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
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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
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.
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.
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.
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.
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,
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,
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.
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.
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,
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,
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.
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.
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
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,
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,
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,
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,
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,
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,
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,
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,
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.
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.
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.
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.
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.
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,
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.
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.
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.
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.
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
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.
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.
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
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.
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.
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.
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.
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.
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
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.
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.
REMOVED L/H WING UPPER SKIN SECTION P/N 6922680-27 (ABOVE L/H MLG) DUE TO LEVEL 2 CORROSION.
FOUND CORROSION IN LH MLG WHEEL WELL AFT SPAR CAP APX W.S. 27.00. FOUND WHILE CLEANING FOD FROM DRAG ANGLE CORROSION REPAIRS.
LEVEL 2 CORROSION FOUND ON R/H WING UPPER INBOARD TRAILING EDGE WING SKIN P/N: 6922681-70 REQUIRED REPLACEMENT
RH AND LH WING @ WING STATION 37 (FWD, MIDDLE, AFT) OVERWING DRAG ANGLES HAVE NUMEROUS AREAS OF CORROSION.
LEFT WING SPAR WEB BULKHEAD FITTING CORRODED.
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.
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.
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.
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.
BIRD STRIKE TO NOSE OF ACFT. REPAIRED IAW S-680-0191 07RD REV A.
NOSE SKIN DISBONDS AROUND ACCESS DOOR OPENINGS. REPAIRED IAW S-680-ATA53 04RD.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
DURING HEAVY MAINTENANCE FOUND CORROSION AT RIGHT WING TIP AND LEFT WING UPPER SKIN. ITEM IS BEING REPAIRED.
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.
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.