N693QS
Registered owner: NETJETS SALES INC, OK (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NETJETS AVIATION, INC. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
A SEGMENT OF THE FLOOR EMERGENCY LIGHTING IS INOPERATIVE BELOW SEAT THREE. DURING T/S GAINED ACCESS TO THE LT AISLE EMERGENCY LIGHT HAD FEW LED LIGHT WERE OUT. REMOVED INOP EMERGENCY LIGHT AND INSTALLED A NEW LED LIGHT ASSY. OPS CHECKED GOOD. REF AMM 33-50-00.
AFT EMERGENCY EXIT LIGHT OVER LAVATORY TOILET NOT ILLUMINATING DURING AIRCRAFT POWER ON CHECKLIST. (AOG) AFT EMERGENCY EXIT LIGHT OVER LAVATORY TOILET NOT ILLUMINATING DURING AIRCRAFT POWER ON CHECKLIST FOUND AFT EMERGENCY EXIT LIGHT OVER LAVATORY TOILET NOT CONNECTED. SECCURED CONNOCTOR AS REQUIRED OPS CHECK GOOD. NO DEFECTS NOTED. INFORMED MCC OF FIDNINGS AND THEY REQUESTED TO PROCEED WITH EMER-LIGHTING BATTERY PACK TASK CARD STILL. ALL WORK DONE IN REF TO CE-560 XL AMM 33-50-02
DURING EXTERNALLY SERVICEABLE TOILET DETAILED INSPECTION FOUND THE TOILET SEAT PANEL TO BE CORRODED AND CRACKING. PERFORM REPAIR TO TOILET DECK SKIN. COMPLIED WITH RFTS-114057 N693QS (560-5657) TOILET DECK SKIN CORROSION. REV 0. DATED 17JUN25. THIS IS A PERMANENT MINOR REPAIR.
MAIN DOOR: REPEAT WRITE UP. MAIN ENTRY DOOR HANDLE IS DIFFICULT TO LOCK AND UNLOCK AND VERY DIFFICULT TO UNLOCK OR LOCK AFTER COLD SOAK FLIGHT. VIDEO ATTACHED. CORRECTIVE ACTION: ADJUSTED LATCH PLATES IAW AMM 52-10-00. OPS CHECK GOOD.
MAIN DOOR: MAIN CABIN DOOR COUNTER BALANCE OUT OF RIG,( TENSION TOO HIGH.) DOOR SLAMS SHUT. CORRECTIVE ACTION: ADJUSTED COUNTER BALANCE TENSION. OPS CHECK GOOD. IAW CE-560XL AMM 52-10-03
COCKPIT HAD A BURNING ODOR, ON SHORT FINAL CREW NOTICED A SMELL SIMILAR TO BURNING RUBBER. ODOR CONTINUED UNTIL AIRCRAFT WAS POWERED DOWN. NO SMOKE OBSERVED, AND NO ODOR OBSERVED IN THE PASSENGER CABIN. APU WAS NOT RUNNING. REMOVED AND REPLACED LEFT HEATED WINDSHIELD ASSEMBLY IAW MM 56-11-00.
AT FL390 APPROX 25 MINUTES INTO THE FLIGHT A FAINT ODOR WAS NOTICED IN THE COCKPIT, AFTER CHECKING THE CABIN AND LAV AREA THE ODOR WAS NARROWED DOWN TO THE COCKPIT. CREW DISCUSSED TYPE OF ODOR AND SOURCE AND DISCOVERED THE STRONGEST PRESENCE WAS COMING FROM THE LEFT COCKPIT SIDE PANEL AND AROUND LEFT COCKPIT WINDOWS. AT THIS POINT CREW BEGAN COMPLYING WITH THE CHECKLIST AND DISCUSSING OPTIONS, AT ABOUT 45 MINS INTO THE FLIGHT THE LEFT AND RIGHT AMP GAUGES BEGAN FLUCTUATE APPROX 50 AMPS. ( LEFT WOULD JUMP TO 100 RIGHT WOULD GO TO ZERO, RIGHT TO 100 LEFT TO ZERO) AT THIS POINT THE SMELL BECAME STRONGER. CREW DECLARED AN EMERGENCY AND DIVERTED TO KBNA. THRU OUT THE DESCENT AMP GAUGES CONTINUED TO FLUCUATE BUT NO OTHER ABNORMAL INDICATIONS IN THE COCKPIT WAS NOTICED, INCLUDING ANY SIDE PANELS AND INSTRUMENT PANEL ABNORMALLY WARM. CREW AGREES THE SMELL DOES NOT SEEM TO BE AN ELECTRICAL SMELL SUCH AS WIRES BURNING AND SMELL CAN NOT BE NOTICED ON THE THE GROUND IF ENVIROMENTAL SYSTEM IS OPERATING. //SIGNOFF// REMOVED AND REPLACED TRIM PCB, PRESS PCB, DIMMING PCB, LANDING GEAR PCB, GEAR CONTROL PCB, SQUATSWIB;H PCB, CABIN DOOR PCB, NO TAKE OFF PCB OPERATIONAL CHECKS GOOD AT THIS TIME REF CE·560XL AMM 24-51-01.
WHILE CLIMBING THRU FL300 WE STARTED TO SMELL A STRONG ODOR. IT WAS STRONGEST NEAR THE FRONT PANEL AND MORE SPECIFICALLY THE LEVEL OF THE MFD AND PFDS. ALL INDICATIONS WERE NORMAL AND THERE WAS NO SMOKE. IT WAS NOT COMING FROM THE WEMAC OR ENVIRONMENTAL SYSTEM. THE APU WAS OFF. WE CHOSE TO DIVERT AND THE SMELL GOT WORSE DURING THE INITIAL DESCENT. AS SOON AS WE WERE ON THE GROUND THE SMELL SUBSIDED. //SIGN-OFF// FOUND EXCESSIVE AMOUNT OF LINT AND DUST BUILD UP ON GLARE SHIELD EQUIPMENT COOLING FANS. ALSO, NOTED EXCESSIVE LINT AND DUST BUILD UP BEHIND THE PILOT, COPILOT AND CENTER DISPLAY UNITS. CLEANED AFFECTED AREAS. AS REQUIRED, REMOVED LEFT HAND AND RIGHT HAND GLARE SHIELD EQUIPMENT COOLING FANS. INSTALLED NEW LEFT HAND AND RIGHT HAND GLARE SHIELD EQUIPMENT COOLING FANS. PERFORMED SATISFACTORY OPERATIONAL CHECK. WORK DONE IN ACCORDANCE WITH MAINTENANCE MANUAL 21-24-00. NO ABNORMAL SMELL NOTED AT THIS TIME.
CORRECTION/// CLIMBING THROUGH FLIGHT LEVEL 210 OFF OF ASE I STARTED TO SMELL AN ODOR. WE HAD ENTERED PRECIPITATION AND I HAD ALSO TURNED ON THE ANT-ICE AND RADAR. SHORTLY AFTER THAT THE ODOR GOT VERY STRONG. I OPENED THE WEMAC?S TO TRY AND DETERMINE IF THAT WAS THE SOURCE. IT WAS NOT. I DETERMINED THE SMELL WAS COMING FROM BEHIND THE PANEL. THERE WERE NO ABNORMAL OR EMERGENCY ANNICATORS AND ENGINE PARAMETERS WHERE NORMAL. NO SMOKE WAS VISIBLE. THE APU WAS SHUT DOWN AND SECURED. WE DECLARED AND EMERGENCY AND DIVERTED TO RIL. AFTER LANDING AT RIL THE CREW WITH THE AIRPORT RF (ARF) CHIEF OPENED THE RIGHT SIDE AVIONICS BAY DOOR AND DETECTED A VERY STRONG ACIDIC ELECTRICAL SMELL.
CLIMBING THROUGH FLIGHT LEVEL 210 OFF OF ASE I STARTED TO SMELL AN ODOR. WE HAD ENTERED PRECIPITATION AND I HAD ALSO TURNED ON THE ANT-ICE AND RADAR. SHORTLY AFTER THAT THE ODOR GOT VERY STRONG. I OPENED THE WEMAC?S TO TRY AND DETERMINE IF THAT WAS THE SOURCE. IT WAS NOT. I DETERMINED THE SMELL WAS COMING FROM BEHIND THE PANEL. THERE WERE NO ABNORMAL OR EMERGENCY ANNICATORS AND ENGINE PARAMETERS WHERE NORMAL. NO SMOKE WAS VISIBLE. THE APU WAS SHUT DOWN AND SECURED. WE DECLARED AND EMERGENCY AND DIVERTED TO RIL. AFTER LANDING AT RIL THE CREW WITH THE AIRPORT RF (ARF) CHIEF OPENED THE RIGHT SIDE AVIONICS BAY DOOR AND DETECTED A VERY STRONG ACIDIC ELECTRICAL SMELL. """"""CORRECTIVE ACTION""""" PERFORMED APU AND ENGINE RUNS FOR TROUBLESHOOTING PURPOSES. MANUALLY CONTROLLED THE COCKPIT TEMPERATURE FULL HOT. NOTED NO ABNORMAL SMELLS COMING FROM THE AIR-DUCTS. CYCLED THE GLARESHIELD COOLING FANS CIRCUIT BREAKER AND NOTED A SLIGHT SMELL OF BURNT LINT/DUST. REMOVED THE PILOTS DISPLAY PART NUMBER 7023460-05001 SERIAL NUMBER 04091315, CENTER DISPLAY PART NUMBER 7023460-05001 SERIAL NUMBER 06073507, CO-PILOTS DISPLAY PART NUMBER 7023460-05001 SERIAL NUMBER 06073378. FOUND EXCESSIVE AMOUNT OF DUST/LINT IN THE SURROUNDING AREA AS WELL AS INSIDE EACH DISPLAY INTERNAL COOLING FAN. CLEANED AS REQUIRED. VERIFIED THE INTERNAL COOLING FANS FOR EACH DISPLAY ARE OPERATIONAL. VERIFIED NO OVERHEATED/BURNT WIRING. REQUEST TO CHANGE GLARESHIELD COOLING FANS. REMOVED BOTH GLARESHIELD COOLING FANS PART NUMBER MC2483 AND INSTALLED NEW FANS PART NUMBER 9G1224A4M03 PROVIDED. OPERATIONAL CHECKS GOOD. INSTALLED ALL ORIGINAL DISPLAYS AS REQUIRED. PERFORMED SATISFACTORY OPERATIONAL CHECK. NO STRANGE ODORS/SMELLS NOTED AT THIS TIME. WORK DONE IN ACCORDANCE WITH MM 21-24-00, 31-10-01 AND WDM 21-20-01.
DURING SANDING PROCESS FOUND RH STRAKE TO HAVE MULTIPLE AREAS OF CORROSION AND TWO AREAS OF DELAMINATED COMPOSITE BEYOND LIMITS. COMPLIED WITH SERVICE BULLETIN SB560XL-53-14 TITLED "FUSELAGE - CARBON FIBER STRAKE MODIFICATION" DATED APRIL 9, 2012 ON RT STRAKE ONLY BY INSTALLING CUSTOMER SUPPLIED KIT P/N SB560XL-53-14-0.
FLOOR EMERG EXIT LIGHT - FORWARD FLOOR LEVEL ENTRY/EXIT LIGHT WAS SHORTING OUT WITH VISIBLE SMOKE AND SPARKS. INSPECTED AND FOUND LED ASSY LIGHT STRIP SHORTED INSIDE, NO VISIBLE DMG TO WIRES OR SURROUNDING AIRCRAFT STRUCTURE REMOVED FAILED IED ASSY AND INSTALLED A NEW LED ASSY IAW CE-560XL AMM 33-20-04 OPS CHECKS GOOD
AFTER NORMAL STARTUP OF BOTH ENGINES AND AFTER AVIONICS POWER ON, AN ABNORMAL CLICKING SOUND WAS HEARD (SOUNDED LIKE AN OVERACTIVE RELAY) THE SOUND LASTED FOR ABOUT 10-15 SECONDS. THE APU WAS ON BUT BLEED AIR WAS OFF. JUST PRIOR TO TAXIING A STRONG SMELL LIKE BURNING ELECTRICAL WAS VERY APPARENT. WE SHUTDOWN THE AIRCRAFT TO TRY AND FIND THE ISSUE. BY THE TIME WE COMPLETELY SHUTDOWN THE AIR INSIDE THE COCKPIT WAS THICK WITH THE SMELL AND FAINT SMOKE WAS SEEN. THE SMELL WAS STRONGEST IN THE COCKPIT AREA. WHEN OPENING THE CABIN DOOR IT WAS OBVIOUS THE SMELL WAS FROM INSIDE THE AIRCRAFT. "SUPPLEMENTAL INFORMATION". OPERATED APU WITH BLEED AIR ON AND ALL AVIONICS EQUIPMENT POWERED. CHECKED AND ABNORMAL OPERATION OR ODORS IN THE CABIN, COCKPIT, AND NOSE AVIONICS ENCLOSURE. NOTHING WAS FOUND. REMOVED COCKPIT CB PANELS AND CHECKS FOR ANY SIGNS OF FAILURE. NOTHING WAS FOUND. RAN ENGINES AND TAXIED AIRCRAFT TO THE RUN UP AREA. RAN BOTH ENGINES (ONE AT A TIME) AT CRUSE AND TAKE OFF SETTINGS AND ALL OPERATION WAS NORMAL. NO SMOKE OR ODOR WAS NOTICED.
REPAIR OF RIGHT WING LEADING EDGE FASTENER PULLED THROUGH SKIN. REPAIR DEFINITION DQ15823M1 DATED SEPTEMBER 19, 2018.
REPAIR TO LT AND RT WING LOWER SKIN DAMAGE. REPAIR DEFINITION DQ15836M1 DATED SEPTEMBER 20, 2018.
COCKPIT ODOR, JET FUEL ODOR COMING FROM OVERHEAD VENTS. NOTICEABLE WITH APU RUNNING ON THE GROUND AND ALSO DURING FLIGHT WITHOUT APU. REMOVED & REPLACED LEAKING APU FUEL MANIFOLD & TEE FLOW DIVIDER IAW M/M 49-30-06. APU OPS & LEAK CHK GOOD.
WHILE PERFORMING COCKPIT PREPARATION AND BEFORE ENGINE START WITH APU OPERATING, LIGHT GRAY SMOKE WITH AN ACRID ODOR THAT WAS DETECTED AND OBSERVED. CREW SHUTDOWN THE BLEED AIR FOR A FEW MOMENTS, THEN RETURNED TO LOW BLEED. A HEAVIER SMOKE WITH THE SAME ODOR AND COLOR IMMEDIATELY BEGAN TO FILL THE COCKPIT. NO OBVIOUS DISCREPANCIES COULD BE FOUND DURING POST APU SHUTDOWN INSPECTION OF AFT COMPARTMENT. INTERNAL OIL LEAKING IN THE APU APU. REMOVED THE APU AND INSTALLED A REPAIRED APU IAW MM 49-10-00. OPS & LEAK CHECKED GOOD.
CLIMBING THROUGH 12000 FEET, NR 2 ENGINE OIL PRESSURE RED LIGHT ILLUMINATED. FOLLOWED SHORTLY BY VIBRATION AND NR 2 ENGINE ITT SPIKED FULL SCALE. DECLARED EMERGENCY AND RETURNED TO DEPARTURE. TRIED ROTATING THE FAN BY HAND AND IT WAS FROZEN. ALSO OBSERVED GOUGE MARKS IN THE ENGINE INLET. REMOVED AND REPLACED THE RT ENGINE. PERFORMED OPS AND LEAK CHECKS WITH NO DEFECTS NOTED. ALL WORK PERFORMED IAW AMM 71-00-01, 71-00-02, 71-00-03, AND EMM 71-00-00.
DURING FLIGHT, ANTI-SKID INOPERATIVE ANNUNCIATOR LIGHT ILLUMINATED. LANDED AFTER RUNNING ABNORMAL CHECKLIST. LOST BRAKES AFTER LANDING, LOW BRAKE ANNUNCIATOR LIGHT ILLUMINATED & POWER BRAKES CIRCUIT BREAKER TRIPPED. USED THE EMERGENCY BRAKE HANDLE TO STOP ACFT. REMOVED FAILED HYDRAULIC PUMP MOTOR AND INSTALLED A NEW MOTOR. PERFORMED BRAKE BLEEDING AND OPS CHECKED GOOD. PERFORMED LEAK CHECKS, NO LEAKS NOTED AT THIS TIME. TAXIED ACFT. OPS CHECKED ANTI-SKID BRAKE, OPS CHECKED GOOD. WORK DONE IAW MM 32-44-20 AND WDM 32-40-01.
BOTH NOSE GEAR INDICATION LIGHTS APPEAR TO BE INOPERATIVE. FLEW BY CONTROL TOWER FOR VISUAL INDICATION & BLEW THE GEAR DOWN, LANDING WAS UNEVENTFUL. PERFORMED TEST OF THE LANDING GEAR SYS & VERIFIED COMPLAINT. FOUND LT GEAR INDICATION OUT. REMOVED DEFECTIVE BULBS & INSTALLED NEW BULBS. PERFORMED A SATISFACTORY OPS CHECK OF THE LANDING GEAR ANNUNCIATORS IAW AMM 32-60-00. CYCLED GEAR NUMEROUS TIMES TO BLEED NITROGEN FROM SYS. SERVICED GEAR NITROGEN BOTTLE IAW MM 12-13-01 & 32-01-00.
THE RED GEAR UNSAFE LIGHT REMAINED ILLUMINATED AFTER TAKEOFF, LEADING TO A FLASHING HYD PRESSURE & STAB MISCOMPARE ANNUNCIATOR. AFTER ABOUT 45 SECONDS, GEAR UNSAFE LIGHT EXTINGUISHED WITH A HEAVIER THAN NORMAL THUD UNDER FLIGHT DECK FLOOR. A FEW SECONDS LATER THE HYD PRESSURE & STAB MISCOMPARE ANNUNCIATOR EXTINGUISHED. RETURNED FOR LANDING WITH NORMAL GEAR EXTENSION. JACKED AIRCRAFT, CYCLED LANDING GEAR THREE TIMES APPROXIMATELY 30 CYCLES EACH TIME WHILE MOVING FLAPS, COULD NOT DUPLICATE. NO STAB MISCOMPARE OR GEAR UNLOCK LIGHT, WORK DONE IAW MM 32-01-00. DOWN JACKED AIRCRAFT. VERIFIED NO DEFECTS DURING GEAR SWINGS. JACKED AIRCRAFT, COMPLIED WITH GEARS SWINGS AND FLAP AND STAB MOVEMENT, UNABLE TO DUPLICATE. SET HYDRAULIC MULE TO THREE GPM AND COMPLIED WITH FUNCTIONAL CHECK, OPS CHECKED GOOD. SUSPECT BAD PRESSURE RELIEF VALVE, COMPLIED WITH SWINGS SYSTEM BEGAIN TO FAIL PRESSURE LIGHT REMAINED ILLUMINATED, STAB MISCOMPARE LIGHT ON AND GEAR UNSAFE LIGHT ON. SUSPECT LOADING VALVE BAD WITH HYDRAULICS APPLIED BEGAN TAPPING ON LOADING VALVE, NO CHANGE. FOUND HYDRAULIC RESERVOIR FAILED. REMOVED HYDRAULIC RESERVOIR AND INSTALLED MODIFIED HYDRAULIC RESERVOIR. OPERATIONAL CHECK NORMAL. NO LEAKS FOUND. WORK DONE IAW MM 29-11-01. COMPLIED WITH GEAR SWINGS AFTER INSTALLATION OF NEW HYD RESERVOIR. UNABLE TO DUPLICATE GEAR UNSAFE LIGHT. CYCLED GEAR & FLAPS AT SAME TIME, NO STAB MISCOMPARE OR GEAR UNSAFE LIGHT PRESENT. VERIFIED NO DEFECTS NOTED DURING OPERATIONAL CHECKS.
LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. RED LIGHT STAYED ILLUMINATED WITH NO GREEN LIGHT. THERE WAS NOTICEABLE DRAG AS IF THE AIRPLANE WAS NOT CLEAN. EXTENDED LANDING GEAR & BLEW THE BOTTLE FOR PRECAUTION. R & R A DEFECTIVE LANDING GEAR PCB NZ004 IAW CE-560XL MM 24-51-00. OPERATIONS CHECKED GOOD. SERVICED NLG STRUT AS REQUIRED IAW CE-560XL MM 12-14-00. PERFORMED LANDING GEAR FUNCTIONAL CHECKS IAW CE-560XLMM 32-01-00, NO DEFECTS NOTED.
DURING INSPECTION OF COMBUSTION CHAMBER LINER COOLING RING SEGMENT SELF LOCKING NUTS. FOUND TWO NUTS MISSING AT POSITION NR 15 AND NR 24. COMPLIED WITH A HOT SECTION REPAIR & 5.1. 36-2013.
DURING TAXI, LOW BRAKE PRESSURE AND ANTI-SKID INOPERATIVE ANNUNCIATORS ILLUMINATED AND CREW LOST BRAKE PEDAL PRESSURE. STOPPED ACFT ON TAXIWAY VIA EMERGENCY BRAKES. POWER BRAKE CIRCUIT BREAKER WAS PULLED AND RESET AND BOTH AND ANNUNCIATORS EXTINGUISHED. LOW BRAKE PRESSURE AND ANTI-SKID INOPERATIVE ANNUCIATORS AGAIN ILLUMINATED SHORTLY AFTER. REMOVED LOW PRESSURE SWITCH. INSTALLED NEW SWITCH. REMOVED HIGH PRESSURE SWITCH. INSTALLED O/H SWITCH. BLED BRAKE SYS. LEAK CHECKED GOOD. TAXI CHECKED GOOD. WORK PERFORMED IAW MM 32-44-20.
ON DEPARTURE, AUTOPILOT DISENGAGED AND SIGNIFICANT FORWARD PRESSURE REQUIRED ON CONTROL WHEEL. AUTOPILOT WAS REENGAGED AND DISENGAGED 2 MORE TIMES UNTIL ACFT WAS SLOWED TO BELOW 160 KNOTS. INSPECTED SYS, FOUND ELEVATOR TRIM WHEEL POINT HAD JUMPED OFF TRACK. RIGGED POINTER AND WHEEL. TRAVEL CHECKED GOOD. OPS CHECKED GOOD. IAW MM 27-31-00.
DURING TAKEOFF, FLAP 15 IMMEDIATELY AFTER ROTATION, A GRINDING/RUBBING FELT IN THE YOKE WITH FORE AND AFT YOKE MOVEMENTS. AFTER RETACTION OF FLAPS AND LEVEL OFF, GRINDING WAS STILL PRESENT. AFTER LANDING, UNABLE TO REPRODUCE GRINDING. INSPECTED ELEVATOR CABLE RUNS, PULLEYS, BELCRANKS, AND TORQUE TUBES FROM COLUMN TO ELEVATOR AND FOUND NO DEFECTS, CHECKED TENSIONS REF CH 27-31-00 WITH TENSIOMETER, SN 27278 (CAL. DUE 04-04-2012) ALL WITHIN LIMITS. OPERATED ELEVATOR SEVERAL TIMES AND COULD NOT DUPLICATE DISCREPANCY.
UNSAFE GEAR ANNUNCIATOR ILLUMINATED AFTER GEAR RETRACTION. TROUBLESHOT TO NOSE STRUT EXTENSION GREATER THAN 9.10 INCHES, IT IS 9.25 INCHES. WHEN RETRACTED UPLOCK ROLLERS ON NLG NOT FULLY SEATED IN UPLOCK HOOK. UPLOCK SWITCH IS AT FULL EXTENSION FOR ADJUSTMENT, BARELY MAKES CONTACT WITH ROLLERS. BEARINGS FROZEN TO STRUT. BOTH UPPER AND LOWER TRUNNION/STRUT BEARINGS CAME APART DURING REMOVAL. R & R BOTH BEARINGS IN TRUNNION. RESEALED NOSE STRUT AND SERVICED. NEW MEASUREMENT FOR NOSE STRUT EXTENSION IS 9.05 " WITHIN LIMITS. NOSE UPLOCK RIGGED GOOD. ALL OPS AND LEAK CHECKED NORMAL. WORK DONE IAW MM 32-20-00 AND CMM 32-20-01.
GEAR WOULD NOT RETRACT. TROUBLESHOT TO BAD NLG ACTUATOR. R & R NLG ACTUATOR AND BLED HYD SYS. OPS CHECKED GOOD IAW MM 32-30-03.
WHILE TAXIING, RT BRAKE FAILED AND ANTI-SKID LT ILLUM, RESET RT ADCR BIT AND APPLIED BRAKES. ANTI-SKID LT ILLUM BUT RT ADCR BIT OK. FOUND NOSE LANDING GEAR UPLOCK SWITCH OUT OF ADJUSTMENT BY MORE THE HALF THE REQUIRED ADJUSTMENT. ADJUSTED NLG UPLOCK SWITCH AS REQUIRED. PERFORMED OPERATIONAL TESTS OF LANDING GEAR WITH ALL RESULTS OF NORMAL OPERATION AND INDICATION. NO OTHER DEFECTS NOTED AT THIS TIME. WORK DONE PER MM 32-60-00 & 32-00-00.
WHILE TAXIING RIGHT BRAKE FAILED AND ANTI-SKID LT ILLUM. RESET RT ADCR BIT AND APPLIED BRAKES. ANTI-SKID LT ILLUM BUT RT ADCR BIT OK. FOUND A GEAR WIRING HARNESS FOR GEAR TRANSDUCER CHAFED THRU FRONT OF RT TIRE. REPLACED RT GEAR WIRING HARNESS ASSY WITH A NEW HARNESS IAW MM 33-10-00. ADJUST RT SQUAT SWITCH IAW MM 31-61-00. LANDING GEAR INDICATION GOOD IAW MM 31-60-00. FUEL LOW LEVEL WARNING GOOD IAW MM 28-42-00. ANTI SKID BRAKE SYS GOOD IAW MM 32-44-00. TAXI CHECKED GOOD. NO FURTHER DEFECTS NOTED.
FUEL FUMES IN COCKPIT AND CABIN WITH APU BLEED AIR ON. SECURED APU AND FUMES STOPPED. REMOVED SECONDARY FUEL MANIFOLD P/N 38838991 DUE TO A FITTING ON LINE LEAKING. INSTALLED A NEW LINE P/N 3883899-1. ALL WORK DONE IAW MM 49-30-06 RAN APU AND ACCOMPLISHED A SATISFACTORY LEAK CHECK, SHUT DOWN APU. REMOVED THE WATER SEPARATOR AND REPLACED THE CONDENSER (COALESER SOCK) P/N 83237-12 WITH A NEW CONDENSER SUPPLIED BY CUSTOMER, SAME P/N. CLOSED UP ALL ACECSS, AND PERFORMED APU RUN WITH BLEED AIR ON FOR ABOUT 15 MINUTES, AND NO FAULTS NOTICED, ALSO WATER SEPARATOR LEAKED CHECKED GOOD.- WORK DONE IAW MM 12-19-02 AND 21-51-00.
DURING A SCHEDULED INSPECTION, FOUND THE LANDING ACTUATOR CHAFING STIFFENER P/N 6621211-26 LOCATED IN LT MAIN GEAR WELL. CONTACTED MFG FIELD ENGINEERS, DISCOVERED THE THE RT SIDE STIFFENER WAS INSTALLED ON THE LT SIDE FROM THE FACTORY. INSTALLED CORRECT STIFFENER AND CLEARANCES WERE GOOD.
LT ENGINE WILL NOT MAKE TAKEOFF POWER IN THE TAKEOFF DETENT AND WITH EECS IN AUTO AND FAILED TO MANUAL. RAN ENGINES AT 88.4 PERCENT N1 WITH SEVERAL ACCELERATIONS AND DECELERATIONS WITH NO FAULTS FOUND I/A/W FAULT ISOLATION SECTION OF MM 72-00-00.
LT ENGINE WILL NOT MAKE TAKEOFF POWER IN THE TAKEOFF DETENT AND WITH EECS IN AUTO AND FAILED TO MANUAL. RAN ENGINES AT 88.4 PERCENT N1 WITH SEVERAL ACCELERATIONS AND DECELERATIONS WITH NO FAULTS FOUND IAW FAULT ISOLATION SECTION OF MM 72-00-00.
(EMERGENCY DECLARED) ON ROTATION AN UNUSUAL NOSE UP FORCE WAS NOTED REQUIRING FULL NOSE DOWN TRIM. BOTH PILOTS APPLIED NOSE DOWN PRESSURE AND CONDITION WORSENED AS SPEED INCREASED. FOUND PITCH TRIM WHEEL IMPROPERLY CLOCKED & PART OF INDICATOR TRACK MISSING. REPLACED PITCH TRIM CONTROL WHEEL WITH A NEW WHEEL & PROPERLY POSITIONED INDICATOR PINS PER CE560XL MM 27-10-05. OPS CHECK GOOD. VERIFIED PITCH TRIM TO OPERATED NORMALLY STOP TO STOP.
DURING DESCENT FROM CRUISE ALTITUDE, CREW EXPERIENCED ENGINE VIBRATION ACCOMPANIED BY EEC MANUAL L ADVISORY WITH NO ENG VIB ANNUNCIATOR. THROTTLE AY IDLE ITT= 650. EEC CHECKLIST DID NOT EFFECT VIBRATION. PERFORMED PRECAUTIONARY S/D. VISUALLY INSPECTED CHIP DETECTOR AND OIL FILTER ON LH ENGINE. PERFORMED BOROSCOPE ON LH ENGINE COMPRESSOR AND HP TURBINE. INSTALLED MODIFIED BLEED VALVE TORQUE MOTOR ON LH ENGINE I.A.W. P&W MM 75-30-01. COMPLETED 5 POINT ENGINE PERFORMANCE RUN I.A.W. P&W MM 71-00-00. ALL CHECKS GOOD.
IN FLIGHT ABOVE 200 KTS THERE IS A RUMBLING VIBRATION THAT VIBRATES THE WHOLE AIRPLANE. IT CHANGES PITCH OR SEVERITY WITH INCREASE IN SPEED, 250 KTS IS THE SPEED THAT IT IS MOST PRONOUNCED. FOUND ACCESS PANEL ON LOWER LT STUB WING NR 313AL TO BE OVERLAPPING PANEL NR 313AC AND OIL CANNING. TRIMMED PANEL NR 313AL IAW SRM OK 51-00-03 AND MM CH 53-30-00. INSTALLED PANEL NR 313AL NO OIL CANNING PRESENT.