11-后续监控项目清单

WORK-CARD FOLLOW UP ACTION FORM AIRCRAFT NO/FUSELAGE NO: ;fJl %/;ffl%: WORKCARD TYPE: I -F:ru!: ORIGNAL WORK CARD REFERENCE NO: (e.g. RTN, NRC, EO No, Add-Ons :I-F%: cm-F-F.IWm. I) CROSS REFERENCE MANUAL: (e.g. SRM, AMM, SB, etc) ktf BJ 1t:ol5 :f. BJJ: C I SRM, AMM, SB ;) SIN-% OD _,._t-_ BLNM ROUTINE Jl-F d NON ROUTINE iW:Iit-F EO/SB It14-/ 9-il n OTHERS ;!tim NRC: 65370640/N0029 SRM53-41-11 PB101 PARA.3A REV.81 INFORMATION/ DATA/ INSTRUCTION TO PERFORMED PERMANENT REPAIR BE FEEDBACK TO CUSTOMER FOR AS PER SRM 53-41-11 FOLLOW UP ACTION: (i.e. Repetitive Inspection Requirement, Monitoring Requirement, Termination Action, Inspection Result, Measurement DATA B Jl PARAGRAPH3A.PLEASE PERFORM INSPECTION: INSPECTION THRESHOLD FROM AIRCRAF TFIRST FLIGHT:2200FC (FH NOT RELEVANT) SUBSEQUENT INSPECTION AT INTERVALS OF 400 FC(FH NOT RELEVANT) INSPECTION METHOD:GENERAL VISUAL INSPECTION(GVI) 16.MAY.2014 Form No ES-016-lRl f1r Customer : ENV Type: A330 Rev. Date: January 1, 2014 Manual: SRM A330 Selected effectivity: ALL AIRBUS 53-41-11 PB 101 Allowable Damage-SKIN PLATES (Revdate = Jul 01/13) Temporary Allowable Damage Limits caused Paragraph 3.E. c - by Lightning Strikes Allowable Rework for surrounding skin panels Paragraph 3.A. B 53-41-11-1-002-00 of the AFT Cargo Door Allowable Rework for Door Surrounding surrounding skin panels Paragraph 3.8. B 53-41-11-1-003-00 Skin Panels of the Bulk Cargo Door Allowable Rework for surrounding skin panels Paragraph 3.C. B 53-41-11-1-004-00 of the Aft Passenger/Crew Door Table 101 A. Allowable Rework for Surrounding Skin Panels -Aft Cargo Door CAUTION: OBEY THE ALLOWABLE DAMAGE EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPE GIVEN IN THE RELEVANT TABLE. CAUTION: OBEY THE ALLOWABLE REWORK LIMITS INFORMATION BY MODIFICATION GIVEN ON FIGURE 103 (SHEET 1 ). C;UTK)!: THESE ALLOWABLE D/NlAGE lilUST BE iNSPECTED .iT DEFINED iNTE;1VALS. THE iiiSPECTiON INSTFWCTJ;Jil REFEREiiCE iS 53-41-11-1-002-00 ;:NO !S DEscqJSED lN THe STRUCTURAL REPAIR ifISPECTJ!JH3 (SRI) SECTION OF THE SKiVi. iNFOF-.!Nl YOUF. FL.AiliNING DEPARTMENT AND PROVIDE THEM VVlTH TI-lE NECESS,LRY ii!FORivY T!CH!. C;UT:();.J: THE ALLOWABLE DiMiG: i_i!/llTS GlVEJi IN THIS P.!.R,iGRAPH J.RE ONLY P.PPLICABLE TO THE TYPE OF DJNL4GE SPESIFIED. IF YOU HAVE: THiS TYPE OF O,AMAGE TOGETHER WITH A DIFFERENT TYPE OF DAMAGE, FOR EXAfvlPLE DENT PLUS SCRATCH, CONTACT AIRBUS. lF AiiY OF THE OAIVlJ.GES ARE VlTHli1 THE CHAPTER 51-73-11 LIMITS THEY DO 1l()T NEEO TO BE TA.lEN !NTO ACCOUNT :li iHE: . D,SSESSfvlENT. NOTE: This allowable damage information is applicable for rework to surrounding skin panels of the Aft Cargo Door and is valid as shown in Table 102 . AIRCRAFT TYPE WEIGHT VARIANT 020,021,022,023,024,025,026,027 A330-200 050,051,052,053,054,055,056,057,058,059, 060, 061 000,001,002,003,004,010,011,012,013,014, A330-300 020,022,024,025 050,051,052,053,056 Table 102 - Effectivity per Weight Variant and Aircraft Type NOTE: Refer to paragraph 22. Weight Variant Information in the INTRODUCTION of the SRM. Tables in the subparagraphs give necessary data about all weight variants and their required information for allowable damage and repair applicability. NOTE: Refer to Figure 103 to find the allowable rework limits applicable for surrounding skin panels of the AFT Cargo Door. NOTE: For general requirements concerning allowable rework for surrounding skin panels of the Aft Cargo Door refer to Chapter 51-70-20 . For specific requirements concerning allowable rework for surrounding skin panels of the Aft Cargo Print Date: May 16, 2014 Local Time Page 2 of 5 Customer : ENV Type: A330 Rev. Date: January 1, 2014 Manual: SRM A330 Selected effectivity: ALL AIRBUS 53-41-11 PB 101-SRI SKIN PLATES (Revdate =Apr 01/13) C. IIR 53-41-11-1-002-00 These inspection instructions give the necessary information to inspect Fuselage skin allowable rework limits on aft cargo door surrounding skin panel. The related allowable damage is given in Chapter 53-41-11 Page Block 101 , Paragraph 3.A., Figure 103. ( 1 ) Location The detailed inspection instructions and methods are given in Paragraph 3.C.(2). Table 103 . Figure 107 (sheet 1) Inspection Location Aft Cargo Door Surrounding Skin Panel (2) Inspection Data Table INSPECTION SSI THRESHOLD SUBSEQUENT WEIGHT FROM INSPECTION AT INSPECTION METHOD REFERENCE AIRCRAFT VARIANT AIRCRAFT INTERVALS OF REMARKS NUMBER FIRST FLIGHT (FC) (FH) (FC) (FH) 050, 051. 052, 053, 53.41.13 A330-200 054, 055, 32 NOT 2 200 NOT DETAILED INSPECTION 056, 057, 000 RELEVANT RELEVANT (01) - 058,059, 060, 061 050, 051 32 NOT NOT DETAILED INSPECTION 53.41.13 A330-300 052,053, 000 RELEVANT 1 900 RELEVANT (01) - 056 020, 021 022, 023, 20 NOT 2 200 NOT DETAILED INSPECTION 024, 025, 000 RELEVANT RELEVANT (01) - 026, 027 53.41.24 A330-200 050, 051 052, 053, 054, 055, 12 NOT 1 100 NOT GENERAL VISUAL 056, 057, 600 RELEVANT RELEVANT INSPECTION (GVI) - 058,059, 060, 061 000, 001 002,003, 004, 010, 18 NOT NOT DETAILED INSPECTION 011,012, 600 RELEVANT 2 200 RELEVANT (01) - 013, 014, 53.41.24 A330-300 020,022, 024, 025 050, 051 11 NOT NOT GENERAL VISUAL 052, 053, 100 RELEVANT 900 RELEVANT INSPECTION (GVI) - 056 020, 021 022, 023, 2 200 NOT 2 100 NOT DETAILED INSPECTION 024,025, RELEVANT RELEVANT (01) - 026, 027 r3.41.26 A330-200 050, 051 052,053, 054,055, 2 200 NOT 500 NOT GENERAL VISUAL 056, 057, RELEVAIIT RELEVANT INSPECTION (GVI) - 058, 059, 060, 061 000, 001, 002, 003, 004,010, NOT NOT DETAILED INSPECTION 011,012, 2 200 RELEVANT 1 900 RELEVANT (01) - 013, 014, 53.41.26 A330-300 020, 022, 024,025 050, 051 NOT NOT GENERAL VISUAL 052, 053, 2 200 RELEVANT 400 RELEVANT INSPECTION (GVI) - 056 000, 001 11 SPECIAL DETAILED 53.41.36 A330-300 002, 003, 000 53 600 3 200 22 000 INSPECTION (SOl) - 004 020, 021 22 90 000 5 900 20 700 DETAILED INSPECTION 022, 023, 800 (01) - 024, 025, Print Date: May 16, 2014 Local Time Page 1 of 2 WORK-CARD FOLLOW UP ACTION FORM AIRCRAFT NO/FUSELAGE NO: lS ;ffl Jij-I ;ffl :!f;t Jij-: WORKCARD TYPE: I-F: ORIGNAL WORK CARD REFERENCE NO: (e.g. RTN, NRC, EO No, Add-Ons !tflli NRC:65370642/N0031 SRM53-41-ll PB101 PARA.3D REV.81 INFORMATION/ DAT AI INSTRUCTION TO PERFORMED PERMANENT REPAIR BE FEEDBACK TO CUSTOMER FOR AS PER SRM 53-41-11 FOLLOW UP ACTION: (i.e. Repetitive Inspection Requirement, Monitoring Requirement, Termination Action, Inspection Result, Measurement DATA ; B fiJI PARAGRAPH3D.PLEASE PERFORM INSPECTION: INSPECTION THRESHOLD FROM AIRCRAF TFIRST FLIGHT:2200FC (FH NOT RELEVANT) SUBSEQUENT INSPECTION AT INTERVALS OF 400 FC(FH NOT RELEVANT) INSPECTION METHOD:GENERAL VISUAL INSPECTION(GVI) l=b 16.MAY.2014 Form No ES-016-lRl Customer : ENV Type: A330 Rev. Date: January 1, 2014 Manual: SRM A330 Selected effectivity: ALL AIRBUS 53-41-11 PB 101 Allowable Damage-SKIN PLATES (Revdate = Jul 01/13) 53-41-11 PB 101 Allowable Damage - SKIN PLATES 1. General A. This topic contains allowable damage data for the skin plates between FR54 and FRS0/82. Allowable damage is damage for which an immediate structural repair is not necessary. You must blend out th