# Service difficulty reports: Boeing 747-341

A list on [Boeing 747-341](https://openairdocs.org/model/boeing-747-341.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 4 · 174 reports

- [SDR UIEA2011122300728](https://openairdocs.org/sdr/UIEA2011122300728.md): Skin · damaged · Dec 21, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > THE 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 REPAI
- [SDR UIEA2011102000603](https://openairdocs.org/sdr/UIEA2011102000603.md): Relay · malfunctioned · Oct 16, 2011 · N355MC · Boeing 747341 · Cabin Pressure Control System
  > AIR 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
- [SDR UIEA2011102000602](https://openairdocs.org/sdr/UIEA2011102000602.md): Logic Card · inoperative · Oct 15, 2011 · N355MC · Boeing 747341 · Cabin Pressure Control System
  > AIRTURN 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. TH
- [SDR UIEA2011081000452](https://openairdocs.org/sdr/UIEA2011081000452.md): Fairing · cracked · Aug 10, 2011 · N355MC · Boeing 747341 · Aerodynamic Fairings
  > DURING 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.
- [SDR UIEA2011080700423](https://openairdocs.org/sdr/UIEA2011080700423.md): Spoiler Sys · malfunctioned · Aug 7, 2011 · N355MC · Boeing 747341 · Drag Control System
  > WHEN 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 ACFT
- [SDR UIEA2011080600429](https://openairdocs.org/sdr/UIEA2011080600429.md): Skin · damaged · Aug 6, 2011 · N355MC · Boeing 747341 · Engine Thrust Reverser
  > DURING 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.
- [SDR UIEA2011052700267](https://openairdocs.org/sdr/UIEA2011052700267.md): Relief Valve · defective · May 27, 2011 · N355MC · Boeing 747341 · Pneumatic Distribution System
  > DURING 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
- [SDR UIEA2011032800163](https://openairdocs.org/sdr/UIEA2011032800163.md): Panel · gouged · Mar 28, 2011 · N355MC · Boeing 747341 · Elevator, Plate/Skin
  > DURING 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 POTTI
- [SDR UIEA2011032000157](https://openairdocs.org/sdr/UIEA2011032000157.md): Access Panel · missing · Mar 20, 2011 · N355MC · Boeing 747341 · Landing Gear Doors
  > DURING 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) AND
- [SDR UIEA2011030100135](https://openairdocs.org/sdr/UIEA2011030100135.md): Rub Strip · damaged · Mar 1, 2011 · N355MC · Boeing 747341 · Engine Air Intake System
  > ACFT 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 PERF
- [SDR UIEA2011022000124](https://openairdocs.org/sdr/UIEA2011022000124.md): Floorbeam · corroded · Feb 20, 2011 · N355MC · Boeing 747341 · Fuselage Main, Floor Beam
  > DURING 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 BLE
- [SDR UIEA2011021900129](https://openairdocs.org/sdr/UIEA2011021900129.md): Skin · corroded · Feb 19, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > DURING 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, 395
- [SDR UIEA2011021900120](https://openairdocs.org/sdr/UIEA2011021900120.md): Skin · cracked · Feb 19, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > DURING 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 TRIM
- [SDR UIEA2011021100062](https://openairdocs.org/sdr/UIEA2011021100062.md): Bulkhead · cracked · Feb 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Bulkhead
  > THE 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 2
- [SDR UIEA2011020800058](https://openairdocs.org/sdr/UIEA2011020800058.md): Stringer · cracked · Feb 8, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/Stringer
  > DURING 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 1
- [SDR UIEA2011020700043](https://openairdocs.org/sdr/UIEA2011020700043.md): Structure · damaged · Feb 7, 2011 · N355MC · Boeing 747341 · Vertical Stabilizer
  > VERTICAL 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
- [SDR UIEA2011020700042](https://openairdocs.org/sdr/UIEA2011020700042.md): Skin · corroded · Feb 7, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > FUSELAGE 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 = 3.2
- [SDR UIEA2011012400123](https://openairdocs.org/sdr/UIEA2011012400123.md): Skin · cracked · Jan 24, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > DURING 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 SR
- [SDR UIEA2011012400119](https://openairdocs.org/sdr/UIEA2011012400119.md): Bulkhead · cracked · Jan 24, 2011 · N355MC · Boeing 747341 · Fuselage Main, Bulkhead
  > DURING 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 PE
- [SDR UIEA2011011700127](https://openairdocs.org/sdr/UIEA2011011700127.md): Skin · scratched · Jan 17, 2011 · N355MC · Boeing 747341 · Vertical Stabilizer, Plate/Skin
  > FOUND 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 REPA
- [SDR UIEA2011011500130](https://openairdocs.org/sdr/UIEA2011011500130.md): Door · dented · Jan 15, 2011 · N355MC · Boeing 747341 · Auxiliary Power Unit (APU) Doors
  > DURING 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.
- [SDR UIEA2011011400126](https://openairdocs.org/sdr/UIEA2011011400126.md): Stringer · cracked · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/Stringer
  > DURING 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.
- [SDR UIEA2011011400098](https://openairdocs.org/sdr/UIEA2011011400098.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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 5
- [SDR UIEA2011011400099](https://openairdocs.org/sdr/UIEA2011011400099.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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 B
- [SDR UIEA2011011400100](https://openairdocs.org/sdr/UIEA2011011400100.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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.
- [SDR UIEA2011011400107](https://openairdocs.org/sdr/UIEA2011011400107.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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
- [SDR UIEA2011011400112](https://openairdocs.org/sdr/UIEA2011011400112.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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.
- [SDR UIEA2011011400113](https://openairdocs.org/sdr/UIEA2011011400113.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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)
- [SDR UIEA2011011400114](https://openairdocs.org/sdr/UIEA2011011400114.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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 53-10-07
- [SDR UIEA2011011400115](https://openairdocs.org/sdr/UIEA2011011400115.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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.)
- [SDR UIEA2011011400116](https://openairdocs.org/sdr/UIEA2011011400116.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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.
- [SDR UIEA2011011400117](https://openairdocs.org/sdr/UIEA2011011400117.md): Intercostal · corroded · Jan 14, 2011 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > BULK 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.)
- [SDR UIEA2011011200125](https://openairdocs.org/sdr/UIEA2011011200125.md): Skin · cracked · Jan 12, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > DURING 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. TH
- [SDR UIEA2011011100094](https://openairdocs.org/sdr/UIEA2011011100094.md): Stringer · corroded · Jan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/Stringer
  > AFT 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.
- [SDR UIEA2011011100095](https://openairdocs.org/sdr/UIEA2011011100095.md): Stringer · corroded · Jan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Structure
  > AFT 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 ASSEMBL
- [SDR UIEA2011011100096](https://openairdocs.org/sdr/UIEA2011011100096.md): Stringer · corroded · Jan 11, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/Stringer
  > AFT 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 SRM
- [SDR UIEA2011010600128](https://openairdocs.org/sdr/UIEA2011010600128.md): Skin · corroded · Jan 6, 2011 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > FOUND 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
- [SDR UIEA2011010600093](https://openairdocs.org/sdr/UIEA2011010600093.md): Stringer · corroded · Jan 6, 2011 · N355MC · Boeing 747341 · Fuselage Main, Longeron/Stringer
  > CARGO 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.
- [SDR Q2SA789030](https://openairdocs.org/sdr/Q2SA789030.md): Acm · malfunctioned · Jan 6, 2011 · N789SA · Boeing 747341 · Cabin Cooling System
  > DURING 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.
- [SDR UIEA2010073100133](https://openairdocs.org/sdr/UIEA2010073100133.md): Rod End · broken · Jul 31, 2010 · N355MC · Boeing 747341 · Landing Gear Retraction/Extension System
  > AFTER 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.)
- [SDR UIEA201000188](https://openairdocs.org/sdr/UIEA201000188.md): Frame · cracked · May 20, 2010 · N355MC · Boeing 747341 · Fuselage Main, Frame
  > EO 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 CONSIST
- [SDR UIEA201000067](https://openairdocs.org/sdr/UIEA201000067.md): Tire · damaged · Mar 29, 2010 · N355MC · Boeing 747341 · Tire
  > AFTER 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 HISTORY
- [SDR UIEA201000051](https://openairdocs.org/sdr/UIEA201000051.md): Failsafe · cracked · Feb 22, 2010 · N355MC · Boeing 747341 · Fuselage Main, Frame
  > FUSELAGE - BS 860, S6-7R FRAME FAIL-SAFE CHORD CRACK REPAIR SRM 53-30-1 FIGURE 1, DETAILS I AND II. REPEAT REQ: PERMANENT.
- [SDR UIEA201000057](https://openairdocs.org/sdr/UIEA201000057.md): Floorbeam · cracked · Feb 17, 2010 · N355MC · Boeing 747341 · Fuselage Main, Floor Beam
  > FUSELAGE: BS 680, BL28-30 FLOORBEAM WEB CRACK REPAIR SRM 53-10-07, FIG 11, COMPLETED.
- [SDR UIEA201000041](https://openairdocs.org/sdr/UIEA201000041.md): Door · damaged · Feb 17, 2010 · N355MC · Boeing 747341 · Landing Gear Doors
  > DOOR - 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.
- [SDR UIEA201000056](https://openairdocs.org/sdr/UIEA201000056.md): Strap · cracked · Feb 16, 2010 · N355MC · Boeing 747341 · Fuselage Main, Bulkhead
  > FUSELAGE - BS 1241, LT BULKHEAD - SPLICE STRAP AND FORGING CRACK - REPAIR 747-53-2283, REV 4.
- [SDR UIEA201000055](https://openairdocs.org/sdr/UIEA201000055.md): Skin · dented · Feb 15, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > FUSELAGE - BS 1520 - 1540, S43L-44L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.
- [SDR UIEA201000054](https://openairdocs.org/sdr/UIEA201000054.md): Skin · dented · Feb 14, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > FUSELAGE - BS 2060-2080, S39L-40L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.
- [SDR UIEA201000049](https://openairdocs.org/sdr/UIEA201000049.md): Beam · cracked · Feb 14, 2010 · N355MC · Boeing 747341 · Fuselage Miscellaneous Structure
  > FUSELAGE - BS 540-560, RBL 45 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.
- [SDR UIEA201000053](https://openairdocs.org/sdr/UIEA201000053.md): Skin · dented · Feb 13, 2010 · N355MC · Boeing 747341 · Fuselage Main, Plate/Skin
  > FUSELAGE - BS 740-755, S46L; 46R SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: I-15,000 FC. R-6,000 FC.

Next page: https://openairdocs.org/model/boeing-747-341/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE aircraft_model_key = '747341'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/boeing-747-341/reports

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