N662QS

Part: RUB BLOCK — OUT OF ADJUST (ZONE 800) · airframe 4,553 hrs · 2,909 cycles

MAIN DOOR: MAIN ENTRY DOOR BINDS WHEN OPENING. DOOR NEEDS TO BE ASSISTED TO OPEN. CORRECTIVE ACTION; ADJUSTED SHIMS OF FWD MED DOOR RUB BLOCK TO PROPER LIMITS. PERFORMED SATISFACTORY OPS CHECK REF. 680A AMM 52-10-45.

Part: CIRCUIT BOARD — FAULTED (ENVIRON CONTROL) · airframe 3,968 hrs · 2,544 cycles

CABIN ODOR: VERY STRONG BURNING SMELL INSIDE AIRCRAFT AT 5K FT... THE PASSENGER SMELLED IT AS WELL. AFTER ENGINE SHUT DOWN, AE OPENED THE REAR EQUIPMENT BAY AND ALL INCLUDING LINE SERVICE SMELLED IT AS WELL. CORRECTIVE ACTION: PER FRS RECOMMENDATION, REMOVED AND REPLACED ENVIRONMENTAL CONTROL PCB NF204 WITH A CUSTOMER SUPPLIED INSPECTED PART. REMOVED AND REPLACED HEPA FILTER WITH A CUSTOMER SUPPUED NEW PART. PERFORMED SATISFACTORY CHECKS OF ENVIRONMENTAL CONTROL PCB NF204 IAW CE-680A AMM 24-60-40 AND 21-70-10.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 3,697 hrs · 2,351 cycles

DURING PRESSURIZATION FAILURE, PASSENGER OXYGEN MASKS DEPLOYED. THERE WERE NO PASSENGERS ON BOARD. REMOVED CABIN PRESSURIZATION CONTROLLER AND REPLACED WITH CUSTOMER SUPPLIED REPAIRED PRESSURIZATION CONTROLLER P/N ON/OFF 65000062-9 S/N OFF/ON 65000062-00397, 65000062-9.

Part: RETAINER — CHAFED (ZONE 800) · airframe 2,634 hrs · 1,640 cycles

ESCAPE HATCH SEAL RETAINER SCREWS ARE MAKING CONTACT WITH BOTH FWD AND AFT LOWER FUSELAGE EMERGENCY ESCAPE HATCH DOOR FRAME CAUSING DAMAGE TO THE FWD SIDE OF THE 7411276-3 DOOR FRAME.

Part: SHIELD — CHAFED (ZONE 200) · airframe 2,634 hrs · 1,640 cycles

INNER STINGER SKIN DAMAGE TO L/H SKIN P/N 6912640-20 AND R/H SKIN 6912640-24, REF ENGINEERING MEMO DQ40101M1.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 2,634 hrs · 1,640 cycles

MAIN DOOR: PIN FELL OUT ON MAIN CABIN DOOR LINKAGE. UNABLE TO CLOSE DOOR USING POWER ASSIST. FOUND PIN. TRIED TO REINSTALL, BUT APPEARS THREADS APPEAR TO BE STRIPPED.//CORRECTIVE ACTION//REINSTALLED PIN IN MCD LINKAGE AND INSTALLED A NEW RETAINING RING IAW CE-680A AMM 52-15-00. NO FURTHER DISCREPANCIES NOTED

Part: SHUTOFF VALVE — FAULTY (RUDDER) · airframe 13,751 hrs · 10,839 cycles

DURING TAKE OFF 10KTS BEEFIER V1 AIRCRAFT PULLED HARD RIGHT, CORRECTED WITH FULL LEFT RUDDER MAINTAINED CONTROL, ROTATED MADE NORMAL CLIMB, CRUISE, DESCENT, LANDING OK. REMOVED AND REPLACED RUDDER BIAS ACTUATOR AND RUDDER BIAS CONTROL VALVE OPS AND LEAK CHECKS GOOD. REMOVED P/N: 5307-1 S/N: 0621C (RUDDER BIAS SHUTOFF VALVE) 6450.5 HOURS 5184 CYCLES P/N: 6660613-12 S/N: 22112 (ACTUATOR AND HEATER ASSY) 3853 HOURS AND 3056 CYCLES.

Part: ACCESS PANEL — CORRODED (VERTICAL STAB) · airframe 13,603 hrs · 10,719 cycles

CORROSION FOUND UNDERNEATH THE ACCESS PANEL 340CR, LOWER AFT ON THE RT SIDE OF THE VERTICAL STAB. BLENDED THE CORROSION, CLEANED, CHEMICALLY TREATED, AND PRIMED AREAS IAW ENGINEERING MEMO.

Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 13,603 hrs · 10,719 cycles

MECHANICALLY BLENDED FOUR AREAS OF CORROSION ON THE LT WING OTBD FLAP PUSHROD ATTACH FITTINGS, PERFORMED AN EDDY CURRENT INSPECTION AND AN ULTRASONIC THICKNESS INSPECTION. FOUND INBOARD FITTING BEYOND LIMITS. PROTECTED BARE METAL IAW SRM 51-10-02 TO AREAS WITHIN CORROSION LIMIT BLENDS. REPAIRED THE LT FLAP PUSHROD ATTACHMENT IAW ENGINEERING MEMO.

Part: AXLE — CORRODED (LT MLG) · airframe 13,603 hrs · 10,719 cycles

FOUND THE LEFT MAIN LANDING GEAR AXLE CORRODED OUT OF LIMITS, REPLACED THE AXLE.

Part: APU — SMOKE (APU BAY) · airframe 11,176 hrs · 8,809 cycles

SMOKE IN THE COCKPIT. APU WAS STARTED ABOUT FIVE MINUTES PRIOR TO LANDING & WAS OPERATING NORMALLY. UPON LANDING & TAXI IN APU QUIT DURING ENG SHUTDOWN. WE THOUGHT WE HAD BUMPED A SWITCH. AFTER THE PAXS DEPARTED ABOUT FIVE MINUTES WE TESTED, GOOD TEST & RESTARTED THE APU & SMOKE & FUMES IMMEDIATELY FILLED THE COCKPIT. SMOKE SEEMED BLUE COLORED & THE FUMES SMELLED LIKE FUEL. WE DID THE ACFT EVACUATION PROCEDURE, EXCLUDING ENG FIRE SWITCHES & BOTTLES BECAUSE ENGS WERE OFF. ALL SYS WERE SHUTOFF. THERE IS A STRIP OF OIL LIKE SUBSTANCE INSIDE THE HELLHOLE DOOR WHICH WAS NOT PRESENT PRIOR TO FLIGHT. R & R APU. SYS OPS CHECKED GOOD IAW MM 49-10-00.

Part: BOLT — WORN (AILERON) · airframe 9,740 hrs · 7,676 cycles

WITH SPEED SLOWLY ACCELERATING PAST 265 KIAS AND IN CLIMB THROUGH FL235, A DEFINITE RUMBLING VIBRATION WAS FELT IN THE ACFT. NO SIGNIFICANT VIBRATION IN YOKE, BUT COULD CLEARLY SEE THE LT AILERON VIBRATING UP AND DOWN .2500". IMMEDIATELY SLOWED DOWN AND THE VIBRATION WENT AWAY. DIVERTED TO GET ACFT ON GROUND. INSPECTING AILERON, FOUND TRIM TAB PUSHROD BOLTS WORN. R & R TRIM TAB BOLTS IAW MM 27-10-01. LUBRICATED TRIM TAB ACTUATOR IAW MM 27-11-01. OPS CHECKED GOOD. ALSO FOUND ELEVATOR TRIM TAB BOLTS AND BEARINGS WORN. R & R THE ELEVATOR TRIM TAB BEARINGS AND BOLTS IAW MM 20-10-08. NO FURTHER DEFECTS NOTED.

Part: PULLEY — DAMAGED · airframe 9,278 hrs · 7,293 cycles

DURING CLIMB OUT, ACFT SUDDENLY PITCHED NOSE DOWN. ON DETECTING THE PITCH CHANGE, AUTOPILOT WAS DISENGAGED. CONTROLS WERE DIFFICULT TO MOVE ALONG VERTICAL AXIS AND EACH CONTROL INPUT REQUIRED EXCESSIVE FORCE TO PITCH THE ACFT IN A CLIMB OR DESCENT. CONTROL INPUTS WERE DIFFICULT TO CONTOL SINCE THE ACFT SEEMED UNSTABLE AND NOSE WOULD CONTINUE TO PITCH DOWN OR UP EXCESSIVELY WITH GENTLE CONTROL INPUTS. AFTER DESCENDING TO BELOW THE FREEZING LEVEL, THERE WAS A SUDDEN LOOSENING OF THE RIGIDITY IN THE CONTROLS AND NORMAL INPUTS AND FORCE COULD BE USED TO ADJUST THE PITCH OF THE ACFT. FOUND RUDDER AND ELEVATOR TENSION AND SERVO LOW. TENSIOIN CHECKED IAW MM 27-20-00 AND 27-31-00. REPLACED PULLEYS FOUND FROZEN AND STIFF IAW MM 27-31-03,

Part: CONTROL CABLE — FRAYED (ELEVATOR TRIM) · airframe 7,829 hrs

FRAYED ELEVATOR TRIM CABLE WAS FOUND DURING A SCHEDULED INSP CABLE WAS FRAYED A HALF OF THE CABLE'S DIAMETER. AND CABLE TENSION WAS WITHIN MM LIMITS.

Part: BRAKE ASSY — MALFUNCTIONED (MLG) · airframe 7,937 hrs · 6,203 cycles

WHILE TAXIING THE BRAKES WERE APPLIED ON THE RT (CO-PILOTS) SIDE, THEY GRABBED ABRUPTLY & PULLED TO ONE SIDE & WOULDN'T RELEASE RIGHT A SECOND TRY PRODUCED SIMILAR RESULTS PULLING TO THE OPPOSITE SIDE. PILOTS SIDE WORKED NORMALLY. INSPECTED TIRE PRESSURES, BRAKE ACCUMULATOR BRAKE FLUID & BRAKE WEAR PINS FOR PROPER SERVICING AND LIMITS IAW MM 12-13-00 12-13-01 & 12-12-02. NO DEFECTS NOTED AT THIS TIME. TAXIED ACFT & PERFORMED MULTIPLE CHECKS OF PILOTS & CO PILOTS BRAKING ON 2 DIFFERENT TAXIWAY & A RUNWAY SURFACE. NO DEFECTS NOTED AT THS TIME IAW MM 32-42-00.

Part: WHEEL — SEPARATED (NLG) · airframe 7,702 hrs · 6,010 cycles

NOSE WHEEL RIM ASSY SEPARATED WHILE BEING SERVICED. TECH USED HIGH PRESSURE TO SERVICE TIRE WITH NO REGULATOR. WHEEL & ATTACHING HARDWARE ARE UNSERVICEABLE. INSTALLED WHEEL , PERFORMED GEAR SWINGS. LEAK & OPS CHECKED GOOD IAW MM 12-14-00.

Part: DISPLAY — MALFUNCTIONED (NR 2) · airframe 7,544 hrs · 5,896 cycles

ON CLIMB OUT, CO-PILOT'S PFD NR 2 WENT BLANK FOR 5 - 6 SECONDS, WITH CHECK PFD NR 2 ANNUNCIATOR ILLUMINATED & MASTER CAUTION. SCREEN CAME BACK ON WITH RED X FOR APROX 10 SECONDS, WITH CHECK PFD NR2 ANNUCIATOR ILLUMINATED WITH MASTER CAUTION. THEN SCREEN REBOOTED & RETURN TO NORMAL DURING RETURNING TO LAND. REMOVED PFD NR 2 AND INSTALLED REPAIRED NR 2 PFD. OPS CHECKED GOOD IAW MM 34-25-01.

Part: DOOR — FAILED (MAIN PAX) · airframe 7,384 hrs · 5,774 cycles

MAIN ENTRY DOOR HISS ON CLIMB OUT, DOOR OPENED IN FLIGHT UPON RETURN TO AIRPORT. NO DEFECTS WERE NOTED WITH THE DOOR LATCHING/WARNING SYS. NTSB INVESTIGATION IN PROGRESS, AWAITING CVR SUMMARY.

Part: OIL SYSTEM — READS HIGH (RT ENGINE) · airframe 7,236 hrs · 5,653 cycles

AT CLIMB TO FL370. RT ENGINE OIL PRESSURE EXCEEDED RED LINE TO 190/200PSI. REDUCED THROTTLE & BEGAN TO DESCEND. AT FLT IDLE, OIL PSI STAYED ABOVE RED LINE UNTIL BELOW FL200. KEPT THROTTLE AT FLT IDLE. PSI HIGHER THAN LT ENGINE BUT STAYED IN GREEN AT 120PSI. AFTER LANDING AT FLT IDLE, PSI DROPPED TO 80-100 PSI. MOMENTARY THRUST REVERSER DEPLOYMENT CAUSED PRESSURE TO EXCEED RED LINE. OIL TEMP ON RT ENGINE HIGHER THAN LT ENGINE, & HIGHER THAN IN PREVIOUS LEGS, BUT STAYED IN GREEN. REMOVED INSPECTED & REPLACED RT ENG OIL FILTER & COLD START VALVE IAW MFG 79-20-01 AND 79-20-05. NO LEAKS NOTED, ADJUSTED OIL PRESSURE OF NEW COLD START VALVE IAW MM 71-00-00, FIG 512. OIL PRESSURE IS GOOD AT ALL POWER SETTINGS.

Part: INDICATOR — FALSE INDICATION (LT ITT) · airframe 6,112 hrs · 4,759 cycles

AFTER BRAKE RELEASE, LT ITT GAUGE WENT OFF SCALE HIGH. TAKEOFF WAS ABORTED AT LESS THAN 20 KNOTS. PRIOR TO BRAKE RELEASE, ALL ENGINE GAUGES RAD NORMAL AT FULL POWER. ENGINE GAUGES ON BOTH ENGINES CONTINUED TO REMAIN NORMAL EXCEPT FOR LT ITT GAUGE WHICH STAYED OFF-SCALE HIGH FOLLOWING ABORT AND CLEARING THE RUNWAY. INSPECTED EXHAUST, JUNCTION BOX AND HARNESS. RAN ENG AND SHOOK HARNESS, COULD NOT DUPLICATE. REPLACED N1/ITT IND IAW AMM 77-40-00.

Part: UNKNOWN — ODOR (CABIN)

JUST PRIOR TO LEVEL OFF AT 15,000 FT, STARTED SMELLING A STRONG "BURNING" ODOR. AT LEVEL OFF, WITH POWER REDUCED, THE ODOR DISSIPATED. ODOR RECURRED ON APPROACH WITH POWER INCREASES. (A)

Part: COALESCER BAG — CONTAMINATED · airframe 6,088 hrs · 4,734 cycles

JUST PRIOR TO LEVEL OFF AT 15,000 FT, WE STARTED SMELLING A STRONG "BURNING" ODOR. AT LEVEL OFF, WITH POWER REDUCED, THE ODOR DISSIPATED. IT RECURRED ON APPROACH WITH POWER INCREASES. REMOVED, CLEANED AND DRIED, INSTALLED WATER SEPARATOR CONDENSER BAG IAW MM 12-19-02. RAN BOTH ENGINES AND APU, NO ODOR NOTED.

Part: CIRCUIT BREAKER — OPEN · airframe 4,792 hrs · 3,708 cycles

DURING TAKEOFF PRIOR TO V1, LT SIDE MASTER WARNING LIGHT CAME ON STEADY. RT SIDE MASTER WARNING DID NOT COME ON AT ALL. (WILL NOT RESET) ALL OTHER INDICATIONS NORMAL.

Part: UPLOCK SWITCH — OUT OF RIG (NLG) · airframe 4,469 hrs · 3,445 cycles

THE RED 'GEAR UNLOCKED' LIGHT WOULD NOT EXTINGUISH AFTER GEAR RETRACTION. RIGGED NOSE GEAR UPLOCK SWITCH FOR POSITIVE ACTUATION. COMPLETED SATISFACTORY FUNCTIONAL CHECKS IAW C560XL MM 32-30-05.

Part: FUEL FILTER — BYPASSING (RIGHT) · airframe 3,762 hrs · 2,885 cycles

RIGHT FUEL FILTER BYPASS LIGHT CAME ON WITH APPLICATION OF T/O POWER DURING TAKEOFF ROLL. REMOVED AND REPLACED RIGHT FUEL FILTER IAW P&W 545 M/M CH 73-10-05, OPS AND LEAK CHECKS SATISFACTORY.

Part: FORK — MALADJUSTMENT (MLG) · airframe 3,549 hrs · 2,742 cycles

A -GEAR UNLOCK- LIGHT REMAINED ON AFTER TAKEOFF WITH THE GEAR IN THE -UP POSITION-, THE -HYD PRESS- LIGHT REMAINED ON AS WELL. REMOVED NLG STRUT PISTON ASSY. FOUND MEASUREMENT BETWEEN FORK AND BEARING ORIFICE ASSY TO BE AT 16 .0 IN. RETORQUED BEARING AND ORIFICE ASSY TO ACHIEVE A MEASUREMENT OF 15.94 IN. (15.9375) BETWEEN FORK AND BEARING ORIFICE. REINSTALLED NLG STRUT PISTON ASSY. GEAR SWING GOOD. NO FAULTS FOUND.

Part: SUPPORT BRACKET — DAMAGED (SPEED BRAKE) · airframe 2,977 hrs · 2,257 cycles

NO TAKEOFF LIGHT AND HORN CAME ON AT TAKEOFF POWER AND TAKEOFF ROLL INITIATION. FLAPS 15, SPEED BRAKE RETRACTED, TRIMS SET FOR T/O). FOUND RT SPEED BRAKE SWITCH JAM NUT BEING PUSHED UP BY SPEED BRAKE DOOR SUPPORT BRACKET, CAUSING PLUNGER TO RELAX. ADJUSTED SPEED BRAKE SWITCHES, RAN A/C AND CYCLED SPEED BRAKES, FLAPS AND TRIM FOR 1 HOUR, NO FAULTS NOTED IAW CE560XL MM 27-61-00.