Boeing 747-341

Service difficulty reports · 174

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  FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
  WHERE aircraft_model_key = '747341'
  ORDER BY difficulty_date DESC"

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SDR UIEA2011122300728Skin · damagedTHE ACFT WAS STRUCK BY GROUND EQUIPMENT AND SUSTAINED DAMAGE TO THE FUSELAGE SKIN, BEAR STRAP AND BS-670 FRAME JUST ABOVE THE THE LOWER AFT CORNER OF THE FWD CARGO DOOR OPENING. THE SEAL DEPRESSOR WAS ALSO DAMAGED IN THE INCIDENT. THE ACFT WAS FERRIED OR REPAIDec 21, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011102000603Relay · malfunctionedAIR TURN BACK, AUTO PRESSURIZATION INOPERATIVE ON CLIMBOUT. IN AUTO, BOTH VALVES INDICATED 90 PERCENT CLOSED AT FL 100. ATC REPORTS TRANSPONDER INOPERATIVE. CYCLED CB & GT, NO HELP. PERFORMED LANDING GEAR RETRACTION EXTENSION IAW MM. UNABLE TO DUPLICATE Oct 16, 2011 · N355MC · Boeing 747341 · Cabin Pressure Control SystemSDR UIEA2011102000602Logic Card · inoperativeAIRTURN BACK DUE UPPER DECK FLIGHT LOCK LIGHT ILLUMINATED AFTER TAKE OFF. CABIN WOULD NOT PRESSURIZE. EXTINGUISHED ON LANDING. ATC COULD NOT RECEIVE SQUAK CODE DURING FLIGHT, MULTIPLE RESETS NO HELP. TRANSPONDERS INOPERATIVE. SIMULATED "AIR" MODE IAW MM. THOct 15, 2011 · N355MC · Boeing 747341 · Cabin Pressure Control SystemSDR UIEA2011081000452Fairing · crackedDURING WALK-AROUND INSP, MX REPORTED LT INBD WING TO FUSELAGE PANEL 293AL - WBL 128.46 CRACK/DAMAGE (REF FIG 1). PERFORMED A TIME LIMITED REPAIR.Aug 10, 2011 · N355MC · Boeing 747341 · Aerodynamic FairingsSDR UIEA2011080700423Spoiler Sys · malfunctionedWHEN TAKEOFF POWER APPLIED, AUTO SPOILERS DEPLOYED AND WARNING HORN SOUNDED. RETURNED TO BLOCKS. APPLIED MEL 27-9 FOR AUTO SPOILERS INOP, COMPLIED WITH MX ACTION AND RELEASED ACFTAug 7, 2011 · N355MC · Boeing 747341 · Drag Control SystemSDR UIEA2011080600429Skin · damagedDURING INSP, MX FOUND THE NR1 ENGINE LT THRUST REVERSER CORE COWL INNER SKIN DAMAGED/DELAMINATED. REF FIG 1. DISPOSITION IS TO REPAIR THE SIDEWALL DAMAGE ON THE THRUST REVERSER IAW AMM 78-31-01, AND REPLACEMENT OF THE THRUST REVERSER AT THE NEXT "A" CHECK. Aug 6, 2011 · N355MC · Boeing 747341 · Engine Thrust ReverserSDR UIEA2011052700267Relief Valve · defectiveDURING CLIMBOUT, NR 2 ENGINE FIRE WARNING SOUNDED WITH BOTH FIRE LOOP INDICATORS AT 9. RAN ENGINE FIRE CHECKLIST. NR 2 ENGINE FIRE LIGHT WENT OUT WHEN THROTTLE WAS AT IDLE, THIS WAS A MAX POWER TAKE-OFF. (TROUBLESHOT AND FOUND THAT PRESSURE RELIEF VALVE AND May 27, 2011 · N355MC · Boeing 747341 · Pneumatic Distribution SystemSDR UIEA2011032800163Panel · gougedDURING ROUTINE CHECK, GOUGE DAMAGE TO THE RT INBD ELEVATOR LOWER PANEL WAS FOUND. THE DAMAGE OCCUPIES AN AREA OF APPROX 4.5-IN BY 3-IN AND LOCATED AT 23-IN FROM THE T/E AND 59-IN FROM THE INBD EDGE. (DISPOSITION WAS MADE TO FILL THE DAMAGE WITH BMS 5-25 POTTIMar 28, 2011 · N355MC · Boeing 747341 · Elevator, Plate/SkinSDR UIEA2011032000157Access Panel · missingDURING WALKAROUND INSP, MX FOUND THE RT BODY GEAR DOOR WITH ACCESS PANELS (2 EA) MISSING (REF FIG 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT INSPECTIONS AT EVERY 1 FC (FLIGHT CYCLE) ANDMar 20, 2011 · N355MC · Boeing 747341 · Landing Gear DoorsSDR UIEA2011030100135Rub Strip · damagedACFT AT SIN D CHECK. THE NR 1 LT FAN COWL WAS ROUTED TO THE COMPOSITE SHOP FOR REPAIRS. DURING INSTALLATION ON THE ACFT THE L/E RUB STRIP MISMATCH (6 O'CLOCK) WITH THE NOSE INLET COWL NOT ALLOWING THE FAN COWL TO LATCH PROPERLY. (DISPOSITION WAS MADE TO PERFMar 1, 2011 · N355MC · Boeing 747341 · Engine Air Intake SystemSDR UIEA2011022000124Floorbeam · corrodedDURING D CHECK OF DATUM AIRCRAFT, CORROSION FOUND ON LOWER LOBE CAP AFT FLANGE LOWER SURFACE OF THE SECTION 46- STA 1680 AFT CARGO FLOOR BEAM BETWEEN LBL 30 AND LBL 40. SEE FIGURE 1 FOR DAMAGE REPORT AND DETAILED LOCATION. CORROSION REMOVAL ACCOMPLISHED BY BLEFeb 20, 2011 · N355MC · Boeing 747341 · Fuselage Main, Floor BeamSDR UIEA2011021900129Skin · corrodedDURING A D-CHECK. SIAE REPORTED CORROSION IN FUSELAGE SKIN ADJACENT TO AND BELOW THE LAP JOINTS AT MULTIPLE LOCATIONS. NO ACTION REQUIRED - THIS PART WAS PREVIOULY ACCOMPLISHED PER NRCS 103, 107, 108, 109, 181, 182, 184, 185, 186, 188, 190, 292, 374, 392, 395Feb 19, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011021900120Skin · crackedDURING A D-CHECK. REPORTED A CRACK IN THE NR 4 STRUT RIGHT SIDE SKIN ASSEMBLY INTERNAL BONDED DOUBLER AT THE 482AR ACCESS PANEL CUTOUT, LOCATED BETWEEN N.S.211.42 ANDN.S.211.5. (THE FOLLOWING WAS ACCOMPLISHED DURING THE REPAIR. THE 65B94128-28 DOUBLER WAS TRIMFeb 19, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011021100062Bulkhead · crackedTHE PURPOSE OF THIS EO IS TO DOCUMENT A REPAIR PERFORMED ON THE DATUM ACFT AT SIAE DURING A D-CHECK. SIAE REPORTED A CRACK IN THE BS 400 BULKHEAD LOWER WEB ASSY PRESSURE PAN. THE CRACKED WEB WAS TRIMMED AND REPAIRED BY INSTALLING A STACK-UP OF 2 DOUBLERS AND 2Feb 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, BulkheadSDR UIEA2011020800058Stringer · crackedDURING D-CHECK OF DATUM ACFT, FOUND A 0.75 INCH LONG CRACK EMANIATING FROM THE CUT OUT EDGE OF S-10AR ON FRAME AT STA 440 WITH PN 65B01715-1022. FIG 1 FOR DAMAGE LOCATION. THERE WAS A PREVIOUS REPAIR WAS PERFORMED ON 13MAR08 AT 67,448 TFH/13,068 TFC IAW SR 1Feb 8, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/StringerSDR UIEA2011020700043Structure · damagedVERTICAL STABILIZER L/E CAP AT L/E STA 133.581 RT SIDE DAMAGED OUT OF LIMIT IAW SRM 55-30-01 DEPTH FOUND TO BE 0.018". TRIMMING OUT OF DAMAGED LEADING EDGE ASSY SKIN CARRIED OUT AS PER SRM 55-3003 FIGURE 2 REV 118. PREPARATION OF DOUBLERS AND FILLER CARRIED Feb 7, 2011 · N355MC · Boeing 747341 · Vertical StabilizerSDR UIEA2011020700042Skin · corrodedFUSELAGE STA 2195, ON S30L, FOUND CORROSION 2" BY 1" AND SKIN CRACKED ACROSS FASTERNER 1.5". TO PROVIDE ACCESS TO DETERMINE EXTEND OF DAMAGED AND CARRY OUT REPAIR. SKIN TRIMED OUT TO COMPLETELY REMOVE CORROSION DAMAGE. DIMENSION OF TRIM OUT L= 4.25" X W = 3.2Feb 7, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011012400123Skin · crackedDURING D-CHECK, BS 2184 FUSELAGE SKIN AT STRINGER 39R, FOUND CRACKED DURING INSPECTION. REPAIRED USING GAUGE 0.071" DOUBLER 10.5 X 7.3". HOLES PICKED UP AND PROTECTED PER SRM 51-30-02. FRAME, WEB, CLIPS AND STIFFERNERS INSTALLED. SKIN REPAIR IS CAT B. PER SRJan 24, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011012400119Bulkhead · crackedDURING D CHECK OF DATUM AIRCRAFT, ONE CRACK OF 1.75 INCH LONG FOUND ON OUTER RING CHORD AFT SIDE ON FWD PRESSURE BULKHEAD IN NOSE SECTION AT STA 140, S-19R, WL248. SEE FIGURE 1 AND 2 FOR DAMAGE REPORT AND DETAILED LOCATION. AN OUTER RING CHORD CRACK THAT IS PEJan 24, 2011 · N355MC · Boeing 747341 · Fuselage Main, BulkheadSDR UIEA2011011700127Skin · scratchedFOUND SCRATCH MARK (APPROX 1.5") ON VERTICAL STABILIZER LEADING EDGE CAP AT LE STA 135.581, BLENDING CARRIED OUT ON SCRATCH MARKS ON ABOVE SAID LOCATION. FOUND OUT OF LIMIT AS PER SRM 55-30-01. FIG 1 DETAIL I. DEPTH FOUND IS 0.018" L/E CAP REMOVED FOR S/M REPAJan 17, 2011 · N355MC · Boeing 747341 · Vertical Stabilizer, Plate/SkinSDR UIEA2011011500130Door · dentedDURING D-CHECK OF THE DATUM AIRCRAFT, FOUND THE APU DOOR DENTED AND BENT AT LOWER FOWARD CORNER. THE DAMAGE COVERS AN AREA OF APPROXIMATELY 4.5-IN BY 5.25-IN. SKIN FWD EDGE REPAIRED IAW 52-40-02.Jan 15, 2011 · N355MC · Boeing 747341 · Auxiliary Power Unit (APU) DoorsSDR UIEA2011011400126Stringer · crackedDURING D-CHECK, FUSELAGE BS 2090 STRINGER 29R WAS FOUND CRACKED DURING INSPECTION. THE CRACKED STRINGER WAS REPAIRED PER SRM 53-10-03 FIGURE 1, BY SPLICING THE STRINGER 29R, AT BS 2101 TO BS 2115.Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/StringerSDR UIEA2011011400098Intercostal · corrodedBULK CARGO STA 2000 - 1920, ANCHOR NUTS UNDER SKIN CORRODED AT RBL 50 INTERCOSTAL. TO REMOVE NUT FOR DAMAGE REMOVAL DETERMINES LIMITS.(NUTS REMOVED AND BLENDOUT PLC SRM 51-10-01. AHCHOR NUT HOLES CORRODED THROUGH TO DO REPAIR AT STA 2000. REPAIR DONE PER SRM 5Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400099Intercostal · corrodedBULK CARGO INTERCOSTAL AT RBL 45. SKIN CORRODED UNDER ANCHOR NUT AT STA 1935. TO REMOVE NUT AND REMOVE DAMAGE FOR ASSESSMENTS. (BLENDING DONE. MATERIAL THICKNESS = 0.063. REMAINING = 0.040. INTERCOSTAL FABRICATED PER DRAWING 65B06126 REV F. CAUSING MATERIAL BJan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400100Intercostal · corrodedBULK CARGO INTERCOSTAL AT RBL 45 STA 2040-2060. SKIN UNDER ANCHOR NUTS CORRODED. TO REMOVE ANCHOR NUTS FOR DAMAGE REMOVAL AND TO DETERMINE LIMITS.(BLENDING DONE. MATERIAL THICKNESS = 0.063. REMAINING = 0.040. INTERCOSTAL FABRICATED PER DRAWING 65B061261 REV F.Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400107Intercostal · corrodedBULK CARGO STA 1940 - 1945 RBL 22.5. ANCHOR NUT UNDER SKIN CORRODED ON INTERCOSTAL. TO REMOVE NUT. REMOVE DAMAGE AND FIND LIMITS.(NUTS REMOVED. BLEND OUT DONE PER SRM 51-10-01. OUT OF SERVICEABLE LIMITS TO REPLACE INTERCOSTAL. INTERCOSTAL SPLICED AT STA 1970 Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400112Intercostal · corrodedBULK CARGO INTERCOSTAL AT STA 2040 -0 2100 RBL 22.5, ANCHOR NUTS UNDER SKIN CORRODED. TO REMOVE NUTS AND REMOVE CORROSION AND DETERMINE LIMITS.(NUTS REMVOED, BLENDOUT DONE PER SRM 57-10-01. FOUND CORRODED THROUGH. INTERCOSTAL REPLCAED PER SRM 51-30-02. SATIS. Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400113Intercostal · corrodedBULK CARGO INTERCOSTAL AT STA 1920 - 1940 RBL 45 ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPAIR.(INTERCOSTAL REMOVED PER SRM 51-30-02. REPLACEMENT DONE PER SRM 51-30-02. SATISFACTORY. NUTS REPLACED PER SRM 51-30-02)Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400114Intercostal · corrodedBULK CARGO INTERCOSTAL AT STA 1955 RBL 50 ANCHOR NUT UNDER SKIN CORRODED. TO REMVOE NUT, REMOVE DAMAGE AND DETERMINE LIMITS(NUTS REMVOED AND BLENDOUT PER SRM 51-10-01. ANCHOR NUT HOLES CORRODED THROUGH. TO DO REPAIR AT STA 12000. REPAIR DONE PER SRM 53-10-07Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400115Intercostal · corrodedBULK CARGO INTERCOSTAL STA 2070. 2025 1965 - 1940 LBL 37.5 ANCHOR NUT UNDER SKIN CORRODED. TO REMOVE NUT, REMOVE DAMAGE AND DETERMINE LIMITS.(INTERCOSTAL REMOVED AND REPALCED PER SRM 51-30-02. NUTS REPLACED PER SRM 51-30-02. SATIS.)Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400116Intercostal · corrodedBULK CARGO INTERCOSTAL STA 1920- 2160. LBL 22.5. ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPLACEMENT(ANCHOR NUTS REMOVED AND BLENDOUT DONE PER SRM 51-10-01. MATERIAL THICKNESS = 0.065. REMAINING THICKNESS 0.060". WITHIN SERVICEABLE LIMITS EPR SRM 53-10-00. Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011400117Intercostal · corrodedBULK CARGO INTERCOSTAL STA 1920 - 1945 LBL 15. ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPAIR.(INTERCOSTAL REMOVED AND REPLACED PER SRM 51-30-02. NUTS REPLACED PER SRM 51-30-02. SATISFATORY.)Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA2011011200125Skin · crackedDURING D-CHECK, FUSELAGE BS 2170, STRINGER 39R WAS FOUND CRACKED DURING INSPECTION. THE CRACKED STRINGER WAS REPAIRED PER SRM 53-10-03 FIGURE 1, BY SPLICING THE STRINGER 39R, AT BS 2144 TO BS 2158. AT THE SAME LOCATION FUSELAGE SKIN ALSO WAS FOUND CRACKED . THJan 12, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011011100094Stringer · corrodedAFT CARGO STA 1700 S40L. STRINGER TOP FLANGE CORRODED 1/2" X 1/4". STRINGER REMOVED FOR REPAIR. REPAIR PARTS FABRICATED PER SRM 53-10-03. WEB, STIFFENERS AND CLIPS INSTALLED PER SRM 51-30-02.Jan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/StringerSDR UIEA2011011100095Stringer · corrodedAFT CARGO STA 1725 - 1733 S36L CORROSION FOUND AT BASE OF STRINGER. BLENDED PER SRM 51-10-01. MATERIAL THICKNESS = 0.063. REMAINING THICKNESS = 0.04. OUT OF SRM LIMITS PER SRM 53-10-01. STRINGER REPAIR PARTS FABRICATED PER SRM 53-10-03. REPAIR PARTS ASSEMBLJan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, StructureSDR UIEA2011011100096Stringer · corrodedAFT CARGO BS 1721 S40L, STRINGER BASE CORRODED. TO REMOVE FASTENERS AND FREE STRINGER FOR CORROSION REMOVAL.(FASTENERS REMOVED, TO DETERMINE EXTENT OF DAMAGE. BLENDED PER SRM 51-10-01. MATERIAL THICKNESS = 0.090. REMAINING THICKNESS 0.04" OUT OF LIMITS PER SRMJan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/StringerSDR UIEA2011010600128Skin · corrodedFOUND PITTING CORROSION AT MULTIPLE LOCATIONS FROM STA 1383.0 TO STA 1480. BELOW STR 19L LAP JOINT. BLENDOUT CARRIED OUT AS PER SRM 53-30-01 AND SRM 51-10-01. THOROUGH VISUAL CHECK CARRIED OUT WITH 10X MAGNIFYING GLASS. NO FURTHER CORROSION FOUND. THICKNESS Jan 6, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA2011010600093Stringer · corrodedCARGO AFT COMPARTMENT STA 1743 S42R. STRINGER CORRODED BELOW TOP HAT 3" CORROSION REMOVED PER SRM 53-30-01. DAMAGED SKIN TRIMMED OUT. STRINGER REPLACED PER SRM 51-30-02.Jan 6, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/StringerSDR Q2SA789030Acm · malfunctionedDURING CLIMB, A BURNING BLEED AIR ODOR WAS DETECTED. SHUTOFF NR 3 A/C PACK AND BURNING ODOR WENT AWAY. REPLACED AIR CYCLE MACHINE IAW AMM 21-51-04, OPS CHECK GOOD. OPS CHECKED IAW AMM 21-51-00.Jan 6, 2011 · N789SA · Boeing 747341 · Cabin Cooling SystemSDR UIEA2010073100133Rod End · brokenAFTER LANDING PERFORMED, 180 DEGREE TURN AND THE RT BODY UNLOCK LIGHT ILLUMINATED AND ACFT WOULD NOT MOVE. WENT OUT FOR VISUAL INSP AND FOUND 1 ALT ROD END BROKEN. (R & R RT BODY GEAR ACTUATOR IAW AMM 32-13-15. OPS CK SATIS. NO LEAKS FOUND.)Jul 31, 2010 · N355MC · Boeing 747341 · Landing Gear Retraction/Extension SystemSDR UIEA201000188Frame · crackedEO 4753A448, A CRACK WAS FOUND IN THE BS 420, S-10R FRAME WEB . THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. PART 1 OF THIS EO DOCUMENTS THE FRAME WEB REPAIR IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. THE REPAIR CONSISTMay 20, 2010 · N355MC · Boeing 747341 · Fuselage Main, FrameSDR UIEA201000067Tire · damagedAFTER LANDING DISCOVERED NR 14 TIRE FLAT SPOTTED. REPLACED NR 14 TIRE AND REPLACED NR 13 TIRE PRECAUTIONARY DUE OVERLOAD AND REPLACED NR 14 WHEEL TRANSDUCER. PRECAUTIONARY REPLACED, ANTI-SKID CONTROL VALVE, ANTI-SKID SERVO VALVE AND ANTI-SKID BOX DUE HISTORYMar 29, 2010 · N355MC · Boeing 747341 · TireSDR UIEA201000051Failsafe · crackedFUSELAGE - BS 860, S6-7R FRAME FAIL-SAFE CHORD CRACK REPAIR SRM 53-30-1 FIGURE 1, DETAILS I AND II. REPEAT REQ: PERMANENT.Feb 22, 2010 · N355MC · Boeing 747341 · Fuselage Main, FrameSDR UIEA201000057Floorbeam · crackedFUSELAGE: BS 680, BL28-30 FLOORBEAM WEB CRACK REPAIR SRM 53-10-07, FIG 11, COMPLETED.Feb 17, 2010 · N355MC · Boeing 747341 · Fuselage Main, Floor BeamSDR UIEA201000041Door · damagedDOOR - RT BODY GEAR DOOR DAMAGE. REPAIRED PER SRM 52-80-01, FIG 3, SH 6 ITEM 3, SRM 51-40-02, SRM 51-40-03. REPEAT REQUIREMENT: PERMANENT.Feb 17, 2010 · N355MC · Boeing 747341 · Landing Gear DoorsSDR UIEA201000056Strap · crackedFUSELAGE - BS 1241, LT BULKHEAD - SPLICE STRAP AND FORGING CRACK - REPAIR 747-53-2283, REV 4.Feb 16, 2010 · N355MC · Boeing 747341 · Fuselage Main, BulkheadSDR UIEA201000055Skin · dentedFUSELAGE - BS 1520 - 1540, S43L-44L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.Feb 15, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA201000054Skin · dentedFUSELAGE - BS 2060-2080, S39L-40L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.Feb 14, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/SkinSDR UIEA201000049Beam · crackedFUSELAGE - BS 540-560, RBL 45 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.Feb 14, 2010 · N355MC · Boeing 747341 · Fuselage Miscellaneous StructureSDR UIEA201000053Skin · dentedFUSELAGE - BS 740-755, S46L; 46R SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: I-15,000 FC. R-6,000 FC.Feb 13, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
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