Allison AE-3007C
Service difficulty reports · 793
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 engine_model_key = 'AE3007C' 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 engine_model_key = 'AE3007C' 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 SIMA200228205Sill · corrodedRIGHT HAND SILL IS CORRODED BETWEEN FRAME 29 AND 35. PERFORMED NDT INSPECTION WITH NO DEFECTS NOTED. REPAIRED RIGHT HAND SILL BETWEEN FR 29-35 IAW GST.SDR SIMA200228Frame · corrodedSTRINGER 19L HAS CORROSION BETWEEN FRAMES 23 AND 24 UNDER FLOOR. PERFORMED EDDY CURRENT AND THICKNESS, NO DEFECTS. REPAIR DONE IAW GST.SDR SIMA200228225Sill · corrodedRIGHT SILL CORRODED BETWEEN FRAME 24 AND 29. PERFORMED EDDY CURRENT AND THICKNESS INSPECTION WITH NO DEFECTS FOUND. REPLACED SILL IAW GST.SDR SIMA200227921Sill · corrodedDURING AN IMBV INSPECTION, CARGO DOOR LOWER SILL WAS FOUND CORRODED BELOW SRM LIMITS. REMOVED EXISTING CARGO DOOR LOWER SILL. INSTALLED SERVICEABLE SILL IAW MFG SRM.SDR SIMA200228206Floorbeam · corrodedLEFT HAND FLOOR BEAM GUSSET IS CORRODED BETWEEN FRAME 65-68. INSTALLED SERVICEABLE GUSSET IAW SRM.SDR SIMA200228214Sill · corrodedCARGO DOOR SILL IS CORRODED. REMOVED AND INSTALLED NEW CARGO DOOR SILL IAW CPM.SDR SIMA200228209Floor Support · corrodedPASSENGER DOOR FLOOR SUPPORT CORRODED. REMOVED AND INSTALLED SERVICEABLE SUPPORT IAW SRM.SDR SIMA200228210Crossbeam · corrodedCROSSMEMBER AT FRAME 23 IS CORRODED. REMOVED CROSSMEMBER AND REPAIRED IAW SRM.SDR SIMA200228211Seat Track · corrodedSEAT TRACK CORRODED BETWEEN FRAMES 18 AND 23 ON LEFT FLOORBEAM. REMOVED AND REPLACED SEAT TRACK IAW AMM.SDR SIMA200228212Angle · corrodedPROFILE AT FRAME 23 IS CORRODED. REMOVED AND REPAIRED PROFILE AND DOUBLER. REPAIR DONE IAW SRM.SDR SIMA200228213Floorbeam · corrodedRIGHT FLOORBEAM CORRODED AT FRAME 23. REPAIRED IAW SRM.SDR SIMA200228215Floorbeam · corrodedPREVIOUS REPAIR AT FRAME 20 ON LEFT FLOORBEAM IS CORRODED. REPAIRED IAW SRM.SDR SIMA200228221Floor Support · corrodedCENTER BEAM RAMP IS CORRODED. REMOVED AND INSTALLED NEW CENTER BEAM GUSSET IAW SRM.SDR SIMA200227920Stringer · chafedDURING AN IMBV INSPECTION, STRINGER 19R WAS FOUND TO BE CHAFED. BLENDED CHAFED AREA. PERFORMED AN NON DESTRUCTIVE TESTING INSPECTION WITH NO DEFECTS NOTED. FABRICATED A DOUBLER ANGLE AND TWO SHIMS. REPAIR DONE IAW MFG SRM AND STANDARD SRM PRACTICES.SDR SIMA200227918Frame · corrodedDURING AN MFG INSPECTION, MAINTENANCE FOUND CORROSION ON LEFT OMEGA BEAM (PREVIOUS REPAIR) AT FRAME 20. REMOVED PREVIOUS REPAIR (CORROSION LIMITED TO PREVIOUS REPAIR ONLY). FABRICATED A DOUBLER ANGLE, FILLER, PLATE, AND TWO SHIMS. REPAIR DONE IAW MFG SRM ANSDR CWQ2002F00003Bushing · frozenELEVATOR FEELS ABNORMALLY STIFF. AILERON CONTROL FEELS NORMAL. CONTROL CHECKS NORMAL. ELEVATOR FEELS SIMILAR TO MANUAL REVISION MADE IN SIMULATOR. TROUBLESHOOT ELEVATOR SYSTEM. FOUND COPILOT PUSH/PULL TUBE AFT/BELOW COCKPIT PEDESTAL, BUSHINGS FROZE, REPLASDR SIMA200222105Skin · damagedDURING INSPECTION FOUND DAMAGE ON THE LOWER LT ELEVATOR SKIN. PERFORMED TWO CUSTS TO REMOVE DAMAGE. FABRICATED A REPAIR DOUBLER. REPAIR DONE IAW STATEMENT AND SRM PRACTICES.SDR SIMA200216310Stringer · chafedDURING AN IMBV INSPECTION FOUND STRINGER 19R CHAFED BETWEEN FRAMES 52 AND 53. BLENDED AREA, PERFORMED NDT INSPECTION NO DEFECTS. FABRICATED A DOUBLER ANGLE, AND TWO SHIMS. REPAIR DONE IAW STANDARD SRM PRACTICES.SDR SIMA200216311Stringer · chafedDURING AN IMBV INSPECTION FOUND STRINGER 19L CHAFED BETWEEN FRAMES 52 AND 53. BLENDED CHAFE. PERFORMED NDT INSPECTION NO DEFECTS. FABRICATED A DOUBLER ANGLER, AND TWO SHIMS. REPAIR DONE IAW STANDARD SRM PRACTICES.SDR SIMA200216201Beam · elongatedDURING AN IMBV INSPECTION FOUND CENTER BEAM UPRIGHT AT FRAME 20 HAD AN ELONGATGED HOLE. REMOVED DAMAGED UPRIGHT. FRABRICATED A SERVICEABLE UPRIGHT IAW STANDARD SRM PRACTICES.SDR CNQ2002F00001Tube · corrodedWHEN THE AUXILIARY POWER UNIT FIRE EXTINGUISHER DEPLOYMENT TUBE WAS REMOVED FOR MAINTENANCE, TECHNICIANS FOUND APPROXIMATELY THREE INCHES OF WATER IN THE VERTICALLY MOUNTED TUBE. MINOR CORROSION WAS REMOVED BEFORE REINSTALLING THE TUBE.SDR SIMA200216305Crossbeam · corrodedTHIS IS A LEVEL 2 FINDING ON CRIC NR 36200. GALLEY CROSSBEAM AND PROFILE HAS CORROSION AT FRAME 23. C/A- INSTALLED NEW CROSSBEAM AND PROFILE IAW SRM.SDR SIMA200216307Floor Support · corrodedTHIS IS A LEVEL 2 FINDING ON CRIC NR 36201. GALLEY FORWARD DIAMOND GUSSET HAS CORROSION INSTALLED SERVICEABLE DIAMOND GUSSET IAW SRM.SDR SIMA200216306Floor Support · corrodedTHIS IS A LEVEL 2 FINDING, GALLEY CENTER BEAM GUSSET HAS CORROSION. C/A-REMOVED AND REPLACED GUSSET IAW SRM.SDR 2002FA0000662Magnetic Seal · wornCREW RECEIVED ENGINE CHIP-L CAS MESSAGE. AIRCRAFT LANDED AT DESTINATION. MAGNETIC INDICATOR PLUG INSPECTED AND SINGLE SLIVER FOUND. 3RD INCIDENT OF THIS NATURE ON THIS ENGINE. ANALYSIS BY ROLL-ROYCE ON 2ND INCIDENT SLIVER SHOWED STAINLESS 410 ALLOY. FOUND WAVESDR UG82002F00002Engine · out of toleranceRIGHT ENGINE OIL PRESSURE OUT OF LIMITS, HI/RED 106 PSI AT 80-90 KTS. ENGINE INTERNAL BEARING SEAL AIR LEAKAGE WHICH MAY OCCUR AS ENGINE APPROACHES ITS MIDLIFE INSPECTION. VISUALLY INSPECTED ENGINE OIL FILTER BYPASS BUTTON. PERFORMED TAKEOFF POWER RUN UP. SDR CA020429001Bracket · cracked(CAN) COMPLIED WITH CESSNA CUSTOMER LETTER NO 0423 DATED APRIL 23, 02. (INSPECTION OF LT AND RT ELEVATOR INBD HINGE BRACKETS) ONE BRACKET HAS TWO SURFACES: INBD AND OUTB.FOUND LEFT ELEVATOR INBD HINGE BRACKET CRACKED. INBD CRACK DIMENSION :. 062 INCH OUTB CRASDR CA020422002Shaft · damaged(CAN) DURING INSPECTION OF THE LPT ASSEMBLY IT WAS DISCOVERED THAT THE LPT SHAFT HAD A SEVERE RUB AND HEAT DISCOLORATION ON THE OUTSIDE DIAMETER, LOCATED IN THE AREA OF THE HPT SLEEVE ALSO RUBBED AT FOUR LOCATION. THE SLEEVE IS ASSEMBLED INSIDE THE HPT SHAFTSDR CA020607001Hinge Bracket · cracked(CAN) A CRACK OF 0.30 INCHES WAS FOUND IN THE INBOARD SIDE OF THE HINGE BRACKET LOCATED IN THE FORWARD FROM THE TRAILING EDGE UNDER STIFFENER.SDR DXT2002F00002Generator · inoperativeDC GENERATOR BEARING MESSAGE ILLUMINATED. COUNTERSUNK SCREW HOLES ENLONGATED ON MOUNTING SIDE FLANGE CAUSING WEAR ON GENERATOR AND QD PAD.SDR DXT2002F00001Pin · loosePIN THAT SECURES PILOTS INBOARD BRAKE PEDAL INBOARD PIN TO BRAKE ACTUATING ROD CLEVIS IS WORKING LOOSE. THE PIN WAS FOUND PROTRUDING FROM CLEVIS. PIN LOOSE ENOUGH TO BE REMOVED BY HAND. RECOMMEND REPLACE PIN WITH LOCKING DEVICE. IE: A BOLT WITH CASTLE NUT SDR CWQ2002F00000Transorb · burnedDISPLAY UNITS 4 AND 5, FMS 2 SCREEN AND RADIO CONTROL UNIT SCREEN BLANK. AVIONICS FAN INSPECTION AND CAS MESSAGES DISPLAYED. CAUSE OF DISCREPENCY APPEARS TO BE TRANSORB (PN S3106-5) WIRED INTO QUICK DISCONNECT FITTING CONNECTED TO THE RIGHT SIDE AVIONICS RELSDR CNQ2001F00000Sensor · intermittentTHE LEFT ENGINE OIL PRESSURE DROPPED IN FLIGHT. TROUBLESHOT TO AN INTERMITTENT OIL PRESSURE SENSOR. REMOVED AND REPLACED THE SENSOR.SDR UG82001F00009Power Unit · failedVIBRATION FELT ON CABIN FLOOR AS WELL AS HUM. LT HYD (A) SYSTEM FLUCTUATED BETWEEN 2400-3300 PSI. WHEN GEAR WAS SELECTED DOWN LT HYD PRES WAS 2100 AND RT HAD AN OT (AMBER) LIGHT. UPON LANDING THEY GOT A (B) SYSTEM FAIL MESSAGE, BOTH SYSTEM PRESSURES WERE 180SDR E4G2001F00001Bushing · out of positionBUSHINGS ARE MIGRATING CAUSING EXCESSIVE WEAR TO ELEVATOR CONTROL QUADRANT SUPPORT FITTINGS.SDR UG82001F00008Hydraulic System · malfunctionedVIBRATION FELT ON CABIN FLOOR AS WELL AS HUM. LEFT HYDRAULIC (A) SYSTEM FLUCTUATED BETWEEN 2400-3300 PSI. WHEN GEAR WAS SELECTED DOWN LEFT HYDRAULIC PRESSURE WAS 2100 AND RIGHT HAD AN OT(AMBER) LIGHT. UPON LANDING THEY GOT A (B) SYSTEM FALL MESSAGE, BOTH SYSSDR M01097Fabric · inoperativeDURING A PREFLIGHT INSPECTION, THE CREW FOUND THE RIGHT AFT FUSELAGE EXTERNAL EMERGENCY FLOOD LIGHT INOPERATIVE. THIS ITEM WAS DEFERRED PER MEL. LATER MAINTENANCE REMOVED AND REPLACED THE EMERGENCY FLOOD LIGHT.SDR 2001FA0000342Acm · seizedFORWARD AIR CYCLE MACHINE SEIZED DURING ROUTINE USAGE. PROBABLE CAUSE IS BEARING FAILURE. UNIT WAS OPERATED NORMALLY, AND WAS SERVICED AS SCHEDULED.SDR 20010509CW003Pump · failedAC ON DECENT WHEN AMBER EICAS INDICATION OF HYD VOLUME LOW(A) ILLUMINATED. FLIGHT CREW CONFIRMED THE EICAS INDICATION WAS AN ACTUAL PROBLEM BY VIEWING EICAS WHICH SHOWED, HYD LEVEL AT 16 PERCENT AND DECREASING. PRESSURE DROPING AND FLUID TEMP INCREASING. FLIGHSDR C2XA00TY016Engine · malfunctionedCLE - FLT 3896 - CREW REPORTED THAT AFTER TAKEOFF AND DURING CLIMB-OUT, THE LEFT ENGINE OIL PRESSURE STAYED IN THE AMBER RANGE, WHEN N1 WAS REDUCED 2 PERCENT THE PRESSURE LOWERED INTO THE GREEN RANGE. THE ENGINE PARAMETERS REMAINED NORMAL FOR THE DURATION OF SDR RAIA0009006Valve · failed7607-CHS- RIGHT ENGINE WILL NOT START. MAINTENANCE INSPECTED AND REPLACED UPPER AND LOWER BLEED VALVES.SDR 20000802SH019Tube · brokenSHORTLY AFTER TAKEOFF, THE FLIGHT CREW NOTICED A SUDDEN INCREASE IN THE RIGHT ENGINE ITT (50-60 DEGREES) AND IT BECAME TEMPERATURE LIMITED. ALL OTHER ENGINE PARAMETERS APPEARED NORMAL SELECTING THE OTHER FADEC IN CONTROL HAD NO EFFECT. THE START BLEED CONTRSDR 20000512SH007Retainer · worn**TONY, ENG IN SYS****THE LEFT ENGINE ALTERNATOR CARBON SEAL WAS REPLACED. A SATISFACTORY LEAK CHECK WAS PERFORMED DURING THE GROUND ENGINE RUN CHECKS. THE ENGINE DEVELOPED A LARGE OIL LEAK DURING A TEST FLIGHT AND IT WAS LATER DISCOVERED THE CARBON SEAL RET
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