N339QS
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NetJets Aviation, Inc. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
79 reports on file, 1998-02-05 – 2026-04-30.
Part: BRACKET — CORRODED (ZONE 100) · airframe 14,278 hrs · 9,522 cycles
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 MATERIAL REMOVED FROM NOMINAL THICKNESS. REMOVED AND REPLACED CORRODED U CHANNEL FWD OF NLG UP-LOCK ACTUATOR SUPPORT WITH NEW U CHANNEL. WORKED IAW SRM 51-40-03 AND RFTS-116654 REV.0.
Part: ACCESS PANEL — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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.
Part: SKIN — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 REPAIR DOUBLERS PER ENGINEERING REPAIR ORDER.
Part: ACCESS PANEL — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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.
Part: SKIN — CORRODED (ZONE 100) · airframe 14,278 hrs · 9,522 cycles
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 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LEVEL 2 CORROSION ON LOWER FUSELAGE SKIN UNDER AFT CHIN FAIRING PER AQRD ERO-988406 REV. IR TITLED "N339QS LOWER FUSELAGE SKIN CORROSION" DATED APR 20 2026 SUPPORTED BY FAA FORM 8110-3 DATED 04/20/2026.
Part: ACCESS PANEL — CORRODED (ZONE) · airframe 14,278 hrs · 9,522 cycles
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 CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED PANEL 642GB LANDS PER NETJETS RFTS-116690 REV. 0, TITLED: "N339QS (680-0191)PANEL 642GB LAND CORROSION", DATED 28MAR26.
Part: DEFLECTOR — CORRODED · airframe 14,278 hrs · 9,522 cycles
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 FROM NOMINAL THICKNESS. REPAIRED DEFLECTORS ON PANEL 323AC PER NETJETS RFTS-116323 REV. 0, TITLED: "N339QS (680-0191) DEFLECTOR PANEL 323AC CORROSION", DATED 31MAR26.
Part: SPAR — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED BLENDS IAW NETJETS AQRD RFTS-116545 REV.0 TITLE: N339QS (680-0191) RH WING SPAR WEB CORROSION, DATE: 05MAR26.
Part: NUT PLATE — CORRODED (ZOEN 600) · airframe 14,278 hrs · 9,522 cycles
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 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED 652DB PANEL LANDS PER NETJETS RFTS-116392 REV. 0, TITLED: "N339QS (680-0191) 652DB PANEL LANDS CORROSION", DATED 28MAR26
Part: DOUBLER — CORRODED (ZONE 100) · airframe 14,278 hrs · 9,522 cycles
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 IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL SKIN THICKNESS. REPAIRED LH LOWER FUSELAGE CARRY-THROUGH CORROSION PER NETJETS RFTS-116584 REV. 0, TITLED: "N339QS (680-0191) LH LOWER FUSELAGE CARRY THROUGH CORROSION", DATED 28MAR26.
Part: SUPPORT — CORRODED (ZONE 100) · airframe 14,278 hrs · 9,522 cycles
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-FAIRING SUPPORTS FOR PANELS 175BC AND 176BC 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 NOMINAL THICKNESS. REPAIRED LEVEL 2 PANEL LAND CORROSION FOR BELLY PANELS 175BC AND 176BC PER NETJETS AQRD RFTS-116476, REV. 0, TITLED "N339QS (680-0191) PANEL 175BC AND 176BC LANDS CORROSION, DATED 28 MAR 2026.
Part: SUPPORT — CORRODED (ZONE) · airframe 14,278 hrs · 9,522 cycles
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 6921010-6 IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE OUT OF LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED SKID RAIL PANEL LAND CORROSION PER NETJETS AQRD RFTS-116580 REV. 0, TITLED: "N339QS (680-0191) SKID RAIL CORROSION", DATED 28 MAR 26.
Part: SKIN — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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.
Part: SKIN — CORRODED (ZONE 100) · airframe 14,278 hrs · 9,522 cycles
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 SURFACE 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 NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS AQRD RFTS-116511 REV. 0, TITLE: N339QS ( 680-0191) CENTER WING LOWER SKIN CORROSION, DATE: 17MAR26.
Part: BOLT — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 CORROSION BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW AQRD RFTS-116436 REV.0,
Part: PULLEY BRACKET — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS AQRD RFTS-116407 REV. 0 TITLE: N339QS ( 680-0191 ) LH SPOILER PULLEY BRACKET CORROSION, DATE: 26FEB26.
Part: ACCESS PANEL — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LH FLAP PANEL LAND PER NETJETS AQRD RFTS-116419 REV. 0,
Part: SPAR — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 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 NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS AQRD RFTS-116443 REV.0.
Part: SPAR — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS AQRD RFTS-116437 REV.0, TITLE: N339QS (680-0191) LH WING AFT SPAR WEB CORROSION DATE: 05MAR26.
Part: NUT PLATE — CORRODED · airframe 14,278 hrs · 9,522 cycles
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 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED RH FLAP PANEL LAND PER NETJETS RFTS-116463 REV. 0,
Part: FRAME — CORRODED (FAIRING) · airframe 14,278 hrs · 9,522 cycles
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 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORRODED BELLY PANEL LAND AT FS312.90 PER AQRD RFTS-116481 REV.0,
Part: MOUNT — CORRODED (ZONE 300) · airframe 14,278 hrs · 9,522 cycles
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 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LEVEL 2 CORROSION ON MOUNTING FLANGES FOR RUDDER FAIRING PANEL 342AB ON APU STINGER PER NETJETS AQRD RFTS-116383, REV 0.
Part: DOOR FRAME — CORRODED (ZONE 200) · airframe 14,278 hrs · 9,522 cycles
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: MAR 16, 2026. REPAIR SUPPORTED BY FORM: FAA FORM 8110-3 TITLED "N339QS AFT TAILCONE SKIN CORROSION", DATED 3/16/2026. THE FATIGUE AND DAMAGE TOLERANCE (F&DT) EVALUATION REQUIRED PER 14 CFR PART 25, 25.571 IS NOT INCLUDED AS PART OF THIS ENGINEERING DOCUMENT. PER NETJETS AVIATION, INC. GENERAL MAINTENANCE MANUAL CHAPTER 11- THE F&DT EVALUATION MUST BE COMPLETED WITHIN 12 MONTHS FROM THE DATE OF ISSUE OF THE ASSOCIATED 8110-3. THE AIRCRAFT AT THE TIME OF REPAIR HAD 14,277.7 FLIGHT HOURS AND 9,522 FLIGHT CYCLES.
Part: SPAR — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED BLENDS IAW NETJETS AQRD RFTS-116544 REV.0
Part: NUT PLATE — CORRODED · airframe 14,278 hrs · 9,522 cycles
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 CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED RH FLAP PANEL LAND PER NETJETS RFTS-116440 REV. 0,
Part: NUT PLATE — CORRODED · airframe 14,278 hrs · 9,522 cycles
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 NOMINAL THICKNESS. REPAIRED RH FLAP PANEL LAND PER NETJETS RFTS-116475 REV. 0,
Part: NUT PLATE — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LH FLAP PANEL LAND PER NETJETS AQRD RFTS-116556 REV. 0,
Part: SPAR — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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, AFT FACE INSIDE FLAP COVE 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 NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS AQRD RFTS-116439 REV.0,
Part: NUT PLATE — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LH FLAP PANEL LAND CORROSION PER NETJETS RFTS-116430 REV. 0,
Part: NUT PLATE — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LH FLAP PANEL LAND PER NETJETS AQRD RFTS-116464 REV. 0,
Part: SPAR — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS AQRD RFTS-116547 REV.0,
Part: NUT PLATE — CORRODED (ZONE 500) · airframe 14,278 hrs · 9,522 cycles
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 CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED LH FLAP PANEL LAND PER NETJETS AQRD RFTS-116429 REV. 0,
Part: PULLEY BRACKET — CORRODED (ZONE 500 SPOILER) · airframe 14,278 hrs · 9,522 cycles
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 LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS AQRD RFTS-116407 REV. 0 TITLE: N339QS ( 680-0191 ) LH SPOILER PULLEY BRACKET CORROSION, DATE: 26FEB26.
Part: SKIN — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 TO BE WITHIN LIMITS IAW CESSNA SRM 51-70-02 NOT EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS AND FOUND 1 CORROSION BLEND TO BE BEYOND LIMITS IAW CESSNA SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. PROTECTED BARE METAL ON 8 AREAS WITHIN LIMITS IAW CESSNA 680 SRM 51-20-01. REPAIRED 1 AREA OF CORROSION BEYOND LIMITS IAW NETJETS AQRD RFTS-116326 REV. 0 TITLE: N339QS (680-0191) RH UPPER WING SKIN CORROSION DATE: 27FEB26.
Part: SKIN — CORRODED (ZONE 300) · airframe 14,278 hrs · 9,522 cycles
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 BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW AQRD RFTS-116341 REV.0, TITLED: N339QS (680-0191) VERTICAL STABILIZER SKIN CORROSION,
Part: SPAR — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW AQRD RFTS-116349 REV.0 TITLE: RH WING AFT SPAR WHEEL WELL CORROSION, DATE: 03MAR26.
Part: STRINGER — CORRODED (ZONE) · airframe 14,278 hrs · 9,522 cycles
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 IAW SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW AQRD RFTS-116431 REV.0 TITLE: N339QS (680-0191) UPPER AFT STRINGER INSIDE PANEL BAY 652DB CORROSION, DATE: 04MAR26.
Part: SKIN — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 LIMITS IAW CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS AQRD RFTS-116344 REV.0, TITLE: N339QS (680-0191) RH UPPER WING SKIN CORROSION DATE: 01MAR26.
Part: SKIN — CORRODED (ZONE 600) · airframe 14,278 hrs · 9,522 cycles
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 51-70-02 NOT EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS AND FOUND 1 CORROSION BLEND TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. PROTECTED BARE METAL ON 8 AREAS WITHIN LIMITS IAW SRM 51-20-01. REPAIRED 1 AREA OF CORROSION BEYOND LIMITS IAW AQRD RFTS-116326 REV. 0.
Earlier reports · 1998–2025 · 40 reports
2025
Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 14,153 hrs · 9,440 cycles
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. REMOVED NR 3 BATTERY PACK AND INSTALLED A NEW NR 3 BATTERY PACK. REMOVED NR 4 BATTERY PACK AND INSTALLED A NEW NR 4 BATTERY PACK IAW AMM 33-50-10. OPS CHECKED NORMAL.
Part: SPRING — DEFECTIVE (ZONE 800) · airframe 13,934 hrs · 9,278 cycles
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. OPS CHECK GOOD.
Part: HINGE — CORRODED (ZONE 800) · airframe 13,588 hrs · 9,038 cycles
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.
2024
Part: CONTROL HANDLE — DEFECTIVE (TE FLAPS) · airframe 13,238 hrs · 8,775 cycles
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: 6965250-2, SN: 0318. INSTALLED PN:6965250-2, SN: 0249
2023
Part: SENSOR — DEFECTIVE (RT ENGINE) · airframe 12,417 hrs · 8,213 cycles
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 INACTIVE" STATUS ON RT NODE INBOARD PROBE. PERFORMED WIRING CHECKS ON PE032 & RECEIVED AN OPEN ELECTRICAL READING. REMOVED & REPLACED FIRE & OVERHEAT SENSOR, APPLIED POWER TO ACFT & VERIFIED MESSAGE IS NO LONGER PRESENT. PERFORMED ENGINE RUN WITH NO LEAKS NOTED, OPS CHECKS GOOD. ALL WORK DONE IAW MM 71-10-00, 36-10-00 & P&WC 306C LMM 26-10-01. OPS & LEAK CHECKS GOOD.
Part: NONE — MISSING · airframe 12,307 hrs · 8,148 cycles
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.
Part: NONE — NONE · airframe 12,289 hrs · 8,132 cycles
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 PROCEDURE AS THE SPRING IS TO STRONG FOR TAPE AND PRECATCH CAN NOT BE SECURED.//CORRECTIVE ACTION//ADJUSTED PLUNGER ASSY PN:6911329-6 AS REQUIRED. AFTER ADJUSTMENTS OPERATED MAIN CABIN DOOR SEVERAL TIMES AND DID NOT NOTE ANY ISSUES AFTER ADJUSTMENTS HAD BEEN MADE
Part: NONE — NONE · airframe 12,277 hrs · 8,125 cycles
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 WAS SHUT NORMALLY. INSPECTED MCD AND FOUND PRECATCH LATCH OUT OF ADJUSTMENT. ADJUSTED MCD PRECATCH LATCH AND PERFORMED SATISFACTORY OPS CHECKS. NO FURTHER DISCREPANCIES NOTED IAW CE-680 AMM 52-10-00.
Part: ACCELEROMETER — FAULTED (RT ENGINE) · airframe 12,199 hrs · 8,074 cycles
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 TIME DURING THE DESCENT WITH POWER ALMOST AT IDLE THE ENG VIBRATION R CAS WAS STILL CYCLYING. DUE TO BEING 200 NM OFFSHORE, DECIDED NOT TO SHUT THE ENGINE DOWN UNLESS A VIBRATION WORSENED IAW THE CHECKLIST. DURING APPROACH/LANDING/TAXI-IN THE ENGINE VIBRATION CAS WAS NOT ILLUMINATED. R & R RT ACCELEROMETER WITH A NEW UNIT. OPS CHECKED SATISFACTORY IAW AMM 77-20-00.
2021
Part: APU — DEFECTIVE · airframe 12,095 hrs · 8,009 cycles
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 APU (LEAKING OIL INTERNALLY) PART NUMBER: 3800785-1 SERIAL NUMBER P-358 AND INSTALLED CUSTOMER SUPPLIED REPAIRED UNIT P/N ON: 3800785-1 S/N ON: P-842 IAW CE-680 AMM 49-10-00. OPS AND LEAK CHECKS GOOD AT THIS TIME. ALL RQC REQUIRED INSPECTION HAVE BEEN VERIFIED AND COMPLETED.
Part: SENSOR — DEFECTIVE · airframe 12,021 hrs · 7,960 cycles
LEED AIR: AT FL430 NORMAL ENGINE ONLY BLEEDS, PAX NOTIFIED US OF SMOKE/HAZE IN CABIN/ INITIATED QRC / UPON ENTERING CABIN I NOTICED A HAZE/ NO PERCEPTIBLE SMOKE/ BUT A SLIGHT ODER, DECLARED EMERGENCY/ DIVERTRED/ FOLLOWED QRC/QRH PROCEEDURES///SIGN-OFF////REMOVED AND REPLACED CABIN TEMP SENSOR P/N: 9914130-6 S/N 12BU70. IAW CE-680 AMM 21-61-00.
2020
Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 11,315 hrs
ALL AFT INTERIOR EMERGENCY LIGHTS AND ALL EXTERIOR LIGHTS ARE INOPERABLE. PRE-FLIGHT SIGN OFF. SPOKEN WITH PILOTS AS THEY WERE STILL ON THE FIELD AND HAS FOUND THAT AFTER POWER WAS APPLIED TO THE AIRCRAFT FOR AN EXTENDED AMOUNT OF TIME THE EMERGENCY LIGHTING WAS OPERATIONAL, BUT AFTER ABOUT 4 TO 5 MINUTES THE LIGHTING DIMMED AND THEN DIES. MCC ADVISED THAT THERE ARE 4 BATTERY PACKS ON ORDER AND TO REPLACE ONCE RECEIVED. TECH HAS REMOVED ALL 4 EMERGENCY BATTERY PACKS DUE TO LOW VOLTAGE FAILURE. TECH HAS INSTALLED 2 REPAIRED EMERGENCY BATTERY PACKS IN THE NR 2 AND NR 3 POSITIONS AND 2 MODIFIED EMERGENCY BATTERY PACKS IN THE NR 1 AND NR 4 POSITION. OPERATIONAL CHECK OF EMERGENCY LIGHTING SYSTEM COMPLETED. NO FURTHER DEFECTS NOTED AT THIS TIME. ALL WORK AND OPERATIONAL CHECKS COMPLETED IN REFERENCE WITH CITATION 680 MAINTENACNE MANUAL CHAPTER 33-50-00 AND 33-50-10.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 10,971 hrs · 7,224 cycles
18 SPOTS OF CORROSION FOUND ON LH AND RH FWD DROPPED AISLE. MECHANICALLY BLENDED 18 SPOTS OF CORROSION ON LH AND RH FWD DROPPED AISLE IAW CESSNA 680 SRM 51-70-02. PERFORMED AN EDDY CURRENT AND ULTRASONIC THICKNESS INSPECTION OF THE 18 BLENDED SPOTS ON THE LH AND RH FWD DROP AISLE. NO CRACK OR CORROSION INDICATIONS WERE FOUND AT THE TIME OF INSPECTION. REPAIRED LEVEL 2 CORROSION BLENDS IN CABIN DROPPED AISLE IAW AQRD ENGINEERING REPAIR ORDER NO. ERO-966017 REVISION: IR, TITLE: FUSELAGE REPAIR, DATED: 03/27/2020 AND SUPPORTED BY FAA FORM 8110-3 DATED MARCH 27, 2020.
Part: DOOR — CORRODED (EMERGENCY EXIT) · airframe 10,971 hrs · 7,224 cycles
CONFIRMED CORROSION ON EMERGENCY EXIT IN 20 AREAS, FOUND DURING TASK 52-20-00-2200. REMOVED FWD AND AFT CONTOUR RINGS. MECHANICALLY BLENDED 20 AREA OF INTERGRANULAR CORROSION INNER SIDE OF CONTOUR RINGS ON OUTER FACE OF E-EXIT IAW C680 SRM 51-70-02. CORROSION DETERMINED TO BE LEVEL 2 PER NJA GMM 2.2.2. BLENDS FOUND BEYOND C680 SRM 51-70-02 LIMITS AND REQUIRED E-EXIT TO BE REPLACED. REMOVED EXISTING CORRODED E-EXIT ASSY AND INSTALLED NEW CUSTOMER SUPPLIED E-EXIT ASSY IAW CESSNA 680 MM 52-20-00
Part: DOWNLOCK SWITCH — DEFECTIVE (LT MLG) · airframe 10,958 hrs · 7,216 cycles
LEFT MLG LANDING GEAR RETRACTION DID NOT RETRACT - L MAIN GEAR FAILED TO RETRACT. OVERSPEED TO 250 KNOTS. REMOVED LEFT MLG DOWNLOCK SWITCH PART NO: 6-0373-3 SERIAL NO: N/A AND INSTALLED CUSTOMER SUPPLIED NEW PART NO: 6-0373-3 SERIAL NO: N/A IAW CE680 M/M CH 32-30-40. ACCOMPLISHED LEFT MLG DOWNLOCK SWITCH OPERATIONAL CHECK IAW CE680 M/M CH 32-60-00. OPERATIONAL CHECKS GOOD.
2018
Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 9,798 hrs · 6,391 cycles
LEVEL 2 CORROSION FOUND ON R/H WING UPPER INBOARD TRAILING EDGE WING SKIN P/N: 6922681-70 REQUIRED REPLACEMENT
Part: DRAG ANGLE — CORRODED (WINGS) · corrosion level 2 · airframe 9,798 hrs · 6,391 cycles
RH AND LH WING @ WING STATION 37 (FWD, MIDDLE, AFT) OVERWING DRAG ANGLES HAVE NUMEROUS AREAS OF CORROSION.
Part: SPAR CAP — CORRODED (LT MLG WW) · airframe 9,798 hrs · 6,391 cycles
FOUND CORROSION IN LH MLG WHEEL WELL AFT SPAR CAP APX W.S. 27.00. FOUND WHILE CLEANING FOD FROM DRAG ANGLE CORROSION REPAIRS.
Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 9,798 hrs · 6,391 cycles
REMOVED L/H WING UPPER SKIN SECTION P/N 6922680-27 (ABOVE L/H MLG) DUE TO LEVEL 2 CORROSION.
Part: SPAR WEB — CORRODED (LT WING) · airframe 9,258 hrs · 6,019 cycles
LEFT WING SPAR WEB BULKHEAD FITTING CORRODED.
2017
Part: PUMP — LEAKING (HYD SYSTEM) · airframe 8,605 hrs · 5,598 cycles
IMMEDIATELY AFTER LOWERING THE GEAR, AN AMBER HYDRAULIC VOLUME LOW CAS ILLUMINATED. VOLUME INDICATED 110 CU IN. IAW QRH LANDED USING EMERGENCY BRAKING. AFTER SHUTDOWN VOLUME INDICATES 90-100. FOUND THE LT ENGINE DRIVEN HYDRAULIC PUMP LEAKING EXTERNALLY. CARRIED OUT REPLACEMENT IAW MM 29-10-04. LT PRESSURE & CASE DRAIN FILTERS WITH NEW IAW MM 29-10-00. INTERCHANGED THE LT & RT HYDRAULIC PUMPS FOR FURTHER EVALUATION. CARRIED OUT HYDRAULIC SYSTEM BLEEDING & SERVICING IAW MM 12-12-02. FUNCTION & LEAK CHECKED SERVICEABLE. CARRIED OUT BLEEDING OF MLG BRAKES IAW MM 32-42-10.
2016
Part: CONTROL HANDLE — DEFECTIVE (COCKPIT) · airframe 7,912 hrs · 5,146 cycles
LANDING GEAR DID NOT EXTEND WHEN GEAR LEVER WAS SELECTED. A RED UNSAFE LIGHT SHOWED. THE GEAR LEVER WAS CYCLED AND THE GEAR EXTENDED. SUP: REPLACED LANDING GEAR CONTROL. REMOVED PN: 049801-001, SN: L1946, INSTALLED PN: 049801-001, SN: 0271.
2015
Part: UNKNOWN — ODOR (COCKPIT) · airframe 7,181 hrs · 4,674 cycles
ON TAKEOFF, DURING ROTATION WITH APU RUNNING & APU BLEEDS RUNNING, A BURNING ODOR IN THE COCKPIT WAS EXPERIENCED & QUICKLY DISSIPATED WITHIN 30 - 40 SECONDS. ODOR DID NOT REOCCUR REMAINDER OF FLIGHT. GROUND RAN APU SEVERAL TIMES, NO UNUSUAL ODORS NOTED, PERFORMED ENG RUNS WHILE APU ON WITH NO ODORS NOTED.
Part: UNKNOWN — MALFUNCTIONED (LANDING GEAR) · airframe 6,619 hrs · 4,305 cycles
THE LEFT MAIN GEAR ANNUNCIATION LIGHTS DO NOT ILLUMINATE. UTILIZED THE SECONDARY GEAR BLOW DOWN SYS. GAINED ACCESS TO THE LANDING GEAR SHUTTLE VALVE & RESET. INSPECTED & FOUND THE PNEUMATIC BOTTLE RESET, SERVICED & SAFETIED. REMOVED THE MLG CIRCUIT BREAKER LOCKOUT & RESET. JACKED THE ACFT & CYCLED THE GEAR SEVERAL TIMES TO REMOVE ANY AIR FROM THE SYS. THE GEAR INDICATORS, GREEN LIGHTS, OPS CHECKED GOOD. THE ACFT WAS LOWERED. ALL WORK WAS DONE IAW MM 32-01-00.
2014
Part: SKIN — DEBONDED (FUSELAGE) · airframe 5,418 hrs · 3,491 cycles
NOSE SKIN DISBONDS AROUND ACCESS DOOR OPENINGS. REPAIRED IAW S-680-ATA53 04RD.
Part: SKIN — DAMAGED (FUSELAGE) · airframe 5,418 hrs · 3,491 cycles
BIRD STRIKE TO NOSE OF ACFT. REPAIRED IAW S-680-0191 07RD REV A.
2013
Part: CONTROL CABLE — DAMAGED (RUDDER) · airframe 4,640 hrs · 2,951 cycles
UPPER RUDDER CABLE FRAYED AT SPLITTER SECTOR ASSEMBLY JUST AFT OF WING. REMOVED FRAYED LT UPPER AFT RUDDER CABLE. INSTALLED A NEW PN S3966-4L183.9A LT UPPER AFT RUDDER CABLE. SET AFT RUDDER CABLE TENSIONS TO 200 LBS. RIGGED CABLE TENSION ON BOTH UPPER RUDDER CABLES IAW MM 27-21-00. CYCLED RUDDER SYS 25 TIMES. SYS OPS CHECKS GOOD.
2011
Part: ENGINE — ODOR (NR 2) · airframe 2,948 hrs · 1,884 cycles
DURING TAKEOFF, THROUGH 2000 FT. ENGINE EXHAUST ODOR NOTICED COCKPIT. TURNED RT ENGINE BLEED SWITCH TO OFF, CLEARED EXHAUST ODOR. REMOVED AND REPLACED NR 2 ENGINE. GROUND RAN AND LEAK CHECKED GOOD.
Part: CONTROL UNIT — DIRTY (MLG) · airframe 2,704 hrs · 1,716 cycles
AFTER TAKEOFF, LANDING GEAR HANDLE COULD NOT BE MOVED FROM THE DOWN POSITION. THIS WAS FOLLOWED BY AN AMBER "WOW MISCOMPARE" CAS MESSAGE. PERFORMED GEAR SWING. NO DEFECTS NOTED. COULD NOT DUPLICATE SQ REMOVED & INSPECTED GEAR HANDLE CONTROL UNIT. FOUND UNIT DIRTY & CLEANED. REINSTALLED UNIT. CHECKED SERVICE OF NOSE STRUT & RESERVICED. OPS & LEAK CK GOOD. INSPECTED ALL 3 SQUAT SWITCHES. NO DEFECTS NOTED. PERFORMED FINAL GEAR SWINGS. OPS CHECKED GOOD. ALL IAW MM 32-20-00.
2010
Part: STRUT — DISCHARGED (NLG) · airframe 1,710 hrs · 1,094 cycles
GEAR WOULD NOT RETRACT. WOW MISCOMPARE CAS MESSAGE FOLLOWED SHORTLY AFTER. 2 MINUTES LATER LOUD "THUNK" NOISE FROM BELLY OF ACFT. FOUND NOSE GEAR STRUT PRESSURE LOW WITH 2 O'RINGS ON SCHADER VALVE. REPLACED 1 O-RING AND SERVICED STRUT IAW MM, CH 32-20-00. ALL OPS CKS GOOD.
2007
Part: BRAKE ASSY — WEAK (MLG) · airframe 10,202 hrs · 8,288 cycles
RT (CO-PILOTS) BRAKE PEDALS ARE VERY SOFT. NOTE CREW REPORTS BOTH COPILOTS PEDALS ARE SOFT. NO SIGN OF FLUID ON FLOOR. [SUP 4-26-07] PERFORMED BRAKE BLEEDING PROCEDURE I/A/W AMM 32-42-00. OPS CHECKS GOOD IN SHOP.
2006
Part: LINK — OUT OF RIG (FCU) · airframe 9,161 hrs · 7,457 cycles
UPON LANDING THE THROTTLES WERE BROUGHT TO THE IDLE POSITION. THE LEFT ENGINE QUIT. AFTER AIRCRAFT PARKED THERE WAS A PUDDLE OF FUEL UNDER THE ENGINE AS WELL AS A TAXI TRAIL OF FUEL. FOUND FCU TO FLOW DIVIDER LINKAGE OUT OF RIG. RE-RIGGED FCU TO FLOW DIVIDER. RAN AIRCRAFT AND PERFORMED POD CHECK AND SEVERAL SLAM DECCELS. CHECKED GOOD. WORK DONE IAW CHAP 76-11-00 OF THE CE560 MM.
2005
Part: SQUAT SWITCH — OUT OF ADJUST (MLG) · airframe 9,141 hrs · 7,438 cycles
AFTER T/O GEAR HANDLE WOULD NOT UNLOCK TO RETRACT GEAR, TOOK 3 ATTEMPTS BEFORE GEAR WOULD COME UP. FOUND LT SQUAT SWITCH INDICATING GROUND, ADJUSTED SWITCH, PERFORMED SEVERAL RIGGING CHECKS, THEN SWUNG GEAR, NO DEFECTS NOTED. JACKED AIRCRAFT AND RIGGED SQUAT SWITCH. TESTED SWITCH WITH GEAR HANDLE INDICATIONS. SWUNG GEAR TO INSURE 3 GREEN. DOWNJACKED AND RAN AIRCRAFT. DISCONNECTED LT SQUAT SWITCH AND COULDN'T GET AIRCRAFT INTO AIR MODE. REJACKED AIRCRAFT ADJUSTED SQUAT SWITCH, PERFORMED SEVERAL OPS CHECKS IN AIR, NO DEFECTS NOTED. SWUNG GEAR, OPS CHECK GOOD. DOWNJACKED AIRCRAFT, PERFORMED, PRESSURIZATION CHECKS, NO DEFECTS NOTED.
Part: FCU — OUT OF ADJUST (RT ENGINE) · airframe 9,039 hrs · 7,346 cycles
DURING BRAKE BURN-IN AT 80 KNOTS. THROTTLES REDUCED TO IDLE. A MASTER LIGHT WITH LOW OIL PRESSSURE AND LIGHT AND N2 AT 24 PERCENT ON RT ENGINE ZERO FUEL FLOW. PLACED THROTTLE IN CUTOFF AND TAXIEDTO EJM. PERFORMED IDLE CUTOFF CHECK, LIGHT CHECKS GOOD, RT FAILS. ADJUSTED RT FCU TO FLOW DIVIDER CONNECTING ROD AND SET MIN N2 STOP. SAFTIED ALL AS REQUIRED. ADJUSTED FUEL FLOW INDICATOR SWITCH, RAN RT ENG - FULL FLOW INDICATION OPERATES NORMAL AT THIS TIME. PERFORMED ALL NECESSARY ENG RUNS. ENG OPERATES NORMAL AT THIS TIME IAW P & W M/M 71-00-00/71-01-03 & 560 M/M 73-30-03.
Part: PRESSURE SYSTEM — FAILED (CABIN PRESSURE) · airframe 8,772 hrs · 7,097 cycles
AIRCRAFT LOST ALL PRESSURIZATION AT 23,000 FT AS THE THROTTLES WERE PULLED BACK PAST 90 PERCENT. THE EMERGENCY CABIN ALT LIGHT AND MASTER WARNING CAME ON. EMERGENCY PRESSURE FAILED TO PRESSURIZE THE PLANE. THE MASKS DID NOT DROP. ITEM IS UNDER INVESTIGATION.
Part: ODOR — DETECTED (CABIN) · airframe 8,713 hrs · 7,048 cycles
IN FLIGHT THERE WAS A SLIGHT BURNING SMELL, THOUGHT IT WAS BLEED AIR FOR HEAT. DURING SHUTDOWN, CAPTAIN SMELLED ELECTRICAL BURNING/MELTING SMELL AND 20 MINUTES LATER F/O TURNED ON MASTER & AVIONICS, AND SMELLED SAME SMELL A LITTLE STRONGER. COULDN'T TELL WHERE THE SMELL WAS COMING FROM. ITEM IS UNDER INVESTIGATION.
Part: SEAL — LEAKING (BRAKE SYSTEM) · airframe 8,671 hrs · 7,008 cycles
BRAKES PULSATE WHEN MEDIUM PRESSURE IS APPLIED. TAXIED A/C. FOUND EXCESSIVE VIBRATION IN PEDAL AND NOSE. BLED BRAKES AND SERVICED RESERVOIR IAW CE560 M/M CH 12-12-02. FOUND SHIMMY DAMPER NEEDS SERVICE. SERVICED SHIMMY DAMPER IAW CE560 M/M CH 12-14-01. CHECKED NOSE STRUT AND FOUND EXCESSIVE AMOUNT OF FLUID ON AIR SIDE. REPACKED NOSE STRUT IAW CE560 COMPONENT M/M CHAP 32-20-01, ALL OPERATIONAL AND LEAK CHECKS GOOD.
2004
Part: SKIN — CORRODED (LT WING) · airframe 8,402 hrs · 6,778 cycles
DURING HEAVY MAINTENANCE FOUND CORROSION AT RIGHT WING TIP AND LEFT WING UPPER SKIN. ITEM IS BEING REPAIRED.
Part: RELAY — MALFUNCTIONED (ANTI SKID SYSTEM) · airframe 8,195 hrs · 6,603 cycles
POWER BRAKE LOW PRESS AND ANTI-SKID WENT INOP. ANNUNCIATORS ILLUMINATED DURING TAXI, FOLLOWED BY A LOSS OF BRAKE PRESSURE IN THE PILOT AND COPILOT BRAKE PEDALS. TROUBLESHOT SYSTEM REPLACED PUMP ELECTRICAL RELAY AND LOW PRESSURE SWITCH OPS CHECK AND LEAK CHECK SATISFACTORY. ALL WORK DONE IAW CESSNA 560 MM CHAPTER 32-42-00.
1998
Part: RELAY — MALFUNCTIONED (PNEUMATIC SYS)
ORIGINAL PROBLEM WAS ERRATIC PRESSURIZATION. TROUBLESHOT SYSTEM DOWN TO A BAD PNEUMATIC RELAY. REMOVED AND REPLACED RELAY AND ACFT FAILED FUNCTIONAL CHECK FLIGHT. ACFT HAD NO PRESSURIZATION. REMOVED AND REPLACED WITH SECOND NEW RELAY. SYSTEM OPS AND CHECKS GOOD ON GROUND AND PASSED FUNCTIONAL CHECK FLIGHT.