N661QS

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 15,234 hrs · 11,530 cycles

REPAIRED CORRODED AREA LOCATED AT THE RH SIDE OF THE AFT WALL OF THE NOSE LANDING GEAR WHEEL WELL BY BLENDING, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION. FABRICATED AND INSTALLED REPAIR DOUBLER IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT ENGINEERING REPAIR ORDER.

Part: TIRE — FAILED (ZONE 700) · airframe 14,603 hrs · 11,059 cycles

RT MLG HAD A BLOW OUT HALF WAY THROUGH OUR LANDING ROLL. THE ANTISKID FAIL ANNUNCIATOR ILLUMINATED AROUND THE SAME TIME AS THE AIRCRAFT STARTED TO PULL TO THE RIGHT. AIRCRAFT REMAINED ON RUNWAY, BUT IS DISABLED. REMOVED RH MAIN WHEEL & TIRE ASSY & INSTALLED OVERHAULED UNIT IN RT POSITION. PERFORMED BLEEDING OF ANTI SKID BRAKE SYSTEM IAW 32-44-00, ALSO PERFORMED ANTISKID SYSTEM FUNCTIONAL TEST IAW MM 32-44-00, OPS & LEAK CHECK GOOD. NO DEFECTS NOTED. INSPECTED MG UPPER BARREL-TO-TRUNNION ATTACHMENT, ACTUATOR ATTACHMENTS & SUPPORT STRUCTURE FOR ANY INDICATIONS OF STRUCTURAL DAMAGE. NO INDICATIONS OF STRUCTURAL DAMAGE NOTED AT THIS TIME. PERFORMED UNSCHEDULED HARD/OVERWEIGHT LANDINGS, MX IAW MM 05-50-00.

Part: NONE — DEFECTIVE (COCKPIT) · airframe 14,108 hrs · 10,709 cycles

MAIN HYDRAULICS: DURING A CLIMB GOING THROUGH 11,500 FEET WE HAD A STAB-MIS-COMP ANNUNCIATOR LIGHT COME ON , AFTER ABOUT 30 SECONDS THE AUTO PILOT DISCONNECTED AND THE AIRPLANE PITCHED DOWN AGGRESSIVELY. IT TOOK THE PIC AND SIC TOGETHER TO PULL BACK ON THE YOKE TO STOP THE DESCENT. THE TRIM WHEEL WOULD NOT MOVE FORWARD OR AFT WHEN TRYING TO MOVE IT. AFTER SLOWING DOWN TO 200KTS WE WERE ABLE TO MOVE TRIM WHEEL AND CONTROL THE AIRPLANE. WE RAN THE APPROPRIATE CHECKLIST AND THE STAB-MIS-COMP ANNUNCIATOR LIGHT WENT OUT. HOWEVER, ON FINAL THE STAB-MIS-COMP CAME BACK ON AND STAYED ON UNTIL WE SHUT DOWN THE ENGINES AT FBO // SIGNOFF// APPLIED AIR DATA TEST SET. TESTED STAB SYSTEM SEVERAL TIMES. NOTED THE AIR SPEED SWITCH WORKING INTERMITTENTLY. REMOVED OLD AND INSTALLED NEW SWITCH. LEAK AND OPERATIONAL CHECKS OF SYSTEM GOOD. WORK DONE IAW 560XL MM CH 34-11-01. OLD P/N D45C-24 S/N 2233 NEW P/N D45C-24 S/N 2321

Part: NONE — NONE (ZONE 300) · airframe 14,082 hrs · 10,681 cycles

DURING 48 MONTH INSPECTION FOUND CRACK IN BOTTOM AFT SECTION OF RUDDER TRIM TAB. REPAIRED RUDDER TRIM TAB CRACK PER AQRD ERO-106811 REVISION IR TITLED N661QS RUDDER TRIM TAB REPAIR DATED AUG 25 2022, FAA APPROVED ON FORM FORM 8110-3 DATED AUG 25-2022. CHECKED BALANCE OF RUDDER AFTER REPAIR AND PAINT AND FOUND TO BE WITHIN LIMITS IAW CESSNA 560XL SRM 51-60-00, 51-60-03.

Part: LANDING GEAR — MALFUNCTIONED · airframe 11,534 hrs · 8,868 cycles

GEAR POSITION & WARNING: ON CLIMBOUT, AFTER THE GEAR GEAR AND FLAPS WERE SELECTED UP, THE 3 GREEN GEAR INDICATORS EXTINGUISHED AND THE GEAR UNLOCK LIGHT REMAINED ON WITH THE STAB MISCOMPARE AND HYD PRESS ANNUCIATORS ON. THE CHECKLIST WAS COMPLETED AND THE GEAR EXTENDED WITH 3 GREEN AND NO RED AND THE STAB MISCOMPARE AND HYD PRESS EXTINGUISHED. LANDING WAS NORMAL. NO OVERWEIGHT LANDING AND GEAR EMERGENCY BOTTLE WAS NOT USED. "CORRECTIVE ACTION" NLG STRUT WAS REPLACKED WITH NEW SEALS AND SERVICED AS REQUIRED PERFORMED MULTIPLE OPS CHECKS, OPS CHECKS PASSED LANDING GEAR LIGHTS CAME OFF AND ON AS REQUIRED NOT LEAKS FOUND DISCONNECTED MULE THE SERVICED THE HYDRAULIC RESEVOIR AS REQUIRED IN REF. TO CE-560XL AMM 12-12-01 CE-56XL AMM 12-20-32 AND CE-560XL AMM 32-01-00.

Part: LAMP — BURNED OUT · airframe 13,693 hrs · 10,385 cycles

RIGHT MLG INDICATOR LIGHT: ON FINAL APPROACH WE SELECTED THE GEAR DOWN AND HAD NO RIGHT MAIN GEAR INDICATOR LIGHT TO ILLUMINATE. WE PERFORMED A GO AROUND, PERFORMED THE QRH, AND BLEW THE GEAR DOWN MANUALLY. WE DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. /// CORRECTIVE ACTION /// REMOVED AND REPLACED BULBS IN RH MLG INDICATOR LIGHT. OPS CHECK GOOD. REF CE 560XL MM 33-10-06. PERFORMED MAIN LANDING GEAR HYDRAULIC SYSTEMS-ADJUSTMENT/TEST & VERIFIED THREE GREEN LIGHTS (GEAR DOWN & LOCKED) & NORMAL OPERATION OF GEAR EXTENSION & RETRACTION CYCLE TIME DURING GEAR SWINGS. THEN SERVICED GEAR & BRAKE PNEUMATIC BOTTLE AS REQUIRED. REF CE-560XL MM 32-01-00 & 12-13-01 FOR MX PERFORMED. EMERGENCY RELEASE MECHANISM IS RESTORED TO NORMAL CONFIG. MX VENDOR SUBMITTED SDR #DXTR202204131 FOR SAME EVENT.

Part: LIGHT — BURNED OUT (COCKPIT) · airframe 13,693 hrs · 10,385 cycles

RIGHT MLG INDICATOR LIGHT: ON FINAL APPROACH WE SELECTED THE GEAR DOWN AND HAD NO RIGHT MAIN GEAR INDICATOR LIGHT TO ILLUMINATE. WE PERFORMED A GO AROUND, PERFORMED THE QRH, AND BLEW THE GEAR DOWN MANUALLY. WE DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. REMOVED AND REPLACED BULBS IN RH MLG INDICATOR LIGHT. OPS CHECK GOOD. REF CE 560XL MM 33-10-06. PERFORMED MAIN LANDING GEAR HYDRAULIC SYSTEMS-ADJUSTMENT/TEST & VERIFIED THREE GREEN LIGHTS (GEAR DOWN & LOCKED) & NORMAL OPERATION OF GEAR EXTENSION & RETRACTION CYCLE TIME DURING GEAR SWINGS. THEN SERVICED GEAR & BRAKE PNEUMATIC BOTTLE AS REQUIRED. REF CE-560XL MM 32-01-00 & 12-13-01 FOR MX PERFORMED. EMERGENCY RELEASE MECHANISM IS RESTORED TO NORMAL CONFIG.

Part: TORQUE TUBE — CORRODED (LT ELEVATOR) · airframe 12,553 hrs · 9,563 cycles

LH ELEVATOR TORQUE TUBE IS CORRODED. REMOVED CORRODED INBOARD TORQUE TUBE DUE TO LEVEL 2 CORROSION FROM L/H ELEVATOR P/N 6634200-809LH S/N 0000210. INSTALLED NEW CUSTOMER SUPPLIED TORQUE TUBE P/N 6634002-15 PER CESSNA 560XL SRM 51-40-03, 51-40-06, AND 55-20-02.

Part: UPLOCK SWITCH — OUT OF ADJUST (LANDING GEAR) · airframe 11,990 hrs · 9,163 cycles

ALL LANDING GEAR RETRACTION DID NOT RETRACT - UPON RETRACTION RED UNLOCK LIGHT ILLUMINATED PREFORMED CHECKLIST. // SIGNOFF// JACKED AIRCRAFT TO PERFORM GEAR SWINGS. INSTALLED HYD. ROBO MULE. PERFORMED GEAR SWING FAULT WAS DUPLICATED INSPECTED ALL GEAR FOR PROPER STRUT LENGTH ANY OBVIOUS DEFECT PREVENTING GEAR FROM RED UPLOCK LIGHT FROM EXTINGUISH FOUND GEAR UPLOCK SWITCH SQUAT SWITCH OUT OF RIG. ADJUSTED GEAR UPLOCK SWITCH PERFORMED 6 GEAR SWINGS OPS CHECK GOOD IAW CESSNA C560XM MM32-30-05

Part: GENERATOR — FAILED (RT AC SYSTEM) · airframe 9,622 hrs · 7,408 cycles

EVIDENCE OF A RIGHT AC ALTERNATOR FIRE WAS SEEN. THE ENGINE NACELLE PAINT WAS BURNT AFT OF ALTERNATOR VENT AND MOLTEN COPPER COMING OUT OF THE VENT. TROUBLESHOT TO A FAULTY AC GENERATOR. REMOVED AND REPLACED THE AC GENERATOR AND AC GENERATOR PCU. COMPLIED WTIH ERO-900139. RT ENGINE LOWER COWLING TEMPORARY REPAIR. APPLIED ALUMINIUM TAPE FOR REPAIR. COMPLIED WITH OPERATIONAL CHECK OF THE RT AC GENERATOR AT ALL POWER SETTING WITH NO FAULTS. WORK DONE IAW AMM 29-20-01.

Part: CONTROL BOX — FAILED (FIRE DETECTION) · airframe 9,622 hrs · 7,407 cycles

DURING CLIMB OUT THRU 6500 FEET, RIGHT FIRE LIGHT CAME ON WITH RIGHT FIRE FAULT DET SYSTEM. RAN APPROPRIATE CHECKLIST AND DETERMINED IT WAS A FIRE DETECTION SYSTEM, DECLARED AN EMERGENCY AND RETURNED FOR LANDING. TROUBLESHOT THE RT FIRE DETECTOR SYSTEM, REMOVED & REPLACED THE RT FIRE DETECTOR CONTROL BOX. SYSTEM OPS CHECKED GOOD IAW MM 26-11-02.

Part: COALESCER BAG — DIRTY (CABIN AIR) · airframe 9,170 hrs · 7,067 cycles

ACM PRODUCED A SOCK ODOR. REMOVED & REPLACED DIRTY WATER SEPARATOR CONDENSER CLOTH IAW MM 12-19-02. OPS & LEAK CHECKS WERE GOOD.

Part: LOCK NUT — MISSING (COMBUST LINER) · airframe 5,823 hrs · 4,475 cycles

DURING A BORESCOPE INSPECTION OF COMBUSTION CHAMBER LINER COOLING RING SEGMENT SELF LOCKING NUTS, IAW MFG SPECIAL INSTRUCTION 35-2013. LINER COOLING RING SELF LOCKING NUT ON NR 1 ENGINE HAD MISSING HARDWARE. ENGINE WAS DISASSEMBLED TO GAIN ACCESS TO CC LINER. ENGINE WAS INSPECTED, MISSING HARDWARE WAS LOCATED. NEW HARDWARE WAS INSTALLED. WORK WAS ACCOMPLISHED IN REF TO MM 30J2242 R13.

Part: CONTROL CABLE — FRAYED (ELEVATOR TRIM) · airframe 4,753 hrs

DURING A SCHEDULED INSPECTION, THE ELEVATOR TRIM CABLE WAS FOUND TO BE FRAYED BEYOND LIMITS. THIS CABLE ASSY IS LOCATED WHERE THE CABLE TRANSITIONS FROM A VERTICAL RUN TO THE HORIZONTAL AT A PULLEY LOCATED IN THE HORIZONTAL STABILIZER.

Part: HINGE BRACKET — CRACKED (ELEVATOR) · airframe 4,753 hrs

DURING A SCHEDULED INSPECTION, FOUND RT ELEVATOR INBD HINGE CRACKED, VERIFIED WITH NDT, R & R HINGE ASSY.

Part: UNKNOWN — ODOR (CABIN) · airframe 3,541 hrs · 4,725 cycles

JUST PRIOR TO DECENT, TRANSFERRED FUEL FROM LT TANK TO RT. AFTER WHICH NOTICED ODOR OF FUEL. OPENED OVERHEAD FRESH AIR VENTS & DID NOT SMELL ANYTHING. ON POST FLT DID NOT SMELL FUEL IN THE HOLE OR THE CARGO BAY, ONLY IN THE CABIN & AFT CLOSET. SUSPECT CREW TRACKED SUBSTANCE INTO CABIN. REMOVED CARPET AND SPOT CLEANED AREA, REINSTALLED CARPET. PERFORMED FUEL CROSS FEED TEST, ALL OPS CHECK GOOD, LEAK CHECK GOOD. NO DEFECTS NOTED.

Part: THROTTLE CABLE — BROKEN (NR 1) · airframe 2,567 hrs · 1,967 cycles

WHILE ATTEMPTING TO SET T/O POWER, NR 1 THROTTLE WOULD NOT REMAIN IN T/O DETENT. TAKEOFF ABORTED, NR 2 ENG SHUTDOWN NORMALLY. IN THROTTLE CUTOFF, NR 1 ENG ACCELERATED TO APPROX 72 % N1. WITH EECS SELECTED TO MANUAL, NR 2 ENG NORMAL. PRIOR TO SELECTING EECS MANUAL, BOTH ENGINES SET AT 66% N1. UPON SELECTING MANUAL, UNABLE TO CONTROL NR 1 ENG WITH THROTTLE LEVER & IT ACCELERATES TO 72% N1, UPON ATTEMPTING ENG SHUTDOWN, NR 2 ENG SHUTDOWN NORMALLY, UNABLE TO SHUTDOWN NR 1 ENG WITH EEC IN AUTO. UTILIZED NR 1 ENG FIRE SWITCH TO SHUT DOWN ENG. OPERATED NR 1 , 2 THROTTLES THROUGH ENTIRE OPERATIONS, FOUND THAT NR 2 THROTTLE IS MUCH SMOOTHER THROUGH OPS THAN NR 1. NR 1 IS GRITTY FEELING & WILL NOT STAY AT FULL POWER. PUT NR 1 AT CUFF OFF, DISCONNECTED CABLE FROM FUEL CONT. RAN THROUGH OPS, FELT SAME, LINKAGE NOT MOVING. DISASSEMBLED CENTER PEDISTAL & PILOTS FLOOR & SEAT IN ORDER TO CHECK FOR MOVEMENT OF PUSH RODS, TORQUE TUBE & FWD LINKAGE, ALL OPS NORMAL OTHER THAN GRITTY FEEL & NOT HAVING FULL MOTION. STARTED DIS-ASSEMBLY OF AFT CABIN AND DISCONNECTED FWD CABLE FROM AFT CABLE TO CHECK FOR MOVEMENT AT CONNECTIONS MORE REMOVAL OF FURNISHING AND CABLE CLAMPS REQ IN ORDER TO GET CABLES SEPERATED. IAW 560XL M/M 76-11-03. SEPERATED CABIN BELOW AFT CABIN AREA. FWD CABLE IS SMOOTH. DISCONNECTED AFT CABLE FROM MID CABLE IN AFT BAGGAGE SIDE WALL OVER DOOR. MID CABLE CHECKS GOOD. FOUND AFT CABLE BINDING. DISCONNECTED CLEVIS AT THROTTLE BELLCRANK. REMOVED CABLE RIBBON FROM CABLE SHROUD- CABLE BROKEN. REPLACED CABLE IAW 560XL MM CHAPT 76-11-03. GROUND RUNS & OPS CHECKS GOOD AFTER RECONNECTING CABLES & RIGGING CABLES. ORIGINAL SUBMISSION: 9/23/2009

Part: ACTUATOR — LACK OF LUBE (ELEVATOR TRIM) · airframe 1,952 hrs · 1,493 cycles

22-1 AUTO PILOT DISENGAGED 5 SECONDS AFTER SELECTING FLAPS TO 15 DEGREES. AUTO PILOT FAIL AMBER LIGHT SHOWED ON PFD'S. SEEMED LIKE AUTO PILOT TRIM COULD NOT KEEP UP. LUBRICATED ELEVATOR TRIM ACTUATORS AND COMPLIED WITH A SATISFACTORY OPS CHECK OF THE ELEVATOR TRIM SYS AND AUTO PILOT SYS IAW CH'S 22-11-01. AND 27-32-04 OF THE MM.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 1,952 hrs · 1,493 cycles

AUTO PILOT DISENGAGED 5 SECONDS AFTER SELECTING FLAPS TO 15 DEGREES. AUTO PILOT FAIL AMBER LIGHT SHOWED ON PFD'S.

Part: AUTOPILOT SYS — FAILED · airframe 1,952 hrs · 1,493 cycles

AUTO PILOT DISENGAGED 5 SECONDS AFTER SELECTING FLAPS TO 15 DEGREES. AUTO PILOT FAIL AMBER LIGHT SHOWED ON PFD'S. SEEMED LIKE AUTO PILOT TRIM COULD NOT KEEP UP. LUBRICATED ELEVATOR TRIM ACTUATORS AND COMPLIED WITH A SATISFACTORY OPS CHECK OF THE ELEVATOR TRIM SYS AND AUTO PILOT SYS IAW MM 22-11-01 & 27-32-04.