# Service difficulty reports: Gulfstream Aerospace 695A

A list on [Gulfstream Aerospace 695A](https://openairdocs.org/model/gulfstream-aerospace-695a.md).

Newest first. General aviation reporting is voluntary.

- [SDR CA110430001](https://openairdocs.org/sdr/CA110430001.md): Isolator · corroded · Apr 30, 2011 · Gulstm 695A · Engine Mount Section
  > (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 RE
- [SDR CA090922004](https://openairdocs.org/sdr/CA090922004.md): Line · obstructed · Sep 21, 2009 · Gulstm 695A · Passenger/Crew Doors
  > (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 OF
- [SDR CA071022005](https://openairdocs.org/sdr/CA071022005.md): Bolt · cracked · Oct 18, 2007 · Gulstm 695A · Nose/Tail Landing Gear
  > (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 CA070918007](https://openairdocs.org/sdr/CA070918007.md): Bulkhead · cracked · Sep 17, 2007 · Gulstm 695A · Nacelle/Pylon, Bulkhead/Firewall
  > (CAN) DURING WINTER MAINTENANCE, REAR NACELLE BULKHEAD FOUND CRACKED IN THE RADIUS. BULKHEAD TO BE REPLACED. (TC NR 20070918007)
- [SDR 2006FA0000572](https://openairdocs.org/sdr/2006FA0000572.md): Bolt · sheared · May 19, 2006 · N333UP · Gulstm 695A · Main Landing Gear
  > DURING 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 REVEAL
- [SDR 2006FA0000069](https://openairdocs.org/sdr/2006FA0000069.md): Angle · mislocated · Jan 11, 2006 · N7896G · Gulstm 695A · Fuselage Miscellaneous Structure
  > JOGGLE IN PART NEEDS TO BE RELOCATED.2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)
- [SDR 2006FA0000068](https://openairdocs.org/sdr/2006FA0000068.md): Angle · mislocated · Jan 11, 2006 · N7896G · Gulstm 695A · Fuselage Miscellaneous Structure
  > JOGGLE IN PRAT NEEDS TO BE RELOCATED.2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)
- [SDR 2006FA0000067](https://openairdocs.org/sdr/2006FA0000067.md): Angle · mislocated · Jan 11, 2006 · N7896G · Gulstm 695A · Fuselage Miscellaneous Structure
  > JOGGLE IN PART NEEDS TO BE RELOCATED.2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)
- [SDR 2006FA0000066](https://openairdocs.org/sdr/2006FA0000066.md): Angle · mislocated · Jan 11, 2006 · N7895G · Gulstm 695A · Fuselage Miscellaneous Structure
  > JOGGLE IN PART NEEDS TO BE RELOCATED.2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K)
- [SDR 2004FA0000551](https://openairdocs.org/sdr/2004FA0000551.md): Stator · damaged · Jun 6, 2004 · N600CM · Gulstm 695A · Turbine Section
  > DURING 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 FR
- [SDR FTU2003F00011](https://openairdocs.org/sdr/FTU2003F00011.md): Collar · loose · Apr 24, 2003 · N7812 · Gulstm 695A · Elevator Structure
  > DURING 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 BOTH
- [SDR FTU2003F00010](https://openairdocs.org/sdr/FTU2003F00010.md): Arm · cracked · Apr 24, 2003 · N7812 · Gulstm 695A · Cargo/Baggage Doors
  > DURING 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 MATERI
- [SDR FTU2003F00009](https://openairdocs.org/sdr/FTU2003F00009.md): Pin · scored · Apr 24, 2003 · N7812 · Gulstm 695A · Main Landing Gear Strut/Axle/Truck
  > DURING 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 INVESTIG
- [SDR FTU2003F00003](https://openairdocs.org/sdr/FTU2003F00003.md): Regulator · failed · Feb 14, 2003 · N79PH · Gulstm 695A · Hydraulic Pressure Regulator, Main
  > HYDRAULIC 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 OVE
- [SDR MV5R055M](https://openairdocs.org/sdr/MV5R055M.md): Servo · seized · Oct 24, 2002 · N695GG · Gulstm 695A · Autopilot System
  > AILERON 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 MV52002F00006](https://openairdocs.org/sdr/MV52002F00006.md): Mount · cracked · Sep 19, 2002 · N707TS · Gulstm 695A · Turbine Engine Reduction Gear
  > OIL 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 MV52002F00004](https://openairdocs.org/sdr/MV52002F00004.md): Rib · cracked · Apr 25, 2002 · N695AB · Gulstm 695A · Horizontal Stabilizer, Spar/Rib
  > RIGHT HORIZONTAL STABILIZER RIB CRACKED RIB LOCATED AT LEADING EDGE.
- [SDR MV52002F00002](https://openairdocs.org/sdr/MV52002F00002.md): Rib · cracked · Apr 25, 2002 · N695AB · Gulstm 695A · Horizontal Stabilizer, Spar/Rib
  > RIGHT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE.
- [SDR MB5R055N](https://openairdocs.org/sdr/MB5R055N.md): Angle · cracked · Apr 16, 2001 · N900EC · Gulstm 695A · Main Landing Gear
  > RIGHT 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 MV5R055N1](https://openairdocs.org/sdr/MV5R055N1.md): Block · separated · Apr 6, 2001 · N695GG · Gulstm 695A · Nose/Tail Landing Gear
  > NOSE 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 CA000830044](https://openairdocs.org/sdr/CA000830044.md): Accumulator · failed · Aug 8, 2000 · Gulstm 695A · Hydraulic Power Accumulator, Main
  > (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 FO
- [SDR 20000609SH017](https://openairdocs.org/sdr/20000609SH017.md): Bearing Support · lack of lube · May 15, 2000 · N508AB · Gulstm 695A · Rudder Tab Control System
  > RUDDER 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 LU
- [SDR 99ZZZX1571](https://openairdocs.org/sdr/99ZZZX1571.md): Control Cable · frayed · Apr 5, 1999 · N7031J · Gulstm 695A · Rudder Control System
  > DURING INSPECTION, FOUND RIGHT RUDDER BALANCE CABLE FRAYED AT LOWER PULLEY. TT: APPROX 1,900 HOURS. INSTALLED NEW CABLE ASSY, RIGHT.
- [SDR 98ZZZX4215](https://openairdocs.org/sdr/98ZZZX4215.md): Windshield · shattered · Nov 4, 1998 · N79PH · Gulstm 695A · Flight Compartment Windows
  > LEFT WINDSHIELD OUTER LAYER SHATTERED AT ALTITUDE. WINDSHIELD HEAT OPERATED NORMALLY PRIOR TO INCIDENT. 500 HOURS ON WINDSHIELD.
- [SDR 97ZZZX4010](https://openairdocs.org/sdr/97ZZZX4010.md): Control Cable · frayed · Sep 2, 1997 · N7896G · Gulstm 695A · Aileron Control System
  > WHILE 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 CA971010012](https://openairdocs.org/sdr/CA971010012.md): Control Cable · broken · Jul 8, 1997 · Gulstm 695A · Trailing Edge Flap Control System
  > (CAN) 75 PERCENT OF RT INBOARD FLAP CABLE STRANDS BROKEN. REPLACED.
- [SDR 97ZZZX3339](https://openairdocs.org/sdr/97ZZZX3339.md): Skin · corroded · Jul 1, 1997 · N79PH · Gulstm 695A · Wing, Plate/Skin
  > ACFT 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 T
- [SDR 97ZZZX3338](https://openairdocs.org/sdr/97ZZZX3338.md): Skin · corroded · Jul 1, 1997 · N79PH · Gulstm 695A · Wing, Plate/Skin
  > ACFT 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 T
- [SDR 97ZZZX2087](https://openairdocs.org/sdr/97ZZZX2087.md): Control Cable · frayed · Apr 18, 1997 · N2270T · Gulstm 695A · Aileron Control System
  > DURING 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 I
- [SDR 97ZZZX1483](https://openairdocs.org/sdr/97ZZZX1483.md): Flap · misinstalled · Mar 1, 1997 · N2267U · Gulstm 695A · Trailing Edge Flaps
  > WHILE 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 APPE
- [SDR 96ZZZX4831](https://openairdocs.org/sdr/96ZZZX4831.md): Starter · wrong part · Sep 4, 1996 · N695NC · Gulstm 695A · Starter-Generator
  > DURING 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 PAH
- [SDR 96ZZZX4129](https://openairdocs.org/sdr/96ZZZX4129.md): Arm Assy · cracked · Aug 2, 1996 · N20GT · Gulstm 695A · Landing Gear Retraction/Extension System
  > FOUND 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 100
- [SDR 96ZZZX2236](https://openairdocs.org/sdr/96ZZZX2236.md): Angle · cracked · Apr 1, 1996 · N79PH · Gulstm 695A · Wing, Landing Gear Attach Fittings
  > DURING 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 ASSOCIA
- [SDR 96ZZZX2235](https://openairdocs.org/sdr/96ZZZX2235.md): Firewall · cracked · Apr 1, 1996 · N79PH · Gulstm 695A · Nacelle/Pylon, Bulkhead/Firewall
  > THE 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 96ZZZX2229](https://openairdocs.org/sdr/96ZZZX2229.md): Truss Support · damaged · Apr 1, 1996 · N79PH · Gulstm 695A · Main Landing Gear
  > AFTER 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 TRUS
- [SDR CA960502057](https://openairdocs.org/sdr/CA960502057.md): Windshield · cracked · Mar 28, 1996 · Gulstm 695A · Flight Compartment Windows
  > (CAN) LEFT HAND WINDSHIELD FOUND CRACKED.
- [SDR 96ZZZX25](https://openairdocs.org/sdr/96ZZZX25.md): Regulator · diaphragm blown · Dec 14, 1995 · N325MM · Gulstm 695A · Pneumatic Distribution System
  > DURING 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

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/model/gulfstream-aerospace-695a/reports

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