Beech A24R

Service difficulty reports · 16

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 = 'A24R'
  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.

SDR 2006FA0000423Drag Brace · brokenTHE AIRCRAFT TOUCHED DOWN UNEVENTFUL. DURING ROLLOUT, THE NOSE GEAR COLLAPSED ABOUT 1500 FT AFTER TOUCHDOWN. THE DRAG BRACE FAILED AT THE YOKE WHERE IT ATTACHES TO THE NOSE GEAR. (K)Apr 19, 2006 · N8015R · Beech A24R · Landing Gear Retraction/Extension SystemSDR CA020723005Bearing · corroded(CAN) WHEN INSPECTING CONTROL SURFACES, IT WAS NOTICED THAT THE HORIZONTAL STABILATOR HAD AN ABNORMAL FORE / AFT MOVEMENT. UPON DISINSTALLATION, THE HORIZONTAL STAB BUSHINGS AND BEARINGS WERE FOUND TO BE WORN AND THE BOLTS WERE FOUND TO BE CORRODED.Jun 26, 2002 · Beech A24R · Horizontal Stabilizer Miscellaneous StructureSDR CA020723003Handle · cracked(CAN) FLAP HANDLE PEDESTAL IS CRACKED AT BEND ON LOWER RT FORWARD CORNER.Jun 26, 2002 · Beech A24R · Trailing Edge Flap Control SystemSDR CA020723002Arm · worn(CAN) FLAPS WERE FOUND TO BE LOOSE. AFTER INVESTIGATION IT WAS FOUND THAT THE FLAP ARMS THAT JOIN THE FLAP CONTROL TUBE TO THE FLAP RODS HAD ELONGATED BOLT HOLES DUE TO WEAR. THE ELONGATED HOLES ARE THE ONES WHERE THE CLEVIS BOLTS ATTACH THE ARMS TO THE FLAP CJun 26, 2002 · Beech A24R · Trailing Edge Flap Control SystemSDR CA020723001Bracket · corroded(CAN) UPON VISUAL INSPECTION OF THE LT WHEEL WELL, THE ANGLE HOLDING THE UPLOCK HOOK BRACKET WAS IDENTIFIED AS BEING HEAVILY CORRODED, SHOWING SIGNS OF ADVANCED EXFOLIATION CORROSION. UPON DISASSEMBLY, INTERGRANULAR CORROSION WAS ALSO FOUND ON THE UPLOCK HOOK Jun 26, 2002 · Beech A24R · Main Landing Gear Attach SectionSDR CA020606005Motor · worn(CAN) NOISE IN FLAP MOTOR CAUSED FURTHER INSPECTION. UPON ACCESSING MOTOR UNDER REAR SEAT, SPARKS WERE NOTED COMING OUT OF DRIVE AND OF MOTOR DURING ACTUATION. ARMATURE MOTOR BUSHINGS WERE WORN TO THE EXTENT THAT THERE WAS CONTACT WITH THE END PLATE DURING OPEJun 5, 2002 · Beech A24R · Trailing Edge Flap ActuatorSDR 20001128SH001Hinge · corrodedTHE PAINT WAS CRACKED AROUND THE HINGE PLATE ON THE RT SIDE. A FINGERNAIL WOULD GO UNDER A COUPLE OF THE RIVETS. WHEN THE RIVETS WERE DRILLED OUT, SEVERAL SPUN AND BROKE BEFORE THE BIT WENT THROUGH. THE BACK SIDE OF THE HINGE PLATES WAS RUSTED AND BLACK GANov 2, 2000 · N8022R · Beech A24R · Horizontal Stabilizer StructureSDR CA990804034Spar · hole oversized(CAN) REQUIRED WASHERS NOT INSTALLED BETWEEN BUSHING AND FUSELAGE FITTING. THIS ALLOWED BUSHING TO MOVE FORWARD. BECAUSE THERE WAS NOT ENOUGH BEARING SURFACE, THIS ALLOWED BUSHING TO ENLARGE HOLE IN SPAR AND FILLER CAUSING CRACKS TO RADIATE FROM HOLE AND ALLJul 20, 1999 · Beech A24R · Wing, Fuselage Attach FittingsSDR CA990804033Spar · hole oversized(CAN) WASHERS ARE REQUIRED BETWEEN BUSHING AND FUSELAGE ATTACH FITTING TO HOLD BUSHING IN PLACE. THESE WASHERS WERE MISSING AND ALLOWED THE BUSHING TO MOVE FORWARD. THERE WAS NOT ENOUGH BEARING SURFACE AVAILABLE, SO THE BUSHING MOVED ENLARGING THE HOLE IN THJul 15, 1999 · Beech A24R · Wing, Fuselage Attach FittingsSDR 98ZZZX1980Side Brace · crackedDURING AN ANNUAL INSPECTION, A CRACK WAS DISCOVERED ON THE MLG UPPER SIDE BRACE WELD ASSEMBLY NEAR THE AFT ATTACH POINT.May 4, 1998 · N66TX · Beech A24R · Landing Gear Retraction/Extension SystemSDR 98ZZZX518Blade · corrodedCORROSION FOUND BELOW THE PTICH LINE IN THE THREADS CAUSING THE BLADE TO BE UNAIRWORTHY PER MCAULEY SM NR 720415. SUBMITTER STATED ADHERING TO PROPER COMPLIANCE TIMES OF AD 91-15-04 MAY HAVE PREVENTED THIS.Jan 20, 1998 · N8015R · Beech A24R · Propeller Blade SectionSDR 98ZZZX517Blade · corrodedCORROSION WAS FOUND BELOW TTE PITCH LINES OF THE BLADE THREADS CAUSING THE BLADE TO BE UNAIRWORTHY PER MCCAULEY SM NR 720415. SUBMITTER STATED ADHERING TO COMPLIANCE TIMES OF AD 91-15-04 MAY HAVE PREVENTED THIS CONDITION.Jan 20, 1998 · N8015R · Beech A24R · Propeller Blade SectionSDR 98ZZZX516Hub · crackedA CRACK WAS FOUND IN THE THREADS OF HUB RENDERING IT UNAIRWORTHY PER AD 91-15-04. THE DEFECT POSSIBLY COULD HAVE BEEN FOUND AT AN EARLIER DATE IF COMPLIANCE TIME OF THE AD HAD BEEN ADHERED TO.Jan 20, 1998 · N8015R · Beech A24R · Propeller Hub SectionSDR CA971031003Cylinder · worn(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CYLINDER FOUND WORN AND WAS REPLACED. THE PROPELLER BLADE (P/N S78FBM-1.5) WAS FOUND NICKED ON THE LEADING EDGE AND THE FACE AND WAS TRIMMED.Oct 23, 1997 · Beech A24R · Propeller Hub SectionSDR 96ZZZX1107Swivel Rod · brokenNOSE WHEEL DID NOT EXTEND NORMALLY. FOUND NOSE WHEEL SWIVEL ROD BROKEN WHICH DID NOT ALLOW WHEEL TO STRAIGHTEN OUT AS IT LEFT WHEELWELL. FOUND ONE CLEVIS, PN 169-820037-3, TIGHTENED TO THE POINT WHERE IT WOULD HARDLY MOVE WITH THE ROD HOOKED. THIS TIGHTNESSFeb 1, 1996 · N9710Q · Beech A24R · Landing Gear Retraction/Extension SystemSDR 95ZZZX2615Block · rivets shearedTHREE CR3212-5-10 CHERRY FASTENERS SHEARED AT THE ATTACHMENT POINT OF THE BLOCK AND TUBE IN THE FLAP SYSTEM. FLAPS WERE SELECTED ON LANDING WITH NO RESPONSE. THIS IS A HIGH-TIME TRAINING AIRCRAFT.Mar 5, 1995 · N101CM · Beech A24R · Trailing Edge Flap Control System
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