# Service difficulty reports: Taylorcraft G-100

A list on [Taylorcraft G-100](https://openairdocs.org/model/taylorcraft-g-100.md).

Newest first. General aviation reporting is voluntary.

- [SDR GQRA20250509001](https://openairdocs.org/sdr/GQRA20250509001.md): Squat Switch · failed · May 9, 2025 · N24ZD · Gulstm G100 · Cabin Temperature Control System
  > 21-10 A RAPID DECOMPRESSION OCCURRED AT 13000' ON DEPARTURE FROM SINGAPORE, DURING LEVEL FLIGHT. AN EMERGENCY DECENT WAS CARRIED OUT AND THE QRH CHECKLIST FOLLOWED. THE AIRCRAFT WAS FLOWN SAFELY BACK TO WSSL. COMPLIED WITH LEFT MAIN LANDING GEAR GROUND CONTAC
- [SDR 2JKA202311280001](https://openairdocs.org/sdr/2JKA202311280001.md): None · none · Oct 28, 2023 · N448GR · Gulstm G100 · Standard Practices/Structures
  > PILOT FOUND FUEL LEAKING FROM LEFT FUEL JETTISON AFTER TAKE OFF. RETURNED TO KOPF. UPON RETURN, MAINTENANCE PERFORMED FUNCTIONAL CHECKS OF THE SYSTEM AND FOUND NO DEFECTS.
- [SDR JGVR20151230001](https://openairdocs.org/sdr/JGVR20151230001.md): Pin · broken · Dec 30, 2015 · N590TA · Gulstm G100 · Main Landing Gear Strut/Axle/Truck
  > WHILE PERFORMING A FACTORY C-INSPECTION, TASK ITEM 32-10-02, REINSTALLING/TORQUEING THE ORIGINAL RT MAIN LANDING GEAR SHOCK STRUT UPPER ATTACHMENT PIN TO THE LANDING GEAR AND THE HEAD BROKE OFF PRIOR TO REACHING THE MINIMUM TORQUE VALUE IAW AMM 32-10-02. VISU
- [SDR CA151208006](https://openairdocs.org/sdr/CA151208006.md): Pump · leaking · Dec 4, 2015 · Gulstm G100 · Hydraulic Pump (Electric/Engine), Main
  > (CAN) LOSS OF MAIN HYDRAULIC SYSTEM PRESSURE. NEITHER ENGINE DRIVEN PUMP WERE ABLE TO MAINTAIN SYSTEM PRESSURE. UPON INSPECTION, FOUND BOTH PUMPS TO HAVE LEAKAGE AT SHAFT SEAL CASE DRAINS.
- [SDR JGVR20150623001](https://openairdocs.org/sdr/JGVR20150623001.md): Duct · mismanufactured · Jun 23, 2015 · N100AK · Gulstm G100 · Engine Anti-Icing System
  > DURING ROUTINE ENGINE WORK, FOUND THE NR 2 ENGINE HP BLEED AIR DUCT ASSY 90 DEGREE CONNECTION, PN SBJ10531-505, WITH A BLOWN GASKET, PN BA7684, BY VISUAL INSPECTION. EVIDENCE OF BLEED AIR LEAK STREAKS FOUND ON THE BYPASS DUCT. THE EFFECTED PARTS IDENTICAL IA
- [SDR JGVR20150325001](https://openairdocs.org/sdr/JGVR20150325001.md): Duct · leaking · Mar 25, 2015 · N109GX · Gulstm G100 · Engine Bleed Air System
  > DURING ROUTINE ENGINE WORK, FOUND THE NR 1 ENGINE HP BLEED AIR DUCT ASSEMBLY 90 DEG. CONNECTION WITH A BLOWN GASKET - BLACK SOOT EVIDENT ON THE BYPASS DUCT AND INNER SURFACE OF UPPER ENGINE COWL. THIS ENGINE IS SIMILAR AS THAT ON THE GULFSTREAM G150 AND THE E
- [SDR CA150326003](https://openairdocs.org/sdr/CA150326003.md): Downlock Switch · intermittent · Mar 22, 2015 · Gulstm G100 · Landing Gear Position and Warning
  > (CAN) ON APPROACH THE CREW NOTED THE NOSE GEAR INDICATOR FOR DOWN & LOCK DID NOT ILLUMINATE. THEY ABORTED THE APPROACH & DID A FLY BY THE TOWER TO VERIFY THE GEAR WAS DOWN & LOCKED. TOWER CONFIRMED IT APPEARED DOWN & THEY CAME AROUND TO LAND. ON FINAL THE LI
- [SDR G6NR2014093000574](https://openairdocs.org/sdr/G6NR2014093000574.md): Collar · broken · Sep 30, 2014 · Gulstm G100 · Wing Main, Frame Structure
  > 14 LT WING FASTENERS AT UPPER WING ROOT STATION ZERO HAVE BROKEN COLLARS.
- [SDR CA131021023](https://openairdocs.org/sdr/CA131021023.md): Drive Shaft · worn · Oct 17, 2013 · Gulstm G100 · Leading Edge Slat Control System
  > (CAN) FLEX DRIVE CABLE HEX END WORN, DRIVE SLIPPED IN ACTUATOR CAUSING A SLAT SYSTEM IMBALANCE. THE SLAT ACTUATOR AND THE FLEX DRIVE CABLE BOTH REPLACED DUE TO EXCESSIVE WEAR.
- [SDR CA130221004](https://openairdocs.org/sdr/CA130221004.md): Apu · shutdown · Feb 14, 2013 · Gulstm G100 · APU Core Engine
  > (CAN) PILOT HAD UN-COMMANDED SHUTDOWN OF APU ON THE GROUND. APU WOULD NOT RESTART AFTER. MAINTENANCE DIAGNOSTIC COMPUTER SHOWED HIGH APU OIL TEMPERATURE. INSPECTED APU OIL TEMPERATURE SENDER FOUND OK. FOUND OIL FILTER BYPASS INDICATION PIN EXTENDED. REMOVE
- [SDR CA130121013](https://openairdocs.org/sdr/CA130121013.md): Exciter · failed · Jan 18, 2013 · Gulstm G100 · Exciter
  > (CAN) ENGINE DEEC DOWNLOAD C/O. FOUND "IGN B FAULT" CHANNEL B OF IGNITION EXCITER FAILED.
- [SDR CA121231003](https://openairdocs.org/sdr/CA121231003.md): Relay · defective · Dec 14, 2012 · Gulstm G100 · Flight Control System
  > (CAN) PRIMARY PITCH TRIM FAILED TO TRIM NOSE UP, RELAY 72C FOUND DEFECTIVE AND REPLACED.
- [SDR CA121004001](https://openairdocs.org/sdr/CA121004001.md): Transducer · weak · Aug 28, 2012 · Gulstm G100 · Fuel Controlling System
  > (CAN) N2 TRANSDUCER SIGNAL WAS WEAK, OUT OF LIMITS THIS CAUSED THE DEEC TO REDUCE FUEL FLOW. REPLACEMENT OF N2 TRANSDUCER CORRECTED ISSSUE.
- [SDR CA111123010](https://openairdocs.org/sdr/CA111123010.md): Current Limiter · overheated · Nov 21, 2011 · Gulstm G100 · APU Start/Ignition System
  > (CAN) SCHEDULED A CHECK INSPECTION, DURING A VISUAL INSPECTION OF THE LT DC CONTACTOR PANEL SIGNS OF OVERHEATING WERE OBSERVED ON THE OUTGOING TERMINAL & WIRE OF CURRENT LIMITER, PN ANL300. THIS CURRENT LIMITER IS FOR THE APU STARTER GENERATOR CIRCUIT & IS PA
- [SDR CA111004008](https://openairdocs.org/sdr/CA111004008.md): Igniter · cracked · Oct 1, 2011 · Gulstm G100 · APU Start/Ignition System
  > (CAN) APU IGNITER PLUG, WAS FOUND CRACKED ON THE END SHELL BETWEEN THE TIP AND THREADED PORTION. THE DEFECT WAS DISCOVERED DURING THE SCHEDULED MX CHECK OF THE APU IGNITER AND WAS REPLACED.
- [SDR CA111003008](https://openairdocs.org/sdr/CA111003008.md): Plug · sheared · Sep 26, 2011 · Gulstm G100 · Hydraulic Reservoir, Main
  > (CAN) MAIN HYD TANK DRAIN PLUG SHEARED/SEPARATED AT O-RING GROVE THREADS REMAINED IN TANK AND PLUG HEAD FELL OFF. PLUG IS DRILLED FOR A MAGNET SO THREADED PORTION IS HOLLOW.
- [SDR CA110822016](https://openairdocs.org/sdr/CA110822016.md): Clamp · loose · Jul 31, 2011 · Gulstm G100 · Cabin Pressure Control System
  > (CAN) DURING CLIMB ALL PRESSURIZATION SEEMED NORMAL AND AT THE 18,000 CHECK SCHEDULING WAS NORMAL. AT 32,000 FT THE CREW GOT A CABIN ALTITUDE WARNING AND THE OXYGEN MASKS DEPLOYED. THE CREW DECENDED THE ACFT AND RETURNED TO DEPARTURE. THE CREW NOTICED SOME
- [SDR CA110913007](https://openairdocs.org/sdr/CA110913007.md): Circuit Card · failed · Jul 8, 2011 · Gulstm G100 · Navigation System
  > (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE ACFT WOW: WENT "BLACK" ACFT, PULLED BOTH GPS C/B`S, POWERED ACFT, INITIALIZED TIME/DATE STAMP IN FMS`S, RESET GPS C/B`S. WHEN GPS`S INITIALIZED THEY WENT THR
- [SDR CA110913006](https://openairdocs.org/sdr/CA110913006.md): Gps · failed · Jul 8, 2011 · Gulstm G100 · Global Positioning System
  > (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE AIRCRAFT W.O.W: WENT "BLACK" AIRCRAFT, PULLED BOTH GPS C/B`S, POWERED A/C, INITIALIZED TIME/DATE STAMP IN FMS`S, RESET GPS C/B`S. WHEN GPS`S INITIALIZED THEY
- [SDR CA110913005](https://openairdocs.org/sdr/CA110913005.md): Gps · failed · Jul 8, 2011 · Gulstm G100 · Global Positioning System
  > (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE ACFT WOW: WENT "BLACK" ACFT, PULLED BOTH GPS C/B`S, POWERED ACFT, INITIALIZED TIME/DATE STAMP IN FMS`S, RESET GPS C/B`S. WHEN GPS`S INITIALIZED THEY WENT THR
- [SDR CA101215002](https://openairdocs.org/sdr/CA101215002.md): Oil Filter · broken · Dec 12, 2010 · Gulstm G100 · Turbine Engine Oil System
  > (CAN) DURING THE SOAP SAMPLE INSPECTION OF THE LT ENGINE, MAINTENANCE DISCOVERED A SECTION OF THE OIL FILTER END CAP MISSING FROM THE CLOSED END OF THE FILTER. HONEYWELL TECHNICAL SUPPORT WAS CONTACTED AND ADVISED TO FIND THE MISSING PIECE. GULFSTREAM MAINTENA
- [SDR CA101202011](https://openairdocs.org/sdr/CA101202011.md): Bracket · cracked · Dec 2, 2010 · Gulstm G100 · Passenger/Crew Doors
  > FOUND BOTH AIR SPRING UPPER SUPPORT BRACKETS ON AIR STAIR DOOR CRACKED DURING A C-CHECK. ALTHOUGH NOT A SAFETY OF FLIGHT ISSUE, THIS IS THE SECOND OF OUR ACFT TO HAVE THIS BRACKET FAIL. HAD 1 FAIL IN THE SUMMER OF 2010, WHICH WE FEEL DID NOT WARRANT AN SDR,
- [SDR CA100908001](https://openairdocs.org/sdr/CA100908001.md): Seal · worn · Aug 4, 2010 · Gulstm G100 · Aileron Control System
  > WHILE CRUISING AT FL380, AUTOPILOT HEADING CONTROL BEGAN BEHAVING ABNORMALLY. WHEN THE FLIGHT CREW DISCONNECTED THE AUTOPILOT THEY WERE UNABLE TO MOVE AILERON CONTROLS, ALTHOUGH LIMITED CONTROL WAS AVAILABLE AT THE CO-PILOT STA AND LEVEL FLIGHT WAS MAINTAINED
- [SDR 2010FA0000627](https://openairdocs.org/sdr/2010FA0000627.md): Windshield · cracked · Jun 14, 2010 · Gulstm G100 · Flight Compartment Windows
  > RT WINDSHIELD OUTSIDE CRACK FOUND WHEN ACFT DESCENT FROM FL430 TO FL250,AND THEN TURNOFF THE WINDSHIELD HEATER, NO-PERSSURE LOSS, AND SAFE LANDING BACK HOME.THE SIGN SHOWS AND DOES NOT STRIKE AS THE SUFFERING EXTERNAL FORCE.
- [SDR CA100614007](https://openairdocs.org/sdr/CA100614007.md): Retainer · broken · Jun 11, 2010 · Gulstm G100 · Turbine Engine Oil System
  > DURING POST FLIGHT INSP, FOUND BROKEN TAB RETAINER IN LOWER COWLING. FURTHER INVESTIGATION REVEALED THE TAB WAS FROM THE OIL COOLER SUPPLY LINE HOLD DOWN RETAINER. THE RETAINER IS USED ON OIL LINE, PN 3060997-1. THE SECOND RETAINER WAS ALSO REPLACED AS IT S
- [SDR 2009FA0001044](https://openairdocs.org/sdr/2009FA0001044.md): Pump · leaking · Dec 17, 2009 · N149GA · Gulstm G100 · Hydraulic Pump (Electric/Engine), Main
  > DISCOVERED A LARGE AMOUNT OF HYDRAULIC FLUID HAD LEAKED FROM THE RT ENG. FURTHER INVESTIGATION SHOWED A LEAK COMING FROM THE RT HYD PUMP CASE DRAIN INDICATING THAT THE HYD PUMP HAD INTERNALLY FAILED. REMOVED AND REPLACED HYD PUMP, PN 4018301, SN AL212AB IAW
- [SDR 2009FA0001043](https://openairdocs.org/sdr/2009FA0001043.md): Starter Gen · failed · Dec 17, 2009 · N749GA · Gulstm G100 · Starter-Generator
  > STARTER GENERATOR FAILED, NO INDICATION OF VOLTAGE PRESENT. PN 23065-018-1, SN 98004. REMOVED AND REPLACED STARTER GENERATOR, SYS OPS CHECK GOOD IAW AMM 24-30-02. ACFT HAD A PREVIOUS FAILURE OF THE HYD SUCTION LINE WHICH HAD RUPTURED. DETAIL REPORT ON THAT P
- [SDR CA090225001](https://openairdocs.org/sdr/CA090225001.md): Flex Line · burst · Feb 20, 2009 · Gulstm G100 · Passenger/Crew Doors
  > (CAN) DURING CLIMB OUT THROUGH 1000` THE CREW REPORTED A BANG LIKE A BALLOON POPING. THE "DOOR SEAL" ANNUNCIATOR ILLUMINATED AND THEN THERE WAS AN INCREASE IN AIR NOISE. AFTER LANDING INVESTIGATION REVEALED THAT THE INLET FLEX LINE HAD SPLIT CAUSING THE DOOR S

## 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 = 'G100'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/taylorcraft-g-100/reports

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