JASC 5740
Service difficulty reports · 3,003
Reports filed under 5740 · Wing, Attach Fittings, newest first.
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 jasc_code = '5740' 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 jasc_code = '5740' 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 AU990290Fitting · corroded(AUS) LEFT FORWARD LOWER WING ATTACHMENT FITTING CONTAINED SEVERE EXFOLIATION CORROSION IN THE AREA OF THE GUSSET.SDR CA990323010Bolt · damaged(CAN) WHILE COMPLETING AD CF-81-25R5, WING BOLT INSPECTION, THE RIGHT FORWARD LOWER BOLT WAS FOUND TO BE VERY TIGHT. AFTER REMOVAL OF THE BOLT, DISCOVERED THE BOLT AND NUT WERE DAMAGED WHICH MADE THE BOLT VERY DIFFICULT TO REMOVE. UPON FURTHER INVESTIGATION,SDR CA990318002Fitting · cracked(CAN) CRACK FOUND IN BOTH THE RIGHT HAND WING LOWER FRONT SPAR AND LOWER REAR SPAR WING TO FUSELAGE FITTING. CRACKS CAN BE SEEN FROM MAIN WHEELWELL. COMPANY PLANS TO X-RAY WINGS, CAPS WEBS, ETC., AND ALSO TO CHECK THE REST OF THEIR FLEET. AIRCRAFT USED SOMSDR CA981230060Bolt · cracked(CAN) WHILE DOING AD CF-81-25R5, NDT TEST SHOWED A SMALL CRACK IN THE RADIUS OF THE BOLT HEAD. IT IS POSSIBLE THAT CRACK IS OVERLAP OF CAD PLATING.SDR 99ZZZX289Fitting · failedAIRCRAFT SUFFERRED AN IN-FLIGHT BREAK-UP DUE TO SEPARATION OF THE RIGHT WING LOWER STRUT CONNECT FITTING. WING SEPARATED FROM AIRCRAFT. PRELIMINARY INVESTIGATION REVEALS POSSIBLE FRACTURE OF ATTACH FITTING AT THE WELD TO FUSELAGE. REF: PTRS NR GL219901523.SDR AU981337Bushing · damaged(AUS) LEFT AND RIGHT STRUT ATTACHMENT BUSHES SEVERELY DAMAGED.SDR AU981335Lift Strut · misinstalled(AUS) MAIN LIFT STRUT ATTACHMENT TO STABILIZER STRUT TEFLON STRIPS HAD THE TEFLON COATING WORN AWAY. THE TEFLON WASHERS HAD BEEN SUBSTITUTED WITH ENGINE LOCK TABS. UNAPPROVED PART.SDR AU981334Bolt · failed(AUS) STABILIZING STRUT TO LIFT STRUT ATTACHMENT BOLTS OVERTORQUED AND BOLTS STRETCHED.SDR CA981019007Bushing · damaged(CAN) COUNTERSUNK WASHER FOUND INSTALLED UPSIDE DOWN ON BOLT P/N NAS6712D52 IN OTHER WORDS, THE COUNTERSINK IS FACING AWAY FROM HEAD OF BOLT. COUNTERSINK BEARING AGAINST THE BUSHING DAMAGING IT.SDR CA980922010Angle · cracked(CAN) WHILE DOING AD CF-97-07 OF WING-TO-FUSELAGE FITTINGS, A CRACK WAS FOUND ON THE RIGHT HAND FORWARD OUTBOARD ANGLE AT THE LOWER 3 FASTENER HOLE LOCATION. THE CRACK WAS VISIBLE TO THE NAKED EYE. CRACK EXTENDED FROM THE CENTER OF FASTENER HOLE TO WITHIN .5SDR CA981027001Fitting · worn(CAN) RIGHT HAND WING FOUND MOVING EXCESSIVELY AT ALL ATTACH POINTS. FITTINGS FOUND WORN TO .016 INCH PLAY. FITTINGS BUSHED IAW CESSNA INSTRUCTIONS AND NAS CLOSE TOLERANCE BOLTS INSTALLED.SDR 98ZZZX2264Bolt · crackedDYE CHECK FOUND A CRACK INDICATION AT THE BOLT HEAD RADIUS. BOLT WAS INCLUDED IN KIT P/N 101-4026-3S, S/N 7673.SDR 98ZZZX1910Bolt · failedDURING THE 7,000 HOUR WING CARRY-THROUGH STRUCTURE INSPECTION AND WING BOLT REPLACEMENT, FOUND BOLT HEAD, WASHER, AND SPACER LYING IN BOTTOM OF SPAR. NOTED CORROSION BETWEEN PARTED SURFACES OF BOLT AND HEAD - SUSPECT CAUSE OF BOLT FAILURE. NOTE: AIRCRAFT ESDR CA980512022Fitting · cracked(CAN) ON 400 HOUR INSPECTION, THE RIGHT HAND WING STRUT LUG FITTING STRUT TO FUSELAGE WAS FOUND CRACKED ON THE INSIDE RADIUS.SDR CA980430022Attach Plate · cracked(CAN) DURING INSPECTION, A SMALL CHIP OF PAINT FOUND ON RIGHT WING FRONT LUG PLATE OUTBOARD OF LUG ATTACH. CLOSER INSPECTION, UNCOVERED EVIDENCE OF STRESS CORROSION AND .1875 INCH FORE AND AFT CRACK ON THE PLATE EXTENDING .25 INCH VERTICALLY. LEFT WING FRONSDR CA980330015Angle · cracked(CAN) ON ROUTINE WING INSPECTION, THE RT OUTBOARD FLAP INBOARD FLAP HANGER, LOWER CLIPS P/N 35-115 396-1 AND -3 WERE FOUND TO BE TORN AT HANGER RIVET ATTACHMENTS AND THE LOWER PORTION OF THE HANGER TO SPAR ATTACHMENT ANGLES P/N 35-115398-1 AND -3 WERE TORN AWASDR CA980330014Nut · cracked(CAN) WHILE COMPLYING WITH AD CF-81-25R, FLUORESCENT PENETRANT INSPECTION SHOWED NUT ON THE RT UPPER AFT WING BOLT WAS CRACKED. THE NUT WAS ALSO FOUND TO BE THREAD BOUND WHEN TORQUED TO SPECIFICATIONS. A NEW WING BOLT KIT WAS INSTALLED WHICH CORRECTED THE PRSDR 98ZZZX1162Angle · crackedDURING ANNUAL INSPECTION AND C/W WING ATTACH ANGLE BOLT INSPECTION, OUTBOARD WING ATTACHMENT ANGLE FOUND CRACKED.SDR 99ZZZX579Bolt · cracked8727 AACT 20,988 TL. FIRST FIVE YEAR WING BOLT INSPECTION AFTER REPLACEMENT. THE LEFT AND RIGHT LOWER FORWARD WING (INCONEL) BOLTS WERE FOUND CRACKED USING DIE PENETRANT. ONE BOLT WAS VERIFIED TO BE CRACKED USING A MICROSCOPE. ONE BOLT WAS VERIFIED TO BE CSDR CA980113007Wing Bolt · cracked(CAN) WHILE PERFORMING AD CF-81-25R5, A CRACK WAS DETECTED. THE RIGHT HAND LOWER FORWARD BOLT WAS FOUND CRACKED AT THE SHANK.SDR CA971231027Bolt · corroded(CAN) DURING REMOVAL OF WINGS FOR TRANSPORT, THE LT WING FORWARD ATTACHMENT BOLT FOUND CORRODED. REPLACED.SDR 98ZZZX88Fitting · damagedWHILE C/W WING BOLT REPLACEMENT AND WING INSPECTION, FOUND LOWER AFT WING FITTINGS ON BOTH WINGS WITH COMPRESSION MARKS. BEECHCRAFT FIELD SERVICE CONTACTED PER MM INSTRUCTIONS. SPECIAL TOOLING AVAILABLE TO RESURFACE FITTING FACE. SUBMITTER SUGGESTED OWNERS SDR AALA974040Bearing Plate · corrodedAFW - BEARING PLATE HAD CORROSION BEYOND SRM LIMITS AFTER BLEND OUT. LOCATED SIDE OF BODY TO REAR SPAR CENTER WING SECTION. TST: 42,646.07 HOURS. CYCLES, 7,044. (X)SDR MWEA97652Skin · crackedDURING TRANS CHK, FOUND CRACK RT WING NR 4 SLAT LWR SKIN. MAINT REPAIRED IAW SRM 57-01 FIG 3 SHT 2.SDR CA970610003Lock Nut · cracked(CAN) THE NUT WHICH HOLDS THE LOWER WING STRUT TO THE WING STRUT FITTING WAS FOUND TO BE CRACKED. NUT REPLACEDSDR 97ZZZX837Bolt · corrodedAIRCRAFT INSPECTION FOUND 1 WING BOLT CORRODED AND OTHERS WITH SOME PITTING. ACFT HAD NEVER HAD BOLTS INSPECTED. BEECH MM GIVES BOLTS AND HARDWARE REPLACEMENT AT 15 YRS AND ANTI-CORROSION TREATMENT. MM ALSO STATES BOLTS TO BE MAGNAFLUXED AND CORROSION TREATSDR 97ZZZX385Fitting · rustedWHEN PERFORMING AN ANNUAL INSP, IT WAS NOTED THAT ALL THE WING TO CENTER SECTION FITTINGS WERE SEVERELY RUSTED, NO PITTING HAS YET OCCURRED ON ANY OF THESE FITTINGS, BUT SOME POWDERY DEPOSITS CAN BE SEEN BETWEEN THE LOWER CAP FITTINGS AND THE SPAR WEB ON THE RSDR 9627796608Bulkhead Fitting · corrodedDURING PERIODIC CHECK, FOUND CORROSION ON LEFT WING LANDING GEAR WHEEL WELL BULKHEAD FITTING. REPAIRED PER EA 66-120423.SDR CA961216001Bolt · corroded(CAN) AFTER REMOVAL OF THE LEFT AND RIGHT WINGS FOR A DETAILED INSPECTION, PITTING CORROSION WAS FOUND IN BOTH LEFT AND RIGHT FORE AND AFT SPAR WING ATTACH BOLTS. CORROSION WAS ALSO EVIDENT IN THE REAR SPAR ECCENTRIC BUSHINGS P/N 0512123 OF THE INTERNAL BORES.SDR CA961018009Support Bracket · cracked(CAN) LEFT AND RIGHT AILERON BELLCRANK SUPPORT BRACKETS FOUND CRACKED AT FORWARD ATTACHMENT BOLT HOLES. RIGHT SIDE P/N 62102-01.SDR CA961007001Bolt · loose(CAN) DURING 100 HOUR INSPECTION WING SHAKEN TO CHECK UPPER STRUT FITTING BOLT. MOVEMENT NOTICED IN THE RIVETS HOLDING STRUT UPPER FITTING. THIS MOVEMENT FOUND IN BOTH STRUT UPPER FITTINGS. RH STRUT P/N C2W115-2.SDR CA960924029Fittings · chafed(CAN) DURING REMOVAL OF CENTRE SECONDARY FLAP DRIVE FLEX SHAFT, FOUND CHAFING DAMAGE TO THE TOP EXTERNAL SURFACE OF BOTH AFT STRINGER #3 BATHTUB FITTINGS (WING TO FUSELAGE), AFT OF REAR SPAR. THE DAMAGE WAS BLENDED OUT AS PER TEMPORARY REPAIR RD.SDR AALA960940Fitting · crackedFOUND 12 INCH FITTING ON UPPER FORWARD LEFT SIDE OF WING SPAR IS CRACK VERT AT RADIUS. E58 1780872 REPLACED FITTING AND SHIM TO FIT USING GENERAL PROCEDURES SRM 51-10. (M)SDR 96ZZZX2975Fitting · damagedWHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE NOT INSTALLED. INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED. WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOTH LOWER AFT OUTBOARDSDR 96ZZZX2974Fitting · damagedWHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE NOT INSTALLED. INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED. WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOTH LOWER AFT OUTBOARDSDR CA960320001Bolt · corroded(CAN)DURING SPAR REPLACEMENT ON THE WING, ALL BOLTS WERE FOUND TO BE CORRODING WHERE THEY CONTACT THE WOOD. THE HEAD AND THREAD OF THE BOLTS WAS FOUND TO BE CLEAN AND BRIGHT BUT THE SHANK OF THE BOLT IN TH E WOOD SHOWS SERIOUS CORROSION.SDR 96ZZZX797Fitting · corrodedAT ANNUAL INSPECTION, CORROSION WAS FOUND ON THE BOTTOM RIGHT REAR WING SPAR ATTACH FITTING. THE FITTING WAS REPLACED.SDR 96ZZZX461Fitting · corrodedDURING ANNUAL INSPECTION, FOUND LEFT REAR WING ATTACH FITTING CORRODED AND WATER STANDING IN FUSELAGE. REMOVED FITTING AND CLEANED CORROSION. LOWER .5 INCH WAS CORRODED APPROXIMATELY 20 PERCENT OF THICKNESS OF PART. REPLACED WITH NEW FITTING IAW PIPER SB 97SDR CA951218017Wing Strut · loose rivet(CAN)DURING INSPECTION UPWARD PRESSURE WAS APPLIED TO THE WING AND A LOUD CRACKING NOISE WAS HEARD. THE SOURCE WAS TRACED TO THE UPPER WING STRUT ATTACH RIVETS WHICH HAD BECOME LOOSE. SUBMITTER REBUCKED TH E RIVETS AND RETURNED THE AIRCRAFT TO SERVICE.SDR 95ZZZX6839Bolts · lost torqueDURING 1,200-HOUR INSPECTION, NOTED TORQUE PUTTY BROKEN ON WING ATTACHMENT BOLTS. CHECKED AND NOTED ALL 8 ATTACHMENT NUTS HAD LOW TORQUE. RE-TORQUED TO MFG SPECS.SDR 95ZZZX6738Attach Fitting · corrodedCHECKED SB 977 (PIPER DATED 12-12-94). REAR STEEL WING ATTACH FITTING CORROSION INSPECTION, FOUND ON THIS ACFT THERE WAS SEVERE CORROSION. REQUIRED THE REPLACEMENT OF THE STEEL ATTACHING PARTS.SDR 95FDEA01327Bonding Jumper · corrodedCORROSION (75C002-00), NR 3 K-FLAP TO BULLNOSE I/B BONDING JUMPER LOWER ATTACH POINT. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REPAIRED NR 3 K-FLAP IAW EA 7-5710-25636 SR 27-57-010.SDR 95ZZZX5027Fitting · corrodedTHE AFT WING SPAR ATTACHMENT FITTINGS WERE INSPECTED FOR CORROSION IAW SB NR 977. NO CORROSION WAS FOUND PER SB, HOWEVER, DURING THE REMOVAL OF CORROSION FROM THE INBOARD END OF THE RIGHT FLAP, THE SEALANT BETWEEN FUSELAGE AND THE FITTING WAS KNOCKED OFF REVESDR MALA954501Attach Fittings · wornDURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE FOUND THE LEFT WING EXTENSION BOLT HOLES WORN. REPAIRS WERE COMPLETED BY REPLACING THE WING EXTENSION ATTACH FITTINGS AND HARDWARE IAW THE SRM 51-90-40. REFERENCE 95ZZZM213.SDR 95ZZZM213Attach Fittings · wornDURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE FOUND THE LEFT WING EXTENSION BOLT HOLES WORN. REPAIRS WERE COMPLETED BY REPLACING THE WING EXTENSION ATTACH FITTINGS AND HARDWARE IAW THE SRM 51-90-40. REFERENCE MALA954501.SDR 95ZZZX5922Bolt · brokenWHEN INVESTIGATING WING BOLTS PER AGAC SB 185, RT WING AFT SHOULDER BOLT FOUND BROKEN.SDR 95ZZZX2433Bolt · wornLEFT WING AFT ATTACH POINT BOLT FOUND LOOSE WHEN MECHANIC WAS CHECKING TORQUE. AN96051B AND 516L WASHERS WERE WORN AND LOOPED. BOLT SHOWED ROTATIONAL O-RING BOLT WOULD NOT TORQUE DUE TO BOTTOM ON THREADS. INSPECTED ATTACH HOLE, OKAY. REPLACED ALL HARDWARE SDR 95ZZZX2405Fitting · corrodedDURING MAJOR AIRFRAME REPAIR WITH WINGS OFF, INSPECTION OF THE WING ATTACH FITTINGS REVEALED BOTH LEFT AND RIGHT UPPER MAIN SPAR FITTINGS HAD INTERGRANULAR CORROSION AT THE POINT WHERE THE FITTINGS CAME OUT OF THE FUSELAGE SPAR ASSEMBLY. THERE WAS NO APPARENTSDR 9505916631Rib · damagedDURING PERIODIC CHECK, THE RIGHT WING LEADING EDGE RIB WAS DAMAGED WHILE INSTALLING THE NR 3 ENGINE STRUT. THE LOWER 'TEE' CHORD WAS BENT. CHORD MATERIAL 1507075-T6 EXTRUSION PER BAC 1505-10042. MADE REPAIR PER EA 66-97904.SDR 95ZZZX2047Fitting · rustedIN COMPLYING WITH PIPER SB 97, AFT WING ATTACH FITTINGS FOUND RUSTED, AND REQUIRED REMOVAL AND REPLACEMENT. SUBMITTER SUGGESTS THIS SB SHOULD BE EXTENDED TO COVER ALL STEEL FITTINGS. ALSO, REMOVAL OF FIBERGLASS INSULATION AND INSTALLATION OF FOAM TYPE WOULD
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