N315QS

Part: DRAG ANGLE — CORRODED (ZONE 500 FLAP) · airframe 14,494 hrs · 9,681 cycles

BLENDED AREAS OF CORROSION ON THE LOWER AFT DRAG ANGLE, LEFT WING INBD OF FLAP, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPLACED BLENDED FASTENERS WITH NEW, CLEANED, TREATED AND PRIMED AREAS PER REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (ZONE 600) · airframe 14,494 hrs · 9,681 cycles

MECHANICALLY BLENDED CORRODED AREA ON LOWER AFT RT WING SKIN, INBOARD OF FLAP, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED AND PRIMED AREAS IAW REQUEST FOR TECHNICAL SERVICES REPORT.

Part: BATTERY — INOPERATIVE (ZONE 200) · airframe 14,454 hrs · 9,650 cycles

ON PREFLIGHT INSPECTION THE ONLY EMERGENCY LIGHTS THAT ILLUMINATE ARE ADJACENT TO THE MAIN CABIN DOOR AND THE FORWARD AISLE LIGHTS. ALL OTHER INTERIOR EMERGENCY LIGHTS ARE INOPERATIVE. REMOVED EMERGENCY BATTERY #1 P/N CBS28-1 S/N 3730M, BATTERY#2 P/N CBS28-1 S/N 008124, BATTERY#3 P/NCBS28-1 S/N 3279M, BATTERY#4 CBS28-1 S/N 0019M AND INSTALLED STOMER SUPPLIED #1 EMER.~--... / BATTERY P/N 6430028-1 N 13 TTERY#2 P/N 6430028-1 S/ 1396 BATTERY#3 P/N 6430028-1 36, ATTERY#4 P/N 6430028-1 SF. 959 IN REF TO CE-680 AMM:33-50-1 , PERFORMED EMERGENCY LIGHT CHECK IN REF TO 680 AMM: 33-50-00,OPERATIONAL CHECK SATISFACTORY WITH NO DEFECTED NOTED

Part: SPAR — CORRODED (ZONE 600) · airframe 14,137 hrs · 9,419 cycles

MECHANICALLY BLENDED 1 EA. AREA OF CORROSION ON AFT SPAR, LOWER CLIP OUTBD AREA, IN THE RH MLG WHEEL WELL, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREA BY CLEANING, TREATING, AND PRIMING PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: ELEC CONNECTOR — OPEN (ZONE 700) · airframe 14,061 hrs · 9,365 cycles

GEAR SELECTED DOWN. RIGHT MAIN GEAR DID NOT ILLUMINATE DOWN. AND THE UNLOCKED LIGHT WAS ILLUMINATED. WE RAN THE FULL GEAR DID NOT EXTEND QRH WITH NO CHANGE TO THE INDICATIONS. CORRECTIVE ACTION: WE PERFORMED TS OF THE RH MLG INDICATION DISCREPANCY. AT RH CONNECTOR PG002 PIN 30 TO PIN 31 WE HAVE AN OPEN READING OF PIN 6 TO PIN 4 OF RH GEAR DOWNLOCK SWITCH. PG002 PIN 33 TO PIN 34 WE HAVE CONTINUITY THROUGH PIN 3 TO PIN 1 OF RH GEAR DOWNLOCK SWITCH. PIN 6 SENDS SIGNAL TO LG CONTROL 2 PCB, PIN 3 SENDS SIGNALS TO LG CONTROL 1 PCB. PERFORMED CONTINUITY CHECK OF HARNESS AND ALL CHECKS GOOD. WE HAVE A BAD RH MLG DOWNLOCK SWITCH. ALSO, THE SWITCH HAS BEEN HIT BY FOD AND IS BADLY DAMAGED. PHOTO ATTACHED. TO EMAIL CHAIN FOR REVIEW. TOOLING PLACED ON ORDER ETA 2300 5/9/2025. SHIPPED STERLING.JOB # 3553443C. TOOLING ONSITE WAITING FOR PART. REMOVED RH MLG DOWNLOCK SWITCH PN: 6-0373-3 SN: NA AND REPLACED WITH NEW SWITCH PN: 6-0373-1 SN: NA. ALL OPS CHECKS GOOD. CURE CHECK GOOD WORK PERFORMED IAW CE 680 AMM 32-30-40

Part: FLAP SYSTEM — FAULTED · airframe 13,955 hrs · 9,279 cycles

FLAPS FAIL AMBER CAS: WHEN SELECTING FLAP POSITION 15 AMBER CAS FLAP FAIL MESSAGE APPEARED. FLAPS DID NOT MOVE FROM ZERO POSITION. CORRECTIVE ACTION; POWERED UP AIRCRAFT AND DISCOVERED 'BITE 2' AND 'BITE 6' FAULTED ON FLAP CONTROLLER AS A RESULT OF FLAP FAIL. CLEARED ALL FAULTS ON FLAP CONTROLLER AND CYCLED FLAPS X6 WITH NO FAILS. GAINED ACCESS AND INSPECTED CONNECTIONS AND PINS ON FLAP HANDLE, FLAP CONTROLLER, PDU, BOTH FLAP POSITION SENSORS, AND SOFT START MODULE IN REF TO CE-680 AMM 27-51-00 AND 27-52-00. DISCOVERED AND CLEANED TRACES OF GREASE IN BOTH FLAP POSITION SENSOR CONNECTORS. COMPLIED WITH RESISTANCE CHECKS FOR BOTH POSITION SENSORS. POWERED UP AIRCRAFT AND CYCLED FLAPS X15. NO FLAP FAILS AND NO FAILS ON FLAP CONTROLLER. SYS OP CK GOOD. MCC NOTIFIED. AIRCRAFT RESTORED TO ORIGINAL CONFIGURATION.

Part: LANDING GEAR — FAULTED (ZONE 700) · airframe 13,847 hrs · 9,213 cycles

DURING DEPARTURE OUT OF TNCM RAISED THE GEAR AFTER T/O AND HEARD A NOISE THEN NOTICED THAT BOTH MAIN LANDING GEAR STILL INDICATED DOWN WITH GREEN DOWN GEAR INDICATION. THE NOSE GEAR LIGHT WAS OUT. PERFORMED THE QRH PROCEDURE AND LOWERED GEAR HANDLE AND GOT ALL 3 GREEN LIGHTS INDICATING ALL GEAR IN THE DOWN AND LOCKED POSITION. CONTINUED FLIGHT AT 10,000FT AND 190KIAS TO TJSJ WHERE WE DID A A LOW PASS DOWN THE RUNWAY TO HAVE TOWER VERIFY GEAR APPEARED IN THE DOWN POSTION. RETURN FOR LANDING WITH NO ISSUES. PERFORMED DVI ON LANDINGS GEARS AND WHEEL WELL. PERFORMED RETRACTION TESTS. OPS CHECKS GOOD. IAW CE-680 AMM 32-00-00.

Part: SKIN — CORRODED (ZONE 300) · airframe 13,799 hrs · 9,175 cycles

LH AND RH HORIZONTAL STAB UPPER AND LOWER SKIN HAS AREAS OF CORROSION JUST FWD OF ACCESS PANELS 351AC AND 352AC. MECHANICALLY REMOVED CORROSION ON LH UPPER AND LOWER HORIZONTAL STAB SKIN TRAILING EDGE JUST FWD OF ACCESS PANEL 351AC AND CORROSION ON RH UPPER AND LOWER HORIZONTAL STAB SKIN TRAILING EDGE JUST FWD OF ACCESS PANEL 352AC. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS RFTS-112238 REV. 0 TITLE: N315QS ( 680-0220 ) LH AND RH HORIZ STAB UPPER AND LOWER SKIN CORROSION, DATED 11/13/2024.

Part: STRINGER — CRACKED (ZONE 100) · airframe 13,799 hrs · 9,175 cycles

REPAIRED CRACKED TAILCONE/STRINGER FIREWALL WEB CRACK PER NETJETS RFTS-112267. REV.0 TITLED "N315QS (680-0220) TAILCONE FIREWALL WEB CRACK" DATED 18NOV24.

Part: SPAR — CORRODED (ZONE 100) · airframe 13,799 hrs · 9,175 cycles

LH MLG WHEEL WELL AFT SPAR, FWD FACE HAS 1 AREA OF CORROSION INBD OF WS 37.00. MECHANICALLY REMOVED CORROSION LOCATED IN LH MLG WHEEL WELL, AFT SPAR, FWD FACE INBD OF WS 37.00 APX 21 INCHES IAW C680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL SKIN THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS ENGINEERING RFTS-112239 REV.0, TITLE: N315QS (680-0220) LH MLG WHEEL WELL AFT SPAR CORROSION ON THE FWD SIDE, DATED: 11/13/2024.

Part: RIB — CORRODED (ZONE 500) · airframe 13,799 hrs · 9,175 cycles

LH WING INBD FLAP COVE SUPPORT RIB HAS CORROSION WHERE HYD STAND-OFF BRACKET IS ATTACHED. MECHANICALLY REMOVED CORROSION LOCATED ON LH WING INBD FLAP COVE SUPPORT RIB, OUTBD SIDE WHERE HYD STAND-OFF BRACKET IS ATTACHED IAW C680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS RFTS-112252 REV.0 TITLE: N315QS ( 680-0220 ) LH WING SPAR TRAILING EDGE RIB CORROSION, DATED: 20NOV2024.

Part: FITTING — CORRODED (ZONE 600) · airframe 13,799 hrs · 9,175 cycles

RH WING SPOILER HYDRAULIC LINE CARRY THRU FITTINGS ON AFT WING SPAR JUST INBD OF WING JACKING POINT HAS 2 CARRY THRU FITTINGS WITH CORROSION AROUND THEM. MECHANICALLY BLENDED 2 EA. AREAS OF CORROSION AROUND RH WING HYDRAULIC LINE CARRY THROUGH FITTINGS ON AFT SPAR LOCATED IN INBD FLAP WELL IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS RFTS-112302 REV. 0, TITLE: N315QS ( 680-0220 ) RH AND LH WING SPAR WEB CORROSION, DATED: 20NOV2024.

Part: HINGE — CORRODED (ZONE 300) · airframe 13,799 hrs · 9,175 cycles

FOUND AN AREA OF CORROSION ON LOWER RUDDER HINGE. MECHANICALLY REMOVED 1 AREA OF CORROSION LOCATED ON RUDDER LOWER HINGE, AFT END, LH SIDE UPPER AREA. EVALUATED AND FOUND TO BE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02. SUBMITTED TO NJA ENGINEERING AND TEXTRON ENGINEERING. REPAIRED AREA IAW TEXTRON REPAIR MEMO DQ46512M1, SUBJECT: RUDDER LWR HINGE FITTING CORROSION, DATED: NOVEMBER 13, 2024.

Part: FITTING — CORRODED (ZONE 500) · airframe 13,799 hrs · 9,175 cycles

LH WING SPOILER HYDRAULIC LINE CARRY THRU FITTINGS ON AFT WING SPAR JUST INBD OF WING JACKING POINT HAS 2 CARRY THRU FITTINGS WITH CORROSION AROUND THEM. MECHANICALLY BLENDED 3 EA. AREAS OF CORROSION AROUND LH WING HYDRAULIC LINE CARRY THROUGH FITTINGS ON AFT SPAR LOCATED IN INBD FLAP WELL IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS RFTS-112302 REV. 0, TITLE: N315QS ( 680-0220 ) RH AND LH WING SPAR WEB CORROSION, DATED: 20NOV2024.

Part: STRINGER — CORRODED (ZONE 100) · airframe 13,799 hrs · 9,175 cycles

STINGER HAS 1 AREA OF CORROSION ON LOWER AFT SIDE NEAR DRAIN HOLE. MECHANICALLY BLENDED 1 AREA OF CORROSION ON STINGER LOWER AFT SIDE NEAR DRAIN HOLE. EVALUATED AND FOUND AREA TO BE BEYOND LIMITS. SUBMITTED AREA TO NJA ENGINEERING FOR REPAIR. REPAIRED AREA PER NJA ENGINEERING RFTS-112242, REV. 0, TITLED: N315QS (680-0220) TAILCONE STINGER CORROSION, DATED: 21NOV24.

Part: CONTROL CABLE — CHAFED (ZONE 600 AILERON) · airframe 13,799 hrs · 9,175 cycles

DURING TASK 27-60-00-2200, FOUND RH WING AILERON OUTPUT CABLE CHAFFING DRAIN TUBE NEXT TO SPOILER MIXER BOX. REMOVED EXISTING DRAIN TUBE FROM AIRCRAFT. REPAIRED DRAIN TUBE PER NJA RFTS-112277, REV 0, TITLE: N315QS (680-0220) WATER DRAIN LINE CHAFE, DATED: 15NOV24.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,008 hrs · 8,577 cycles

AVIONICS POWER: WITH THE MAIN POWER ON DURING FINAL DESCENT MY SIC IN THE RIGHT SEAT SMELLED A FAINT ELECTRICAL SMELL RIGHT BEFORE I DID. IT SEEMED TO GO AWAY AND WE LANDED VERY SHORTLY AFTERWARD. UPON STARTING APU THE SMELL CAME BACK MUCH STRONGER AND SMELLED LIKE AN OLD HAIR DRYIER. WE SHUT IT DOWN IMMEDIATELY. //SIGNOFF// REMOVED ALL 4 DISPLAY UNITS, PERFORMED GVI OF ALL DISPLAYS AND NO VISIBLE FAULTS NOTED NEITHER ANY FOUL SMELL FROM THEM. PERFORMED GVI OF ALL THE POWER HARNESS OF ALL 4DISPLAYS AND NO VISIBLE FAULTS NOTED, PERFORMED GVI BEHIND INSTRUMENT PANEL NO VISIBLE FAULTS NOTED. REINSTALLED ALL 4 DISPLAY UNITS TO ORIGINAL POSMONS AND OPS CHECKED GOOD IAW CE6BOAMM 34-23-00. REMOVED BOTH MCDUS, PERFORMED GVI OF MCDUS NO VISIBLE FAULTS NOTED NOR FOUL SMELL. REINSTALLED BOTH MCDUS AND OPS CHECKED GOOD IAW CE680AMM 23-80-00. VISIBLE FAULTS NOTED NOR FOUL SMELL. REINSTALLED BOTH MCDUS AND OPS CHECKED GOOD IAW CE680AMM 23-80-00.INSULATION SHOWS SIGNS OF OVERHEATING. REPLACED TERMINAL LUG AND OPS CHECKED GOOD IAW CE680SPM 20-30-25, CLOSED RH CB PANEL IAW CE680AMM 24-60-20, POWERED UP AIRCRAFT, RAN APU AND ENGINES NO ELECTRICAL SMELL DETECTED AT THIS TIME, PER AIRBOSS RECOMMENDATION, INSPECTED ALL CABIN AND COCKPIT LIGHTING WIRING FOR EVIDENCE OF OVERHEAT WITH NO VISIBLE FAULTS FOUND AT THIS TIME, STARTED APU AND RAN FOR 30 MINUTES WITH ONLY NORMAL SMELL FROM APU START.

Part: SPRING — BROKEN (PAX DOOR) · airframe 12,419 hrs · 8,166 cycles

MAIN DOOR COUNTER WEIGHT SPRING BROKE UNABLE TO CLOSE DOOR WITHOUT HELP. REMOVED AND REPLACED MED FWD COUNTERBALANCE SPRING. PERFORMED RIGGING OF MED COUNTERBALANCE SYSTEM IAD CE680 AMM 52-10-50. MED COUNTERBALANCE SYSTEM OPS CHECK GOOD

Part: NONE — NONE · airframe 11,557 hrs · 7,621 cycles

RIGHT MLG BRAKE: RIGHT BRAKE REQUIRED MUCH GREATER THAN NORMAL APPLICATION FORCE BEFORE IT WOULD ENGAGE DURING LANDING ROLLOUT (REPORTED FROM RIGHT SEAT PILOT) // SIGNOFF// VISUALLY INSPECTED BOTH INBOARD AND OUTBOARD RH BRAKE ASSEMBLES FOR ANY DEFECTS/ LEAKS. NONE NOTED AT THIS TIME. (RF 12/10/21} C/W BLEED OF RH BRAKE ASSEMBLIES. NOTED BUBLES IN #3 AND #4 BRAKS. HAD FBO BRING AIRCRAFT OUT FOR TAXI .CHECKS. ALL CHECKS GOOD. REF CE-680 AMM 32-42-10 AND QRH

Part: ENGINE — LEAKING (RIGHT) · airframe 11,282 hrs · 7,426 cycles

COCKPIT ODOR: ABNORMAL ODOR IN COCKPIT AT TAKEOFF POWER. LENGTHY 10-15 MIN TAXI WITH APU OFF. APPLIED TAKEOFF POWER AND WITHIN 5 SECS NOTED UNUSUALLY STRONG ABNORMAL ENVIRON ODOR. ABORTED TAKEOFF AND ODOR APPEARED TO QUICKLY DISSIPATE AS POWER BACK TO IDLE. NOT ELECTRICAL OR BURNING SMELL AND NO SMOKE OR HAZE OBSERVED IN COCKPIT/CABIN. ODOR. DID NOT COME BACK DURING FOLLOWING 10 MIN TAXI BACK TO FBO AND SHUTDOWN. POST BORESCOPE INSP OF LT AND RT ENGINES, FOUND RT ENGINE TO HAVE EVIDENCE OF OIL THRU HIGH PRESSURE BLEED PORT WITH OIL PUDDLING AT BOTTOM. NO ADDITIONAL OIL NOTED THRU OUT INSPECT. MAINTENANCE ACCOMPLISHED IAW EMM 72-00-00. WITH DAA2021-703-PW306C-CG0017 ENGINE CHANGE TO BE ACCOMPLISHED.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 11,282 hrs · 7,426 cycles

COCKPIT ODOR: REPEAT WRITE UP. WITH APU OFF UNPLEASANT STRONG ABNORMAL ODOR IN COCKPIT AND CABIN AFTER TAKEOFF. ODOR WAS ENVIONMENTAL IN NATURE AND WAS STRONGEST AFTER TAKEOFF, IT DISSIPATED DURING THE CLIMB BUT DID BECOME STRONGER IN THE DESCENT OR WITH LARGE POWER CHANGES. PREFORMED ENGINE/APU RUNS AND CONFIRMED THE SMELL IS A MILDEW SMELL AND NOT OIL OR BURNT REMOVED THE CONDENSER BAG PIN 83237-12 SIN NA. CLEANED CONDENSER HOUSING. INSTALLED CUSTOMER SUPPLIED NEW CONDENSER BAG PIN 83237-12 SIN NA. REFERENCE . OPS CHECK NORMAL AT THIS TIME. THE SMELL IS NO LONGER PRESENT AT THIS TIME. WORK DONE JAW CESSNA 680 AMM 21-21-03.

Part: CONDENSER — DIRTY (COCKPIT AIR) · airframe 11,282 hrs · 7,426 cycles

COCKPIT ODOR: UNPLEASANT UNUSUALLY STRONG ABNORMAL ODOR IN COCKPIT JUST AFTER TAKEOFF. ODOR SEEMED TO BE ENVIRONMENTAL, ALMOST OILY IN NATURE BUT NOT ELECTRICAL OR GAS. NO SMOKE/HAZE OBSERVED. ODOR DISSIPATED AND THEN REOCCURRED ON INITIAL DESCENT AND POWER CHANGE. UPON LANDING AND SHUTDOWN ODOR VERY PRONOUNCED IN HELL HOLE COMPARTMENT. DISCOVERED LOOSE HOSE CLAMP CONNECTING LARGE BLACK DUCT TO WHITE BOX DIRECTLY OVERHEAD IN HELL HOLE // SIGNOFF // RE-SECURED LOOSE HOSE CLAMP FOUND IN HELL HOLE. REMOVED WATER SEPERATOR CONDENSOR SOCK AND INSPECTED AND FOUND TO BE DIRTY AND MUSTY SMELLING. INSTALLED NEW SERVICEABLE CONDENSOR SOCK AND PERFORMED OPERATIONAL CHECKS WITH NO DISCREPANCIES NOTED AT THIS TIME. NO FOWL SMELL COMING INTO COCKPIT OR CABIN AT ANY TEMPERATURE SETTING OR POWER SETTINGS. ALL WORK DONE !AW CE 680 AMM 21-21-03.

Part: NOT REPORTED — CORRODED (FUSELAGE) · airframe 10,139 hrs · 6,679 cycles

REPAIRED SPOTS OF CORROSION ON LH AND RH SIDES OF FORWARD DROPPED AISLE PER AEROSPACE QRD ERO-965791, TITLED "FUSELAGE REPAIR", DATED 27 FEB 2020 AND SUPPORTED BY FAA FORM 8110-3 DATED FEBRUARY 27, 2020.

Part: DOOR — CORRODED (EMERGENCY EXIT) · airframe 8,556 hrs · 5,585 cycles

EMERGENCY EXIT DOOR CORRODED BEYOND ECONOMIC REPAIR, REPLACED THE DOOR.

Part: RIB — CORRODED (RT WING) · airframe 8,556 hrs · 5,585 cycles

REPAIRED AREAS OF CORROSION ON LOWER FLANGE OF WING RIB P/N 6922037-20, AT WING STATION 18.50 IN RT MLG WELL PER ENGINEERING MEMO DQ10680M1, DATED JANUARY 5, 2018.

Part: STRUCTURE — CORRODED (EMERGENCY EXIT) · airframe 8,249 hrs · 5,366 cycles

EMERGENCY EXIT HAS CORROSION AROUND MULTIPLE NUT PLATES UNDER CONTOUR RING. BLENDED AREAS. PERFORMED EDDY CURRENT INSPECTION ON BLENDED AREAS. NO CRACKS OR CORROSION INDICATIONS NOTED. PERFORMED ULTRASONIC THICKNESS INSPECTION ON BLENDED AREAS. PREPPED, TREATED, AND PRIMED BLENDED AREAS IAW SRM 51-10-01 AND 51-20-01.

Part: UPLOCK SWITCH — OUT OF ADJUST (RT MLG) · airframe 8,190 hrs · 5,328 cycles

DURING TAKEOFF, THE GEAR HANDLE WAS PLACED IN THE FULL UP POSITION. ALL GREEN GEAR INDICATIONS EXTINGUISHED BUT THE RED UNLOCK LIGHT REMAINED ILLUMINATED. CHECKLIST PROCEDURES WERE PERFORMED AND ALL GEAR EXTENDED AND LOCKED DOWN. PERFORMED LANDING GEAR SWINGS WITH NO FAULTS NOTED. RESISTANCE CHECKS OF ALL UPLOCK SWITCHES ARE GOOD. NOTED THAT THE RT MAIN UPLOCK SWITCH WAS AT LOW END OF SWITCH TRAVEL LIMIT. ADJUSTED RT UPLOCK SWITCH TO HIGH END OF TRAVEL LIMIT. OPS CHECKED GOOD. WORK DONE IAW MM 32-60-00.

Part: APU — COKED (ENGINE) · airframe 7,905 hrs · 5,129 cycles

WHEN HEAT CAME ON AT CRUISE ALTITUDE, A VERY STRONG BURNED OIL ODOR COMES OUT OF THE VENTS. HAD TO TURN THE HEAT DOWN TO AN UNCOMFORTABLY COOLER TEMPERATURE TO REDUCE THE ODOR. TROUBLESHOT THE OIL ODOR, REMOVED THE INLET TO THE APU AND BORESCOPING THE INTAKE AND COMPRESSOR. THE INLET AROUND THE COMPRESSOR WAS COKED WITH OIL AND CARBON. FURTHER INTO THE APU, THE INTAKE WAS COKED AS WELL WITH SIGNS OF FOD ENTERING THE APU. THESE SIGNS INDICATE A FAILURE OF THE COMPRESSOR SEAL. REMOVED THE APU FROM THE ACFT AND INSTALLED A NEW APU IAW MM 49-10-00.

Part: TUBE — CRACKED (APU) · airframe 4,667 hrs

DURING SCHEDULED INSPECTION, WE FOUND APU BLEED AIR TUBE ASSY CRACKED AT THE APU COMPARTMENT ATTACH FLANGE. THE FLANGE WAS CRACKED 2 TO 3" WHERE THE FLANGE IS WELDED TO THE TUBE ASSY.

Part: HOSE — DAMAGED (MLG) · airframe 3,245 hrs · 2,142 cycles

DEPARTED, MOVED GEAR HANDLE TO UP, NOSE GEAR FAILED TO RETRACT FOLLOWED BY BOTH A HYD PRESSURE LOW LT AND HYD VOLUMN LOW AMBER CAS MESSAGES. RETURNED TO DEPARTURE WITH 3 GREEN INDICATIONS AND LANDED UNEVENTFULL. HYD FLUID CAME OUT OF NOSE GEAR AREA AND ON RAMP. DID NOT BLOW BOTTLE. REPLACED NOSE STEERING PRESSURE AND CENTERING HOSES. OPS & LEAK CHECKED GOOD IAW MM 32-50-00.

Part: TUBE — CRACKED (SERVICE AIR)

FOUND SERVICE AIR TUBE ASSY CRACKED IN BEND RADIUS THAT LEADS TO THE RUDDER ACTUATOR IN THE TAIL

Part: ENGINE — VIBRATION · airframe 754 hrs · 520 cycles

RED ENGINE VIBRATION R CAS MSG POSTED REPEATEDLY FOR A FEW SECONDS EACH TIME AND THEN DISAPPEARED ( N1 96.3 , N2 95.4, FL 360, SAT -52*C , RAT -25*C , ISA +3) CRUISE PWR WAS SET. NO VIBRATION WAS EVER EXPERENCED. REPLACED ENGINE HARNESS WIRE PINS AND SOCKETS IAW WDM 20-10-01. ENGINE VIBRATION CHECK AND OPS CHECKS GOOD.

Part: TIRE — FAILED (MLG) · airframe 288 hrs · 186 cycles

BOTH RIGHT MAIN TIRES BLEW ON LANDING. LEFT INBOARD MAIN TIRE FLAT. LEFT OUTBOARD MAIN TIRE FLAT. RIGHT MAIN GEAR DOOR DAMAGED ON LANDING.

Part: UNKNOWN — UNKNOWN (LANDING GEAR) · airframe 11,907 hrs · 9,621 cycles

AFTER DEPARTING, A CONTAMINATING RUNWAY GEAR UNLOCKED LIGHT, ILLUMINATED. CLEANED GEAR AND FLAP WELLS, INSPECTED, AND OPERATED SYSTEMS NUMEROUS TIMES WITH NO DEFECTS NOTED.

Part: SWITCH — OUT OF ADJUST (DOOR WARN SYS) · airframe 11,531 hrs · 9,318 cycles

ON TAKEOFF AT ROTATION, "CABIN DOOR" LIGHT CAME ON. ONCE ON THE GROUND WITH THE DOOR OPEN, LIGHT FLICKERED ON AND OFF SEVERAL TIMES. GAINED ACCESS TO THE CABIN DOOR SWITCH. INSPECTED CONDITION AND WIRING FOUND SATISFACTORY; ADJUSTED SWITCH AND TIGHTENED AS REQUIRED. OPS CHECKED SATISFACTOR IAW CE-560 MM CHAPTER 20-00-00.

Part: ENGINE — FLAMED OUT (RIGHT) · airframe 11,306 hrs · 9,129 cycles

DURING TAXI WHEN THE RT THROTTLE WAS ADVANCED, THEN MOVED TO IDLE, THE RT ENGINE FLAMED OUT. ADJUSTED RT THROTTLE IAW MM 76-11-00. OPS CK NORM.

Part: BRAKE — MALFUNCTIONED (MLG) · airframe 10,748 hrs · 8,693 cycles

LEFT AND RIGHT BRAKES FROM BOTH SEATS FEEL SPONGY. THE LEFT BRAKE (BOTH SEATS) FEELS TO BE WORST THAN THE RIGHT. THE BRAKE WEAR INDICATOR ON THE LEFT MAIN ARE LOW BUT NOT FLUSH. THE BRAKE FLUID RESERVOIR HAS ADEQUATE FLUID. BLED LT AND RT BRAKES IAW 560 MM CHAPT 32-42-00, OPS CHECK AND LEAK CHECK GOOD. SERVICE BRAKE RESERVOIR IAW 560 MM CHAPT 12-12-02

Part: FCU — MISRIGGED (RT ENGINE) · airframe 10,385 hrs · 8,336 cycles

WHEN PERFORMING THE SPEED BRAKE TEST DURING THE (AFTER START) CHECKLIST, THE RT ENGINE SHUTS DOWN WHEN THE THROTTLE IS BROUGHT TO IDLE. ATTEMPTED THE TEST AGAIN AND ENGINE SHUTDOWN (RT) AGAIN. PERFORMED FCU RIGGING INSPECTION IAW MM 73-20-01 AND MM 76-11-00. RIGGING CHECK PROCEDURE. NOTED FCU AND FCU TO AIRFRAME INTERFACE CHECKED GOOD. PERFORMED IDLE CUTOFF CHECK IAW MM 71-01-03 NOTED IDLE CUTOFF CHECKED GOOD NO DISC. NOTED.

Part: WIRE — BURNED (CARGO BAY) · airframe 9,432 hrs · 7,593 cycles

DURING POSTFLIGHT, SMELLED ACRID ELECTRICAL SMELL INSIDE NOSE BAGGAGE COMPARTMENT. SMELL CAME FROM BEHIND PANEL ON AFT SIDE OF NOSE BAGGAGE COMPARTMENT. PERFORMED WIRE BUNDLE/ELECTRICAL COMPONENT INSPECTION, NO DEFECTS NOTED. ACTIVATED EQUIPMENT, FUNCTION CHECKS GOOD. NO SMELL OF ELECTRICAL BURNING PRESENT. WORK DONE IAW CESSNA CITATION MODEL 560 ULTRA MM CH 20-21-03.

Part: SEAL — MALFUNCTIONED (DOOR) · airframe 9,035 hrs · 7,275 cycles

ON TAKEOFF HEARD A POPING NOISE FOLLOWED BY A DOOR SEAL LIGHT AND CABIN DOOR LIGHT. INSPECTED DOOR SEAL AS REQUIRED. PURGED SERVICE AIR SYSTEM AND DOOR SEAL WITH N2 EVACUATING ALL MOISTURE AS REQUIRED. OPS AND LEAK CHECK GOOD. ALL WORK PERFORMED IAW CE-560 MM CHAPTER 21-31-00.

Part: B-NUT — LOOSE (BRAKE SYS) · airframe 8,762 hrs · 7,054 cycles

DURING TAXI ON CO-PILOTS SIDE, LT BRAKE PEDAL GOES NEARLY TO THE FLOOR BEFORE BRAKING ACTION IS FELT. INSPECTED ALL BRAKE MASTER CYLINDERS, FOUND PILOT LT PEDAL MASTER LEAKING. TIGHTENED B-NUT AND BLED BRAKE SYSTEM, NO LEAKS ON OTHER MASTER CYLINDERS OR ON BRAKES, SERVICED BRAKE RESERVOIR. TAXIED AIRCRAFT WITH PILOTS BRAKES OPERATING NORMALLY IAW 560 MM CHAPTER 32-42-02.

Part: HOSE — LEAKING (BRAKE ASSY) · airframe 8,354 hrs · 6,709 cycles

ON LANDING NOTICED NO BRAKING FORCE WITH THE RIGHT BRAKE PEDAL, ON POST FLIGHT INSPECTION FOUND BRAKE FLUID VISIBLY LEAKING FROM RIGHT MAIN WHEEL ASSEMBLY. JACKED AIRCRAFT AND FOUND WITH GEAR EXTENDED THE RIGHT HAND BRAKE HOSE LEAKING. REMOVED AND REPLACED BRAKE HOSE. BLEED BOTH LT AND RT BRAKE ASSEMBLY, OPS CHECK GOOD. LEAK CHECK GOOD IAW CESSNA 560 MM CHAPTER 32-42-01.

Part: SKIN — CRACKED (RUD RT LOWER)

FOUND CRACK ON RIGHT SIDE LOWER RUDDER SKIN. THIS IS THE 2ND TIME A CRACK HAS BEEN FOUND IN THIS AREA ON THIS PARTICULAR RUDDER. THE FIRST WAS AT 718.2 HOURS TOTAL TIME. THE SKIN WAS REPLACED AT THAT TIME AND WAS CHANGED AGAIN THIS TIME. SUBMITTER STATED IT SEEMS THERE MAY BE AN ENGINEERING AND/OR A PRODUCTION DEFECT. NINTH OCCURRENCE IN FLEET.