N602QS

Part: STRINGER — CRACKED (ZONE 200) · airframe 16,381 hrs · 12,689 cycles

DURING INSPECTION FOUND FUSELAGE STRINGER 15L IS CRACKED ON THE AFT END OF THE TAIL CONE SECTION AT F.S. 580.00. TRIMMED DAMAGED STRINGERE AND PERFORMED A DOUBLER REPAIR IAW APPROVED DATA.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 16,323 hrs · 12,647 cycles

EMERGENCY LIGHTING: DROPPED AISLE LIGHTS, LEFT FORWARD HALF, THE MAJORITY OF THEM ARE INOP. IT APPEARS THE SECTION BETWEEN SEAT 3 AND 5 ARE INOP. // SIGNOFF/ REPAIRED WIRING CONNECTION TO AISLE LIGHT STRIP AT SEAT 3 REF CE560XL SPM 20-30-20 & OPS CKED EMERG EXIT DROPPED AISLE LIGHTS NORMAL REF CE560XL AMM 33-50-00

Part: PCB — DEFECTIVE (ZONE 800) · airframe 16,099 hrs · 12,473 cycles

MAIN CABIN DOOR ANNUNCIATOR IS ILLUMINATED WITH AN ASSOCIATED VENT DOOR SIX PACK LIGHT. WHEN THE VENT DOOR IS MANUALLY CLOSED, VENT DOOR, SIX PACK LIGHT EXTINGUISHERS, BUT CABIN DOOR ANNUNCIATOR REMAINS ON WITH THE MAIN CABIN DOOR CLOSED & LOCKED. BOTTOM FORWARD LOCK FLAG IS PARTLY OUT OF VIEW. LOCATED & ADJUSTED FLAG AS NEEDED. INSTALLED STEPS TO VERIFY THAT FLAGS ARE ALL ABLE TO BE SEEN WHEN DOOR IS LOCKED. OPS CHECK GOOD. WORK PERFORMED IAW AMM 52-10-01. REMOVED OLD CABIN DOOR PCB & INSTALLED INSPECTED DOOR PCB, OPS CHECK GOOD IAW AMM 24-51-02 & 52-10-00. OPS CHECKED DOOR VENT SYS, DOOR VENT CLOSED, 6 PACK EXTINGUISHED & CABIN DOOR OPEN ANNUNCIATOR EXTINGUISHED. OPS CHECKED GOOD.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 15,960 hrs · 12,362 cycles

FOUND CORROSION AROUND FASTENER HOLE ON LH WING UPPER SKIN AT WS 64.073. REPAIRED IAW NETJETS RFTS 108114 REV.0 DATED 16MAY2023. THIS IS A PERMANENT REPAIR

Part: HEAT EXCHANGER — DAMAGED (ACM) · airframe 15,960 hrs · 12,362 cycles

INSTALLED AIR CYCLE MACHINE (ACM) HEAT EXCHANGER THAT UNDERWENT A MAJOR REPAIR DUE TO BOTH HEAT EXCHANGERS BEING DAMAGED. HEAT EXCHANGER UNIT WAS REPAIRED UNDER THE FOLLOWING REFERENCES: AQRD RS-890517 REV C DATED 06/14/2020, AQRD RS-890517-1 REV C DATED 06/14/2020, AQRD EWO-2700 REV IR DATED 12/15/2021, AND FAA 8110-3 DATED 6/15/2020 SIGNED BY DERT-710086-SW.

Part: DOOR LATCH — LACK OF LUBE · airframe 15,626 hrs · 12,123 cycles

MAIN DOOR HANDLE: MAIN CABIN DOOR HANDLE VERY HARD TO LATCH CLOSED. SEEMS TO BE BINDING. // SIGNOFF// VERIFIED MED IS DIFFICULT TO LATCH. LUBED ALL PINS IN DOOR. DOOR STILL HAS A CATCH WHEN LATCHING. REMOVED FIXED STAIRS. PERFORMED GVI OF DOOR PULLIES. NOTICED AT POINT AT HANDLE BARREL HAS FRICTION_ LUBED POINTS OF CONTACT DOOR NOW LATCHES SMOOTHLY. WERT PERFORMED WITH REFERENCE TO CITATION 560 XL AMM 52-10-02

Part: ROLL PIN — FAILED (MED HANDRAIL) · airframe 15,485 hrs · 12,025 cycles

MAIN CABIN DOOR HANDRAIL DOES NOT LOCK THE DOOR IN THE DOWN POSITION. HANDRAIL CAN BE MOVED ALMOST STRAIGHT DOWN AND DOES NOT STOP IN CORRECT POSITION. PIN MISSING IN HANDRAIL LOCKING ASSYMBLY. FOUND PIN HARDWARE ON GROUND. REINSTALLED ORIGINAL ROLL PIN AND PERFORMED OPS CHECKS OF MAIN ENTRY DOOR. OPS CHECKED GOOD. WORK DONE IAW MM 52-10-00.

Part: NOT REPORTED — NOT REPORTED · airframe 14,598 hrs · 11,382 cycles

CABIN DOOR PRECATCH WILL NOT RELEASE CABIN DOOR. // SIGNOFF// ADJUSTED CABIN DOOR PRECATCH IAW CESSNA 560XL MM 52-10-01. OPS CHECK GOOD AT THIS TIME.

Part: HANDLE — LACK OF LUBE (PAX DOOR) · airframe 14,107 hrs · 11,032 cycles

MAIN DOOR HANDLE: MAIN DOOR HANDLE IS VERY DIFFICULT TO OPEN FROM BOTH OUTSIDE AND INSIDE THE AIRCRAFT. GAINED ACCESS TO MAIN DOOR HANDLE. INSPECTED, CLEANED AND LUBRICATED THE DOOR HANDLE AND LINKAGES, OPERATIONAL TEST OF MAIN DOOR CHECKED GOOD IAW CE-560XL MM 52-10-00, NO DEFECTS NOTED. CLOSED UP ACCESS.

Part: CONNECTOR — FAILED (EMERGENCY LIGHTS) · airframe 14,028 hrs · 10,971 cycles

EMERGENCY LIGHTING: ON POST FLIGHT FOUND THAT ALL OF THE LEFT FORWARD DROPPED AISLE LIGHTING SYSTEM IS NOT WORKING. // SIGNOFF// INSPECTED LH AISLE DROP LIGHTING ELECTRICAL CONNECTOR AND FOUND MOLEX CONNECTOR DISCONNECTED AND 1 WIRE PULLED FROM THE ELECTRICAL CONNECTOR AIRFRAME SIDE. EXTRACTED PIN FROM DROP AISLE LIGHTING CONNECTOR AND CRIMPED BACK ON TO PULLED WIRE IAW CE-560XL SPM 20-30-25. RESEATED CONNECTOR AND PERFORMED SUCCESSFUL OPERATIONAL TEST OF THE AISLE LIGHTING AS REQUIRED. WORK DONE IRW CE-560XL IMM 25-92-1 2.

Part: DOOR — BINDING (MAIN PAX) · airframe 13,547 hrs · 10,611 cycles

NO RESISTANCE ON MAIN DOOR WHEN OPENING FROM THE OUTSIDE. EXTREMELY HARD TO PULL DOOR IN WHEN CLOSING FROM THE INSIDE. CORRECTIVE ACTION: OPERATED CABIN DOOR MULTIPLE TIMES AND VERIFIED SQUAWK. MEASURED PRECATCH PLUNGER RETRACTION INTO HOUSING AND VERIFIED PLUNGER IS FLUSH WITH HOUSING WITH PRECATCH BUTTON PUSHED, IAW 560XL MM 52-10-00. NOTICED WITH CLOSING CABIN DOOR, DOOR HAD EXCESSIVE TENSION CAUSING DOOR TO RETRACT HALFWAY AUTOMATICALLY WHEN INITIALLY CLOSING THE DOOR. DOOR STEPS AND OPERATED DOOR. DOOR OPERATED CORRECTLY AND PRECATCH WORKS GOOD. WORK DONE IAW 560XL MM52-10-03.

Part: DOOR — BINDING (MAIN CABIN) · airframe 13,410 hrs · 10,496 cycles

MAIN CABIN DOOR IS VERY HEAVY TO OPEN FROM BOTH OUTSIDE & INSIDE. CONFIRMED WRITE UP CHECKED SPADE DOOR AND TELESCOPING RODS, BOTH CHECKED GOOD, REMOVED STEPS AND OPERATED DOOR, FOUND THAT DOOR WOULD START TO COME UP BUT THEN STOP, BUT WHEN PUSHED UP THE SPRINGS WOULD CATCH THEN EXPAND COUNTER BALANCE SPRINGS EXPECT SPRINGS TO HAVE CRACKS. REMOVED AND REPLACED COUNTER BALANCE SPRINGS IAW CESSNA CE-560XL MM CH 52-10-03. OPS CHECKED SATISFACTORY.

Part: ACTUATOR — OUT OF LIMITS (RUDDER) · airframe 12,202 hrs · 9,625 cycles

DURING TAKEOFF AND CLIMB COPILOTS RIGHT OUT BOARD PEDAL COULD NOT BE MOVED. WITH AUTO PILOT AND YAW DAMP OFF FROM COPILOTS SIDE RIGHT RUDDER (OUTBOARD PEDAL) COULD NOT BE MOVED. FROM PILOT SIDE INFLIGHT WITH AUTO PILOT AND YAW DAMP OFF RIGHT PEDAL COULD WHEN PUSHED BE MOVED BUT SEEMED VERY STIFF AND MUCH HARDER TO PUSH THAN THE LEFT PEDAL. ONCE WE RETURNED FOR LANDING RUDDER FUNCTION SEEMED TO PERFORM NORMAL DURING TAXI BACK TO RAMP. DISCONNECTED NWS BUNGEE FROM STEERING ARM, CONNECTED AFTER PEDAL STIFFNESS TEST. PERFORMED RUDDER PEDAL STIFFNESS TEST IAW MM 27-20-05. FOUND ALL PEDALS IN BOTH DIRECTIONS BREAKING OUT AT 19-20 LBS. NO GRAININESS OR INCONSISTENCY FOUND IN RUDDER PEDAL MOVEMENT, IAW THE MANUAL, THE ACTUATOR IS ACCEPTABLE. REPLACED THE RUDDER BIAS ACTUATOR, DETENSIONED RUDDER BIAS CABLE, RUDDER BIAS ACTUATOR, TENSIONED RUDDER BIAS CABLE AND SAFETIED TURNBARREL. PERFORMED RUDDER BIAS OPS CHECK AND RUDDER PEDAL STIFFNESS TEST. RUDDER PEDAL BREAKOUTS IMPROVED TO 16-17 LBS. WITHIN MM LIMITS. LEAK CHECKED RUDDER BIAS ACTUATOR BLEED AIR FITTINGS. ORIGINAL SUBMISSION DATE. 02/13/2019

Part: ENGINE — MALFUNCTIONED (RIGHT) · airframe 11,777 hrs · 9,289 cycles

RIGHT ENGINE OIL PRESSURE INDICATION NOT READING, RIGHT ENGINE OIL PRESSURE DROPPED TO ZERO IN FLIGHT. ABNORMAL CHECK LIST REQUIRED ENGINE SHUTDOWN. ENGINE ITT TEMP NORMAL AND ENG OIL TEMP NORMAL. INSPECTED RIGHT ENG OIL LEVEL AND FOUND TO BE 1 QUART LOW BUT NO INDICATION OF ANY OIL LOSS. R&R RIGHT ENGINE

Part: STRAKE — CORRODED (RT WING) · airframe 11,387 hrs · 8,860 cycles

RIGHT WING, TOP SPAR HAS A COUPLE OF AREAS OF SUSPECTED CORROSION ON THE LT AND RT STRAKES NEAR THE COMPOSITES. FABRICATED AND INSTALLED REPAIR DOUBLERS.

Part: SKIN — GOUGED (DOOR INTERIOR) · airframe 11,609 hrs · 9,148 cycles

THE MAIN ENTRY DOOR HAS A GOUGE ON THE INNER SURFACE OF THE DOOR SKIN IN THE FWD COUNTERBALANCE SPRING BAY. THERE IS A DENT ON THE EXTERIOR SURFACE AT THE SAME LOCATION.

Part: ANTENNA — DETACHED (HF SYSTEM) · airframe 10,180 hrs · 8,041 cycles

THE HF ANTENNAE IS DETACHED FROM THE VERTICAL STABILIZER AND IS HANGING FROM TOP OF FUSELAGE. TECH DISCOVERED DAMAGE TO TAILCONE WHILE PERFORMING MEL PROCEDURE. REMOVED HF ANTENNA SUPPORT SLEEVE & ELBOW AND INSTALLED HF ANTENNA, HF ANTENNA SUPPORT SLEEVE, ELBOW, AND APPROVED ALTERNATE PN HF ANTENNA TENSION UNIT. OPS CHECKS NORMAL. COMPLETED REPAIR PROCEDURE FOR DAMAGE AREA 3, 5 AND 6 STEPS 1-5. COMPLIED WITH ERO 851404, REV IR TAIL CONE REPAIR PROCEDURES FOR DAMAGE AREAS 1, 2, 4 STEPS 5-9. COMPLIED WITH REPAIR PROCEDURES FOR DAMAGE AREAS 3, 5, 6 STEPS 6-9. REINSTALLED TAIL CONE, WORK PERFORMED IN REF WITH MM 53-10-15. PARTS REPLACED: TENSION UNIT ANTENNA, PN: 5ARM300-11C-5LN, ELECTRIC CABLE, PN: 14379-

Part: BRAKE CABLE — BROKEN (BRAKE SYS) · airframe 9,705 hrs · 7,659 cycles

LEFT BRAKE PEDAL ON LT SEAT HAS NO PRESSURE. LT WEAR PIN WILL MOVE WHEN LT BRAKE ON THE RT SEAT IS PRESSED. FOUND PILOT'S LT MIDDLE BRAKE CABLE BROKEN. R & R CABLE WITH NEW IAW MM 32-44-10. RIGGED & SAFETIED CABLE, TAXI CHECKED GOOD AT THIS TIME.

Part: BRAKE ASSY — FAILED (LT MLG) · airframe 8,372 hrs · 6,614 cycles

LEFT MAIN TIRE FAILED ON LANDING ROLL OUT. SUSPECT FAILURE OF ANTISKID. LT BRAKE APPEARS TO HAVE LOCKED UP. R & R LT BRAKE WITH OVERHAULED UNIT IAW MM 32-42-01. PERFORMED BLEED OF LT BRAKE IAW MM 32-42-00. OPS & LEAK CHECKED GOOD.

Part: SPRING — FAILED (BRAKE SYS) · airframe 8,277 hrs · 6,534 cycles

WITH EQUAL PRESSURE APPLIED TO BOTH BRAKE PEDALS, ACFT PULLS HARD TO THE LEFT. FOUND THAT BRAKES HAD A BROKEN RETURN SPRING AT LT POWER BRAKE METERING VALVE ACTUATION ARM. R & R SPRING, OPS CHECKED GOOD IAW MM 32-44-10.

Part: CABLE ASSY — FRAYED (COCKPIT) · airframe 8,111 hrs · 6,407 cycles

DURING A SCHEDULED INSPECTION, BRAKE METERING VALVE AND THE RT FORWARD CABLE WAS FOUND TO BE DEFECTIVE, FRAYED, APPROXIMATELY 18 INCHES FROM CLEVIS WHERE IT ATTACHES TO THE BRAKE PEDAL. THERE WERE NO SIGNS OF THE CABLE CONTACTING ANY STRUCTURAL MEMBERS OR IN AN AREA THAT A PULLEY WOULD CAUSE A SHARP BEND. IT WAS NOTED THAT THE CABLE FRAYING OCCURRED IN A STRAIGHT RUN. THE OTHER RT CABLE WAS CHANGED AS A PRECAUTIONARY MEASURE.

Part: UPLOCK SWITCH — INOPERATIVE (NLG) · airframe 7,310 hrs · 5,716 cycles

NOSE GEAR DID NOT RETRACT AFTER TAKEOFF. GREEN NOSE GEAR LIGHT ON AND RED GEAR UNLOCK LIGHT ON. NO OTHER INDICATIONS. SELECTED GEAR DOWN GOT ALL 3 GREEN DOWN AND LOCKED AND NO RED AND LANDED. JACKED ACFT. RETRACTED GEAR, FOUND NLG WOULD PARTIALLY RETRACT THEN WOULD FAIL TO EXTEND POSITION ONCE MLG WERE UP AND LOCKED. RANG OUT NLG UPLOCK SWITCH. FOUND PINS D AND E OPEN. SHOULD BE NORMALLY CLOSED. R & R NLG UPLOCK SWITCH. ADJUSTED SWITCH IAW MM 32-30-05. PERFORMED LANDING GEAR FUNCTIONAL CHECK. SYS CHECK GOOD IAW MM 32-01-00. REMOVED MULE ON STICK. DOWN JACKED ACFT.

Part: UPLOCK SWITCH — FAILED (MLG) · airframe 7,231 hrs · 5,650 cycles

AFTER TAKEOFF, BROUGHT GEAR UP AND NOTICED A THUMPING SOUND LIKE A TIRE HITTING SOMETHING SPINNING DOWN, SAW THE HYDRAULIC ANNUNCIATOR FLASHING ON AND OFF, WITH THE RED GEAR UNLOCK LIGHT ALSO FLASHING ON AND OFF. ALL THREE GREEN GEAR LIGHTS WERE OUT. EXTENDED GEAR AND THE NOISE WENT AWAY, RECEIVED THREE GREEN GEAR LIGHT ON AND RED GEAR UNLOCK LIGHT WENT OUT. RETURNED AND LANDED WITH NO OTHER PROBLEMS. DURING GEAR SWING, GEAR WOULD NOT REMAIN UP AND WOULD CREATE A THUMPING SOUND. INSPECTED UPLOCKS TO FIND RIGHT UPLOCK SWITCH FAULTY. REMOVED AND REPLACED RIGHT UPLOCK SWITCH WITH NEW SWITCH IAW MM 32-30-05. RIGGED UPLOCK SWITCH. OPERATIONAL CHECKED NORMAL.

Part: SPIGOT — CORRODED (HORIZONTAL STAB) · airframe 11,414 hrs · 4,072 cycles

LEFT HORIZONTAL STAB SPIGOT FITTING CORRODED.

Part: WARNING LIGHT — FALSE ACTIVATION (MLG) · airframe 5,580 hrs · 4,365 cycles

WHEN EXTENDING THE GEAR FOR LANDING, THE LEFT MAIN DOWN LIGHT DID NOT ILLUMINATE AND THE UNSAFE LIGHT DID NOT EXTINGUISH. AFTER ABOUT ONE MINUTE, THE GEAR DOWN INDICATOR LIGHTS ILLUMINATED AND THE THE GEAR UNSAFE LIGHTS EXTINGUISHED.

Part: ACTUATOR — SLOW (LT MLG) · airframe 5,580 hrs · 4,365 cycles

WHEN EXTENDING THE GEAR FOR LANDING, THE LEFT MAIN DOWN LIGHT DID NOT ILLUMINATE AND THE UNSAFE LIGHT DID NOT EXTINGUISH. RAN ROTARY TEST AND ASSURED THAT ALL GEAT INDICATORS WERE WORKING, AND EXTENDED FLAPS BEYOND 15 DEGREES AND RECEIVED WARNING HORN. AFTER ABOUT 1 MINUTE, GEAR DOWN INDICATOR LIGHTS ILLUMINATED AND GEAR UNSAFE LIGHTS EXTINGUISHED. THERE WAS NO ACCOMPANYING GEAR MOVEMENT NOISE JUST PRIOR TO WHEN THE LIGHTS INDICATED DOWN. REMOVED LT MAIN GEAR ACTUATOR. INSTALLED NEW ACTUATOR AND SLOW CYCLED GEAR. HYD SYS CHECKED LEFT GEAR CAMBER. CAMBER CHECKED GOOD. ACTUATOR INSTALLED WITH NEW ATTACH HARDWARE. ALL WORK IAW 32-30-04 OF MM. OPS CHECK AND LEAK CHECKED GOOD.

Part: SWITCH — MALFUNCTIONED (THROTTLE) · airframe 5,441 hrs · 4,260 cycles

GEAR WARNING HORN INTERMITTENT. HORN DIDN'T WORK DURING ROTARY TEST WITH APU. SHUT ALL ELECTRICAL OFF, DISCONNECTED BATTERY, RETRIED WITH BATTERY POWER AND HORN DIDN'T WORK. RETRIED WITH APU AND HORN CAME ON AFTER 15-20 SECONDS. REPLACED THE RT THROTTLE SWITCH BANK AND RIGGED SWITCHES IAW MM CH 76-11-00. GEAR WARNING HORN OPS CHECKED GOOD.

Part: COMPUTER — FAILED (AHRS) · airframe 5,239 hrs · 4,101 cycles

ATTITUDE AND HEADING ON CO-PILOTS PFD FAILED SHORTLY AFTER TAKEOFF. REMOVED INTERMITTENT AHRU NR 2. INSTALLED A REPAIRED AHRU NR2. SYS OPS CHECKED GOOD. WORK DONE IAW AMM 34-21-01.

Part: INLET — CONTAMINATED (APU) · airframe 8,372 hrs · 6,739 cycles

SMOKE IN CABIN. APU WAS RUNNING FOR APPROX 5 MINS WITH BLEED OFF. NOTICED NO SMOKE. TURNED BLEED ON AND AFTER APPROX 2 MINS HAD SMOKE IN THE CABIN. LATER WE RAN BOTH ENGINES WITH NO APU AND DID NOT NOTICE ANY SMOKE. FOUND OIL IN APU AIR INLET. REMOVED WATER SOCK, CLEANED, AND CLEANED DUCT. INSTALLED WATER SEPARATOR IAW MM 12-19-02. RAN BOTH ENGINES AND SMOKE IN CABIN OR COCKPIT.

Part: WARNING LIGHT — ILLUMINATED (TAIL DE ICE) · airframe 4,580 hrs · 3,569 cycles

ENROUTE, LT TAIL DEICE FAIL LIGHT ILLUMINATED. SELECTED OFF THEN MANUAL IAW THE ABNORMAL CHECKLIST WITH NO CHANGE . ACFT WAS AT FLT 270 DURING FAILURE.

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 4,162 hrs · 3,242 cycles

EEC MANUAL LIGHT ILLUMINATED ON NR 2 ENGINE DURING DESCENT FOLLOWED BY LOSS OF THRUST AND CONTINUOUS COMPRESSOR STALLS. AFTER DOWNLOADING DCU FILES AND SENDING TO MANUFACTURER. REMOVED REPLACED AND OPS CHECK GOOD OF RT BLED AIR TORQUE MOTOR IAW MM 73-20-03, 75-30-01 AND 71-00-00.

Part: WARNING LIGHT — ILLUMINATED · airframe 3,826 hrs · 2,994 cycles

AFTER TAKEOFF AND GEAR RETRACTED, THE GEAR UNLOCK LIGHT REMAINED ILLUMINATED.

Part: STRUT — LEAKING (NLG) · airframe 3,826 hrs · 2,994 cycles

AFTER TAKEOFF AND GEAR RETRACTED, THE GEAR UNLOCK LIGHT REMAINED ILLUMINATED. RAN CHECKLISTS AND NOSE GEAR EXTENDED WHEN HYD CTRL CB WAS PULLED. LOWERED GEAR AND LANDED NORM. POST FLIGHT REVEALED FLAT NOSE STRUT AND FLUID LEAKAGE. DISASSEMBLED NOSE STUT AS NESSISERY INSTALLED SEAL KIT CPDL32-1 AND ASSEMBLED REF CMM 32-20-01 REV 7. SERVICED WITH SKYDROL AND NITROGEN IAW MM 12-14-00. INSPECTED UPLOCK DOORS, AND ACTUATORS FOR GENERAL CONDITION ALL OK COMPLETED 5 FAULT FREE CYCLES.

Part: ANTI-ICE SYSTEM — MALFUNCTIONED (RT ENGINE) · airframe 835 hrs · 646 cycles

DURING TAKEOFF ROLL RT ENGINE ANTI-ICE ANNUNCIATOR ILLUMINATED WITH SWITCH IN THE OFF POSITION. TAKEOFF ABORTED. TROUBLESHOT ENGINE ANTI-ICE SYSTEM, PERFORMED ENGINE ANTI-ICE SYSTEM, FUNCTIONAL CHECK PER CESSNA 560XL MAINT MANUAL 30-11-00-710 SYSTEM FUNCTIONS PROPERLY AT THIS TIME.