# Service difficulty reports: N339QS

A list on [N339QS](https://openairdocs.org/aircraft/N339QS.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 2 · 70 reports

- [SDR 2026FA0000739](https://openairdocs.org/sdr/2026FA0000739.md): Angle · corroded · Sep 17, 2026 · N339QS · Cessna 680CE · Fuselage Miscellaneous Structure
  > CORROSION FOUND ON LT VERTICAL CAP ANGLE.
- [SDR 2026F00091](https://openairdocs.org/sdr/2026F00091.md): Bracket · corroded · Apr 30, 2026 · N339QS · Cessna 680CE · Fuselage Miscellaneous Structure
  > MECHANICALLY REMOVED 8 AREAS OF CORROSION WHERE 8 LOCK FASTENERS WERE PREVIOUSLY REMOVED ON FWD BRACKET INSIDE NLG WHEEL WELL, ON FWD FACE OF UP-LOCK BRACKET IAW SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING.002" OF MATE
- [SDR JGVR20260429023](https://openairdocs.org/sdr/JGVR20260429023.md): Access Panel · corroded · Apr 29, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > REPAIRED RH FLAP PANEL LAND RIBS BY BLENDING CORRODED AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR ANGLE DOUBLERS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
- [SDR JGVR20260429022](https://openairdocs.org/sdr/JGVR20260429022.md): Access Panel · corroded · Apr 29, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > REPAIRED RH FLAP ACCESS PANEL LAND BY BLENDING CORRODED AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
- [SDR JGVR20260429021](https://openairdocs.org/sdr/JGVR20260429021.md): Skin · corroded · Apr 29, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > REPAIRED CORRODED AREAS AND TOOLING MARKS ON THE LH WING LOWER CENTER SKIN IN THE MLG WHEEL WELL COMMON TO THE LOWER SPAR CAP BY REMOVING FASTENERS AS REQUIRED, MECHANICALLY BLENDING, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING
- [SDR 2026F00090](https://openairdocs.org/sdr/2026F00090.md): Skin · corroded · Apr 28, 2026 · N339QS · Cessna 680CE · Fuselage Main, Plate/Skin
  > FOUND MULTIPLE AREAS OF CORROSION UNDER AFT CHIN FAIRING. MECHANICALLY REMOVED AREAS OF CORROSION LOCATED UNDER AFT CHIN FAIRING ON FUSELAGE OUTER SKIN IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDIN
- [SDR 2026F00088](https://openairdocs.org/sdr/2026F00088.md): Skin · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > REPAIRED CORROSION ON LH UPPER WING AT W.S. 37.00 PER AQRD ERO-988403, REV. IR, TITLED "N339QS LH WING UPPER SKIN CORROSION" DATED MAR 16 2026. SUPPORTED BY FAA FORM 8110-3 DATED 3/16/2026.
- [SDR 2026F00087](https://openairdocs.org/sdr/2026F00087.md): Skin · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > CENTER WING LOWER SKIN IN PANEL BAY 175AC HAS 13 AREAS OF CORROSION. MECHANICALLY REMOVED CORROSION LOCATED WHERE 19 HI-LOK'S WERE PREVIOUSLY REMOVED ALONG WITH SMALL AREAS AROUND REMOVED HI-LOK'S LOCATED IN ACCESS BAY 175AC, LOWER CENTER WING SKIN, OUTER SURF
- [SDR 2026F00086](https://openairdocs.org/sdr/2026F00086.md): Support · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Aerodynamic Fairings
  > CORROSION FOUND AROUND AND UNDER NUTPLATES ON LH (P/N 6921340-3) AND RH (P/N 6921340-4) UNDER-FAIRING SUPPORTS FOR PANELS 175BC AND 176BC. MECHANICALLY REMOVED CORROSION LOCATED AROUND AND UNDER NUTPLATES ON LH (P/N 6921340-3) AND RH (P/N 6921340-4) UNDER-FAI
- [SDR 2026F00085](https://openairdocs.org/sdr/2026F00085.md): Support · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Fuselage Miscellaneous Structure
  > CORROSION FOUND ON SKID RAIL UPPER LH SUPPORT LOWER LH SUPPORT AND LOWER RH SUPPORT, MECHANICALLY REMOVED CORROSION LOCATED WHERE 21 NUTPLATES ARE LOCATED ON SKID RAIL UPPER LH SUPPORT P/N 6921010-3, LOWER LH SUPPORT P/N 6921010-5, AND LOWER RH SUPPORT P/N
- [SDR 2026F00084](https://openairdocs.org/sdr/2026F00084.md): Access Panel · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > FOUND 12 AREAS OF CORROSION AROUND NUT PLATES FOR PANEL 642GB. MECHANICALLY REMOVED 12 AREAS OF CORROSION WHERE 12 NUTPLATES WERE REMOVED LOCATED INSIDE WING LOWER ACCESS BAY 642GB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CES
- [SDR 2026F00082](https://openairdocs.org/sdr/2026F00082.md): Spar · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #8 SPOILER BOTH HYDRAULIC PRESSURE AND RETURN CARRY THROUGH'S HAVE CORROSION AROUND THEM ON RH WING AFT SPAR. MECHANICALLY REMOVED CORROSION WHERE #8 SPOILER HYD LINES ARE LOCATED ON RH WING, FLAP WELL, AFT SPAR, AFT FACE IAW CESSNA 680 SRM 51-70-02. FOU
- [SDR 2026F00081](https://openairdocs.org/sdr/2026F00081.md): Nut Plate · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Wing, Attach Fittings
  > FOUND 6 AREAS OF CORROSION AROUND NUT PLATES FOR PANEL 652DB, MECHANICALLY REMOVED 6 AREAS OF CORROSION WHERE 6 NUTPLATES LOCATED INSIDE RH WING ACCESS BAY 652DB WERE REMOVED IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 68
- [SDR 2026F00079](https://openairdocs.org/sdr/2026F00079.md): Doubler · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Fuselage Miscellaneous Structure
  > LH LOWER FUSELAGE CARRY-THROUGH DOUBLER UNDER BAGGAGE FLOOR IS CORRODED. MECHANICALLY REMOVED CORROSION LOCATED ON ELECTRICAL CARRY THROUGH DOUBLER ON THE LH SIDE UNDER THE BAGGAGE FLOOR IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS I
- [SDR 2026F00083](https://openairdocs.org/sdr/2026F00083.md): Deflector · corroded · Apr 23, 2026 · N339QS · Cessna 680CE · Fuselage Main, Plate/Skin
  > FOUND 7 AREAS OF CORROSION ON DEFLECTORS ON PANEL 323AC. MECHANICALLY REMOVED 7 AREAS OF CORROSION ON DEFLECTORS ON PANEL 323AC IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA SRM 51-70-02 EXCEEDING.002" OF MATERIAL REMOVED
- [SDR 2026F00077](https://openairdocs.org/sdr/2026F00077.md): Pulley Bracket · corroded · Apr 20, 2026 · N339QS · Cessna 680CE · Wing Main, Frame Structure
  > FOUND 2 AREAS OF CORROSION ON SPOILER PULLEY BRACKET ON LH WING INBD, AFT SPAR. MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED ON LH WING SPOILER PULLEY BRACKET, INSIDE INBD FLAP WELL, AFT SPAR IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND
- [SDR 2026F00076](https://openairdocs.org/sdr/2026F00076.md): Bolt · corroded · Apr 20, 2026 · N339QS · Cessna 680CE · Spoilers
  > FOUND BOTH INBD SPOILER RETRACT AND EXTEND CARRY THRU'S HAVE CORROSION AROUND THEM. MECHANICALLY REMOVED CORROSION LOCATED ON LH WING AFT SPAR INSIDE INBD FLAP COVE AROUND INBD SPOILER RETRACT AND EXTEND HYDRAULIC LINES, AFT FACE ONLY IAW SRM 51-70-02. FOUND C
- [SDR 2026F00048](https://openairdocs.org/sdr/2026F00048.md): Spar · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #5 SPEED BRAKE HYDRAULIC RETRACT CARRY THRU HAS CORROSION AROUND IT ON LH WING AFT SPAR. MECHANICALLY REMOVED CORROSION LOCATED WHERE #5 SPEED BRAKE RETRACT LINE FITTING IS LOCATED ON LH WING, AFT SPAR, AFT FACE IN FLAP COVE IAW CESSNA 680 SRM 51-70-02.
- [SDR 2026F00058](https://openairdocs.org/sdr/2026F00058.md): Spar · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #4 SPEED BRAKE BOTH HYDRAULIC PRESSURE AND RETURN CARRY THRU'S HAVE CORROSION AROUND THEM ON LH WING AFT SPAR. MECHANICALLY REMOVED CORROSION LOCATED WHERE #4 SPEED BRAKE HYD PRESSURE AND RETURN LINE CARRY THRU FITTINGS ARE LOCATED ON LH WING AFT SPAR, A
- [SDR 2026F00057](https://openairdocs.org/sdr/2026F00057.md): Spar · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #2 SPOILER HYDRAULIC PRESSURE CARRY THRU HAS CORROSION AROUND IT ON LH WING AFT SPAR. MECHANICALLY REMOVED CORROSION LOCATED WHERE #2 SPOILER HYD PRESSURE LINE CARRY THRU FITTING IS LOCATED ON LH WING AFT SPAR, AFT FACE INSIDE FLAP COVE IAW CESSNA 680 SR
- [SDR 2026F00056](https://openairdocs.org/sdr/2026F00056.md): Access Panel · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing, Plate/Skin
  > FOUND 39 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 523AB AND 2 AREAS ON PANEL LAND. MECHANICALLY REMOVED 39 AREAS AROUND NUTPLATES WHICH WERE REMOVED PLUS 2 AREAS OF CORROSION ON PANEL LAND OF CORROSION IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS T
- [SDR 2026F00055](https://openairdocs.org/sdr/2026F00055.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing, Attach Fittings
  > FOUND 20 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 532GB. MECHANICALLY REMOVED 22 AREAS OF CORROSION WHERE 20 NUTPLATES WERE REMOVED LOCATED ON LH WING INSIDE ACCESS BAY 532GB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESS
- [SDR 2026F00054](https://openairdocs.org/sdr/2026F00054.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Miscellaneous Structure
  > FOUND 21 AREAS OF CORROSION AROUND NUTPLATES FO. R PANEL 532FB. MECHANICALLY REMOVED 21 AREAS OF CORROSION WHERE 21 NUTPLATES WERE REMOVED LOCATED ON LH WING INSIDE ACCESS BAY 532FB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CE
- [SDR 2026F00053](https://openairdocs.org/sdr/2026F00053.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing, Attach Fittings
  > FOUND 12 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 542GB. MECHANICALLY REMOVED 12 AREAS OF CORROSION WHERE 12 NUTPLATES WERE REMOVED LOCATED ON LH WING INSIDE ACCESS BAY 542GB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESS
- [SDR 2026F00052](https://openairdocs.org/sdr/2026F00052.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Miscellaneous Structure
  > FOUND 13 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 542FB. MECHANICALLY REMOVED 13 AREAS OF CORROSION WHERE 13 NUTPLATES WERE REMOVED INSIDE WING LOWER ACCESS BAY 542FB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680
- [SDR 2026FA0000244](https://openairdocs.org/sdr/2026FA0000244.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing, Attach Fittings
  > FOUND 8 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 632GB. BLENDED 8 AREAS OF CORROSION AT CORRODED NUTPLATE AREAS IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING.002" OF MATERIAL REMOVED FROM NO
- [SDR 2026F00051](https://openairdocs.org/sdr/2026F00051.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing, Attach Fittings
  > FOUND 20 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 642FB. MECHANICALLY REMOVED 20 AREAS OF CORROSION LOCATED WHERE 20 NUTPLATES WERE REMOVED INSIDE WING LOWER ACCESS BAY 642FB IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESS
- [SDR 2026F00047](https://openairdocs.org/sdr/2026F00047.md): Nut Plate · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Fuselage Main, Attach Fittings
  > FOUND 8 AREAS OF CORROSION AROUND NUTPLATES FOR PANEL 642EB. MECHANICALLY REMOVED 8 AREAS OF CORROSION LOCATED INSIDE WING LOWER ACCESS PANEL 642EB WHERE 8 NUTPLATES WERE LOCATED IAW SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXC
- [SDR 2026F00050](https://openairdocs.org/sdr/2026F00050.md): Spar · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #7 SPEED BRAKE HYDRAULIC RETURN CARRY THRU HAS CORROSION AROUND IT ON RH WING AFT SPAR. MECHANICALLY REMOVED CORROSION WHERE #7 SPEED BRAKE HYD RETURN LINE IS LOCATED ON RH WING, FLAP WELL, AFT SPAR, AFT FACE IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION
- [SDR 2026F00049](https://openairdocs.org/sdr/2026F00049.md): Spar · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Wing Spar
  > FOUND #9 SPOILER BOTH HYDRAULIC PRESSURE AND RETURN CARRY THRU'S HAVE CORROSION AROUND THEM ON RH WING AFT SPAR. MECHANICALLY REMOVED CORROSION WHERE #9 SPOILER HYD PRESSURE AND RETURN LINE CARRY THRU FITTINGS ARE LOCATED ON WING AFT SPAR, AFT FACE IAW CESSNA
- [SDR 2026F00045](https://openairdocs.org/sdr/2026F00045.md): Frame · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Fuselage Main, Structure
  > CORROSION FOUND UNDER NUTPLATES ON FAIRING FRAME AT FS 312.90. MECHANICALLY REMOVED 6 AREAS OF CORROSION LOCATED ON INNER AND OUTER SURFACES OF FAIRING FRAME FS 312.90 IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 5
- [SDR 2026F00046](https://openairdocs.org/sdr/2026F00046.md): Mount · corroded · Mar 31, 2026 · N339QS · Cessna 680CE · Vertical Stabilizer
  > FOUND CORROSION ON MOUNTING FLANGES FOR PANEL 342AB. MECHANICALLY REMOVED CORROSION LOCATED WHERE 18 NUTPLATES WERE REMOVED ON INNER AND OUTER SIDE OF FLANGES ON PANEL 342AB ATTACHMENT BRACKETS (10 NUTPLATES ON LH SIDE AND 8 NUTPLATES ON RT SIDE) IAW SRM 51-70
- [SDR 2026F00044](https://openairdocs.org/sdr/2026F00044.md): Door Frame · corroded · Mar 31, 2026 · N339QS · Cessna 680A · Fuselage Main, Structure
  > FOUND 1 AREA OF CORROSION AROUND AIRCRAFT DATA PLATE. REPAIRED CORROSION ON AFT TAIL CONE UNDER DATA TAG IN REFERENCE TO AEROSPACE QUALITY RESEARCH AND DEVELOPMENT ENGINEERING REPAIR ORDER: ERO-988391 REV. IR; TITLED: N339QS AFT TAILCONE SKIN CORROSION; DATED:
- [SDR 2026F00039](https://openairdocs.org/sdr/2026F00039.md): Pulley Bracket · corroded · Mar 19, 2026 · N339QS · Cessna 680A · Wing Main, Frame Structure
  > FOUND 2 AREAS OF CORROSION ON SPOILER PULLEY BRACKET ON LH WING INBD, AFT SPAR. MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED ON LH WING SPOILER PULLEY BRACKET, INSIDE INBD FLAP WELL, AFT SPAR IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND
- [SDR 2026F00037](https://openairdocs.org/sdr/2026F00037.md): Stringer · corroded · Mar 19, 2026 · N339QS · Cessna 680A · Fuselage Main, Longeron/Stringer
  > FOUND SEVERAL AREAS OF CORROSION ON UPPER STRINGER INSIDE PANEL 652DB. MECHANICALLY REMOVED SEVERAL AREAS OF CORROSION ON UPPER STRINGER INSIDE PANEL 652DB, AFT AREA, FWD EDGE OF STRINGER, FROM INBD EDGE CONTINUING APPROXIMATELY 12 INCHES IN LENGTH GOING OUTBD
- [SDR 2026F00036](https://openairdocs.org/sdr/2026F00036.md): Spar · corroded · Mar 19, 2026 · N339QS · Cessna 680A · Wing Spar
  > FOUND 2 AREAS OF CORROSION ON AFT WING SPAR, FWD SIDE IN RH MLG WHEEL WELL. MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED IN RH MLG WHEEL WELL, REAR SPAR WEB NEAR RWS 17.30 IAW SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEE
- [SDR 2026F00035](https://openairdocs.org/sdr/2026F00035.md): Skin · corroded · Mar 19, 2026 · N339QS · Gulstm 680 · Vertical Stabilizer, Plate/Skin
  > LEFT AND RIGHT VERTICAL STAB UPPER SKINS HAVE 2 AREAS OF CORROSION JUST BELOW TIP CAP. MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED ON VERTICAL STAB OUTER SKIN JUST BELOW TIP CAP, AFT AREA, 1 BLEND PER SIDE IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLE
- [SDR 2026F00038](https://openairdocs.org/sdr/2026F00038.md): Skin · corroded · Mar 19, 2026 · N339QS · Cessna 680A · Wing, Plate/Skin
  > FOUND 1 AREA OF CORROSION ON RH WING UPPER SKIN, OUTBOARD OF #7 SPEED BRAKE IN ZONE 642. MECHANICALLY REMOVED 1 AREA OF CORROSION ON RH WING UPPER SKIN, JUST OUTBOARD OF #7 SPEED BRAKE IN ZONE 642 IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND
- [SDR 2026F00034](https://openairdocs.org/sdr/2026F00034.md): Skin · corroded · Mar 19, 2026 · N339QS · Cessna 680A · Wing, Plate/Skin
  > FOUND 9 AREAS OF CORROSION OF RH WING UPPER SKIN, FWD OF AILERON IN ZONE 652. MECHANICALLY REMOVED 9 AREAS OF CORROSION LOCATED ON RH WING UPPER SKIN, FWD OF AILERON IN ZONE 652 ON WING SKIN TRAILING EDGE IAW CESSNA 680 SRM 51-70-02. FOUND 8 CORROSION BLENDS T
- [SDR 2026F00030](https://openairdocs.org/sdr/2026F00030.md): Skin · corroded · Mar 17, 2026 · N339QS · Cessna 680A · Wing, Plate/Skin
  > FOUND 9 AREAS OF CORROSION OF RIGHT WING UPPER SKIN, FWD OF AILERON. MECHANICALLY REMOVED 9 AREAS OF CORROSION LOCATED ON RT WING UPPER SKIN, FWD OF AILERON ON WING SKIN TRAILING EDGE IAW SRM 51-70-02. FOUND 8 CORROSION BLENDS TO BE WITHIN LIMITS IAW SRM 51-70
- [SDR DXTA2025101605306](https://openairdocs.org/sdr/DXTA2025101605306.md): Battery Pack · inoperative · Oct 14, 2025 · N339QS · Cessna 680SOV · Emergency Lighting
  > WITH SHIP BATTERIES CONNECTED, CONDUCTING THE EMER LIGHT TEST IN THE ON. ARM POSITION NO EMERGENCY LIGHTS ILLUMINATED. REMOVED NR 1 EMERGENCY BATTERY PACK AND INSTALLED NEW NR 1 BATTERY PACK. REMOVED NR 2 BATTERY PACK AND INSTALLED A NEW NR 2 BATTERY PACK.
- [SDR DXTA2025063004051](https://openairdocs.org/sdr/DXTA2025063004051.md): Spring · defective · Jun 26, 2025 · N339QS · Cessna 680SOV · Passenger/Crew Doors
  > MAIN ENTRY DOOR TENSIONER NEEDS A TIGHTENING ADJUSTMENT. WHEN OPENING, THE DOOR ALMOST FREE FALLS AND BOUNCES AT BOTTOM. ANY INITIAL MOMENTUM WHEN INITIALLY OPENING WILL HAVE THE DOOR SIGNIFICANTLY BOUNCE. REPLACED BOTH OF THE MED SPRINGS IAW AMM 52-10-50. OP
- [SDR JGVR20250217001](https://openairdocs.org/sdr/JGVR20250217001.md): Hinge · corroded · Feb 17, 2025 · N339QS · Cessna 680CE · Fuselage, Door Hinge
  > MECHANICALLY REMOVED 2 AREAS OF SURFACE CORROSION ON MED FWD HINGE, AFT LUG AFT FACE AREA, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED CORROSION BLENDS IAW BY, CLEANING, TREATING AND PRIMING BLENDED AREAS IAW TEXTRON FIELD REPAIR.
- [SDR DXTA2024091700552](https://openairdocs.org/sdr/DXTA2024091700552.md): Control Handle · defective · Sep 15, 2024 · N339QS · Cessna 680SOV · Trailing Edge Flap Control System
  > FLAPS FAIL AMBER CAS: DURING APPROACH TO KHND WE RECEIVED A FLAP FAIL AMBER CAS WHEN SELECTING FLAPS 15. RAN THE FLAP FAIL QRC. CORRECTIVE ACTION: REMOVED AND REPLACED THE FLAP HANDLE IAW CE 680 MM 27-51-00. OPS CHECK GOOD, NO DEFECTS NOTED. REMOVED PN: 696525
- [SDR DXTA2023050185090](https://openairdocs.org/sdr/DXTA2023050185090.md): Sensor · defective · May 1, 2023 · N339QS · Cessna 680SOV · Fire Detection
  > DURING FLIGHT THE YELLOW CAS MESSAGE ENGINE FIRE DETECT FAIL-R ILLUMINATED. CONTINUED TO KLUK. COMPLIED WITH RESISTANCE CHECK OF THE LOWER FIRE DETECT LOOP ON RH ENG & FOUND NO DEFECTS NOTED. INVESTIGATED MAINTENANCE DIAGNOSTIC PAGE FOR PCB JZ208 & FOUND AN I
- [SDR DXTA2023030681980](https://openairdocs.org/sdr/DXTA2023030681980.md): None · missing · Mar 4, 2023 · N339QS · Cessna 680CE · Passenger/Crew Doors
  > MAIN CABIN DOOR MAKES LOUD CREAKING NOISE WHEN OPENING / CLOSING. BINDING APPEARS TO BE COMING FROM THE TOP ENTRY STEP. INSTALLED NEW RISER COVER CLIPS. IAW CE-680 AMM 52-10-00. OPS CHECK GOOD.
- [SDR DXTA2023022781380](https://openairdocs.org/sdr/DXTA2023022781380.md): None · none · Feb 27, 2023 · N339QS · Cessna 680SOV · Passenger/Crew Doors
  > MAIN DOOR: MAIN CABIN PRECATCH EXTENDS AS DOOR IS OPEN APPROX 2 FEET AWAY FROM FUSE BODY AND STAYS EXTENDED AS DOOR IS CLOSED. ONCE DOOR IS ALMOST CLOSED THE HANDLE HAS TO BE CYCLED TO RETRACT PRECATCH THEN DOOR CAN BE FULLY SECURED. WAS UNABLE TO PERFORM MEL
- [SDR DXTA2023022481170](https://openairdocs.org/sdr/DXTA2023022481170.md): None · none · Feb 23, 2023 · N339QS · Cessna 680CE · Passenger/Crew Doors
  > MAIN DOOR: MAIN DOOR WILL NOT FULLY CLOSE FROM THE OUTSIDE OR THE INSIDE, UNLESS THE DOOR IS PLACED INTO A POSITION WHERE IT IS NEARLY CLOSED. IF THE CREW THEN PUTS THE DOORHANDLE INTO THE FULLY LOCKED POSITION, THEN MOVED IT TO THE UNLOCK POSITION, THE DOOR W
- [SDR DXTA2023010377650](https://openairdocs.org/sdr/DXTA2023010377650.md): Accelerometer · faulted · Jan 1, 2023 · N339QS · Gulstm 680 · Engine Vibration Analyzer
  > AFTER BEING AT CRUISE PROBABLY 30 MINUTES THE ENGINE VIBRATION R CAS ILLUMINATED AND WENT BACK OUT. HAD THE EMER/ABNORMAL CHECKLIST IN HAND WHEN THE CAS REAPPEARED AND STAYED ON. RAN CHECKLIST. REDUCED POWER, DECLARED AN EMERGENCY & DIVERTED. THE ENTIRE T
- [SDR DXTA2021120252870](https://openairdocs.org/sdr/DXTA2021120252870.md): Apu · defective · Dec 1, 2021 · N339QS · Cessna 680CE · APU Cowling/Containment
  > APU BLEED AIR: WHEN APU BLEED AIR IS INITIALLY TURNED ON, OCCASIONALLY YOU CAN SEE A SLIGHT HAZE IN THE CABIN. SEEMS TO BE MORE PRONOUNCED WHEN APU AIR IS FIRST TURNED ON AND YOU ARE REQUESTING HOT AIR. THE HAZE QUICKLY DISSIPATES. // SIGNOFF// REMOVED FAULTY

Next page: https://openairdocs.org/aircraft/N339QS/reports.md?page=2

## 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 n_number = 'N339QS' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N339QS/reports

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.