N317QS

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 15,744 hrs · 10,625 cycles

ON EMERGENECY LIGHTS TEST THE FOLLOWING LIGHTS ARE NOT ILLUMINATING: SEAT LIGHT OVER SEAT 8 RT SIDE WING INSPECTION LIGHT & RT FWD EMERGENCY LIGHT ABOVE WING ALL OF THE OTHER LIGHTS TEST PROPERLY DURING THE TEST & ALL OF THE LIGHTS WORK WHEN THE BATTERIES/APU ARE ON WITH PAX SAFETY SELECTED ON. SPOKE WITH MCC & THEY INFORMED US THAT THEY WANTED TO CHANGE ALL EMERGENCY BATTIRES, REMOVED 4 BATTERIES & INSTALLED REPLACEMENT BATTIERS IAW AMM 33-50-10, OPS CKD GOOD.

Part: HINGE BRACKET — CORRODED (ZONE 300) · airframe 15,538 hrs · 10,466 cycles

UPPER RUDDER HINGE BRACKET, CORROSION, THAT REQUIRED THE REPLACEMENT OF THE UPPER RUDDER HINGE BRACKET PN: 6931050-64

Part: SKIN — CORRODED (WING ROOT) · airframe 15,538 hrs · 10,466 cycles

REPAIRED CORRODED AREAS OF THE UPPER INBOARD WING SKINS LOCATED UNDER AND ADJACENT TO THE LH AND RH WING AFT DRAG ANGLES (WING-TO-FUSELAGE FAIRING STRUCTURE), BY R&R THE AFT DRAG ANGLES, BLENDING CORRODED AREAS, PERFORMING NDT AND REPORTING FOR REPAIR DISPOSITION. REPAIRED THE LH WING AREAS BY CLEANING, TREATING AND PRIMING IN ACCORDANCE WITH TEXTRON STANDARD REPAIR AND REPLACING THE RH WING INBOARD TRAILING EDGE SKIN REFERENCING CESSNA 680 SRM 51-40-03 AND 51-40-04.

Part: ANGLE — CORRODED (ZONE 100) · airframe 15,538 hrs · 10,466 cycles

RH MLG WHEEL WELL AFT SPAR LOWER CLIP INBD OF WS 37.00 IS HEAVILY CORRODED NEAR 2 HI-LOK'S. MECHANICALLY REMOVED CORROSION LOCATED IN RH MLG WHEEL WELL, AFT SPAR, LOWER CAP RWS 17 TO RWS 19 INBD OF WS 37.00 IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL SKIN THICKNESS. REPAIRED CORROSION BLENDS IAW TEXTRON ENGINEERING FIELD REPAIR FR-680-0160-14848 REV- DATED MARCH 6, 2025 TITLED FIELD REPAIR-CORROSION, RH WING, REAR SPAR, LOWER CAP, RWS 17 TO RWS 19. REPAIR IS SUPPORTED WITH FAA FORM 8100-9 DATED MARCH 6, 2025.

Part: SKIN — CORRODED (ZONE 100) · airframe 15,538 hrs · 10,466 cycles

BLENDED 3 AREAS OF CORROSION ON THE LOWER FUSELAGE SKIN AROUND LH FWD FUSELAGE CHIN FAIRING, R&R LH FORWARD CHIN FAIRING FOR ACCESS, PERFORMED NDT AND REPORTED FOR DISPOSITION. REPAIRED BY INSTALLING ONE REPAIR DOUBLER AS REQUIRED AND CLEANING, TREATING AND PRIMING AREAS FOUND ACCEPTABLE PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: STRUCTURE — CORRODED (ZONE 800) · airframe 15,538 hrs · 10,466 cycles

MECHANICALLY REMOVED 11 AREAS OF CORROSION FROM E-EXIT DOOR STRUCTURE NEAR CONTOUR RING, PERFORMED NDT AND REPORTED FOR DISPOSITION. REPAIRED CORROSION BLENDS BY TREATING PRIMING AND PAINTING AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SUPPORT BEAM — CORRODED (ZONE 600) · airframe 15,538 hrs · 10,466 cycles

MECHANICALLY REMOVED AREA OF CORROSION ROUND CARRY THRU HYDRAULIC FITTING LOCATED IN RH MLG WHEEL WELL FORWARD END OF WS 37.00 BEAM SUPPORT ON INBOARD SIDE, PERFORMED NDT AND REPORTED FOR DISPOSITION. REPAIRED BY LEANING, TREATING, AND PRIMING BLENDED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: HANDLE — LACK OF LUBE (ZONE 800) · airframe 15,521 hrs · 10,453 cycles

MAIN DOOR LOCK: WHEN CLOSING THE MAIN CABIN DOOR THE PUSH BUTTON IN THE HANDLE WOULD NOT POP OUT WHEN THE HANDLE WAS IN THE CLOSED POSITION AND THE DOOR WOULD NOT LOCK. THE HANDLE MOVED FREELY FROM THE CLOSED TO OPEN POSITION AND THE CABIN DOOR OPEN CAUTION WOULD NOT EXTINGUISH. SEE PHOTO AND VIDEO. CORRECTIVE ACTION: CLEANED AND LUBRICATED MAIN CABIN DOOR HANDLE. OPS CHECKED GOOD. NO FURTHER DEFECTS REF CE-680 SPM 20-00-00.

Part: SPRING — DAMAGED (ZONE 800) · airframe 15,390 hrs · 10,365 cycles

MAIN DOOR: WHEN LOCKING PLANE UP FOR THE NIGHT WHEN WE LIFTED THE UNLOCK BAR TO CLOSE THE AIRSTAIRS WE HEARD A LOUD BANG AND THE DOOR WOULD NOT MOVE. WE REALIZED THE RIGHT CABLE IS JUST HANGING WITH NO TENSION. THE AIRSTAIR HAVE TO BE FORCED UP AND WILL JUST FREE FALL OPEN. REMOVED MAIN CABIN DOOR STEPS, FOUND AFT COUNTER BALANCE SPRING BROKEN. REMOVED AFT LUBRICATED SPRING FOR BROKEN INSTALLED NEW UNIT AND RIGGED IAW CESSNA 680 MM 52-10-50

Part: SKIN — CORRODED (TE FLAPS) · airframe 14,746 hrs · 9,883 cycles

BLENDED CORRODED AREAS UNDER THE NUTPLATES COMMON TO THE LH & RH WING FLAP PANELS 523AB AND 623AB, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS BY FABRICATING AND INSTALLING REPAIR DOUBLERS IN ACCORDANCE WITH NETJETS RFTS-110102.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,689 hrs · 9,844 cycles

EMERGENCY EXIT SIGN ON THE AFT RIGHT FACING UPPER DIVIDER MIRROR IS OUT. ALL EMERGENCY LIGHTS TESTED OKAY DURING PREFLIGHT INSPECTION AND FAILED IN FLIGHT. IAW 20-30-25 REV 1 AND MM 25-20-10 REV 20 CABIN DIVIDERS MAINT PRACTICES REMOVED LT LAV BULKHEAD AND REPAIRED EMERGENCY EXIT LIGHT WIRES AND INSTALLED BULKHEAD OPS CHECK GOOD

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,397 hrs · 9,632 cycles

SHADE IN THE EMERGENCY EXIT DOOR/HATCH IS FAILED IN THE CLOSED POSITION. REMOVED EMERGENCY DOOR AND GAINED ACCESS TO THE WINDOW SHADE. TROUBLESHOT THE WINDOW SHADE TO THE SHADE ASSY. POSITIONED SHADE IN THE FAILED UP POSITION. PLACED PARTS ON ORDER. DUE TO PARTS MCC PLACED FAILED UP SHADE ON MEL. SEE TASK T2PL6DOOAP2QS.REF AMM 25-20-25

Part: SPAR — CORRODED (ZONE 600) · airframe 13,176 hrs · 9,618 cycles

R/H MLG WHEEL WELL FUEL AND HYDRAULIC LINE THRU PLATE HAS SURFACE CORROSION. ACCOMPLISHED TEXTRON AVIATION ENGINEERING REPAIR S-680-ATA57/03RD REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS DATED AUGUST 23, 2018 AND FAA FORM 8100-9 DATED 3/18/2019.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,281 hrs · 9,555 cycles

UPON TESTING THE EMER LIGHTS ON POWER UP, THE MAIN EXIT LIGHT OVER THE MAIN CABIN DOOR DID NOT ILLUMINATE. VERIFIED DISCREPANCY, ATTEMPTED TO CHARGE #1 BATTERY PACK WITH NO SUCCESS. ACCESSED #1 BATTERY PACK, INSPECTED THE FUSE ON THE #1 BATTERY PACK AND FOUND IT OPEN, REMOVED FUSE PN S2565-5, INSTALLED NEW CUSTOMER SUPPLIED FUSE PN S2565-5, OPERATIONAL CHECK IS GOOD, OPERATED LIGHTS FOR 10 MINUTES THEN CYCLED ON AND OFF SEVERAL TIMES WITH NO DEFECTS NOTED IAW AMM 33-50-10.

Part: SPAR — CORRODED (ZONE 600) · airframe 13,962 hrs · 9,358 cycles

FOUND DURING BASE CHECK RIGHT MAIN WHEEL WELL AFT SPAR HAS LEVEL 2 CORROSION IN 2 LOCATIONS WILL REQUIRE CLEAN AND BLEND

Part: SPRING — DAMAGED (PAX DOOR) · airframe 13,151 hrs · 8,790 cycles

MAIN DOOR CABLE: UPON RAISING CABIN DOOR THE FORWARD CABLE RELEASED AND THE DOOR WENT DOWN HARD. CABLE IS STILL ATTACHED AT BOTH ENDS BUT LOOSE. THE REAR CABLE IS WORKING. DOOR WILL NOT CLOSE DROM INSIDE.//CORRECTIVE ACTION// R/R MAIN CABIN DOOR FWD COUNTER BALANCE SPRING P/N 6911319-202 WITH A CUSTOMER SUPPLIED NEW PART. COMPLIED WITH COUNTERBALANCE SYSTEM RIGGING AND PERFORMED SATISFACTORY OPERATIONAL CHECK OF MAIN CABIN DOOR IAW CE-68 AMM 52-10-50

Part: SPAR CAP — CORRODED (LT WING) · airframe 11,492 hrs · 7,673 cycles

REMOVED FOUR HI-LOK FASTENERS FOR ACCESS AND BLENDED CORRODED AREA ON THE UPPER SURFACE OF THE LOWER WING SPAR CAP LOCATED IN THE LEFT HAND MAIN LANDING GEAR WHEEL WELL AREA, PERFORMED NDT REPORTED FOR REPAIR DISPOSITION. PERFORMED BOLT HOLE NDT, POLISHED, CLEANED, TREATED AND PRIMED BLENDED AREAS AND INSTALLED FOUR NEW HI-LOK FASTENERS WET WITH SEALANT IAW TEXTRON FIELD REPAIR. ICA INSPECTION OF REPAIRED AREA NEEDS TO BE COMPLETED ON A RECURRING 6,000 HR INTERVAL, COINCIDENCE WITH THE RECURRENT INSPECTIONS FOR THE REAR SPAR LOWER SPLICE MODEL 680 NDTM, PART 6, CHAPTER 57-10-01. BHET: REMOVE FASTENERS AND BOLT HOLE EDDY CURRENT INSPECT ALL LAYERS PER THE MODEL 680 NDTM, PART 6, CHAPTER 20-00-01

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,729 hrs · 7,148 cycles

REPAIRED NUMEROUS AREAS ON LOWER FUSELAGE SKIN, DOUBLERS, AND STRINGERS OF THE DROP AISLE AREA BETWEEN FS 157 AND FS 426 BY BLENDING OUT CORROSION, PERFORMING NDT AND INSTALLING DOUBLERS AND FILLERS AS REQUIRED PER RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER.

Part: DOUBLER — GOUGED (FUSELAGE) · airframe 10,729 hrs · 7,148 cycles

REPAIRED TWO GOUGED AREAS OF THE INTERIOR FUSELAGE DOUBLER NEAR THE ESCAPE HATCH AT FS 399.75 AND FS 403 BY BLENDING/SMOOTHING THE GOUGED AREAS PERFORMING NDT, TREATING, AND PRIMING IN ACCORDANCE WITH FIELD REPAIR.

Part: SKIN — CORRODED (LT WING) · airframe 10,367 hrs · 6,936 cycles

THE LT WING SKIN WAS CORRODED. BLENDED CORRODED AREAS ON THE UPPER WING SKIN.

Part: SKIN — CORRODED (EMERGENCY EXIT) · airframe 7,326 hrs · 6,936 cycles

FOUND EMERGENCY EXIT DOOR CORRODED AROUND THE CONTOUR RINGS AND DOOR SKIN. REPLACED THE CONTOUR RINGS WITH NEW PARTS AND REPAIRED THE DOOR SKIN BY BLENDING AND TREATING PER REPAIR.

Part: SPAR — CORRODED (LT WING) · airframe 9,655 hrs · 6,431 cycles

DURING GENERAL VISUAL INSPECTION OF THE LEFT MAIN WHEEL WELL INSPECTION, FOUND CORROSION ON THE AFT LOWER WING SPAR ASSEMBLY.

Part: SWITCH — FAILED (NLG WOW) · airframe 6,279 hrs · 4,142 cycles

AFTER TAKEOFF, GEAR WOULD NOT RETRACT. WOW MISCOMPARE CAS MESSAGE CAME ON FOR THE REST OF THE FLIGHT. FOUND NOSE GEAR WOW SWITCH LOOSE, ADJUSTED & TIGHTENED SWITCH. COMPLETED GEAR SWING, OPS CHECKED GOOD IAW AMM 32-60-00.

Part: VALVE — MALFUNCTIONED (MLG) · airframe 6,188 hrs · 4,082 cycles

AFTER TAKEOFF, THE GEAR HANDLE WOULD NOT COME UP. THE PIN NEVER RELEASED & THE GEAR LIGHTS REMAINED GREEN. AMBER WOW INCOMPARABLE CAS MESSAGE CAME ON & REMAINED UNTIL LANDING, LANDING WAS NORMAL. POWERED ACFT & FOUND NO FAULTS ON EICAS. RANG OUT ALL SQUAT SWITCHES, ALL GOOD. JACKED NOSE GEAR & NOTICED LOWER OLEO WAS NOT FULLY EXTENDING, CAUSING SQUAT SWITCH STRIKE PLATE TO NOT CONTACT SQUAT SWITCH. CHECKED SERVICING OF UPPER OLEO IN LIMITS, 280 PSI, LWR OLEO WAS EMPTY. FOUND NITROGEN SERVICING VLV LEAKING. R & R SERVICING VLV & SERVICED LWR OLEO WITH NITROGEN TO -10 PSI. LOWERED & JACKED NOSE GEAR SEVERAL TIMES, NOSE GEAR EXTENDS SMOOTHLY EACH TIME MAKING CONTACT WITH NOSE SQUAT SWITCH IAW WDM 32-60-01 & WDM 32-20-00.

Part: SQUAT SWITCH — DAMAGED (NLG) · airframe 6,188 hrs · 4,081 cycles

AFTER TAKEOFF, THE GEAR HANDLE WOULD NOT MOVE TO THE RETRACT POSITION. ABOUT TWO MINUTES LATER, RECEIVED AN AMBER WOW INCOMPARABLE CAS MESSAGE. BEFORE LANDING THE CAS MESSAGE CLEARED. DID NOT TRY TO RETRACT GEAR AT THAT TIME. GEAR REMAINED DOWN WITH THREE GREEN LIGHTS AT ALL TIMES. TROUBLESHOT, GEAR HANDLE WOULD NOT TRANSITION WITH WEIGHT OFF WHEELS. FOUND MISALIGNED NOSE SQUAT SWITCH CAM NOT MAKING CONTACT. ADJUSTED CAM & OPS CHECKED GOOD IAW MM 32-00-00.

Part: DISPLAY — MALFUNCTIONED (COCKPIT) · airframe 3,660 hrs · 2,390 cycles

CO-PILOTS PFD WOULD NOT DISPLAY ANY FLIGHT INFORMATION. IT WOULD ONLY DISPLAY RED X. YOU COULD GET THE FLIGHT INFORMATION IF YOU REVERTED THE DISPLAY TO DU 3. CYCLED DU4 C/B DISPLAY NEVER RECOVERED STAYED BLANK REPLACED DU 4, LOADED OPS S/W IAW MM, 34-23-10. OPS CHECKED DU4 GOOD IAW MM 34-23-10.

Part: BRAKE ASSY — WEAK (MLG) · airframe 2,830 hrs · 1,838 cycles

LEFT OUTER WHEEL BRAKE INDICATOR AT LIMITS. LT BRAKE MUSHY. REMOVED NR 1 BRAKE ASSY, INSTALLED O/H BRAKE ASSY. BLED BRAKES. REINSTALLED WHEEL ASSY AND TORQUED. ALL WORK PERFORMED IAW MM 32-42-10, 32-41-20. SERVICED HYD RESERVOIR IAW MM 12-12-02.

Part: COFFEEMAKER — ODOR (GALLEY) · airframe 2,573 hrs · 1,659 cycles

15 MIN INTO FLIGHT CREW NOTICED BURNING ODOR COMING FROM COFFEE & WATER POTS. TURNED POWER OFF TO POTS & ODOR CEASED. OPERATED BOTH TANKS FOR 30 MINUTES WITH NO ODOR NOTED. REMOVED REFRESHMENT CENTER PANELS & INSPECTED WIRING & CONNECTIONS BEHIND BAR, NO DEFECTS NOTED. POWER & GROUND AT BOTH TANK CONNECTORS CHECKS GOOD. REINSTALLED PANELS. REMOVED LOWER TANK. INSTALLED CUSTOMER SUPPLIED REPAIRED TANK. OPS CHECK GOOD. REMOVED UPPER TANK AND INSTALLED NEW TANK. CLEANED, RINSED AND FILLED TANK. OPERATED TANK HEATER FOR 15 MINS, OPS CHECK GOOD. LEAK CHECK GOOD. SPIGOT ASSY TRANSFERRED FROM REMOVED TANK AND INSTALLED ON NEW TANK WITH NEW SPIGOT GASKET WORKED REF EQUIPMENT OPERATIONS MANUAL.

Part: COUPLING — UNSECURE (COALESER) · airframe 2,378 hrs · 1,520 cycles

ON CLIMBOUT, "CABIN ALT" LIGHT ILLUMINATED. ACFT WAS 25,000 FT.; PAX O2 MASKS WERE DEPLOYED. CABIN ALT MAINTAINED 9,500' UNTIL DESCENT BELOW 10K'. DURING THE INSP OF THE PRESSURIZATION SYS DUCTING WE FOUND THE EXIT COUPLING ON THE COALESER SOCK CAN HAD BECOME DETACHED. RESECURED ACM WATER SEPERATOR EXIT DUCTING AND COUPLING IAW MM 21-21-00. PERFORMED: AUTO EMERGANCY PRESS SYS FUNCTIONAL CHECK, PRESS SYS GROUND TEST, AUTO CABIN DESCENT TEST, AUTO CABIN ASCENT TEST, LANDING MODE TEST, CABIN DUMP TEST AND MANUAL MODE TEST IAW MM 21-30-00. OPS CHECK GOOD AT THIS TIME.

Part: BRAKE — INTERMITTENT (MLG) · airframe 9,495 hrs · 7,535 cycles

PON - LANDING RIGHT BRAKE PEDAL FOR RIGHT SIDE PILOT WAS SOFT (APPROX 3"- 4" TRAVEL) MUCH FIRMER ON SECOND APPLICATION. SAME SEQUENCE EXPERIENCED DURING TAXI. LEFT SIDE BRAKES OPERATE NORMALLY.

Part: WIRE — BROKEN (MLG INDICATOR) · airframe 9,198 hrs · 7,205 cycles

UPON GEAR EXTENSION, RIGHT MAIN GEAR INDICATOR LIGHT WOULD NOT ILLUMINATE. EMERGENCY GEAR EXTENSION CHECKLIST WAS ACCOMPLISHED; GEAR EXTENDED MANUALLY. EMERGENCY DECLARED. TROUBLESHOT RT GEAR INDICATION FOUND A BROKEN WIRE J64 & S82 OFF OF PIN A REPAIRED WIRE IAW CESSNA 560 WIRING MANUAL CHAPTER 20-00-00 INDICATOR OPS CHECK SATISFACTORY PERFORMED GEAR RETRACTION BLED SYSTEM IAW CESSNA 560 MAINTENANCE MANUAL CHAPTER 32-30-00. SERVICED EMERGENCY GEAR BOTTLE IAW CESSNA 560 MAINTENANCE MANUAL 12-13-01. GEAR SYSTEM CHECKS SATISFACTORY.

Part: RUDDER SKIN — CRACKED (LT BELOW TAB)

A LT RUDDER SKIN CRACK HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB.