N357QS

Part: BATTERY PACK — FAULTY (ZONE 200) · airframe 15,173 hrs · 10,093 cycles

PREFLIGHT - PORTION/ALL OF CABIN EMERGENCY LIGHTING IS INOP. HERE ARE ALL THE CONDITIONS: APU OFF -EMER LTS SWITCH IN ON (MAIN BATTERIES OFF) - ALL EMER LIGHTS FUNCTION EXCEPT THE 3 EXIT SIGNS AROUND MED AND GALLEY READ LIGHT (BULB IS GOOD) -EMER LTS SWITCH IN ARM (MAIN BATTERIES ON, PASS SAFETY ON) - NO LIGHTS AT ALL APU ON -EMER LTS SWITCH IN ON - ALL EMER LIGHTS ARE ON EXCEPT THE 3 EXIT SIGNS AROUND MED AND GALLEY READ LIGHT (BULB IS GOOD) -EMER LTS SWITCH IN ARM (PASS SAFETY ON) - NO LIGHTS AT ALL. REMOVED EMERGENCY LIGHT BATTERY #1 DUE TO LIGHT NOT HOLDING CHARGE AND INSTALLED A REPAIRED EMERGENCY LIGHT BATTERY. ALLOWED BATTERY TO CHARGE FOR 2 HOURS. PERFORMED OPS CHECKS. OPS CHECKS SATISFACTORY. DISCREPANCY NO LONGER STANDS. WORK PERFORMED IRW AMM 33-50-10.

Part: SKIN — DAMAGED · airframe 15,072 hrs · 10,012 cycles

REPAIRED CORROSION UNDER THE BAGGAGE FLOOR BOARDS ON THE TAILCONE SKIN AND STRINGERS BETWEEN FS 501.25 AND FS 548.50 PER AQRD ERO-985795 REV.A, TITLED "N357QS TAILCONE SKIN CORROSION" DATED AUG 28, 2025. SUPPORTED BY FAA FORM 8110-3 DATED 08/28/2025. 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 15,071.9 FLIGHT HOURS AND 10,012 FLIGHT CYCLES. (ALTERNATE TERMINATING ACTIONS TO THE F&DT EVALUATION REQUIREMENT MUST BE SEPARATELY APPROVED AND ARE NOT INCLUDED IN THIS ERO.)

Part: SKIN — CORRODED (ZONE 100) · airframe 15,072 hrs · 10,012 cycles

MECHANICALLY BLENDED 7 AREAS OF CORROSION LOCATED BELOW AFT BAGGAGE FLOOR BETWEEN FS534.70 AND FS548.50 IAW SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING 0.002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS ENGINEERING RFTS-114465 REV. 0, TAIL CONE SKINS UNDER BAGGAGE FLOOR.

Part: STRUCTURE — CORRODED (ZONE 100) · airframe 15,072 hrs · 10,012 cycles

MECHANICALLY BLENDED 7 AREAS OF CORROSION LOCATED BELOW AFT BAGGAGE FLOOR BETWEEN FS501.25 AND FS519.37 IAW SRM 51-70-02. FOUND 5 AREAS OF CORROSION BLENDING TO BE WITHIN LIMITS IAW SRM 51-70-02. PROTECTED BARE METAL IAW C680 SRM 51-20-01. THIS IS A PSE AREA IAW SRM 51-00-01. PER NJA GMM 2.1.2 THIS IS LEVEL 1 CORROSION. FOUND 2 AREAS OF CORROSION BLEND TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING 0.002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS.

Part: SKIN — CORRODED (ZONE 100) · airframe 15,072 hrs · 10,012 cycles

MECHANICALLY BLENDED 17 AREAS OF CORROSION LOCATED BELOW AFT BAGGAGE FLOOR BETWEEN FS468.05 AND FS484.65 IAW SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND LIMITS IAW SRM 51-70-02 EXCEEDING 0.002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW ENGINEERING RFTS-114465 REV. 0, TAIL CONE SKINS UNDER BAGGAGE FLOOR DATED 20AUG25.

Part: SKIN — CORRODED (ZONE 100) · airframe 15,072 hrs · 10,012 cycles

MECHANICALLY BLENDED 12 AREAS OF CORROSION LOCATED BELOW AFT BAGGAGE FLOOR BETWEEN FS519.37 AND FS534.70 IAW SRM 51-70-02. FOUND 10 AREAS OF CORROSION BLENDING TO BE WITHIN LIMITS IAW SRM 51-70-02. PROTECTED BARE METAL IAW C680 SRM 51-20-01. THIS IS A PSE AREA IAW SRM 51-00-01. PER NJA GMM 2.1.2 THIS IS LEVEL 1 CORROSION. FOUND 2 AREAS OF CORROSION BLENDING TO BE BEYOND LIMITS IAW CESSNA 680 SRM 51-70-02. EXCEEDING 0.002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS ENGINEERING RFTS-114465 REV. 0, TAIL CONE SKINS UNDER BAGGAGE FLOOR. PAGE 6, AREAS #6 AND #7 ON FIGURE 1 DATED 20AUG25.

Part: SKIN — CORRODED (ZONE 800) · airframe 15,072 hrs · 10,012 cycles

1 AREA OF CORROSION FOUND ON E-EXIT OUTER SKIN, UPPER /AFT CORNER. MECHANICALLY REMOVED 1 AREA OF CORROSION LOCATED ON E-EXIT, EXTERIOR SKIN, UPPER AFT CORNER AREA IAW C680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND SRM LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS ENGINEERING RFTS-114422 REV 0. TITLE: N357QS (680-0155) EMERGENCY EXIT DOOR CORROSION,

Part: ACM — FAULTED (ZONE 100) · airframe 14,883 hrs · 9,877 cycles

CONCURRENT WITH FULL HOT ENVIROMENTAL AIR DISCREPANCY, A STRONG BURNING ODOR WAS NOTED BY BOTH CREWMEMBERS PERMEATING BOTH THE CABIN AND COCKPIT COMPARTMENTS. AGREED ON ODOR DESCRIPTION AS RESEMBLING THAT OF A "BURNT PLASTIC SMELL." STRENGTH DIMINISHED NOTICEABLY WHEN BLEED AIR WAS SELECTED TO OFF. RECEIVED HISTORY FROM MCC NOTING 1 PREVIOUS WRITEUP ON 1/10/25 AND THE WATER SEPARATOR CLEANING WAS ACCOMPLISHED. ARRIVED AT AIRCRAFT AND STARTED APU PER AFM NOTING AFTER APU START AND BLEED AIR SELECTED, A BURNING SMELL WAS NOTED WITH ASSOCIATED HOT AIR EMANATING FROM THE COCKPLT DUCTS. PERFORMED TEMP CHECK OF OUTLET DUCT ON ACM NOTING TEMPERATURES REACHING 300° F AND RISING, A STRONG BURNING SMELL NOTED IN THE AFT EQUIPMENT BAY. SHUTDOWN APU AND POWERED DOWN AIRCRAFT AS REQUIRED. GAINED ACCESS TO ACM AND PERFORMED ACM TORQUE CHECK REF SIL GP-10 NOTING TORQUE CHECK FAILS AND ACM FOUND SEIZED. RESEARCHED REQUIRED PARTS, CONTACTED MCC AND PLACED REQUIRE PARTS ON ORDER. / REMOVED FAULTY ACM AND INSTALLED REPAIRED ACM USING NEW BOLTS, HOSE, SLEEVE, SLEEVE IAW CMM AND IAW. AMM 21-51-00. / INSTALLED ACM COMPRESSOR OUTLET DUCT ASSEMBLY USING NEW COUPLING, PACKING IAW CMM. POWERED THE AIRCRAFT WITH APU IAW AFM, ENGAGED APU BLEED AIR AND ALSO ENGAGED MAX COOL FOR ACM LEAK CHECK PERFORMED LEAK CHECK OF THE ACM AND SURROUNDING AREA WITH NO DEFECTS NOTED. PERFORMED LEAK CHECK OF THE TAILCONE PLUMBING REF MM 21-30-00 WITH NO DEFECTS NOTED. SHUT DOWN AIRCRAFT IAW AFM WITH NO DEFECTS NOTED AT THIS TIME.

Part: FITTING — CORRODED (HYD LINE) · airframe 14,678 hrs · 9,738 cycles

REMOVED CORROSION LOCATED AROUND SPOILER PRESSURE HYDRAULIC LINE FITTING AND SPOILER RETURN HYDRAULIC LINE CARRY THRU FITTINGS ON LH AND RH WING AFT SPARS, AFT FACE, JUST INBD OF JACK POINT, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDS IAW NETJETS REQUEST FOR TECHNICAL SERVICES BY CLEANING, TREATING, AND PRIMING BLENDED AREAS.

Part: SPAR — DAMAGED (ZONE 500) · airframe 14,678 hrs · 9,738 cycles

R&R FASTENERS AS REQUIRED, BLENDED 9 AREAS OF CORROSION ON LH WING AFT SPAR, LOWER CLIP, FWD SIDE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED AND PRIMED BLENDED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (FUSELAGE) · airframe 14,278 hrs · 9,424 cycles

BLENDED CORRODED AREAS OF THE FUSELAGE SKIN JUST AFT OF THE MAIN ENTRY DOOR, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, PRIMED AND TOPCOATED AREA PER TEXTRON FILED REPAIR.

Part: SKIN — DAMAGED (BS 518) · airframe 14,278 hrs · 9,424 cycles

REPAIRED BENDED AREA OF FUSELAGE LH UPPER SKIN AT APPROXIMATELY FS 518.5 AND BL 0.0, TWO AREAS OF FUSELAGE RH UPPER SKIN AT APPROXIMATELY FS 464 AND BL 0.0, AND ONE AREA FS 517 AND BL 0.0 BY BLENDING, PERFORMING NDT, TREATING AND PRIMING AREAS FOUND ACCEPTABLE. REPAIRED BLEND AT THE ADF ANTENNA LOCATION BY TRIMMING SKIN, INSTALLING REPAIR DOUBLER, FILLER, AND SHIM IN ACCORDANCE WITH TEXTRON AVIATION FIELD REPAIR

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 14,278 hrs · 9,424 cycles

REPAIRED CORRODED AREAS OF THE UPPER SKIN OF THE RH HORIZONTAL STABILIZER AT THE INBOARD AFT EDGE JUST FORWARD OF ACCESS PANEL 352AC AND AREA AT THE TRAILING EDGE OUTBOARD ELEVATOR AREA BY BLENDING, PERFORMING NDT, TREATING AND PRIMING IAW NETJETS REQUEST FOR TECHNICAL SERVICES RFTS-108566.

Part: SKIN — CORRODED (RT WING) · airframe 14,278 hrs · 9,424 cycles

REPAIRED THE RH WING UPPER INBOARD SKIN BY BLENDING CORRODED AREAS LOCATED UNDER AND ADJACENT TO THE DRAG ANGLES (WING-TO-FUSELAGE FAIRING AREA), PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH & DEVELOPMENT ENGINEERING REPAIR ORDER

Part: ANGLE — CORRODED (VERTICAL STAB) · airframe 14,278 hrs · 9,424 cycles

MECHANICALLY REMOVED 4 AREAS OF CORROSION ON LH SIDE OF RUDDER COVE ON VERTICAL STAB SPAR CLIP AND 1 AREA OF CORROSION EXTENDING UNDERNEATH CROSS BRACKET SUPPORT LH SIDE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPLACED BLENDED FASTENERS AS REQUIRED, CLEANED, TREATED, AND PRIMED REPAIRED AREAS IN ACCORDANCE WITH TEXTRON FIELD REPAIR

Part: SKIN — DAMAGED (TAIL CONE) · airframe 14,278 hrs · 9,424 cycles

REPAIRED THE TAILCONE SKINS LOCATED UNDER AND ADJACENT TO THE AFT CHIN FAIRING BY BLENDING CORRODED AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLER, FILLER, AND SHIM IN ACCORDANCE WITH TEXTRON FIELD REPAIR

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 14,278 hrs · 9,424 cycles

REPAIRED LH VERTICAL STABILIZER SKIN AT THE OPENINGS OF ACCESS PANELS 341AL, 341BL, 341CL, AND 341DL BY BLENDING CORRODED AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATED AND INSTALLING REPAIR DOUBLERS IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH & DEVELOPMENT ENGINEERING REPAIR ORDER.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 14,278 hrs · 9,424 cycles

REPAIRED THE LH SKIN OF VERTICAL STABILIZER AT THE UPPER AFT CORNER BY BLENDING CORRODED AREA, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT ENGINEERING REPAIR ORDER

Part: SKIN — DAMAGED (LT WING) · airframe 14,278 hrs · 9,424 cycles

BLENDED CORRODED AREA ON THE UPPER SURFACE OF THE UPPER INBOARD SKIN ON THE LH WING, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION, TREATED, PRIMED AND TOPCOATED BLENDED AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: FITTING — CORRODED · airframe 14,677 hrs · 9,738 cycles

REPAIRED CORROSION AROUND LH AND RH EMERGENCY BRAKE RIB FEED THRU FITTINGS AT WS 37 BY FABRICATING AND INSTALLING REPAIR DOUBLERS PER AEROSPACE QUALITY RESEARCH AND DEVELOPMENT ENGINEERING REPAIR ORDER

Part: BATTERY — DISCHARGED (CABIN) · airframe 14,064 hrs · 9,279 cycles

ON POSTFLIGHT, NOTICED EXTERIOR EMERGENCY LIGHT ILLUMINATING THE AIRSTAIR DOES NOT ILLUMINATE ON EMERGENCY BATTERY POWER. IT WILL ILLUMINATE ON BATTERY/GENERATOR POWER, EITHER WITH THE ENTRY LIGHT SWITCH OR THE PAX SAFETY SWITCH. *** CORRECTIVE ACTION *** REMOVED FAULTY #2 AND #3 EMERGENCY BATTERY AND REPLACED WITH REPAIR AND NEW UNIT RESPECTIVELY. OPS CHECKS GOOD REF 680 AMM 33-50-10 AND NJA TC-FLT-33-1001 REV 2.

Part: SPAR — CORRODED (ZONE 700) · airframe 14,038 hrs · 9,266 cycles

CORROSION - EXFOLIATION FOUND IN LOWER SPAR OF LH AND RH MLG WHEEL WELLS

Part: G SWITCH — ACTIVATED (EMERGENCY LIGHTS) · airframe 13,974 hrs · 9,228 cycles

DURING MX CHECK FOUND EMER LIGHTS STAY ON WITH SWITCH IN ARM POSITION

Part: WARNING LIGHT — INOPERATIVE (THRUST REVERSERS) · airframe 13,888 hrs · 9,173 cycles

UPON APPLYING TAKEOFF POWER FOR DEPARTURE, AROUND 50KTS IAS THE RIGHT THEN LEFT THRUST REVERSER EMERGENCY STOW SWITCH LIGHTS STARTED FLASHING. THEY WORKED FINE ON PREVIOUS LEGS AND WERE NOT TESTED BETWEEN LEGS IAW NORMAL PROCEDURE. FOLLOWED MEL PROCEDURE AND REACTIVATED BOTH LH AND RH T/R'S. GAINED ACCESS INTO AIRCRAFT AND STARTED BOTH ENGINES. PERFORMED THE OPERATIONAL CHECK FOR BOTH LH AND RH T/R'S. PERFORMED A SATISFACTORY OPERATIONAL CHECK. ALL WORK DONE IAW AMM 78-30-00. NO DEFECTS NOTED.

Part: I/O CARD — FAULTED (LT ENGINE) · airframe 13,322 hrs · 8,791 cycles

ENGINE CONTROL FAULT L AMBER CAS: AT FL 380 GOT ENGINE CONTROL FAULT L. SUBSEQUENTLY FOLLOWING INDICATIONS WERE AMBER DASHES, N1L, OIL TEMPL, STAB TRIM, ,DC AMP, BATT AMP , HYD PRESS AFTER LOWERING GEAR RECEIVED ANTISKID FAIL CAS. RECEIVED REPAIRED CUSTOM 1/0 CARD. REMOVED AND REPLACED CUSTOM 1/0 CARD PER CE680 AMM 34-17-00. LOADED SOFTWARE AND PERFORMED OPERATIONAL CHECKS, OPS CHECKS GOOD

Part: NONE — BROKEN (ZONE 700) · airframe 13,155 hrs · 8,687 cycles

NLG LANDING GEAR EXTENSION: HAD AN UNSAFE NOSE GEAR INDICATION, RED UNLOCK LIGHT AND NO DOWN GREEN NOSE GEAR LIGHT. HAD 2 GREEN MAIN GEAR DOWN INDICATIONS. COMPLETED THE GEAR UNSAFE EMERGENCY PROCEDURE. THE NOSE GEAR WAS DOWN, LANDED UNEVENTFULLY.//SIGNOFF// PER CREW: AFTER PARKING AIRCRAFT ON FBO RAMP, THE DISAGREE WENT AWAY AND THEY GOT 3 GREEN AFTER MANIPULATING THE NLG WIRE HARNESS NEAR THE SCISSORS. REMOVED NLG WIRE BUNDLE ASSEMBLY AND TEMP INSTALLED REPLACEMENT WIRE BUNDLE ASSEMBLY REF CE680 AMM 32-00-00.2. MXI ADMIN, 01-JAN-2022 12:38 ESTSTARTED ROUTING/FIT AND INSTALL OF NLG WIRE HARNESS - CONTINUING TO INSTALL PLUG BY PLUG AND CLAMP BY CLAMP. WILL CONTINUE INSTALL INSTALLED THE WBA - NOSE LANDING GEAR WIRING HARNESS IN THE NOSE GEAR WELL AREA AS REQUIRED. MX IAW CE-680 MM 12-30-45. OFF/ON PN: 6948001-4 SN:NA COMPLIED WITH TASK 32-00-00-7200 (CHAP 4 • LANDING GEAR EXTENSION AND RETRACTION SYSTEM FUNCTIONAL AND OPERATIONAL CHECK) IAW NJA MODEL 680 AAIP. COMPLIED WITH CE-680 AMM TASK 32-30-20-7100 (CHAP 4 • LANDING GEAR CONTROL VALVE, AND LANDING GEAR RETURN CHECK VALVE TEE FUNCTIONAL CHECK). COMPLIED WITH TASK 32-42-00-7100 (CHAP 4 • ANTI-SKID CONTROLLER OPERATIONAL CHECK) IAW NJA MODEL 680 AAJP.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 13,003 hrs · 8,596 cycles

COCKPIT ODOR: AN ODOR OF EXHAUST FUMES AFTER TAKEOFF UP TO 12,000 FEET WITH APU OFF. WHILE IN FLIGHT IF THE THROTTLES ARE ADVANCED CLOSE TO MCT WILL RECEIVE ODOR OF EXHAUST FUMES FOR APPROXIMATELY 20 TO 30 SECONDS THEN DISSIPATES. // SIGNOFF // AS REQUESTED REPOSITIONED AC TO THE ALPHA RUNUP AREA TO COMPLY WITH HIGH ENGINE POWER RUNS AT VARIOUS SETTINGS NO ABNORMALITIES NOTED CONTACTED TROY@ CESSNA INFORMED HIM WITH FINDINGS HE AGREED WITH THE CORRECTIVE ACTION TAKEN NO FURTHER MX ACTION REQUIRED IAW PW306D EMM71-00-00.

Part: BATTERY — DEFECTIVE · airframe 12,917 hrs · 8,526 cycles

CABIN EMERG LIGHT: PHOTO TAKEN WITH EMERGENCY LIGHT SELECTED OFF PRIMARY DOOR EXIT LIGHT AS YOU CAN SEE IS ILUMINATED AND WIRES HANGING DOWN ABOVE DOOR. PRELIMINARY TESTING OF THE LIGHTS DID NOT TEST PROPERLY AND WE ARE UNABLE TO EXTINGUISH EMERGENCY LIGHT OVER THE DOOR///SIGN-OFF///REMOVED AND REPLACED #1 EMERGENCY BATTERY PACK P/N CBS28-1, S/N005874.PER CE-680 AMM CHAPTER 3-50-10.

Part: BATTERY — DEFECTIVE (ZONE 100) · airframe 12,917 hrs · 8,526 cycles

MAIN EXIT SIGN/LIGHT: EXIT LIGHT OVER MAIN CABIN DOOR AND BOTH EXIT SIGNS ON EITHER SIDE OF DOOR WILL NOT ILLUMINATE. ALSO EXIT SIGNS IN AFT CABIN AND ISLE LIGHTING EXTINGUISHES WHEN PAX SAFETY SWITCH IS ON. // SIGN OFF // ACCESSED AIRCRAFT, REMOVED CARPET FORWARD OF #2 PASSENGER SEAT IN CABIN. REMOVED #1 EMERGENCY BATTERY ACCESS PANEL, REMOVED ELECTRICAL CONNECTOR FROM BATTERY. REMOVED SCREWS SECURING BATTERY. REMOVED BATTERY FROM AIRCRAFT, INSTALLED CUSTOMER SUPPLIED REPAIRED EMERGENCY BATTERY INTO POSITION, INSTALLED SCREWS SECURING BATTERY, INSTALLED ELECTRICAL CONNECTORS, AIJPLIED POWER TO AIRCRAFT. PERFORMED OPS CHECK OF #1 EMERGENCY BATTERY. ALL OPS CHECK GOOD. RE INSTALLED #1 EMERGENCY BATTERY ACCESS PANEL. REINSTALLED CARPET FORWARD OF #2 PASSENGER SEAT.RETURNED AIRCRAFT TO ORIGINAL CON FIG, WORK PERFORMED IN REF, TO CE680 AMM 33-50-10,

Part: COALESCER BAG — ODOR · airframe 12,366 hrs · 8,127 cycles

COCKPIT ODOR: STRONG OILY SMELL IMMEDIATELY AFTER TAKEOFF. NOTICED ON FIRST TAKEOFF OF THE DAY BUT AFTER SECOND TAKEOFF ODOR SMELLED WORSE. INSTALLED NEW CUSTOMER SUPPLIED COALSCER BAG P/N 98237-12. IAW CE-680 AMM 12-19-00. INSTALLED WATER SEPARATOR IAW CE-680 AMM 21-21-03. OPS AND LEAK CHECK GOOD.

Part: SPAR — CORRODED (RT WING) · airframe 12,342 hrs · 8,110 cycles

ONE AREA OF VERIFIED CORROSION IN THE RH WHEEL WELL, WING LOWER SPAR. MECHANICALLY BLENDED ONE AREA OF CORROSION ON RH WHEEL WELL, WING LOWER SPAR IAW CESSNA 680 SRM 51-70-02. FOUND CORROSION DEPTHS EXCEEDING C680 SRM 51-70-02 LIMITATIONS OF .002". REPAIRED CORROSION BLENDS IAW TEXTRON ENGINEERING MEMO REF: DQ29106M1 RRL SUBJECT: 680-0155 N357QS RRL RH WING AFT SPAR LOWER CORROSION DATED: MARCH 1,2021. THIS IS A MINOR REPAIR.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 12,342 hrs · 8,110 cycles

ONE AREA OF VERIFIED CORROSION ON VERTICAL STAB LH SKIN, NEAR TIP CAP. MECHANICALLY BLENDED ONE AREA OF CORROSION ON VERTICAL STAB LH SKIN, NEAR TIP CAP IAW CESSNA 680 SRM 51-70-02. PERFORMED NDT ON BLENDED AREA TO VERIFY CORROSION REMOVAL AND REMAINING MATERIAL THICKNESS. FOUND BLENDED AREA TO OUT OF LIMITS PER CESSNA 680 51-70-02. SUBMITTED FINDINGS TO TEXTRON AVIATION. REPAIRED BLENDED AREA PER TEXTRON ENGINEERING MEMO DQ29108M1 RRL "680-0155 N357QS RRL VERTICAL STABILIZER LH SKIN CORROSION" DATED MARCH 1, 2021. CORROSION CLASSIFIED AS LEVEL 2 PER NETJETS GMM 2.2.2. THIS IS CONSIDERED A MINOR REPAIR.

Part: BATTERY — DEFECTIVE (MASTER) · airframe 12,258 hrs · 8,056 cycles

AFTER TAKE-OFF WE GOT CAS MESSAGE BATTERY OTEMP L. ACCOMPLISHED EMERGENCY/ABNORMAL PROCEDURES CHECKLIST. LANDING GEAR WOULD NOT EXTEND. ACCOMPLISHED EMERGENCY/ABNORMAL CHECKLIST. PULLED LANDING GEAR BLOWDOWN HANDLE. REMOVED AND REPLACED LT MAIN BATTERY WITH AN OVERHAULED UNIT. OPERATIONS CHECK IS GOOD. BATTERY OTEMP L CAS MESSAGE WAS NOT ACTIVE BEFORE OR AFTER THE BATTERY REPLACEMENT. BATTERY OFF L (R) CAS MESSAGE WILL DISPLAY ON CAS WITH BOTH ENGINES RUNNING AND BATTERY SWITCH OFF. WORK DONE IAW CESSNA 680 AMM, REV 29, CH 24-31-00. OVERHAUL PERFORMED BY BOEING DISTRIBUTION INC., CRS RD42488M, WO 2000385919.

Part: NUT PLATE — CORRODED (VERTICAL STAB) · airframe 12,165 hrs · 7,993 cycles

FOUND CORROSION AROUND THE NUTPLATES FOR SEVERAL VERTICAL STABILIZER ACCESS PANELS. BLENDED CORRODED AREAS, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS, PER TEXTRON REPAIR MEMO.

Part: SPAR — DAMAGED (RT WING) · airframe 12,165 hrs · 7,993 cycles

MECHANICALLY BLENDED ONE CORRODED AREA ON RT WING AFT SPAR, LOCATED IN RT MLG WHEEL WELL AT WS 30. PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED REPAIR AREA, PER TEXTRON FIELD REPAIR.

Part: BRACKET — CORRODED (TAILCONE) · airframe 12,165 hrs · 7,993 cycles

FOUND TAILCONE AFT BRACE LT SIDE AND AFT BRACE LOWER MOUNTING BRACKET CORRODED. REPLACED WITH NEW CESSNA PARTS P/N 6912162-12, P/N 6912162-3, AND P/N 6912162-9.

Part: SKIN — CORRODED (TAILCONE) · airframe 12,165 hrs · 7,993 cycles

FOUND SEVERAL AREAS OF CORROSION ON THE INTERIOR SURFACE OF THE LT TAILCONE BETWEEN FS 642 AND FS 672 AT STRINGER 13. BLENDED CORRODED AREAS, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. CLEANED TREATED AND PRIMED REPAIR AREAS, PER TEXTRON REPAIR MEMO.

Part: SKIN — CORRODED (EMERGENCY EXIT) · airframe 12,165 hrs · 7,993 cycles

FOUND THREE AREAS OF CORROSION ON THE EMERGENCY EXIT DOOR OUTER SKIN. REMOVED THE FWD AND AFT CONTOUR RINGS FROM THE DOOR ASSEMBLY FOR ACCESS AND FOUND AN ADDITIONAL 24 AREAS OF CORROSION. REPLACED CORRODED EMERGENCY EXIT DOOR WITH A REPAIR DOOR, CESSNA P/N 6911251-4.

Part: SKIN — DEBONDED (RT WING) · airframe 12,165 hrs · 7,993 cycles

VERTICAL STAB AFT SPAR LT UPPER ANGLE HAS 2 AREAS OF VERIFIED INTERGRANULAR CORROSION. MECHANICALLY BLENDED 2 AREAS ON VERTICAL STAB AFT SPAR LT UPPER ANGLE, IAW CESSNA 680 SRM 51-70-02. EVALUATED AREA AND FOUND TO BE OUT OF SRM LIMITS. PERFORMED TEXTRON FIELD REPAIR-CORROSION, VERTICAL STABILIZER, LT REAR SPAR CAP, VFS 190 AND 220 FR-680-0220-8415 REV- DATED: 09/30/2020, APPROVED ON FAA FORM 8100-9 DATED 09/30/2020.

Part: DOUBLER — GOUGED (ZONE 200) · airframe 11,397 hrs · 7,471 cycles

REPAIR OF SCREW GOUGES, AFT CABIN, ESCAPE HATCH INTERIOR SURROUND, FS 405-FS 423. FIELD REPAIR FR-680-0155-6893 DATED 29 JUL 2019 WITH FAA FORM 8100-9 DATED 30 JUL 2019.

Part: SKIN — DAMAGED (LT WING) · airframe 11,397 hrs · 7,471 cycles

REPAIR OF LT AND RT WING LEADING EDGE ROOT SKIN/LIGHT COVER ATTACH HOLE DAMAGE (PULLED TROUGH). ENGINEERING LETTER DQ22386M1 DATED JULY 23, 2019. LEADING EDGE ROOT SKINS P/N 6922590-1 / 6922590-2 AND LIGHT COVERS P/N 6922530-45 / 6922530-46.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,337 hrs · 6,712 cycles

CORROSION FOUND ON THE FUSELAGE SKIN AROUND THE RT NOSE AVIONICS DOOR AFT LATCH. BLENDED THE CORROSION ON THE FUSELAGE SKIN. INSTALLED A REPAIR DOUBLER IAW ERO-922424, REV IR.

Part: SKIN — CORRODED (E/E BAY DOOR) · airframe 10,337 hrs · 6,712 cycles

DURING A VISUAL INSPECTION, FOUND CORROSION AROUND RIGHT FORWARD EQUIPMENT BAY AFT LATCH. CORROSION WAS FOUND TO BE DEEPER THAN THE MAINTENANCE MANUAL ALLOWED. REPAIRED IAW ERO-922424, REV IR.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,212 hrs · 6,631 cycles

CORROSION ON THE SKIN. ACCOMPLISHED ENGINEERING LETTER DQ11022M1.

Part: SKIN — CORRODED (RUDDER) · airframe 10,212 hrs · 6,631 cycles

CORROSION ON THE RUDDER TE SKIN. ACCOMPLISHED LETTER DQ11021M1.

Part: FAIRING — DEBONDED (LETT WING) · airframe 10,212 hrs · 6,631 cycles

PLY SEPARATION DAMAGE TO THE LEFT WING UPPER DRAG ANGLE FAIRING. ACCOMPLISHED MANUFACTURER LETTER DQ11166M1 REV A.

Part: SKIN — CORRODED (BS 321) · airframe 10,212 hrs · 6,631 cycles

CORROSION ON THE USELAGE UPPER SKIN, BS 321, RBL 4.

Part: SKIN — CORRODED (LT WING UPPER) · airframe 10,212 hrs · 6,631 cycles

UPPER WING SKIN CORRODED.

Part: SKIN — CORRODED (RT WING) · airframe 10,212 hrs · 6,631 cycles

RIGHT WING UPPER TRAILING EDGE CORRODED.

Part: SKIN — CORRODED (LT WING) · airframe 10,212 hrs · 6,631 cycles

LEFT WING LOWER SKIN CORRODED.

Part: SKIN — DAMAGED (NOSE) · airframe 10,212 hrs · 6,631 cycles

RIGHT NOSE SKIN DAMAGED.

Part: SKIN — CORRODED (UPPER FUSELAGE) · airframe 10,212 hrs · 6,631 cycles

CORROSION ON THE AFT FUSELAGE SKIN.

Part: COUPLING — TORN (DUCT) · airframe 10,033 hrs · 6,524 cycles

EXPERIENCED A LOSS OF CABIN PRESSURIZATION AT FL400. SELECTING BLEED AIR TO HP MODE, USING ALTITUDE SELECT AND MANUAL CONTROLLER SELECTION DID NOT CHANGE THE 300-400 FPM CABIN RATE OF CLIMB. THERE WERE NO UNUSUAL SOUNDS AND THE ANTI-ICE WAS OFF. OPERATOR REPORTS LOSS OF CABIN PRESSURE IN FLIGHT. COMPLIED WITH SB680-21-08. ALL PRESSURIZATION AND OPERATIONAL CHECKS NORMAL. PARTS INSTALLED DUCT COUPLINGS S3295-8-15

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 9,086 hrs · 5,893 cycles

RIGHT HORIZONTAL STABILIZER CORRODED.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 9,086 hrs · 5,893 cycles

HORIZONTAL STABILIZER CORRODED.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 9,086 hrs · 5,893 cycles

HORIZONTAL STABILIZER LT LOWER SKIN CORRODED.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 7,287 hrs · 4,902 cycles

HORIZONTAL STABILIZER LEFT LOWER SKIN CORRODED. REPAIRED.

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 8,898 hrs · 5,751 cycles

REPAIR OF CORROSION ON THE VERTICAL FIN AFT SPAR. REPAIRED IAW RDR S-680-0155/03RD.

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 8,470 hrs · 5,473 cycles

CORROSION FOUND ON VERTICAL STABILIZER AFT SPAR RT ANGLE, APPROXIMATELY RS 170, MARKED. REMOVED 2 AREAS OF CORROSION ON VERTICAL STABILIZER AFT SPAR RT ANGLE FOR NDT INSPECTION, REF MM 51-10-01. ACCOMPLISHED ULTRASONIC INSPECTION OF THE RT VERTICAL STABILIZER AFT SPAR FLANGE AT VFS 170 AND VFS 174 IN THE AREA OF DAMAGE AFTER BLENDING. IAW NDI PART-4-20-00-01. ACCOMPLISHED EDDY CURRENT INSPECTION OF THE RT VERTICAL STABILIZER AFT SPAR FLANGE AT VFS 170 AND VFS 174 IN THE AREA OF DAMAGE AFTER BLENDING FOR CRACKS IAW NDI PN-6-20-00-02. NO CRACKS NOTED AT TIME OF INSPECTION. REMAINING THICKNESS DOCUMENTED FOR REPAIR INFORMATION. ACCOMPLISHED ERO-821756.

Part: TRIM SYSTEM — OUT OF RIG · airframe 8,064 hrs · 5,233 cycles

CLIMB OUT, IN A HIGH POWER SETTING, ACFT RAN OUT OF NOSE DOWN TRIM & COULD ONLY BE TRIMMED IN THE PITCH AXIS BY REDUCING POWER & LOWERING FLAPS TO GET NOSE DOWN. FOUND PRIMARY STAB ACTUATOR BREAK AWAY TORQUE TO BE EXCESSIVE IAW MM 27-40-00. BREAK AWAY TORQUE CHECK PROCEDURE IAW MM 27-40-00. INSTALLED PRIMARY TRIM ACTUATOR, OPS & RIG CHECKED GOOD IAW MM 27-40-00. FOUND ELEVATOR TRIM TABS OUT OF RIG WITH EXCESSIVE TE DOWN IAW MM 27-40-00. RIGGED ELEVATOR TRIM TABS IAW MM 27-40-00. FOUND MACH TRIM ACTUATOR INSTALLED INCORRECTLY. POSITIONED TRIM LINK ASSEMBLY TO CORRECT POSITION. CHECKED RIG OF STABILIZER TAB SYS. COMPLETED IAW MM 27-40-00. RIG & OPS CHECKED GOOD.

Part: STEERING UNIT — INOPERATIVE (NLG) · airframe 5,388 hrs · 3,459 cycles

AFTER TAKEOFF, RT MAIN GEAR AND NOSEWHEEL DID NOT RETRACT. CONFIRMED BY ATC. LT MAIN GEAR LIGHT WENT OUT, BUT BOTH THE OTHER GREEN LIGHTS REMAINED ILLUINATED IN ADDITION TO THE RED UNLOCK LIGHT. LT MAIN EXTENDED NORMALLY. JACKED ACFT FOUND NOSE STEERING UNIT BYPASSING (NOT CENTERING) STARTED REPLACEMENT OF STEERING UNIT, BOTTLES NEED INSTALLED. TEAM 680 SUGGESTED RINGING OUT UPLOCKS AND CHECKED GEAR HANDLE FOR ANY DAMAGED PARTS. RANG OUT NOSE, LT & RT UPLOCK SWITCHES IAW WD 32-30-01 NO DEFECTS NTOED. COMPLETED NOSE STEERING UNIT INSTALLATION IAW MM 32-50-00. BLED STEERING UNIT & PERFORMED FUNCTIONAL TEST IAW MM 32-50-00. OPS TRAVEL, LEAK CHECK GOOD. (48740) TAXI CHK GOOD. AFTER REPLACING THE NOSE GEAR STEERING UNIT, SUCCESSFUL GEAR FUNCTIONAL CHECKS WERE COMPLETED MM 32-00-00 ALL 3 GEAR WENT UP AND LOCKED AND THE INDICATOR LIGHTS FUNCTIONED NORMALLY.

Part: LANDING GEAR — MULTIPLE FAIL (RIGHT) · airframe 3,930 hrs · 2,511 cycles

RT MAIN GEAR WOULD NOT RETRACT. RT MAIN GEAR GREEN DOWN LIGHT REMAINED ILLUMINATED. RESEATED LANDING GEAR PCB'S JF207, AND JF205 IAW MM 24-60-10. CHECKED RT WOW SWITCH. OPS CHECKED GOOD. INSPECTED GEAR HANDLE ASSY AND CONNECTIONS. OPS CHECKED GOOD. PERFORMED L/G OPS CHECKED IAW MM 32-00-00. OPS CHECKED GOOD. PERFORMED 25 GEAR SWINGS. OPS CHECKED GOOD.

Part: CONNECTOR — DAMAGED (FUEL PANELS)

WHILE PERFORMING THE 2B INTERNAL WING INSP, FOUND THAT THE LT & RT ELECTRICAL CONNECTOR BLANKING PINS WERE FALLING OUT, BECOMING FOD IN THE CTR FUEL TANK. CONNECTORS ARE LOCATED IN THE FUEL BAYS OF PANEL 175AB AND 176AB, ON THE FWD WALL.

Part: STRUT — UNDERSERVICED (MLG) · airframe 2,240 hrs · 1,412 cycles

GEAR HANDLE WAS MOVED TO "UP" POSITION, NOSE GEAR RETRACTED WHILE BOTH MAIN GEAR LIGHTS STAYED ILLUMINATED WITH GEAR "UNLOCK" LIGHT ON. MAIN GEAR CYCLED SEVERAL TIMES IN A 20-25 SECOND TIME PERIOD. FINALLY MAIN GEAR RETRACTED, AND UNLOCK LIGHT EXTINGUISHED. FOUND ALL LANDING GEAR STRUTS REQUIRING SERVICE. SERVICED NOSE GEAR UPPER AND LOWER CHAMBER AS REQUIRES, NO LEAKS NOTED. SERVICED BOTH MAINS AS REQUIRED. COMPLIED WITH GEAR SWING, OPS CHECKS GOOD.

Part: CONTROL HANDLE — FAULTY (MLG) · airframe 2,220 hrs · 1,401 cycles

AFTER TAKEOFF, RETRACTED MLG AND BOTH MLG RETRACTED NORMALLY. RED "UNLOCK" COCKPIT ANNUCIATOR REMAINED ILLUMINATED FOR ABOUT 10 -12 SECONDS. NLG RETRACTED NORMALLY AFTER 5 OR 6 CYCLES OF BANGING / VIBRATIONS IN NOSE WHEEL WELL AREA. MLG LATER EXTENDED NORMALLY WITH 3 GEAR INDICATIONS. JACKED ACFT & CYCLED MLG WOULD NOT RETRACT UNITL CONTROL HANDLE WIGGLED BACK & FORTH. ALSO NOTED NLG DID NOT LOCK UP FOR A LONG TIME. FOUND NLG UPLOCK SWITCH OUT OF ADJUSTMENT. ADJUSTED NLG UPLOCK SWITCH IAW MM 32-60-00. R & R MLG CONTROL UNIT IAW MM CH 32-40-10. PERFORMED GEAR SWINGS & OPS CHECK OF MLG CONTROL UNIT. ALL TESTS PASS. LANDING GEAR EXTENSION & RETRACTION OPS CHECKS NORMAL.

Part: CONTROL HANDLE — FAULTY (MLG) · airframe 2,220 hrs · 1,401 cycles

AFTER TAKEOFF, RETRACTED MLG AND BOTH MLG RETRACTED NORMALLY. RED "UNLOCK" COCKPIT ANNUCIATOR REMAINED ILLUMINATED FOR ABOUT 10 -12 SECONDS. NLG RETRACTED NORMALLY AFTER 5 OR 6 CYCLES OF BANGING / VIBRATIONS IN NOSE WHEEL WELL AREA. MLG LATER EXTENDED NORMALLY WITH 3 GEAR INDICATIONS. JACKED ACFT & CYCLED MLG WOULD NOT RETRACT UNITL CONTROL HANDLE WIGGLED BACK & FORTH. ALSO NOTED NLG DID NOT LOCK UP FOR A LONG TIME. FOUND NLG UPLOCK SWITCH OUT OF ADJUSTMENT. ADJUSTED NLG UPLOCK SWITCH IAW MM 32-60-00. R & R MLG CONTROL UNIT IAW MM CH 32-40-10. PERFORMED GEAR SWINGS & OPS CHECK OF MLG CONTROL UNIT. ALL TESTS PASS. LANDING GEAR EXTENSION & RETRACTION OPS CHECKS NORMAL.

Part: LANDING GEAR — MALFUNCTIONED · airframe 1,158 hrs · 739 cycles

AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT.

Part: SQUAT SWITCH — OUT OF RIG (MLG) · airframe 1,158 hrs · 739 cycles

AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT. GEAR HANDLE WAS RAISED, ONE SECOND OF ODD "CLUNKING" WAS HEARD NEAR THE NOSE GEAR THEN UNUSUAL NOISE STOPPED. ALL 3 GEAR SHOWED DOWN AND LOCKED AND RED "UNLOCKED" ILLUMINATED. ABOUT 30 SECONDS LATER "WOW MISCOMPARE" CAS MESSAGE CAME ON. GEAR HANDLE WAS LOWERED AND COULD NOT BE RAISED AGAIN. "WOW MISCOMPARE" WENT AWAY ON LANDING. FOUND NLG SQUAT SWITCH OUT OF RIG. PROPERLY RIGGED NOSE GEAR SQUAT SWITCH IAW MM 32-60-00. CYCLED GEAR SEVERAL TIMES. OPS CHECK GOOD.

Part: RELEASE MECH — MISINSTALLED (PAX DOOR) · airframe 1,009 hrs · 632 cycles

CABIN DOOR JAMMED CLOSED AND FAILS TO OPEN. INSPECTED DOOR AND FOUND PRECATCH RELEASE ASSY INSTALLED INCORRECTLY. INSTALLED PRECATCH RELEASE TO CORRECT CONFIGURATION AND OPERATED DOOR SEVERAL TIMES AND WITH PWR ON. OPS CHECK GOOD IAW MM 52-10-00.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 670 hrs · 419 cycles

AFTER RAISING THE GEAR ON DEPARTURE FROM CLE, THE 3 GREEN GEAR LIGHTS EXTINGUISHED BUT THE UNLOCK LIGHT REMAINED ON. JACKED ACFT. INSPECTED LANDING GEAR AND RETRACT/EXTEND COMPONENTS. SWANG GEAR MULTIPLE TIMES. COULD NOT DUPLICATE DESCREPANCY. ALL OPS CHECKS GOOD. IAW MM 32-00-00.

Part: LATCH — OUT OF ADJUST (LT MLG DOOR) · airframe 366 hrs · 240 cycles

AFTER T/O AND AFTER GEAR RETRACTION, AMBER NOSE DOOR L CAS MESSAGE APPEARED. ADJUSTED L DOOR LATCHES IAW MM CHAP 52-40-20. OPERATIONAL CHECKS GOOD.

Part: STARTER GEN — FAILED (NR 2) · airframe 65 hrs · 44 cycles

ABORTED NR 2 ENGINE START WHEN LINE MAN SIGNALED CUT AFTER SMOKE WAS SEEN EMANATING FROM THE BOTTOM OF THE ENGINE NACELLE, ITT STAYED WITHIN LIMITS. REMOVED AND REPLACED RT ENG STARTER GEN. OPS CHECK GOOD IAW CESSNA 680 M/M 24-30-00.

Part: STRINGER — CORRODED (BS1148-BS1166)

STRINGER EXFOLIATED BETWEEN BS 1148 TO BS 1166 BETWEEN STRINGER 3L AND 4L IN THE AFT CABIN CROWN AREA. ACCOMPLISHED FUSELAGE STRINGER REPAIR BS 1148 TO 1166 BETWEEN STRINGER 3L AND 4L. DUE TO CORROSION IAW SRM. (MATERIAL USED 301 CRESS .5000 HARD .050 INCH, 14 INCH X 1 INCH X 2 INCH.)

Part: FITTING — CRACKED (CARGO DOOR)

FOUND CRACK AROUND C2 DOOR FORWARD UPPER HINGE ATTACH POINT AT BS 1070 STRINGER 20R AND 19R. ACCOMPLISHED C2 DOOR FORWARD FRAME REPAIR AT BS 1070 STRINGER 20R AND 19R IAW B727 SRM 53-10-2, FIGURE 5. (M)

Part: STRINGER — DAMAGED (FUSELAGE)

HOLE FOUND IN LOWER RADIUS AT BS 370 STRINGER 6R. ACCOMPLISHED FUSELAGE STRINGER REPAIR AT BS 370, STRINGER 6R IAW B727 SRM 53-10-2, FIGURE 2. (M)

Part: SKIN — DAMAGED (BS1085-BS1110)

BULGING AND PILLOWING SKIN AT BS 1085 THRU BS 1110 ALONG FASTENER ROWS AT STRINGER 17R THRU 19R ON EXTERNAL FUSELAGE. ACCOMPLISHED FUSELAGE SKIN REPAIR FROM BS 1085 TO BS 1110 BETWEEN STRINGER 17R AND 19R DUE TO CORROSION IAW MFG ENGINEERING RO. (MATERIAL USED 2024-T3 .090 INCHES, 86 INCHES X 38 INCHES.

Part: SKIN — CORRODED (BS1176-BS1183)

BULGING SKIN/DISHED FASTENER AT BS 1176 THRU BS 1183, STRINGER 20L THRU 21L UNDER AFT LAV SERVICE VALVE. ACCOMPLISHED FUSELAGE SKIN REPAIR FROM BS 1176 TO BS 1183 STRINGER 20L TO STRINGER 21L DUE TO CORROSION. (MATERIAL USED 2024-T3. 071, 28 INCHES X 30 INCHES.)

Part: PRESSURE PANEL — CORRODED (NLG WW)

NOSE WHEEL WELL SKIN CRACKED LEFT SIDE AT STATION 243.7. ACCOMPLISHED NOSE WHEEL WELL RIGHT SIDE SKIN REPAIR AT BS 243.7 IAW B727 SRM 51-40-2, FIGURE 1. (M)

Part: FRAME — CORRODED (MLGWW)

RIGHT NOSE WHEEL WELL, MID CHORD EXFOLIATED AT INTERSECTION OF RIGHT WEB AND FLOOR WEB AS VIEWED FROM DOG HOUSE. ACCOMPLISHED RIGHT NOSE WHEEL WELL MID CHORD REPLACEMENT IAW B727 SRM 51-30-2 AND 51-20-4. (M)

Part: FRAME — CORRODED (FUSELAGE)

RIGHT NOSE WHEEL WELL, MID CHORD EXFOLIATED AT INTERSECTION OF RIGHT WEB AND FLOOR WEB AS VIEWED FROM DOG HOUSE. ACCOMPLISHED RIGHT NOSE WHEEL WELL MID CHORD REPLACEMENT IAW B727 SRM 51-30-2 AND 51-20-4. (M)

Part: SKIN — DAMAGED (STRINGER)

BULGING/PILLOWING SKIN ALONG STRINGER 4L AT LAP JOINT BS 1130 THRU BS 1183. ACCOMPLISHED FUSELAGE SKIN REPAIR FROM BS 1130 TO BS 1183 STRINGER 4L DUE TO CORROSION IAW SRM. (MATERIAL USED 2024-T3 .050 INCH, 98 INCHES X 9.1250 INCHES)

Part: SKIN — CORRODED (FUSELAGE)

BULGING SKIN ALONG STRINGER 10L AT BS 920 THROUGH 1005 DUE TO CORROSION. ACCOMPLISHED FUSELAGE SKIN REPAIR FROM BS 920 TO BS 1005 AT STRIGNER 10L IAW B727 SRM 53-30-3 FIG 14. (M)

Part: PRESSURE PANEL — CORRODED (NLG WW)

DUE TO CORROSION, RIGHT NOSE WHEEL WELL VERTICAL WEB EXFOLIATED AT INTERSECTION WITH UPPER NOSE CHORD AS VIEWED FROM DOG HOUSE BS 315. ACCOMPLISHED RIGHT NOSE WHEEL WELL VERTICAL WEB REPAIR IAW B727 SRM 53-10-2 FIGURE 1. (M)

Part: PRESSURE PANEL — CRACKED (NLG WW)

NOSE WHEEL WELL RIGHT SIDE SKIN HAS A VERTICAL CRACK AT STATION 270. ACCOMPLISHED NOSE WHEEL WELL RIGHT SIDE SKIN REPAIR AT BS 270 IAW B727 SRM 51-40-2, FIGURE 1 AND 53-10-2, FIGURE 2. (M)

Part: STRUCTURE — CORRODED (NLG WW)

LEFT NOSE WHEEL WELL VERTICAL WEB EXFOLIATED AT INTERSECTION WITH UPPER NOSE CHORD AS VIEWED FROM DOG HOUSE AT BS 315 DUE TO CORROSION. ACCOMPLISHED NOSE WHEEL WELL LEFT VERTICAL WEB REPAIR DUE TO CORROSION IAW B727 SRM 53-10-2, FIGURE 1. (M)

Part: SUPPORT — DAMAGED (CARGO DOOR)

AT MAIN CARGO DOOR FORWARD ACTUATOR, FORWARD AND AFT SUPPORT BLOCK ON DOOR STATION 540, 5 BOLTS HAVE OBLONGED/ELONGATED HOLES AND 1 LOOSE BOLT. ACCOMPLISHED MAIN CARGO DOOR FORWARD ACTUATOR SUPPORT BLOCK ATTACH INTERCOSTALS (2 EACH: FORWARD AND AFT) REPLACEMENT DUE TO ELONGATED HOLES.

Part: SKIN — CORRODED (FUSELAGE)

BULGING AND PILLOWING SKIN ON STRINGER 8L AT BS 1166 THROUGH BS 1183. ACCOMPLISHED FUSELAGE SKIN REPAIR FROM BS 1166 TO BS 1183 STRINGER 8L DUE TO CORROSION IAW B727 SRM 53-30-3, FIGURE 3. (M)

Part: FLAP — OUT OF ADJ (RT WING)

MODERATE VIBRATION DURING CLIMB-OUT, ABOVE 260 KNOTS. VIBRATION STOPPED WHEN APPLYING SPEED BRAKES. FUEL DUMPED. RETURNED TO AIRPORT WITH NO INCIDENT. ADJUSTED UPPER ECCENTRICS ON INBOARD RIGHT FLAP. OPERATIONAL CHECK GOOD. (M)

Part: BULB — DAMAGED (SMOKE DETECTOR)

FLT 736 - IAD - NR 1 SMOKE DETECTOR WILL NOT TEST. REMVOED AND REPLACED NR 1 SMOKE DETECTOR BULB. SYSTEM OPERATES NORMAL. (M)

Part: FIRE DETECTOR — MALFUNCTIONED (CARGO BAY)

FLT 640 - GRR - LOWER CARGO COMPARTMENT FIRE DETECTOR HAS YELLOW MAINTENANCE LIGHT AND NO GREEN SYSTEM LIGHT. REMOVED AND REPLACED LOWER AFT CARGO FORWARD DETECTOR. SYSTEM STILL SHOWS MAIN CONTROL FAULT LIGHT. REMAINS ON DEFERRAL. (M)

Part: VALVE — BROKEN (NR 3 PRECOOLER)

FLT 649 - AIR RETURN TO OMA, ON CLIMB-OUT AT 1000 FEET AGL FLAPS 2 DEGREES WERE SELECTED AND A SPLIT FLAP CONDITION OCCURRED. SMOKE BEGAN TO FILL THE COCKPIT, AND EMERGENCY WAS DECLARED AND AN IMMEDIATE RETURN INITIATED. INSPECTED NR 1 AND NR 3 PRECOOLER REGULATOR AIR FLOW VALVES, FOUND NR 3 VALVE BROKEN. REPLACED NR 3 PRECOOLER MODULATING VALVE. (M)

Part: BULB — BURNED (SMOKE DETECTOR)

FLT 701 - IND- NR 1 SMOKE DETECTOR WON'T SELF TEST. RELAMPED TEST BULBS. (M)

Part: DOOR — UNSECURED (E/E BAY)

UNABLE TO PRESSURIZE AIRCRAFT. AIRCRAFT MADE AN ATB INTO DAYTON. RESEATED E/E COMPARTMENT DOOR.