Gulfstream Aerospace 695A
Service difficulty reports · 37
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 = '695A' 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 = '695A' 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 CA110430001Isolator · corroded(CAN) DURING SCHEDULED 3600 HOUR REPLACEMENT OF ENGINE ISOLATORS, ISOLATOR WAS FOUND CORRODED ONCE REMOVED FROM THE AIRCRAFT. THE MOUNTING DESIGN OF THE ISOLATOR DOES NOT ALLOW A VISUAL INSPECTION OF THIS AREA OF THE ISOLATOR. IT COULD ONLY BE OBSERVED ONCE RESDR CA090922004Line · obstructed(CAN) THE TUBE THAT SUPPLIES PRESSURIZED AIR FROM AIRFRAME SYSTEMS TO INFLATE THE ENTRANCE DOOR SEAL BECOMES KINKED. (SEE ATTACHMENT)THE TUBE COMES FROM UNDER THE CABIN FLOOR, UP THE FUSELAGE CABIN WALL BEHIND THE PILOT SEAT AND HAS A LOOP TO ALLOW MOVEMENT OFSDR CA071022005Bolt · cracked(CAN) DURING DISASSEMBLY OF NOSE LANDING GEAR FOR ITS 5 YEAR INSPECTION/OVERHAUL, BOLT P/N 750076-1 OF THE NOSE LANDING GEAR DRAG BRACE-NOSE LANDING GEAR STRUT WAS FOUND BENT WITH VISIBLE CRACK. CRACK WAS CONFIRMED BY NDT(LPI AND MPI). THIS WAS THE AIRCRAFT’S SDR CA070918007Bulkhead · cracked(CAN) DURING WINTER MAINTENANCE, REAR NACELLE BULKHEAD FOUND CRACKED IN THE RADIUS. BULKHEAD TO BE REPLACED. (TC NR 20070918007)SDR 2006FA0000572Bolt · shearedDURING LANDING GEAR EXTENSION ON APPROACH, (GEAR IN TRANSIT) LIGHT REMAINED ON, NLG DID NOT INDICATE DOWN AND LOCKED. INITIAL FLY BYS INDICATED NLG TO BE ONLY PARTIALLY EXTENDED. AFTER RECYCLING GEAR SEVERAL TIMES, CLUNK WAS HEARD, NLG EXTENDED. INSP REVEALSDR 2006FA0000069Angle · mislocatedJOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)SDR 2006FA0000068Angle · mislocatedJOGGLE IN PRAT NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)SDR 2006FA0000067Angle · mislocatedJOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)SDR 2006FA0000066Angle · mislocatedJOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)SDR 2004FA0000551Stator · damagedDURING ENGINE START THE OPERATOR OBSERVED SMOKE EXITING THE ENGINE EXHAUST DUCT. THE OPERATOR SHUT THE ENGINE DOWN. VISUAL INSPECTION REVEALED OIL AND IMPACT DAMAGE IN THE EXHAUST PATH. THIRD STAGE TURBINE WHEEL BLADES WERE FRACTURED. FRAGMENTS FROM THE FRSDR FTU2003F00011Collar · looseDURING A NORMAL PERIODIC INSPECTION, BOTH LEFT AND RIGHT ELEVATORS WERE FOUND LOOSE. CLOSER INSPECTION REVEALED WORKING RIVETS WHICH HOLD COLLARS (PN 440000-246) TO THE ELEVATOR TORQUE TUBES (PN 440000-96). HOLES WERE DAMAGED BEYOND ALLOWABLE LIMITS AND BOTHSDR FTU2003F00010Arm · crackedDURING A NORMAL PERIODIC INSPECTION, WHILE INSPECTING UNDER THE BAGGAGE COMPARTMENT FLOOR, THE ELEVATOR BOB WEIGHTS ARE BOLTED TO CRACKS WERE FOUND AROUND THE BOLT HOLES. ITS OUR OPINION THAT THE AREA WHERE THE WEIGHTS ARE BOLTED TO SHOULD BE A THICKER MATERISDR FTU2003F00009Pin · scoredDURING A NORMAL PERIODIC INSPECTION IT WAS DISCOVERED THAT THE TAPERED PINS WHICH RETAIN THE MLG HOUSING SUPPORT PINS HAD INCORRECT HARDWARE (PLAIN WASHERS UNDER THE NUT, INSTEAD OF SPECIAL AN975-5 WASHERS) SECURING THE TAPERED PINS IN PLACE. FURTHER INVESTIGSDR FTU2003F00003Regulator · failedHYDRAULIC REGULATOR WAS INSTALLED IN THIS AIRCRAFT AS A OVERHAULED, EXCHANGED. THIS UNIT FAILED DURING TAKEOFF, WHICH PREVENTED HYDRAULIC PRESSURE TO BUILD UP TO SYSTEM PRESSURE. UNIT WAS REMOVED AND REPLACED BY THE OWNERS ORIGINAL REGULATOR AFTER IT WAS OVESDR MV5R055MServo · seizedAILERON PRIMARY AUTO PILOT SERVO SEIZED. FLIGHT CREW APPLIED SUFFICIENT FORCE IN AN ATTEMPT TO FREE AILERON MOVEMENT. CAUSING AILERON CONTROL CABLE TO BECOME DISLODGED FROM FORWARD AILERON CONTROL DRUM. INVESTIGATION OF THE SERVO REVEALED A BEARING FAILURE SDR MV52002F00006Mount · crackedOIL JET UTILIZED TO LUBRICATE THE BULL GEAR LOCATED WITHIN THE GEARBOX WAS CRACKED AT THE MOUNTING BASE. THIS CONDITION COULD CAUSE A REDUCED AMOUNT OF OIL FOR LUBRICATION TO THE BULL GEAR.SDR MV52002F00004Rib · crackedRIGHT HORIZONTAL STABILIZER RIB CRACKED RIB LOCATED AT LEADING EDGE.SDR MV52002F00002Rib · crackedRIGHT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE.SDR MB5R055NAngle · crackedRIGHT MAIN LANDING GEAR OUTBOARD GEAR MOUNT SIDE BRACE TO WING ATTACHMENT ANGLE CRACKED. CRACK LOCATED AT THE AFT PORTION OF THE ANGLE EXTENDING ONE INCH FORWARD.SDR MV5R055N1Block · separatedNOSE GEAR SEARING ATTACHMENT BLOCK PIN HAD SEPERATED FROM THE BLOCK. THE ROLL PIN THAT SECURES THE PIN TO THE BLOCK HAD SHEARED, INSPECTION OF THE ROLL PIN INDICATED THAT THE SHEAR WAS IN A DOWNWARD DIRECTION.SDR CA000830044Accumulator · failed(CAN) 1.A/C JUST COMPLETED ROUTINE 100 HR PERIODIC INSP. 2. HYDRAULIC ACCUMULATOR REGULATOR ASSY REPL, DUE TO LEAKING ACCUMULATOR (INTERNAL). IT WOULD NOT STORE FLUID PRESSURE: O HR T.S.O. PART INST FUNCTION TESTS & P OST INSP CHECK FLT CARRIED OUT NO FAULT FOSDR 20000609SH017Bearing Support · lack of lubeRUDDER PEDAL BEARINGS FAILED DUE TO LACK OF LUBRICATION. NO WAY TO LUBE WITHOUT COMPLETE DISASSEMBLY. BEARINGS CUT HALF WAY THROUGH RUDDER PEDAL TUBES, TUBES ARE ONLY .0625 INCH THICK. FOUND DURING GRAND RENAISSANCE PROGRAM. SUBMITTER STATED NEED WAY TO LUSDR 99ZZZX1571Control Cable · frayedDURING INSPECTION, FOUND RIGHT RUDDER BALANCE CABLE FRAYED AT LOWER PULLEY. TT: APPROX 1,900 HOURS. INSTALLED NEW CABLE ASSY, RIGHT.SDR 98ZZZX4215Windshield · shatteredLEFT WINDSHIELD OUTER LAYER SHATTERED AT ALTITUDE. WINDSHIELD HEAT OPERATED NORMALLY PRIOR TO INCIDENT. 500 HOURS ON WINDSHIELD.SDR 97ZZZX4010Control Cable · frayedWHILE PERFORMING SB 226, THE LEFT AILERON CABLE WAS FOUND SEVERELY FRAYED AT WS 142.0. THE CABLE WAS PROPERLY ROUTED AND RUBBING ON THE FAIRLEAD AS IT WAS INTENDED TO DO. SUBMITTER SUGGESTS INSPECTING ALL OF AILERON CABLES BEHIND WING TO FLAP FAIRINGS WHILE SDR CA971010012Control Cable · broken(CAN) 75 PERCENT OF RT INBOARD FLAP CABLE STRANDS BROKEN. REPLACED.SDR 97ZZZX3339Skin · corrodedACFT RETURNED FOR FUSELAGE INSP AND FINAL REPAIRS OF THE RT WING. DURING INSP, CORROSION FND IN THE LT WING IN SAME AREA, WS 39, BOTTOM SIDE, FWD OF THE MAIN SPAR. EFFECTED PARTS, THE L/E SKIN, STR NR 6 INBD, AND 2 ANGLES FWD. EXTENT OF CORROSION REQUIRED TSDR 97ZZZX3338Skin · corrodedACFT RETURNED FOR FUSELAGE INSP AND FINAL REPAIRS OF THE RT WING. DURING INSP, CORROSION FND IN THE LT WING IN SAME AREA, WS 39, BOTTOM SIDE, FWD OF THE MAIN SPAR. EFFECTED PARTS, THE L/E SKIN, STR NR 6 INBD, AND 2 ANGLES FWD. EXTENT OF CORROSION REQUIRED TSDR 97ZZZX2087Control Cable · frayedDURING A 100-HOUR INSPECTION, RUST WAS FOUND ON RIGHT HAND AILERON CABLE AS IT PASSED THROUGH A PULLEY AT FS 217. AFTER CLEANING RUST OFF, NOTED CABLE WAS BROKEN THROUGH HALF OF ITS STRANDS. INVESTIGATION REVEALED THE RELIEF TUBE SIX INCHES AWAY HAD A CUT ISDR 97ZZZX1483Flap · misinstalledWHILE AIRCRAFT WAS UNDERGOING MAINTENANCE, THE INBOARD LEFT FLAP WAS REMOVED. UPON INSTALLATION OF THE FLAP THE ATTACH BOLT MISSED THE ROD END THAT WAS COMING FROM THE PULLEY; THUS, WEDGING THE ROD END BETWEEN BOLT AND THE FLAP SKIN. THIS GAVE THE FALSE APPESDR 96ZZZX4831Starter · wrong partDURING INSPECTION, NOTED ONE OF THE STARTER/GENERATORS HAD A DATA TAG ISSUED BY AIRCRAFT PARTS CORPORATION AND IDENTIFIED WITH P/N 300.S.G.119Q, NOT THE LEAR SIEGLER (LUCAS) P/N 23079-000-1 REQUIRED BY THE IPC. APC CONTACTED TO INQUIRE IF EVER AN STC OR A PAHSDR 96ZZZX4129Arm Assy · crackedFOUND NLG ARM ASSY CRACKED FROM BOTH BOLT HOLES AND ALONG TUBE PORTION. TWO CRACKS FROM BOLT HOLES OUTBOARD AND ONE CRACK FROM OUTER EDGE .75 INCH INBOARD ON PART. BOLT HOLE CRACKS FROM THESE BOLTS DO NOT APPEAR TO BE DEBURRS FROM INSTALLATION. FOUND ON 100SDR 96ZZZX2236Angle · crackedDURING A 100-HOUR INSPECTION, THE RT MLG INBOARD TRUSS ATTACH ANGLE WAS FOUND TO HAVE A 0.9 INCH RADIUS CRACK 1.0 INCH FROM AFT END. THIS CRACK WAS STOP DRILLED AND A DOUBLER AND RADIUS BLOCK WAS INSTALLED PER DER'S REPAIR SCHEME. CRACKS APPEAR TO BE ASSOCIASDR 96ZZZX2235Firewall · crackedTHE LT AND RT ENGINE FIREWALLS FOUND TO HAVE CRACKS IN THE ALUMINUM PORTION OF FIREWALL AT THE AFT ENGINE MOUNT UPPER ATTACH FASTENERS DURING OTHER MAINTENANCE REQUIRING THE LOWER AFT NACELLES TO BE REMOVED. WITH THE NACELLES REMOVED, THE CRACKS ARE VISIBLE. SDR 96ZZZX2229Truss Support · damagedAFTER RIGHT AFT LOWER NACELLE REMOVED TO FACILITATE MAINTENANCE, DISCOVERED THAT DURING A PREVIOUS LANDING GEAR REMOVAL, THE LEFT AND RIGHT OUTBOARD MLG TRUSS SUPPORTS WERE ACCIDENTLY DRILLED WHEN THE OUTBOARD TRUNNION PIN COVER WAS DRILLED OFF. THE LEFT TRUSSDR CA960502057Windshield · cracked(CAN) LEFT HAND WINDSHIELD FOUND CRACKED.SDR 96ZZZX25Regulator · diaphragm blownDURING THE COURSE OF A 100-HOUR INSPECTION, FOUND THE BLEED AIR REGULATOR TO HAVE A BLOWN DIAPHRAGM. THIS IS THE REGULATOR LOCATED IN AFT BAGGAGE AREA THAT REDUCES THE BLEED AIR FROM THE ENGINE DOWN TO 18 PSI TO INFLATE THE DOOR SEAL AND DEICE BOOTS. HAVE FO
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