Boeing 747-2D3B
Service difficulty reports · 182
Newest first. General aviation reporting is voluntary.
Query with SQL
duckdb -csv -c "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 = '7472D3B' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
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 = '7472D3B' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR UIEA01077Frame · crackedDURING INSPECTION FOUND FRAME CRACKED AT BS 400, STRINGER 15L CUT OUT. CRACK IS APPROXIMATELY .30 INCH LONG RUNNING FROM STRINGER CUT OUT TO FASTENER HOLE. HFEC INSPECTED EXISTING FASTENER HOLE FOR CRACK CONTAINMENT. NO ADDITIONAL CRACKS FOUND. FABRICATED SDR UIEA01078Frame · crackedDURING INSPECTION FOUND FRAME AND CHORD CRACKED AT BS 440, STRINGER 13AL/14L. CRACK IS APPROX 1 INCH LONG. CHORD IS COMPLETELY SEVERED. HFEC INSPECTED EXISTING FASTENER HOLE IN FRAME FROM CRACK CONTAINMENT. NO ADDITIONAL CRACKS FOUND. FABRICATED REPLACEMESDR UIEA01079Frame · crackedDURING INSPECTIN FOUND FRAME WEB CRACKED AT BS 460, STRINGER 13AL AT TWO LOCATIONS COMMON TO THE FRAME AND DOUBLER. HFEC INSPECTED EXISTING FASTENER HOLES IN WEB FOR CRACK CONTAINMENT. NO ADDITIONAL CRACKS FOUND. FABRICATED REPLACEMENT DOUBLERS, FILLERS ANDSDR 2001F00222Frame · crackedDURING INSPECTION FOUND FRAME WEB CRACKED AT BS 500, STRINGER 9L AND STRINGER 8 TO 10AR. STOP DRILLED ALL CRACKS. FABRICATED REPLACEMENT DOUBLERS. INSTALLED DOUBLER AT STRINGER 9L LOCATION AND AT STRINGER 8 TO 10AR LOCATION PER STANDARD PRACTICES OF THE SRMSDR UIEA01080Web · crackedDURING INSPECTION FOUND FRAME WEB CRACKED AT BS 500, STRINGER 9L AND STRINGER 8 TO 10AR. STOP DRILLED ALL CRACKS. FABRICATED REPLACEMENT DOUBLERS. INSTALLED DOUBLER AT STRINGER 9L LOCATION AND AT STRINGER 8 TO 10AR LOCATION PER STANDARD PRACTICES OF THE SRMSDR UIEA01081Frame · crackedDURING INSPECTION FOUND FRAME WEB CRACKED AT BS 480 BETWEEN STRINGER 15 AND 16R CUT OUTS. STOP DRILLED CRACKS. FABRICATED REPLACEMENT DOUBLER. INSTALLED DOUBLER PER STANDARD PRACTICES OF THE SRM. CONTINUE CURRENT INSPECTION REQUIREMENTS PER SB 747-53A2265 SDR UIEA01082Frame · crackedDURING INSPECTION FOUND FRAME AN INNER CHORD CRACKED AT BS 440 STRINGER 15R TO EXISTING FASTENER. HFEC INSPECTED EXISTING FASTENER HOLE TO INSURE CONTAINMENT OF CRACK. NO ADDITIONAL CRACKS FOUND. FABRICATED REPLACEMENT DOUBLER AND NEW CLIP. PROCURRED NEW RSDR UIEA01083AngleDURING INSPECTION FOUND NR 4 PYLON REAR ENGINE MOUNT OUTBOARD UPPER BULKHEAD ANGLE CRACKED AT FIRST FASTENER COMMON TO THE CENTER LINE OF PYLON. PYLON HAS KIN CAP IN PLACE (PCW). TRIMMED AWAY CRACKS. FABRICATED STRAP AND ANGLE. OVERSIZED EXISTING HOLES IN RSDR UIEA01084Skin · corrodedDURING INSPECTION, FOUND CORROSION INSIDE THE LEFT WING BOOST PUMP HOUSING AT WS 677 ON THE UPPER WING SKIN SURFACE LIP EXPOSED WITHIN THE HOUSING. CORROSION REMOVED, POLISHED, SHOT PEENED, TREATED AND MEASURED. AREA FILLED IN WITH EPOCAST. ROTART DOOR LATCSDR UIEA01085Fitting · corrodedDURING INSPECTION FOUND BOTH LEFT AND RIGHT MAIN LANDING BODY GEAR UPPER TRUNNION FITTING HAVE CORROSION IN THE FORWARD BOLT HOLE POCKET. REMOVED CORROSION PER SRM 51-10-01. MEASURED AND SPOT FACED AREA. PERFORMED PENETRANT INSPECTION PERFORMED. NO CRACKS SDR UIEA01086ShimDURING INSPECTION FOUND SHIMS MIGRATING FROM BS 1240 LEFT/RIGHT BULKHEAD UPPER CHORD FITTING. REMOVED BOLTS IN AFFECTED AREA, TRIMMED SECTION OF MIGRATED SHIM. FABRICATED REPLACEMENT SHIM FROM SOLID MATERIAL, ALODINED AND PRIME PAINTED. REINSTALLED REMOVED SDR UIEA01087Fitting · corrodedDURING INSPECTION FOUND LEFT AND RIGHT BODY GEAR INBOARD TRUNNION SUPPORT FITTINGS CORRODED AT BS 1480 AFT SIDE OF LUG AT LONGERON ATTACH POINT. CLEANED CORROSION, SPOT FACED AFFECTED AREAS, FLAP PEENED, TREATED, PRIME PAINTED. PENETRANT INSPECTION PERFORMEDSDR UIEA01088Web · corrodedDURING INSPECTION FOUND WEB CORRODED BEHIND BS 1480 INBOARD BODY GEAR VERTICAL TRUNNION SUPPORT. CORROSION BLENDED PER SRM 51-10-01. PERFORMED HFEC OF BLENDED AREA TO INSURE CRACK AND CORROSION FREE. NO CRACKS OR CORROSION. MEASURED BLEND AREAS. FABRICATESDR UIEA01089Fitting · corrodedDURING INSPECTION FOUND CORROSION AT BS 1480 LEFT AND RIGHT BULKHEAD CAP FITTINGS. CORROSION BLENDED PER SRM 51-10-01. PERFORMED HFEC OF BLENDED AREA TO INSURE CRACK AND CORROSION FREE. NO CRACKS OR CORROSION. MEASURED BLENDED AREAS. OVERSIZED EXISTING HOSDR UIEA01074Skin · crackedDURING HFEC INSPECTION FOUND THE LOWER AFT CARGO COMPARTMENT DOOR CUTOUT, UPPER FORWARD CORNER SKIN CRACKED AT STATION 1814, STRINGER 27R. CRACK TRIMMED AWAY. FILLER AND REPAIR DOUBLER FABRICATED AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-30-03 FIG 60 TSDR UIEA01075Floorbeam · crackedDURING INSPECTION FOUND FLOORBEAM WEB CRACKED AT BS 270 NEAR STRINGER 13 BOTH LEFT AND RIGHT SIDE. FASTENERS REMOVED, OPEN HOLE HFEC INSPECTION PERFORMED TO ENSURE NO OTHER CRACKS. NO ADDITIONAL CRACKS FOUND. FABRICATED REPLACEMENT DOUBLERS AND CLIP. INSTASDR P5CA0401104Fire Loop · inoperativeNR 2 ENGINE A-LOOP INOP IN FIRE TEST MODE. TRANSFERRED TO DMI 32697 AND PLACARD PER MEL 26-1.SDR UIEA00052ASkin · crackedDURING HFEC INSPECTION PER SB 747-53A2488 FOUND LOWER LOBE CARGO COMPARTMENT AFT DOOR UPPER CUT OUT, FORWARD CORNER CRACKED UNDER 2 INCHES. SHIMS OVER .055 THICK. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR DOUBLER. INSTALLED IAW SRM 53-30-03 TYPE II DSDR UIEA01054Skin · crackedDURING HFEC INSPECTION PER SB 747-53A2488 FOUND LOWER LOBE CARGO COMPARTMENT AFT DOOR UPPER CUT OUT, FORWARD CORNER CRACKED UNDER 2 INCH. SHIMS OVER .055 THICK. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR DOUBLER. INSTALLED IAW SRM 53-30-03 TYPE II. (SDR UIEA0033Skin Panel · crackedDURING ACCOMPLISHMENT OF ATLAS EO 4753A099, INSPECTION REVEALED A 1 INCH SKIN CRACK AT BS 980, STRINGER 38L. FURTHER DISASSEMBLY REVEALED TWO ADDITIONAL CRACKS UNDER THE LOWER DRAG FITTING FORWARD HOLE, ONE WAS 1 INCH LONG AND THE OTHER WAS 3 INCH. THE 1 INCSDR UIEA00028Warning System · activatedFLT GT051 - MIA/BOG-ATB, NR 4 ENGINE A AND B LOOP FIRE WARNING LIGHTS ILLUMINATED AND BELL SOUNDED. BOTH LOOPS WENT TO 5. AIRCRAFT RETURN TO MIA WAS UNEVENTFUL. MAINTENANCE FOUND CLAMP TO 8TH STAGE DUCT FAILED AND THRUST REVERSER HALVES DAMAGED. REPLACED ASDR UIEA0005Web · corrodedSPOT CORROSION UNDER FRAME SUPPORT FITTING LEFT WHEEL WELL OUTBOARD FORWARD CORNER, AFT FACE CENTER TANK WEB, STATION 1264 LBL 100. CORROSION REMOVED, AREA MEASURED AND WITHIN LIMITS, SURFACE TREATED AND PAINTED IAW SB 747-57-2263R2 AND SRM 51-40-02 REVE 86. SDR UIEA0007Bolt · crackedDURING INSPECTION OF LEFT KICK PLATE, AFT FACE CENTER TANK, LOWER SPAR PER SB747-57A2309, TWO BOLTS WERE FOUND SHEARED. ATLAS QC INSISTED ON AND U/T INSPECTION AND DISCOVERED AN ADDITIONAL TWO BOLTS FAILED. FAILED BOLTS REMOVED, HOLES CLEANED, INSPECTED, REISDR UIEA0006Bolt · crackedDURING INSPECTION OF RIGHT KICK PLATE, AFT FACE CENTER TANK, LOWER SPAR PER SB747-57A2309, ONE NUT WAS FOUND SHEARED. ATLAS QC INSISTED ON AN U/T INSPECTION AND DISCOVERED AN ADDITIONAL TWO BOLT FAILED. FAILED BOLTS REMOVED, HOLES CLEANED, INSPECTED, REINSTASDR UIEA9994Spar Web · corrosionWING CENTER SECTION, BS 1241 REAR SPAR WEB CORROSION. CORROSION REMOVED FROM WEB AND REWORKED, THIS IS AN APPROVED ALTERNATE METHOD OF COMPLIANCE REF 8110-3. (M)SDR UIEA9992Bolt · crackedLEFT WING REAR SPAR STATION 1241, LOWER SPLICE PLATE AND KICK FITTING INBOARD BOLT AND BOLT HOLE HAS CRACK INDICATIONS, VERIFIED WITH HFEC INSPECTION. OVERSIZED KICK FITTING AND REAR SPAR LOWER CHORD BOLT HOLE TO .975 INCH. VERIFIED HOLE IS CRACK FREE WITH HSDR UIEA9991Spar Web · crackedRIGHT WING MID SPAR UPPER CHORD FOUND WEB CRACKS. INDICATIONS VERIFIED USING HFEC INSPECTION, BETWEEN MSS 563.24 AND 592.45. AT MSS 575 THE WEB AT THE TWO CRACKED FASTENER HOLES WERE TRIMMED OUT AND A PERMANENT REPAIR WAS ACCOMPLISHED USING FILLERS, A DOUBLESDR UEIA9993Skin · crackedLEFT WING STATION 1241 SPLICE STRAP AND SKIN FOUND CRACKED IN FORWARD HOLE, VERIFIED WITH HFEC INSPECTION. FAIL/SAFE STRAP WAS REMOVED AND REPLACED AND CRACKED SKIN WAS TRIMMED OUT AND REPAIRED. THIS IS AN APPROVED ALTERNATE METHOD OF COMLIANCE REF 8110-3. SDR UIEA9924Tire · failedFLT EK9990 - AMS/DXB - ATB - DURING TAKEOFF ROLL, AIRFRAME VIBRATION OCCURRED AT 160 KNOTS. VIBRATION INCREASED AS AIRSPEED INCREASED. ALL OTHER INDICATION NORMAL. ON CLIMB-OUT, AMS CONTROL ADVISED THAT PIECES OF RUBBER WERE FOUND ON THE RUNWAY. ATLAS AIR SDR UIEA9910Wheel · failedFLT 1871 - BTB - DURING TAXI OUT, CREW REPORTED THAT THEY FELT A BUMP AND HEARD A LOUD BANG. AIRCRAFT STOPPED AND AREA CHECKED. FOUND NR 8 WHEEL RIM BROKE, DAMAGE TO NR 11 RIM, LEFT BODY GEAR DOORS, WIRING CONDUITS AND TRUCK BEAM. PERFORMED FAILED TIRE INSPECSDR UIEA9705Actuator · damagedCREW REPORTS: ON MAINTENANCE WALK-A-ROUND CHECK, FOUND RT INBD MID T/E FLAP, AFT T/E FLAP, AND SPOILER NR 7 DAMAGED. FURTHER INVESTIGATION REVEALED THAT NR 7 SPOILER ACTUATOR ALSO DAMAGED. BELIEVE SPOILER FAILURE CAUSED DAMAGE TO T/E FLAPS. SPOILER PANEL PSDR 96ZZZX495Cover Plate · seal leakLUX - AIRCRAFT DEPARTED, DURING CLIMB THE NR 2 ENGINE'S OIL QUANTITY DROPPED AND WAS SHUT DOWN. AIRCRAFT RETURNED TO LUX AND LANDED SAFELY. OIL SERVICED AND ENGINE MOTORED - NO LEAK, IDLE CHECK - NO LEAK, POWER LEVEL ADVANCED AND LEAK APPEARED AT THE GEARBOX
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