI , \ !I///,. J I , \/ I+ I', _k _k(.I'I''''''''''''>,_v + 1+'--"" , I ...._-- ;r 71'(/""///~,~ ./ t -h \-_.---'II-·-----===:::====----- ----- ......eN/,4-_.~__ ...~/' 1-" 1\ '"\ T , ----- -------....:'------ ====- ..- \+ 1 ...... .:.:::\~- ~- 1STR 2 ===.=.-::::-=:::=~~.========:::.';===;;:;=;;:;;;:;;;:;=;;:;=;;;:;;::.==.=====.=-==.=======~
-.~-..({]-------- -1--:..-=::.....::·::..:::.:-:...-:::...-:.::::::...":.:":..~~~:--~;f~-:...~*~-==--'::::::;::,+ (.jll,,;:;=l-, , I ,....------- ___lL ___lL ++ .....,.I" ,+- I / ?( 7]"- \ I+ II
\! , / \ I II11+11 DONOTINSTALL if~' ~ -t: ~ 1:+11'I 11 RIVETS THROUGH II . I'II + II STRINGER FLANGES. I' + 11I! 11 r I 'III +11 ,1+11I I I\ I I ,t11+', /1+'\
10)Fill voids and fillet seal around the edges ~f the repair doubler, per sketch below, withPR1422B2, or equivalent, per Structural Repair Manual, PSM 1-83-3, Chapter 51-30-26
Repair DoubJer
_-.1.t ~04011(Ref)
11)RIVET KEY* CR3214·4 New locations at .70{SO"pitch, except across stringerHole size )29/ 132" Dia. : Csk .1911 196"Dia.
I+ Reference only.
l28-: LOO/LOO d 2l8-1 sm SL¬ 9ly SO-vo-sO
i~lOS EASA PART-145 AT.145.001, FAR-AUXY103F Austrian Airlines, Oesterreichsche Luftverkehrs AG
Illt.II~1I11~VO: EASA PART-145 AT.145.030 Tyrolean Airways - Tiroler Luftfahrt GmbH W.O. Rev. 1 IAircraft/ LTM Maintenance Workorder r·'~~-\ \~;~Cust.: - \~','V·',,'~>.~.'~o A32 OB77 o MD8o A33 o CRJ o 3RD Date Issued by ATA o Pirep No.2075067o A34 o DH8 o COMP 01.Mar2006 ID VPRI S7-S0 o Mainto B73 o F70 Fit No. From Tol (Side 1 of 2) (§9o B76 o F100 ~ SchedP/r--.;
Stn INN Statistics I DBase
SIN o Canni Project ~ Struct. Damage o Insuranceo Tech. Irreg. o WarrantyMEL Ref: MEL Interval D HIL D Fit Deck Info D Cabin Info D SDC
Classification [6]ffil[g[Q] D F.B. req: D AOG Risk ETOPS Restr.: CAT Restr.:OPS Reporting Text:
List any available Fault Codes, Messages, Observations either in Description- or Action Text
Aircraft Log D ETOPSILJ Entry req, Critical PathIf Taskcard Finding I Zone I I Area I Date ID t-'egpJ~edrecort Task No.:
ET-INSPECTION PERFORMED ACC. RD 8-S7-3314 ISSUE 1 ITEM 3WITHOUT FINDINGS SEE ATTACHED REPORT.
UT DISBONDING INSPECTION PERFORMED ON STRINGER AND FRAMENO DISBONDING COULD BE FOUND AT THE TIME OF INSPECTION.EQ.IJ.IPMENT USED: FOKKERBONDTESTER 80L CRYSTAL 3418J! l)TER704 SETTING SRF M1SS. OS.OSVEBN %r---
c -----------------------------_--_-----------------------0D L/H<{ PERFORMED PERMANENT REPAIR ON INB.FLAP ACC: I L! •
RD8-S7-3314 ISSUE1 04.0SVZIN fh.-~O~OS VK1E, ~
I-' A .......-
/ I
/ I
(IReference W 207S0S0 W 2079012Type / No.:w. F. CD. I. M
Valid Ex1.Codes: Combination of GTI Groundtime. MPI Manpower, TOI Tool. HAl Hangar. PWI Paperwork, PRI Partrequest and CHI Change. ICllncomplete, lSI Insufficient. NAI Not avail. WRI Wrong
Transfer Due Date TAH TAC Prio Ext. Codes ID Sign
0 PIC for MEL Dispatch
16'16S 3 PWNA VPRI
b AcrrunistratonWorkorder,noMaintenanceReleaserequired E va Only:workoroer Completion- CRSto be issued in TAL
o This aircraft or airframeidentif,iedabovewas repairedand inspectedin accordancewithcurrent Regulationsof the Fe~eralAviationAdministrationand is approvedfor returnto service~_~1'~lrs,gned for the Austrian Airlines FAR 145 Approved Repair Stauon, Certificate Number: AUXY 103F at Austrran Airlines Technical Base A·1300 Vienna Airport, Austria, Europe
o C~ )hat the workspecifiedexceptas otherwisespecifiedwascarried out in accordancewithPART-145and in respectto thatwork the aircraft/aircraftcomponentis consideredreadyfor releasetoservl....c::
Approval No.: DoS EASA PART-145 AT 145001 D VO EASA PART-145 AT.145.030 D Other
Closing Closing Time UTC Last Fit No. Hrs: 16' 002 Rel~lD Dbllnsp.ID (if req) ~Station Date Sign@,j Sign .
INN OS.May.2006 OS288 Cyc: 17'448 -:c ~\ IIf) RA
printed by WARTUNG on Friday. the 5 May 2006 at 1944 out of database prod_vo hosted on amosp.vie.aua.com ~ pcedbY AMOS wwwmYAMOSCO~4505 .
o A32 OB77 o MD8 Dateo A33 o CRJ o 3RD Issued by ATA o Pirep No.2075067o A34 o DH8 o COMP 01.Mar2006 10 VPRI 57-50 o Mainto B73 o F70o B7 o F100 Fit No. From Tol ~ Sched (Side 1 of 2) , ~
i,/
PINStn INN Statistic~ DBase
SINo Canni Project ~ Struct. Damage o Insurance
o Tech. Irreg.:"
o Warranty
I MEL Ref: MEL Interval o HIL o Fit Deck Info o Cabin l~fO ". o SOC
Classification [6JffiJ[9[_QJ o F.B. req. o AOG Risk ETOPS Restr.: CAT Restr.:I, OPS Reporting Text:
List any available Fault Codes, Messages, Observations either in Description-or Action Text
PERFORM PERMANENT REPAIR ON L/H INB. FLAP UPPER' SKIN. RD FOR
W.F.CD.I.MValid Ext. Codes: Combination of GTI Groundtime. MPI Manoower. TOI Tool. HAl Hanoar. PWI Paperwork. PRI Partreauest and CHI cnance. ICI Incom
ete, IS/Insufficient. NAI Not avail, WRI Wren
Transfer DueDate TAH TAC Prio Ext. Codes 10 Sign
-:" o PIC for MEL Dispatch
16'165 3 PWNA VPRI
5Administration Workorder, no Maintenance Release requiredo VO Only, WorMrder Completion - CRS to be issued in TAL
0ircraft or alrtrame identified above was repaired and inspected in accordance Withcurrent Regulations of the Federal Aviation Administration and is approved for retum to service.dersigned for the Austrian Airlines FAR 145 Approved Repair Station. Certificate Number AUXY 103F at Auslrian Airlines Technical Base A·1300 Vienna Airport. Austna. Europe.
tcJ Certifies that the worl<specified except as otherwise specified was carried out in accordance with PART- '45 and In respect to that work the aircrafVaircraft component is considered ready for release to
service.
Approval No.: DOS EASA PART-145 AT.145.001 o vo EASA PART-145AT.145.030 o Other
rrime UTev. Release 10 Obi Insp.ID (if req)
Closing Closing Last Fit No. Hrs:
Station DateSign Sign
Cyc:
printed by VEBN on Fnday. the S.May 2006 at 13:14 out of database prod_vo hosted on amosp.vle.aua.comproduced by AMOS www.myAMOS.com
Standard setting slightly varyfied for each application
Result of examination: Findings: 0 Yes ~ No
No surface discontinuity indications, which exceeds the rejection criteria, could be found at thetime of inspection
Additional information: NoneAll NOTwork done in accordance with applicable NOT Procedures and Tasks as shown above and approvedunder Austrian MOT Nr.: AT.145.030, 01 Rating for TYROLEAN AIRWAYS.
Inspectiondone by: Franz EBNER Qualification: EN 4179 Level II
Signature 1 License: Date: 05.05.2006
Form 12058Rev.1
SECTION 2.2
Bombardier AerospaceDASH 8
SPECIFIC AIRWORTHINESS LIMITATION
IN·SERVICEDEVIATIONINSPECTIONREQUIREMENTS]
The following task is a specific Airworthiness Lirnftatlon. Compliance with this task isrequired to ensure continuIng compliance with the airworthiness standards of theDHC-8 basis of Type Approval,
The count for the threshold commences upon incorporation of the deviation specifiedin the reference document.
Task No Threshold(flights)
40000
RepeatInterval(flights)
20000
OH Ref. Task Procedure
RO 8-57-3314 Low Frequency Eddy CurrentIssue 1 for basic aircraft structure
(sub-surface) and standardHigh Frequency EddyCurrent for repair patch(surface).Refer to NDT Manual, PSM1-83-7A, Section 51-00-06,
DAD Slgnature:_lI~",iI:....;;......!>Jd~_,;___#_~_o_G._and Number
APPROVED IN ACCORDANCE WITH TRANSPORT CANADADAO #93-0-02
APPROVAL PAGE
(RD 8-57-3314, Issue 1)
A copy of this page must be inserted in the SDIR manual.
The following pages detail a Permanent Repair for Chafing on the Upper Skin ofthe LH Inboard Flap Upper Skin, 85750051, at Yw 79.0 Forward of Stringer 2.Damage is as reported in Temporary RD8-57-3312. Blended damage is left as is andan external repair doubler installed.
Thls repair is void if there is any damage to underlying structure.
This repair will require a special inspection as defined on Page 2. Thisinspection must be incorporated into the operators approved maintenanceprogram.
This Repair is detailed in: RD8-57-3314 Section 1 Pages 1 Iss.l2 155.13 155.14 Iss. 15 155.1
Title:~--------4---------~---------4 ~Permanent Repair for Chafing on~--------4---------~---- -+ ~the Upper Skin of the LH Inboard
This repair affects the airworthiness limitations document and requires anadditional task. The inspection requirements for this task, which are shownbelow, are Transport Canada approved. The operator must incorporate thisadditional task as an amendment in the airworthiness limitations document forthe affected aircraft serial number. It is the operator's responsibility to obtainapproval of the amended airworthiness limitations document from his regulatoryauthority and to incorporate the added inspection task in the maintenanceprogram for the affected aircraft. The time for threshold inspection Is measuredfrom the time of the incorporation of this repair.
Threshold: 40000 Flights
Repeat: 20000 Flights
The above inspection times were determined in Report AEROC 8.4.AC.12,Section 57-0054..1.
Inspection Method: Low frequency Eddy Current for basicaircraft structure (subsurface) and standardhigh frequency Eddy Current for RepairDoubler (surface).
==;;;;;;;;;;;;;;;;;;;;;;;;;==:;;;;=::=================== ===:===============;;;:;;;:;;;:==1+ L+1 ------.... (..-...,--~--:"'--1~- -;:-.=..."::.-::...~-::...~-::...~-=--===--::..."=--::.."=.,-:::.:::.-=- -::.."=.,~-::.-::...-::..~.:::---- - - .......~<~T:-+I;'....-" / . I / \- I I /
\ I + 1/ FWD' \ I + III' II \ I 1/11+11 ~ 11+11II [I ~ _lL _k. II II11+111 71 ~ 7J~ 7( ~ 111+11I I I 1/II , I liB _lL .._k .JL II I I
JI I + 1 I 71- 71 ~ -t :f- II+ i I
, I \ !I///,. J I I \/ 1+' \., .JL ....k(NN"/>,~ ~ / I + I._/ I I <,----_______ 71 7j '(//////'1 .. -+--h \---1+,....,.-----____ ----- --- __ -V(////,~__ ,/ / I 1\'
<; I ;i-~;-.=.-=--:..-=--=--:. --:..-==--:.:~-=--=-*-:::.r~·-;j2--f -::\-I~-r//\ I 1/ \ I "11+11 DONOTINSTALL if * t- * ~ il+11I I :: RIVETS THROUGH I: II: I+ II STRINGER FLANGES II + III II . II II11+/1 11+11
PREI'ARED: I B RDS-S7 ·3314CHECKED BOMBARDIER SECT 1
J>AGE 4DATE: May'U6 ISSUE 1
GENERAL NOTES
1) This repair is void if there is any damage to underlying structure.
2) Before installation of the repair, ultrasonic inspection of the bonded skin, waffle doubler andstringers is required Laensure that no disbanding indications are present in the repair area. Ifdisbonding is found contact Bombardier Aerospace Regional Aircraft before proceedingfurther. Ultrasonic testing is the preferred method of inspection for skin/waffle/stringerdisboriding. If the preferred method is impractical, or j f' ultrasonic test facilities are notavailable, an alternative non-destructive inspection procedure may be used provided it isapproved by an appropriate airworthiness authority and is performed by an operator withdemonstrated expertise.
3) Crack detect using preferred Eddy Current method, per NDT Manual, PSM 1-83-7A,Chapter 51-00-06, or fluorescent dye penetrant method. No crack indications permitted.
4) All cut edges to be smooth and nick free.
5) Maintain a minimum of two (2) times the fastener diameter edge distance un1ess otherwisespecified. Edge distance is measured from the centre of the hole to the nearest materialedge. The minimum edge distance, or better, must be maintained on all parts, includingwaffle doublers where applicable, through which the fasteners pass,
6) When drilling off new fastener locations, near existing structure or waffle doubler edges,take care to locate hole centres far enough from existing: edges to provide clearance forinstalling rivets (.20" for -4 diameter rivets.).
7) All new P81ts and bare metal to be finished with Alodine, Epoxy Primer and Enamel.i) Alodine per Structural Repair Manual, PSM 1-83-3, Chapter 51-20-16.ii) Epoxy Prime per Structural Repair Manual, PSM 1-83-3, Chapter 51-20-36.iii) Externally, apply a coat of Polyurethane Enamel (F24) per Structural Repair Manual,
PSM 1-83-3, Chapter 51-20-51, except on mating surfaces.
8) Fay seal all mating surfaces with Pro-Seal 870C, or equivalent per Structural RepairManual, PSM 1-83-3, Chapter 51-30-26.
9) Install all fasteners wet with Pro-Seal 870C, or equivalent per Structural Repair Manual,PSM 1-83-3, Chapter 51-30-26.
10)Fill voids and fillet seal around the edges ~fthe repair doubler, per sketch below, withPR1422B2, or equivalent, per Structural Repair Manual, PSM 1-83-3, Chapter 51-30-26.
.40/.50" ,---- Repair Doubler
_---1.t_.04011 (Ref)
11)RIVET KEY
-t CR3214~4 New locations at .7°1.80" pitch, except across stringer.Hole size .129/.132"Dia. • C'sk .191/.l96'1 Dia.
+ Reference only.
IZ8-d lOOllOO d Z18-1 6ESv SlS 9lv
J ~
~1yrolean Aircraft- Equipment- List VFLO 07 .Apr .201108:52 Page 18/27
Aircraft- Equipment- List of Aircraft LTM SIN 527Only rotables with requirements with subtrees, group by 2 char. on ATA-Chapter ( AlC Data: 24'949/H, 27'009/C )
Aircraft- Equipment -List of Aircraft LTM SIN 527I Only rotables with requirements with subtrees, group by 2 char. on ATA-Chapter (AIC Data: 24'9491H, 27'OO9/C)I
ATA: ; i! ':".Di!!mption.r- ,,', .' ,.",_" , i D_riPtipn