N359QS

Part: DOOR SEAL — WORN (ZONE 800) · airframe 15,406 hrs · 10,221 cycles

DOOR SEAL HAS AN AUDIBLE FREQUENCY THAT PRESENTS ON CLIMB STARTING AT FL200 THROUGH FL320 WITH PRESSURE DIFFERENTIALS OF 7.5-9.2 RESPECTIVELY. AIRSPEED IN CLIMB WAS 240 KIAS AND .68M. ABOVE FL320 WITH HIGHER TAS AND P DIF, THE NOISE STOPS. GAINED ACCESS TO AND REMOVED DAMAGED TOP ACOUSTIC SEAL P/N 9919042-1 S/N 0278 AND INSTALLED NEW SEAL P/N 9919042-1 S/N 0169 / IAW CE680 MM 52-10-10. CLOSED ALL ACCESS AS REQUIRED.

Part: HINGE — CORRODED (ZONE 300) · airframe 15,384 hrs · 10,205 cycles

FOUND UPPER HINGE UPPER HALF AND CENTER HINGE LOWER HALF ON THE RUDDER CORRODED BEYOND REPAIR. REPLACED PARTS WITH NEW TEXTRON P/N 6931050-46 AND 6931050-52.

Part: HINGE BRACKET — CORRODED (ZONE 300) · airframe 15,384 hrs · 10,205 cycles

REMOVED CORRODE AREAS ON THE LOWER RUDDER HINGE BRACKET AND RUDDER TRIM BRACKET, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (ZONE 200) · airframe 15,384 hrs · 10,205 cycles

REMOVED 10 AREAS OF CORROSION LOCATED ON EMERGENCY EXIT DOOR AROUND CONTOUR RINGS ON OUTER E-EXIT SKIN, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: FUSE — INOPERATIVE (ZONE 200) · airframe 14,852 hrs · 9,843 cycles

EMERGENCY LIGHTS DO NOT WORK IN THE ARM POSITION WITH ALL POWER SHUT DOWN. ALSO, EMERGENCY EXIT LIGHT OVER MAIN CABIN DOOR AND EMERGENCY LIGHT OVER SEAT FOUR DO NOT ILLUMINATE IN THE ON POSITION. ALL OTHER INTERIOR/EXTERIOR EMERGENCY LIGHTS ILLUMINATE IN THE ON POSITION. CORRECTIVE ACTION: REPLACED BATTERY SUPPLY ASSY FUSE. OPS CHECK GOOD. IAW CESSNA CE-680 AMM 33-50-10

Part: FUSE — BLOWN (ZONE 200) · airframe 14,800 hrs · 9,813 cycles

POST-FLIGHT - DURING AN EXTERIOR LIGHT INSPECTION (APU ON, EMER LTS-ARM, PAX SAFETY-ON) AFTER FLYING FOR 7 HOURS, NONE OF THE THREE OVER/FRONT WING LIGHTS ILLUMINATED. AFTER RETURNING INSIDE THE CABIN, NONE OF THE INTERIOR EMERGENCY LIGHTING WAS ILLUMINATED EITHER. MOVING THE EMER LTS SWITCH FROM ARM TO ON (REGARDLESS OF PAX SAFETY SWITCH POSITION ON OR OFF) ILLUMINATED ALL INTERIOR AND EXTERIOR LIGHTING EXCEPT FOR THE MOST FORWARD FOUR INTERIOR LIGHT FIXTURES (GALLEY READING, RED MED PILLAR EXITS, WHITE ABOVE MED EXIT). PERFORMED TROUBLESHODTING FOUND NO 1 EMERG, LIGHTS BATTERY FUSE SLOWN, REPLACED RJSE P/N 52565,5 WITH CUSTOMER SUPPLIED NEW PART. OPS CHECK OK IAW CE680 AMM 33-50-00

Part: SPAR SPLICE — CRACKED (ZONE 500) · airframe 14,628 hrs · 9,691 cycles

CRACK INDICATIONS, CENTER WING, CENTER SPAR SPLICE W.S 37 REF FIELD REPAIR FR680-0126-13812 REV-

Part: BATTERY — FAULTED (ZONE 100) · airframe 14,459 hrs · 9,586 cycles

SUSPECT BATTERY PACK 4 FOR CABIN AND OVERWING PAX EMERGENCY LIGHTING CONTROLLING MECH DOES NOT ILLUMINATE LIGHTS OVER SEAT 8 & FWD OVERWING EGRESS LIGHT WITH ONLY EMERGENCY BATTERY PACK PROVIDING POWER TO LIGHTS. INSPECTED, PERFORMED OPS CK IAW MM 33-50-00 EMERGENCY BATTERY PACK T/S CONTINUATION GAINED ACCESS TO ALL 4 BATTERIES, PERFORMED RESET OF ALL G SWITCHES PROBLEM CONTINUED INSPECTED BATTERY FUSES FOUND GOOD, INSPECTED CONNECTORS, NO DEFECTS NOTED. SWAPPED BATTERIES POSITION 3 WITH 4 & PROBLEM FOLLOWS TO POSITION 4. SWAPPED BACK. R & R POWER SUPPLY 3 IAW AMM 33-50-10, PERFORMED TOP CHARGE FOR 1 HR, PERFORMED EMERGENCY LIGHT TEST IAW AMM 33-50-00, FOUND SYS OK.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,415 hrs · 9,564 cycles

EMERGENCY LIGHTS FAILED PREFLIGHT INSPECTION TEST. DURING TEST WE ONLY GOT THREE LIGHTS TOTAL THAT CAME ON, THE EXIT LIGHT ABOVE THE MAIN ENTRY DOOR, THE READING LIGHT OVER THE GALLEY, AND THE EXTERIOR LIGHT LEFT-HAND SIDE NEXT TO MAIN ENTRY DOOR. ALL OTHER LIGHTS WERE OUT. COMPLIED WITH TC -FLT-33-1001 EMERGENCY LIGHT TEST SUCCESFUL. NO DEFECTS NOTED

Part: SPAR CAP — CORRODED (ZONE 300) · airframe 14,287 hrs · 9,476 cycles

CORROSION FOUND ON AFT RH OUTBOARD VERTICAL SPAR CAP VFS 168.94. ACCOMPLISHED FIELD REPAIR-CORROSION, VERTICAL STABILIZER, RH VERTICAL SPAR CAP IAW TEXTRON AVIATION FIELD REPAIR FR-680-0126-12539 DATED 10/23/2023.

Part: SPAR CAP — CORRODED (ZONE 300) · airframe 14,287 hrs · 9,476 cycles

CORROSION, VERTICAL STABILIZER, RH VERTICAL SPAR CAP, VFS 168.94: REMOVED CORROSION AND ACCOMPLISHED ULTRASONIC THICKNESS CHECK. VERIFIED NO CRACK INDICATIONS. REAPPLIED PROTECTIVE FINISH AND CIC. ALL WORK ACCOMPLISHED IAW TEXTRON AVIATION FIELD REPAIR: FR-680-0126-12539.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,227 hrs · 9,428 cycles

UPON CHECKING AIRCRAFT LIGHTS ON POST FLIGHT INSPECTION, WE FOUND THE AFT CABIN EXIT SIGN LIGHT BURNT OUT. PAIRED BROKEN WIRE FOR AFT LEFT EXIT SIGN ON LAV BULKHEAD IA W SPM 20-30-25, OPS CHECK GOOD IAW AMM 33-50-00.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,227 hrs · 9,428 cycles

UPON CHECKING AIRCRAFT LIGHTS ON POST FLIGHT INSPECTION, WE FOUND THE AFT CABIN EXIT SIGN LIGHT BURNT OUT. REPAIRED BROKEN WIRE FOR AFT LEFT EXIT SIGN ON LAV BULKHEAD IA W SPM 20-30-25, OPS CHECK GOOD IAW CE680 AMM 33-50-00.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,168 hrs · 9,388 cycles

ON CLIMB OUT THE RT ENG WAS ABOUT 50 DEG HOTTER THAN LT. PASSING FL 380 ENG TEMP SPIKED UP THROUGH AMBER RANGE & TO RED AT 928 DEGREES. PULLED THROTTLE BACK & ENG BACK TO NORMAL TEMP. ON DESCENT, RT ENG STARTED ABOUT 40 DEG HOTTER THAN LT FLUCTUATING 5-15 DEG UP & DOWN. REMOVED RT ENG HP SHUTOFF VALVE, INSTALLED OVERHAULED HP REG SHUTOFF VALVE. CLEANED TERMINAL STRIP AS REQUIRED. ALL WORK PERFORMED IAW MM 36-10-00,71-10-00.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,118 hrs · 9,349 cycles

MECHANICALLY BLENDED MULTIPLE AREAS OF CORROSION APX 3 INCHES IN LENGTH LOCATED ON LH HORIZONTAL STAB, AFT SPAR ELEVATOR COVE, APX 12 INCHES INBD OF STAB TIP UPPER SPAR CLIP. MECHANICALLY REMOVED MULTIPLE AREAS OF SURFACE CORROSION APX 12 INCHES IN LENGTH LOCATED ON RH HORIZONTAL STAB AFT SPAR ELEVATOR COVE INBD/UPPER AREA IAW C680 SRM 51-70-02. PROTECTED BARE METAL IAW C680 SRM 51-20-01. REPAIRED CORROSION BLENDS BEYOND C680 SRM 51-70-02 LIMITS LOCATED ON LH STAB AFT SPAR/ELEVATOR COVE IAW TEXTRON FIELD REPAIR FR-680-0126-11926.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,118 hrs · 9,349 cycles

MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED ON VERTICAL STAB AFT SPAR RUDDER COVE LOCATED JUST ABOVE RUDDER FAIRING PANEL LH SIDE ON SPAR CLIP, PERFORMED NDT AND SUBMITTED FOR REPAIR DISPOSITION. TREATED AND PRIMED BLENDED AREAS IAW TEXTRON FIELD REPAIR FR-680-0126-11911.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,118 hrs · 9,349 cycles

REPLACED THE CORRODED RUDDER TORQUE TUBE WITH NEW TEXTRON P/N 6933025-55 ON RUDDER ASSEMBLY P/N 6933000-20 S/N CE0187 PER CESSNA 680 SRM 55-40-09.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,118 hrs · 9,349 cycles

MECHANICALLY BLENDED 1 AREA OF CORROSION IN LH GEAR WELL, AFT LOWER SPAR WS 21 TO 23 AND MECHANICALLY BLENDED 1 AREA OF CORROSION IN RH GEAR WELL, AFT LOWER SPAR WS 30 TO 33. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED FINDINGS AND SUBMITTED FOR REPAIR DISPOSITION. TREATED AND PRIMED AREAS PER TEXTRON FIELD REPAIR FR-680-0126-11863.

Part: SWITCH — TRIPPED (EMERGENCY LIGHTS) · airframe 13,604 hrs · 9,022 cycles

EMERGENCY LIGHTS BATTERY: 5G SWITCH TRIPPED ON ONE OF THE EMERGENCY LIGHT BATTERIES. LIGHT OVER SEAT 8 AS WELL AS THE FORWARD OVER-WING LIGHT AND SHARK LIGHT REMAIN ON WITH EMER LIGHTS SWITCH OFF AND POWER REMOVED FROM THE AIRCRAFT. GAINED ACCESS TO AND RESET INERTIA SWITCH ON #3 EMER BATTERY PACK. INSTALLED ALL PANELS REMOVED TO GAIN ACCESS. WORK DONE IAW CE-680 AMM CH 33-50-10

Part: WATER SEPARATOR — ODOR · airframe 13,439 hrs · 8,902 cycles

APU BLEED AIR: UPON STARTING THE APU AND THE BLEEDS THERE WAS A SMELL OF OIL IN THE AIR//CORRECTIVE ACTION// COMPLETED BORESCOPE INSP OF APU IAW TC-C68-49-1001 AND PROVIDED PHOTOS TO CUSTOMER. NDN. COMPLETED ECS DUT BURN OUT RUN IAW TC-680-21-120905M NDN. R/R COALESCER SOCK FROM WATER SEPERATOR IAW CE-680 AMM 21-21-03 NDN. C/W LEAK CHECK OF WATER SEPERATOR AND CONFIRMED NO SMELL OF OIL IN CABIN OR COCKPIT NDN.

Part: NONE — NONE · airframe 12,743 hrs · 8,470 cycles

MAIN DOOR HANDLE: THE MAIN DOOR HANDLE IS VERY STIFF AND HARD TO ACTUATE AT THE VERY END OF CLOSING AS WELL AS THE START OF OPENING THE DOOR. // SIGN OFF // REMOVED ENTRY DOOR STEP COVER, REMOVED ACCESS PANEL TO INSPECT LATCHING MECHANISM, V!SUAUY INSPECTED LATCHING MECHANISM, OPENED I AND CLOSED DOOR MULTIPLE TIMES VISUALLY INSPECTING LATCHES AND ROLLERS. CLEANED DEBRIS AND DUST FROM AROUND LATCHING MECHANISMS. DOOR HANDLE ACTUATION IMPROVED. DOOR OPENED AND CLOSED AS NORMAL. CLOSED ALL ACCESS AND RBNSTALLED STEPS, WORK ACCOMPLISHED IN · REFERENCE WITH CE 680 AMM CH 52-10-00

Part: SKIN — CORRODED (LT WING)

CORROSION ON WING SKIN. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ11111 DATED NOV 2020.

Part: SKIN — OUT OF ALIGNMENT (WING) · airframe 11,899 hrs · 7,901 cycles

MISALIGNED HOLES COMMON TO THE HEATED LEADING EDGE SKIN AND THE REPLACEMENT DIFFUSERS. ACCOMPLISHED TEXTRON AVIATION LETTER DQ27749 DATED NOV 8, 2020; 680-0126, N359QS, REPAIR RECOMMENDATION.

Part: DOOR — CORRODED (THRUST REVERSER)

CORROSION ON THE RT LOWER THRUST REVERSER LOWER DOOR ASSEMBLY, PART NUMBER 07ND78004-5. ACCOMPLISHED NORDAM FIELD ENGINEERING DISPOSITION DATED 6 NOV 2020 NTRSD-20TP-241. LOWER DOOR CORROSION REMOVAL.

Part: SPAR CAP — DAMAGED (VERTICAL STAB) · airframe 11,899 hrs · 7,901 cycles

VERTICAL FIN AFT SPAR CAP (LEFT SIDE) DAMAGE. ACCOMPLISHED TEXTRON AVIATION LETTER DQ27908M1 DATED NOV 19, 2020; 680-0126 (N359QS) VERTICAL FIN AFT SPAR CAP (LEFT SIDE) DAMAGE.

Part: DOOR — DELAMINATED (RT NACELLE) · airframe 11,899 hrs · 7,901 cycles

REPAIR OF RIGHT ENGINE UPPER COWL DOOR DAMAGE. TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ27776M1 DATED NOV 10, 2020.

Part: DIFFUSER — ELONGATED (LEADING EDGE) · airframe 11,899 hrs · 7,901 cycles

REPAIR TO LEADING EDGE DIFFUSER. TEXTRON AVIATION REPAIR LETTER DQ27749 DATED NOV 8, 2020. 680-0126 N359QS REPAIR RECOMMENDATION.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 10,916 hrs · 7,222 cycles

REPAIRED SIX AREAS OF CHAFES /GOUGES IN THE DOUBLER BOND ASSEMBLY OF THE EMERGENCY EXIT OPENING SURROUND P/N 6911166-2 AND FRAME SEGMENT 6911122-3 BETWEEN FS 405.4 AND FS 432 BY REPLACING FRAME SEGMENT 6911122-3 WITH NEW, AND BLENDING, PERFORMING NDT, TREATING, AND PRIMING CHAFED AREAS OF THE DOUBLER BOND ASSEMBLY IAW FIELD. REPAIRED CHAFE/GOUGE AT FS 399.75 IN FRAME SEGMENT 6911121-5 AND DOUBLER BOND ASSEMBLY 6911166-2 BY BENDING, PERFORMING NDT, TREATING BARE METAL AREAS AND INSTALLING REPAIR DOUBLER IAW RESEARCH AND ENGINEERING MRO ENGINEERING REPAIR ORDER. DAMAGE CAUSE BY IMPROPER FASTENER LENGTHS OF INTERIOR COMPONENTS.

Part: CONTROLLER — DEFECTIVE (CABIN PRESSURE) · airframe 10,834 hrs · 7,169 cycles

CABIN ALTITUDE AMBER CAS ILLUMINATED - CLIMBING THROUGH FL 180 AMBER CAS CABIN ALTITUDE ILLUMINATED AND CABIN SHOWED 9000 FEET. CABIN ALTITUDE CHECKLIST WAS COMPLETED AND THE MAX CABIN WAS 9500 FEET. PASSENGER MASKS WERE NOT DEPLOYED. DESENDING THROUGH FL 180 CAS MESSAGE EXTINGUISHED. // SIGNOFF // PERFORMED CONTINUITY CHECKS OF WOW SWITCHES IAW DWG 6908321, WITH NO FAULTS FOUND, EACH OPEN/CLOSE FROM .4OHM OR LESS CLOSED TO INFINITE WHEN OPEN, INSTALLED PLUGS WHICH WERE REMOVED FOR TESTING. GAINED ACCESS TO PRIMARY AND SECONDARY OUTFLOW. RAN APU, PRESSURIZE AIRPLANE AND VISUALLY SAW OPERATION OF OUTFLOW VALVES, OPENING AND CLOSING AS INDICATED (OPS CHECK GOOD). COMPLIED WITH PRESSURIZATION CONTROLLER BUILT IN TEST (OPS CHECK GOOD). COMPLIED WITH PRESSURIZATION CHECK ON MANUAL MODE (OPS CHECK GOOD). RAN ONLY LT ENGINE AND COMPLIED WITH PRESSURE SOURCE, (LT ENGINE BLD AIR) OPERATIONAL CHECK (OPS CHECK GOOD). RAN ONLY RT ENGINE AND COMPLIED WITH PRESSURE SOURCE, (RT ENGINE BLD AIR) OPERATIONAL CHECK (OPS CHECK GOOD) IAW MM CHAPTER 21-30-00. REMOVED PRESSURIZATION CONTROLLER PIN 9914487-11 SIN 66-F0L0L AND INSTALLED AN INSPECTED PRESSURIZATION CONTROLLER PIN 9914487-11 SIN 18-F0240 IAW MM 21-31-00. PERFORMED PRESSURIZATION CONTROL SYSTEM OPERATIONAL CHECK IA W CESSNA 680 MM 21-30-00, OPERATIONAL CHECK GOOD.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 9,898 hrs · 6,547 cycles

REMOVED FIRST LOCK FASTENER COLLAR, JUST ABOVE APU STINGER, ON LT SIDE OF VERTICAL STAB AFT SPAR FACE. MECHANICALLY BLENDED CORROSION APX 3 INCHES ABOVE APU STINGER PANEL 342AB. SUBMITTED FINDINGS TO CESSNA ENGINEERING AND PERFORMED BLEND TREAT REPAIR PER TEXTRON AVIATION MEMO DQ10551M1R1 RRL DATED 20 DEC 2017. INSTALLED 1 NEW HI-LOK COLLAR HL70-6 IN SAME LOCATION AS REMOVED.

Part: WARNING LIGHT — FALSE ACTIVATION (MLG) · airframe 5,560 hrs · 3,634 cycles

IN CRUISE AT FL 410, OBSERVED AN FMS MESSAGE OF "GEAR SPEED LIM 210". OBSERVED RT MAIN GEAR LIGHT ON. GEAR HAD BEEN VERIFIED UP AFTER TAKE OFF. RIGHT GEAR DOWN INDICATION & NO RED UNLOCKED LIGHT. LAV DOOR OPEN CASS MESSAGES SHORTLY BEFORE WHEN THE LAV WAS USED. SLOWED BELOW 210 KTS FOR REST OF FLIGHT. GEAR EXTENDED NORMALLY & BLEW DOWN AS A PRECAUTION. FOUND LANDING GEAR CNTL 1 CIRCUIT BREAKER TRIPPED. RESET BREAKER. RESET EMERGENCY BLOW DOWN BOTTLE & LANDING GEAR CONTROL VALVE OVERRIDE IAW MM 32-00-00. CHECKED RT GEAR DOWNLOCK SWITCH & WIRING IAW MM 32-30-01. NO DEFECTS NOTED. LANDING GEAR CNTL 1 CIRCUIT BREAKER PULLED FOR EMERGENCY PROCEDURES. REMOVED, TESTED, AND REINSTALLED RT DOWNLOCK SWITCH IAW MM 32-60-00 AND 32-30-40, ALL CHECKED GOOD. SERVICED EMERGENCY GEAR BLOWDOWN BOTTLE IAW MM 12-13-01. COMPLIED WITH STEPS 8 A.7 THROUGH 8 A.17 FOR HYD SYS BLEED IAW MM 12-12-02. R & R GEAR CONTROL 2 PCB IAW AMM 24-60-10. OPS CHECKED NORMAL.

Part: RIB — CRACKED (ZONE 300) · airframe 5,391 hrs

DURING A SCHEDULED INSPECTION, FOUND THE RT STABILIZER RIB CLOSE-OUT PANEL CRACKED ON THE UPPER ATTACH FLANGE TO SKIN ATTACH AREA, 4.5" LONG.

Part: RIB — CRACKED (ZONE 300) · airframe 5,391 hrs

DURING A SCHEDULED INSPECTION, WE FOUND THE RT INBD STABALIZER RIB CRACKED ON THE INBD LOWER FLANGE TO SKIN ATTACH AREA IN A ZIZAG PATTERN AND 2.2 INCHES LONG.

Part: HEAT EXCHANGER — CRACKED (ZONE 400) · airframe 5,391 hrs

DURING A SCHEDULED INSPECTION, PERFORMED A PRODUCT IMPROVEMENT. REPLACEMENT OF DUCT ASSY 6914070-67. NOTICED THAT THE HEAT EXCHANGER SIDE PLATE HAD TWO CRACKS ABOUT .30 INCHES LONG. OPPOSITE SIDE OF THE HEAT EXCHANGER WAS CRACKED IN NONE OF THE FOUR CORNERS. A NEW HEAT EXCHANGER WAS INSTALLED. PERFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN.

Part: HEAT EXCHANGER — CRACKED · airframe 5,391 hrs

DURING A SCHEDULED INSPECTION, PERFORMED A PRODUCT IMPROVEMENT (REPLACEMENT OF DUCT ASSY 6914070-67) NOTICED THAT THE HEAT EXCHANGER SIDE PLATE HAD THREE CRACKS ABOUT .30 INCHES LONG. OPPOSITE SIDE OF THE HEAT EXCHANGER WAS CRACKED IN ONE OF THE FOUR CORNERS. A NEW HEAT EXCHANGER WAS INSTALLED. PERFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN.

Part: OIL SYSTEM — OVERSERVICED (APU) · airframe 4,359 hrs · 2,839 cycles

WITH APU ON, NON-ELECTRICAL SMOKE STARTED TO FILL CABIN. WITH BLEED AIR TURNED ON, SMOKE INCREASED RAPIDLY. OIL FOUND LEAKING FROM APU COMPARTMENT. FOUND DEICE FLUID DRIPPING DOWN THE RUDDER, TRAILING INTO THE APU EXHAUST CONE. ALSO FOUND APU TO BE OVER SERVICED AND FOUND SOME RESIDUAL APU OIL SITTING ON APU'S BOTTOM ACCESS PANEL. DEPANELED APU, CORRECTED APU OIL LEVEL IAW MM 12-11-03 AND CLEANED UP RESIDUAL OIL. ODOR IN THE CABIN SEEMS TO HAVE BEEN COMING FROM A MIXTURE OF DEICE FLUID AND RESIDUAL APU OIL BEING SUCKED INTO THE APU INLET ON INITIAL APU START UP WITH ACFT TAIL PARKED IN WIND.

Part: STRUT — DISCHARGED (NLG) · airframe 3,257 hrs · 2,127 cycles

ON TAKEOFF, UNABLE TO RAISE GEAR. TAKE OFF + 20 SEC, WOW MISCOMPARE MESSAGE ILLUMINATED. THRUST REVERSERS & NOSEWHEEL STEERING WERE AVAILABLE ON LANDING. TROUBLESHOT LANDING GEAR RETRACTION PROBLEM. FOUND NOSE LANDING GEAR LOWER STRUT NITROGEN PRESSURE LOW. RESERVICED NLG STRUT WITH FLUID AND NITROGEN IAW MM 32-20-00-600. ALSO FOUND NOSE GEAR SQUAT SWITCH OUT OF RIG. RERIGGED NOSE LANDING GEAR SQUAT SWITCH IAW MM 32-60-00. NO OTHER DEFECTS NOTED. OPS & LEAK CHECKED GOOD.

Part: BRACKET — MISINSTALLED (COCKPIT WINDOW) · airframe 3,004 hrs

DURING MX THE TECH OPENED THE PILOT'S SIDE WINDOW, AFTER UN-LATCHING THE WINDOW IT SWUNG IN AND FELL OFF IT'S HINGE POINTS. UPON FURTHER INVESTIGATION, FOUND THAT THE LOWER HINGE POINT HAD COME LOOSE AT THE HINGE ATTACH BRACKET RIVETS. AND THAT THE UPPER HINGE ATTACHED BRACKET WAS DOUBLE FLUSH RIVETED AND ALSO HAD VERY LITTLE COUNTER SINK ON BACK SIDE OF THE RIVET. FOUND THAT SL680-56-01 ADDRESSES THIS PROBLEM, FROM SN -0001 THRU -0067, BUT DID NOT INCLUDE OUR SN. BELIEVE THAT SL680-56-01 SN AFFECTIVITY SHOULD BE EXPANDED TO INCLUDE MORE ACFT.

Part: CABLE — LOOSE (ELEVATOR) · airframe 1,598 hrs · 1,043 cycles

ACFT HAS AN AIRFRAME FLUTTER- INCREASE W/SPEED ABOVE 250KTS. SOME INDICATIONS W/ AP AND YD ON OR OFF, NOT NOTICED IN RUDDER OR AILERON FLUTTER APPEARS TO BE IN ELEVATOR. BALANCED LT AND RT ELEVATORS. FOUND ELEVATOR SERVO CABLE TENSIONS LOW. ADJUSTED TENSIONS IAW MM 27-30-00 AND MM CH 52-20-00 TRAVEL CHECK GOOD. OP'S CHECK GOOD.

Part: SKIN PANEL — CORRODED (FUSELAGE)

FOUND FUSELAGE SKIN PANEL CORRODED AT STATION 320 STRINGER 19R. (M)

Part: FRAME — CORRODED (FUSELAGE)

FOUND LOWER END OF FRAME AND BRACKET AT STATION 312 RBL 40 EXFOLIATED. (M)

Part: DOUBLER — DENTED (CARGO DOOR)

FOUND DENT IN CARGO DOOR DOUBLER AT BS 540 TO BS 560 STRINGER 19L AND 20L. REPAIRED FUSELAGE SKIN AT BS 540 TO BS 560 STRINGER 19L AND 20L IAW SIDE REPAIR DRAWING 1-10-8-01 AND 727 SRM 51-30-2. 2024-T3 .050 INCH 16.5 INCH BY 14.5 INCH AND 2024-T3 .100 INCH 16.5 BY 14.5 INCH. (M)

Part: WIRE — DAMAGED (START VALVE)

NR 1 ENGINE START VALVE LIGHT ILLUMINATED IN FLIGHT. EMERGENCY DECLARED. COMPLIED WITH ENGINE SHUTDOWN CHECK LIST. DIVERTED TO MCI. AIRCRAFT LANDED WITHOUT INCIDENT. REPAIRED WIRE TO START VALVE AT CANNON PLUG. OPERATIONAL CHECK OF SYSTEM GOOD. (M)

Part: BATTERY — DISCHARGED (CARGO BAY)

FLT 731 - EN ROUTE TO IND, MAINTENANCE LIGHT ON CARGO FIRE DETECTOR ILLUMINATED. AIRCRAFT LANDED IND SAFELY. REMOVED AND REPLACED FORWARD LOWER CARGO DETECTOR BATTERY. SYSTEM TESTED AND NO DEFECTS NOTED. (M)

Part: WARNING LIGHT — ILLUMINATED (SMOKE DETECTION)

FLT 710 - MSP-IND - LOWER CARGO COMPARTMENT SMOKE DETECTION SYSTEM SHOWING FAULT CODE CCU RX AND AMBER MAINTENANCE LIGHT IS ILLUMINATED. RESET SYSTEM FIRE DETECTION SYSTEM. (M)

Part: AIR DISTRIBUTION — ODOR (COCKPIT)

CLT/IND - FLT 713 - FUEL ODOR SMELL IN COCKPIT WITH PACK(S) OPERATING. OPERATED PACKS FOR SEVERAL MINUTES, FUEL ODOR DISSIPATED, ALL OPERATIONS NORMAL. (X)

Part: COMPRESSOR — DAMAGED (NR 3)

BWI - FLT 705 - REJECTED TAKEOFF FROM BWI DUE TO COMPRESSOR STALLS NR 3 ENGINE. (ENGINE WAS FOUND TO HAVE FOREIGN OBJECT DAMAGE TO THE C-1 AND C-2 DISK PLUS STATOR DAMAGE. A TWO ENGINE FERRY TO IND WAS ACCOMPLISHED FOR MAINTENANCE). REMOVED AND REPLACED NR 3 ENGINE. (X)

Part: VALVE — LEAKING (CARGO DOOR)

FLT 631 - IND-PHX - AT FL280 CRUISE CABIN STARTED CLIMBING RAPIDLY TRIED TO CONTROL AND REQUEST DESCENT TO FL200 MAIN CARGO DOOR LIGHT CAME ON. COMPLETED IRREGULAR CHECK LIST STILL COULD NOT CONTROL CABIN, TURNED BACK FOR ICT, CONTINUED TO DESCEND TO 10,000 FT. HAD TO DUMP FUEL TO MAKE LANDING WEIGHT AND LANDED AT ICT. REMOVED AND REPLACED DOOR OPEN SEQUENCE VALVE. (M)

Part: CLAMP — DISTORTED (NR 3 ENGINE)

AT APPROX 6000 FEET, A LOW AIR PRESSURE WAS NOTED ON NR 3 BLEED SHORTLY THEREAFTER THE NR 3 FIRE WARNING LIGHT ILLUMINATED INTERMITTENTLY. THE NR 3 ENGINE WAS SHUT DOWN AND AIRCRAFT WAS LANDED AT CAE WITHOUT INCIDENT. FOUND 13TH STAGE BLEED DUCT SEPARATED FROM ENGINE AT V-BAND CLAMP CONNECTION. NO DAMAGE NOTED AT DUCT FLANGES AND CLAMP WAS IN A 'TIGHTENED' CONDITION. RECONNECTED DUCT AND REPLACED CLAMP. PERFORMED ENGINE RUN WITH NO LEAKS NOTED. (M)

Part: DNLOCK ACTUATOR — FAILED (NLG)

ON APPROACH INTO DAYTON, THE NOSE LANDING GEAR GREEN LIGHT DID NOT ILLUMINATED ON GEAR EXTENSION. PERFORMED MANUAL GEAR EXTENSION AND ALL GEARS INDICATED DOWN AND LOCKED. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. REPLACED THE NOSE GEAR DOWNLOCK ACTUATOR, OPS CHECKED GOOD.