N635QS

Part: TILLER — FAULTY · airframe 5,366 hrs · 3,484 cycles

DURING TAXI OUT TILLER BOUND AND STUCK LEFT. HAD TO STOP THE AIRCRAFT IN ORDER FOR IT TO FREE UP. ALSO NOTICE DURING THE LANDING PHASE AT LOWER SPEEDS AIRCRAFT, TENDED TO TRACK LEFT AND RIGHT. ALSO NOTICED A CLICK AND BIND IN THE TILLER. CORRECTIVE ACTION:REMOVED AND REPLACED TILLER HANDWHEEL IAW AMM 32-50-00. PERFORMED HANDWHEEL OPS CHECKED AND TAXI CHECKS. AIRCRAFT TAXI CHECKS SATISFACTORY. NO DEFECTS FOUND AT THIS TIME.

Part: UPLOCK SWITCH — DEFECTIVE (ZONE 700) · airframe 4,813 hrs · 3,091 cycles

LEFT MAIN GEAR HAS YELLOW X WHEN EXTENDED. RAN CHECKLIST AND GEAR STILL DOES NOT SHOW DOWN AND LOCKED. CORRECTIVE ACTION: REPLACED LH MLG UPLOCK SWITCH OPS CHECK GOOD IAW CE680A AMM 32-32-25

Part: STARTER — FAULTED (APU) · airframe 4,121 hrs · 2,715 cycles

DURING LEVEL FLIGHT 380 WE NOTICED THE RIGHT GEN OVERCHARGING AND AMPS VARYING BETWEEN 40 AND 80. RIGHT BATTERY WAS 10 DEGREES WARMER THEN LEFT. FUEL FLTR BYPASS R AMBER CAS: DURING DESCENT FROM 360 WE RECEIVED A FUEL FILTER BYPASS RIGHT AMBER CAS MESSAGE. REPOSITIONED APU AND RH ENGINE STARTERS IAW AMM, 80-10-25 AND 80-10-20, OPS CHECKS SATISFACTORY AT THIS TIME. REMOVED/INSTALLED APU STARTER. REMOVED/INSTALLED RH ENG STARTER . REMOVED/INSTALLED BATTERY.

Part: SKIN — DAMAGED (RUDDER) · airframe 13,290 hrs · 10,456 cycles

OVER TRAVEL DAMAGE TO RIGHT RUDDER SKIN AND VERTICAL SKIN AT THE ACTUATOR CUTOUT.

Part: BRAKE — MALFUNCTIONED (LT MLG) · airframe 8,993 hrs · 7,082 cycles

DURING TAXI THE LT BRAKE IS VERY SENSITIVE & GRABBING. IT WAS OBSERVED DURING LANDING ROLLOUT & TAXI IN. BLED LT BRAKE SYSTEM, SERVICED BRAKE RESERVOIR. OPS AND LEAK CHECKED GOOD IAW 32-42-00.

Part: GCU — FAILED (APU) · airframe 7,603 hrs · 5,997 cycles

ON THE GROUND WITH THE APU RUNNING AND GENERATOR ONLINE, THE COCKPIT LIGHT STARTED GETTING BRIGHT AND THE AVIONICS FAN STARTED SPEEDING UP. I SAW THE VOLTS RAPIDLY CLIMB, AND THE GCU DID NOT KICK THE GENERATOR OFFLINE UNTIL APPROX 33 VOLTS. AN UNUSUAL SMELL WAS ALSO NOTED FROM UNKNOWN SOURCE. REMOVED AND REPLACED APU GCU IAW MM 24-31-02. OPERATIONAL CHECK GOOD. PERFORMED GENERAL OPERATION ON SYSTEMS IN COCKPIT WITH REF TO A/C FLIGHT MANUAL CHECKLIST AND OPERATIONAL CHECK GOOD. NO UNUSUAL SMELLS NOTED.

Part: COALESCER BAG — CONTAMINATED · airframe 7,448 hrs · 5,863 cycles

AFTER 10-15 MINUTES OF FLIGHT THERE IS AN ODOR (DIRTY DIAPER/OLD SOCKS) APPARENT IN THE CABIN THAT MOVES FORWARD TO THE COCKPIT. ODOR IS NOT NEAR THE FLOOR, ONLY MID CABIN AND HIGHER. CLEANED WATER SEPARATOR AND LT & RT OZONE CONVERTERS. LEAK AND OPS CHECK NORMAL. WORK IAW MM 12-19-02. RAN ACFT AND ISOLATED LT ENGINE, RT ENGINE AND APU BLEED SOURCES. NO ABNORMAL ODOR NOTED. CLEANED WATER SEPARATOR AND LT & RT OZONE CONVERTERS. LEAK & OPS CHECK DUE. OPS & LEAK CHECKS NORMAL IAW MM 12-19-02.

Part: LINE — MISINSTALLED (RUDDER) · airframe 5,598 hrs · 4,352 cycles

WHILE ACCOMPLISHING THE RUDDER BIAS CHECK, WHEN PUSHING RT THROTTLE UP, LT PEDAL ADVANCED. WHEN PUSHING LT THROTTLE UP, RT PEDAL ADVANCED. INSPECTED & FOUND LINES INSTALLED IN WRONG POSITION. REMOVED RUDDER BIAS VALVE. REMOVED FITTINGS GOING INTO VALVE AND REPOSITIONED LINES IN TAIL CONE GOING TO VALVE TO THE CORRECT POSITION. REINSTALLED FITTINGS IN CORRECT POSITION, REINSTALLED RUDDER BIAS VALVE AND CONNECTED LINES. RAN BOTH ENG'S OPS CHECK GOOD IAW MM 27-20-05.

Part: GENERATOR — FAILED · airframe 5,160 hrs · 3,996 cycles

DUAL GENERATOR FAILURE WITH ACCOMPANYING GEN ANNUNCIATOR L/R AND MASTER WARNING. FAILURE OCCURED WHILE CLIMBING THROUGH 15,000' WITH APU GEN ON AND LASTED 3-4 SECS. BOTH AMPHERES READ "0" BEFORE RETURNING ON LINE.

Part: WHEEL — CRACKED (TRIM) · airframe 3,997 hrs · 3,047 cycles

TRIM INDICATOR IS NOT INDEXED CORRECTLY. TRIM WAS CHECKED AND SET TO TAKEOFF RANGE BEFORE START. JUST PRIOR TO ENGINE START, BOTH PILOTS NOTICED TRIM INDICATOR FULL FORWARD. TRIM WAS RESET TO TAKEOFF RANGE, TAXI AND TAKEOFF WERE BEGUN. DURING TAKEOFF, YOKE STARTED MOVING AFT BEFORE FIRST OFFICER STARTED PULLING AFT FOR ROTATION. AFTER TAKEOFF FIRST OFFICER STARTED CALLING FOR FORWARD TRIM, THEN ASKED FOR PITCH TRIM C.B. TO BE PULLED. HE STATED THAT AFTER PITCH TRIM C.B. WAS PULLED, HE DIDN'T FEEL INCREASING AFT PRESSURE ANYMORE. TRIM WAS OPERATED MANUALLY AND NORMAL LANDING FOLLOWED. AFTER LANDING, TRIM INDEXER SHOWED 1/2 INCH FORWARD OF WHITE ARC WITH FULL NOSE DOWN TRIM AND RIGHT IN THE MIDDLE OF THE TAKEOFF RANGE WITH FULL NOSE UP TRIM. FOUND TRIM WHEEL DAMAGED AND REPLACED WITH NEW PART - PERFORMED RE-ALIGNMENT/INDEXING OF TRIM WHEEL/POINITER. MX IAW CE560XL MM 27-31-00 & 27-32-01.PERFORMED/RAN TRIM THROUGH 'FULL' TRAVELS STOP TO STOP. ALL STOPS MADE AT FULL TRAVEL END MARKS (I.E. WHITE ARCS) NO DEFECTS NOTED AT THIS TIME - OPS CHECK GOOD.

Part: FLOAT SWITCH — INOPERATIVE (FUEL SYS) · airframe 2,291 hrs

THE RIGHT LOW FUEL LEVEL SYSTEM WAS INOPERATIVE. REMOVED SWITCH AND FOUND SIGNS OF ARCING ON THE TOP SIDE OF THE SWITCH. TROUBLESHOT FURTHER AND FOUND THE PC BOARD WAS DEFECTIVE. IT IS NOT KNOWN IF THE SWITCH DAMAGED THE PC BOARD. THIS IS NOT THE FIRST TIME WE HAVE SEEN A DEFECTIVE FLOAT SWITCH WITH SIGNS OF ARCING, HOWEVER, IT IS THE FIRST TIME THAT A DAMAGED PC BOARD WAS ASSOCIATED WITH IT. IT WAS NOTED THAT WHEN THE FLOAT SWITCH IS IN THE 'HIGH FUEL LEVEL' POSITION THE CONTACT SURFACES ARE ALIGNED. WHEN THE SWITCH IS IN THE 'LOW FUEL LEVEL' THE CONTACTS ARE NEARLY COMPLETELY MISALIGNED.

Part: RUDDER — MALFUNCTIONED (FLIGHT CONTROLS) · airframe 1,514 hrs · 1,149 cycles

ON TAKEOFF ROTATION ACFT YAWED HARD TO LEFT. INSPECTED RIGGING OF RUDDER AND RUDDER TRIM SYSTEM. CHECKED CABLE TENSIONS AND TRAVELS. CHECK GOOD. INSPECTED RUDDER BIAS SYSTEM. OPS CHECKED GOOD. NO DEFECTS NOTED IAW C560XL MM 27-20-05.

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 1,048 hrs · 800 cycles

WHILE IN DESCENT THE LT GREEN LANDING LIGHT CAME ON ALONG WITH THE "LO BRAKE PRESS" AND "ANTISKID INOP" ANNUNCIATORS & MASTER CAUTION. ALL LIGHTS WENT OUT AFTER A COUPLE OF MINUTES AND LANDING WAS NORMAL. COULD NOT DUPLICATE AT THIS TIME. JACKED ACFT, PERFORM FUNCTIONAL CHECKS OF GEAR SYSTEM. INSPECTED AND CLEANED CONNECTORS, FROZE UPLOCKS SWITCHES. MEGA OHM CHECKED WIRING. ALL CHECKED GOOD. ALL WORK COMPLIED WITH REF CE560XL M/M 32-61-00.

Part: MODULE — FAILED (MLG LOGIC CONTRO) · airframe 922 hrs · 708 cycles

RIGHT GEAR LIGHT CAME ON DURING FLIGHT (GEAR HANDLE UP) FOLLOWED BY LOW BRAKE PRESS & ANTI SKID INOP CAUTION LIGHT ON. AFTER 20 MIN ALL 3 LIGHTS EXTINGUISHED, DURING DESCENT (10,000 FT) OPERATION OF GEAR AND BRAKES DURING LANDING WAS NORMAL. REPLACED LANDING GEAR CONTROL LOGIC MODULE IAW 560XL 24-51-02 OPS CHECK GOOD

Part: WARNING SYSTEM — ACTIVATED (ANTI SKID SYS) · airframe 916 hrs · 704 cycles

LOW BRAKE PRESSURE/ANTISKID INOP (IN-FLIGHT) ANNUNCIATOR ILLUMINATED WITH RT GEAR LIGHT ILLUMINATED. CHECKLIST CONDUCTED EMERGENCY BRAKES USED. ITEM IS UNDER INVESTIGATION.

Part: STRUT — DAMAGED (NLG) · airframe 599 hrs · 450 cycles

ON GEAR RETRACTION RED UNLOCK LIGHT ON GEAR. EXTENDED GEAR, 3 GREENS, NO RED LANDED UNEVENTFULLY. TROUBLESHOT LANDING GEAR SYSTEM. FOUND NLG STRUT NOT EXTENDING COMPLETELY, CAUSING UPLOCK LOCK TO CONTACT UPLOCK ROLLERS NOT ALLOWING GEAR TO RETRACT. DISASSEMBLED NOSE GEAR STRUT AND REBUILT STRUT IAW COMPONENT MM 32-20-01. REASSEMBLED NLG AS REQUIRED. SERVICED NOSE STRUT IAW MM 12-14-00. PERFORMED OP'S CHECK OF LANDING GEAR SYSTEM. OPS CHECK GOOD.

Part: MOUNT — FAILED (PAX DOOR FRAME) · airframe 543 hrs · 405 cycles

AFTER TAKEOFF DOOR SEAL & CABIN DOOR ANNUNCIATOR ILLUMINATED, LOUD WIND NOISE FROM AROUND DOOR. ACCOMPLISHED AIR TURNBACK AND UPON LANDING THE MAIN ENTRANCE DOOR FELL OPEN. REPLACED AFT DOOR STRUT MOUNTING FRAMES IAW CESSNA 560XL B/P 6611267, BOTH DOOR CABLES IAW CESSNA 560 XL MM 52-10-03. PERFORMED CABIN LEAK RATE PRIMARY AND SECONDARY SEALS CHECKED GOOD IAW CESSNA 560 XL MM 21-30-00. VERIFIED DOOR OPERATION AND DOOR SEAL LEAK DOWN RATE GOOD IAW CESSNA 560 XL MM 52-10-04.