N655QS

Part: SWITCH — INOPERATIVE (STAB POSITION) · airframe 15,730 hrs · 11,988 cycles

AFTER TAKEOFF, AT FRA, WE SELECTED THE FLAPS TO 0. WITHIN A FEW SECONDS A MASTER CAUTION STAB MISCOMPARE AND HYD PRESS ILLUMINATED. WE RAN THE STAB MISCOMPARE CHECKLIST, WHICH HAD US PULL THE STAB CONTROL CIRCUIT BREAKER. PULLING THE STAB CONTROL CIRCUIT BREAKER EXTINGUISHED THE HYD PRESS LIGHT AS IT SHOULD. THE REST OF THE DIVERTED FLIGHT WAS CONTINUED AT 200 KNOTS AND 10,000FT WITH THE STAB MISCOMPARE MASTER CAUTION ILLUMINATED, WITH NO FURTHER ISSUES. ON POST FLIGHT WE CONFIRMED THE STAB IS IN THE DOWN POSITION WITH THE FLAPS IN THE FULL UP POSITION. REPLACED THE H-STAB TWO POSITION SWITCH IAW CE-560XL AMM 27-40-00. COMPLETED OPS CHECK WITH NO DEFECTS NOTED.

Part: WIRE — BROKEN · airframe 15,693 hrs · 11,964 cycles

IN CRUISE THE CROSFEED PUMP WAS SWITCHED TO L TANK R ENG. THE FUEL BOOST R BEGAN FLASHING IMMEDIATELY. THE MASTER CAUTION WAS PRESSED AND FUEL BOOST R REMAINED ON STEADY. QRH WAS COMPLETED. CROSSFEED WAS SELECTED OFF. DURING ALL THAT TIME NO FUEL CROSSFEED WAS OBSERVED. PERFORMED FUEL CROSSFEED FROM LH TO RH TANK AND RH TO LH TANK ONGROUND WITH NO DEFECTS. NETJETS MCC ADVISED TO REMOVE AND REPLACE CROSSFEED VALVE ACTUATOR AS PRECAUTIONARY. DURING REMOVAL OF PANEL 313AL BOTH WIRE PINS BROKE OFF ISIDE OF SPLICES. PLACED PARTS ON ORDER. DURING REMOVAL OF ACTUATOR FOUND BOTH LOWER SCREW ALLEN HEADS TO BE STRIPPED AND ROUNDED OUT AND HAD TO PERFORM EXTRACTION. PLACED PARTS ON ORDER. (KK MB 11/18/2024). REMOVED AND REPLACED CROSSFEED VALVE ACTUATOR P/N: 9914423-2 S/N: AA746318 WITH"NEW" P/N: 9914423-2 S/N: AA882790 WITH "NEW" SCREWS P/N:NAS1352-08H8P QTY: 2 ALL FOLLOW ON CHECKS PASS. REPLACED DAMAGEDSPLICES P/N: M81714/65-20-1 WITH "NEW" QTY: 2 WITH NEW. WORK PERFORMED IAW CE-560XL MM 28-21-06, AND 20-30-15. CAL: JE1703, 0922904090

Part: ACTUATOR — DAMAGED (BOOST PUMP)

IN CRUISE THE CROSFEED PUMP WAS SWITCHED TO L TANK R ENG. FUEL BOOST R BEGAN FLASHING. MASTER CAUTION PRESSED & FUEL BOOST R REMAINED ON STEADY. QRH WAS COMPLETED. CROSSFEED SELECTED OFF. DURING THAT TIME NO FUEL CROSSFEED WAS OBSERVED. PERFORMED FUEL CROSSFEED FROM LT TO RT TANK & RT TO LT TANK ON GROUND, NO DEFECTS. ADVISED R & R CROSSFEED VALVE ACTUATOR AS PRECAUTION. DURING REMOVAL OF PANEL 313AL BOTH WIRE PINS BROKE OFF ISIDE OF SPLICES. DURING REMOVAL OF ACTUATOR FOUND BOTH LOWER SCREW ALLEN HEADS TO BE STRIPPED & ROUNDED OUT. R & R CROSSFEED VALVE ACTUATOR. ALL FOLLOW ON CHECKS PASS. REPLACED DAMAGED SPLICES. PERFORMED IAW MM 28-21-06, AND 20-30-15.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 14,045 hrs · 10,705 cycles

THREE MAIN CABIN DOOR EMERGENCY LIGHTS INOP. WITH BATTERY OFF & LIGHT SWITCH ON, ALL EMERGENCY LIGHTS ILLUMINATE EXCEPT 3 MAIN CABIN DOOR EXIT LIGHTS. WITH BATTERY OFF AND LIGHT SWITCH IN THE ARM POSITION, ALL EMERGENCY EXIT LIGHTS ILLUMINATE EXCEPT THE 3 DOOR EMERGENCY LIGHTS. SWAPPED BATTERIES AND THE FORWARD BATTERY WAS MALFUNCTIONING. PLACED THE AFT BATTERY IN ITS ORIGINAL POSITION. REPLACED THE FORWARD BATTERY AND ACCOMPLISHED A TWO HR CHARGE. FUNCTIONAL TESTED THE EMERGENCY LIGHT SYSTEM, NO DEFECTS NOTED. WORK ACCOMPLISHED MM 33-50·01.

Part: LIGHT — DEFECTIVE (ZONE 200) · airframe 13,397 hrs · 10,221 cycles

FLOOR EMERG EXIT LIGHT: LEFT FORWARD FLOOR EMERGENCY LIGHTING INOP. ALL OTHER INTERIOR EMERGENCY LIGHTING IS OPERATIVE. //SIGNOFF// REMOVED AND REPLACED INOPT LH FORWARD MOST AISLE UGHT WITH NEW LED LIGHTING ASSEMBLY. OPS CHECK GOOD. ALL WORK DONE IAW CE560XL AMM 33·20-04. PN (OFF) 9919040-26 , SN (OFF) 121004500, PN (ON) 9919040-29, SN (ON) 124004376

Part: BATTERY — DEFECTIVE (ZONE 100) · airframe 12,749 hrs · 9,759 cycles

ONE OF THE EMERGENCY BATT PACKS IS NOT HOLDING A CHARGE. EMER EXIT LIGHTS AROUND MAIN CABIN DOOR ARE NOT WORKING (3 LIGHTS BOTH ON SIDES OF DOOR AND ONE ABOVE), 2 CEILING LIGHTS ON SIC SIDE, HALF OF AISLE LIGHTS ARE OUT. // SIGNOFF// REMOVED FAULTY FWD EMERGENCY BATTERY PACK AND INSTALLED OVEHAULED EMERGENCY BATTERY PACK. REF CE 560XL/XLS AMM 33-50-01. OPS CHECKS GOOD REF

Part: SIGN — INOPERATIVE (EMERGENCY LIGHTS) · airframe 12,148 hrs · 9,311 cycles

CABIN EMERG LIGHT: RED EXIT SIGN ABOVE PRECATCH (FORWARD OF MAIN CABIN DOOR) IS INOP. WHEN ACTUATING AND/OR JIGGLING THE PRECATCH LEVER, SOMETIMES THE EXIT SIGN WILL ILLUMINATE INTERMITTENTLY. REMOVED AND REPLACED CABIN EMERGENCY LIGHT FORWARD OF MED IAW CE-560XL 33-50-00. OPS CHECK GOOD.

Part: PIN — LACK OF LUBE (PAX DOOR) · airframe 11,984 hrs · 9,202 cycles

WHEN OPENING MAIN CABIN DOOR FROM THE OUTSIDE, THE HANDLE IS STIFF. WHEN RETURNING THE OUTER HANDLE TO THE STOWED POSITION AFTER UNLOCKING PINS, IT DRAGS THE DOOR PINS WITH IT TO THE EXTENDED POSITIONS. SEEMS IT NEEDS LUBRICATED INTERNALLY. CLEANED AND LUBED BOTH INTERNAL AND EXTERNAL MAIN CABIN DOOR HANDLES, IAW CE-560XL SPM 20-40-10. OPERATIONAL CHECKS, NORMAL PER CE-560XL AMM 52-10-01.

Part: LIGHT — DEFECTIVE (CABIN) · airframe 11,077 hrs · 8,543 cycles

COCKPIT ODOR BURNING SMELL - ON DECENT INTO IAD, AT FL180, WE STARTED SMELLING A BURNING ELECTRICAL OR METALIC SMELL. THERE WAS NO SMOKE AND I'M NOT SURE WHAT THE SOURCE WAS. IT WAS MOST INTENCE AT 180 AND REMAINED UNTILL LANDING WHEN IT THINNED OUT. ALSO NOTE THAT IT STARTED WHEN WE STARTED THE APPROACH CHECK LIST, TURNNING ON IGNITIONS, LIGHTS, ETC. //SIGNOFF// REMOVED BOTH PFD AND MFD SCREENS AND INSPECTED INTERNAL FANS FOR EXCESS LINT AND FOUND NONE. INSPECTED INSTRUMENT PANEL FANS FOR EXCESS LINT AND OPERATION, NO LINTFOUND AND FANS OPS CHECKED GOOD. LNSPECTED RECCRC FAN FOR OPERATION AND BLOCKAGE AND NO BLOCKAGE FOUND AND FAN OPS CHECKED GOOD. WHILE RUNNING APU LOADED UP ELECTRICAL SYSTEM FOR 1.5 HOURS AND NO ABNORMAL SMELL WAS NOTICED. CHECKED OPERATION OF PFDS AND MFD INTERNAL FANS AND TIIEY OPS CHECKED GOOD. RAN APU WITH ACRON AND NO ABNORMAL SMELL WAS NOTICED. REVLEWED PILOTS CHECKLLST FOR POSSIBLE SCENARIOS AND ALL OPS CHECKED GOOD. RAN ENGINES FOR 45 MINUTES WITH APU OFF AND ENGIN!C. BLEED AIR ON WITH NO DEFECTS NOTED. TURNED ON ALL EXTERIOR AND COCKPIT LIGHTING FOR OVER 2 HOURS WITH NO BURNING SMELL NOTICED. AS PER MX CONTROL RECOMMENDATIONS THEY ASKED US TO PERFORM A DUCT BURN OUT AND OPERATE ALL CABIN SYSTEMS, NO DEFECTS WERE NOTED. DURING COMPLETION OF DUCT BURNOUT IA W TC-5XL-2 L -I 20902M WE WERE INSPECTING CABIN LIGHTING AND NOTICED TL IE UH ISLE LIGHTING IN FRONT OF GALLEY FLICKERING AND WHEN ~ BENT DOWN TO LNSPECT 1 NOTICED THE BURNING SMELL 1N FRONT OF GALLEY. REMOVED ALSLE STRIP LIGHTFNG AND FOUND IT SEVERELY BURNED AND SHORTED OUT IN SECTIONS. WHEN REMOVING STRIP LIGHTING IT BROKE APART IN OUR HANDS. SENT PICTURES TO MX CONTROL AND !ORDERED NEW STRIP LIGHTING. REMOVED AND REPLACED TWO FORWARD MOST LT DROPPED ALSLE LIGHT ASSY'S LAW 33-20-04. PERFORMED ADDITIONAL OPS CHECKS. NO ODOR DETECTED. OPS CHECK K}OOD. SMELL NO LONGER DETECTED. ALLOWED AISLE LIGHTS TO REMAIN ON FOR I IIR. NO DEFECTS.

Part: WINDOW — DEFECTIVE (COCKPIT) · airframe 10,708 hrs · 8,246 cycles

WHILE IN CRUISE FLIGHT AT 40000 FT THE PILOT SIDE LEFT SIDE WINDOW DE ICE ELEMENT ON LOWER PANE BEGAN ARCING AND SPARKING. TRIED TO ISOLATE THE WINDOW FROM POWER AFTER FOLLOWING APPLICABLE CHECKLIST. THE ARC AND SPARKING GOT BIGGER AND STRECHED FURTHER ALONG THE ELEMENT UNTIL POWER WAS REMOVED. REMOVED & REPLACED PILOT SIDE HEATED WINDOW IAW CE-560XL M/M 56-12-00. OPS CHK GOOD.

Part: ENGINE — ODOR (LEFT) · airframe 10,188 hrs · 7,846 cycles

DURING FLIGHT, A STRONG ODOR WAS PRESENT, ESPECIALLY DURING TAKEOFF, AFTER WEIGHT OFF WHEELS. THE ODOR WAS SIMILAR TO BURNING PLASTIC. THE ODOR WAS INTERMITTENT THE REST OF THE FLIGHT. THE APU WAS OFF APPROXIMATELY 3 MINUTES BEFORE TAKEOFF AND STAYED OFF THE ENTIRE FLIGHT. TEMPS WERE FULL COLD. REPLACED THE LT ENGINE.

Part: RELAY — FAILED (BRAKE MOTOR) · airframe 6,410 hrs · 4,936 cycles

APPROACHING PARKING AREA, LOW BRAKE PRESSURE & ANTI SKID INOPERATIVE ANNUNCIATORS ILLUMINATED. APPLIED BRAKES, PEDALS WENT TO THE FLOOR & THE BRAKES FAILED. COMPLIED WITH THE WHEEL BRAKE FAILURE MEMORY ITEMS & USED THE EMERGENCY BRAKE HANDLE TO STOP THE ACFT. POST FLIGHT REVEALED BRAKE FLUID DRIPPING FROM THE LT BRAKE ASSEMBLY. REPLACED THE BRAKE MOTOR CONTROL RELAY IAW CE-560XL MM 24-50-03 AND MM 32-44-00. OPS CHECKS GOOD. BLED BRAKE SYSTEM AND EMERGENCY BRAKE SYSTEM AS REQUIRED IAW MM 32-44-00.

Part: VALVE — INOPERATIVE (RUDDER) · airframe 5,376 hrs · 4,142 cycles

AT HIGH POWER SETTINGS THE RUDDER COULD NOT BE USED. LEFT RUDDER PEDAL WAS STIFF AND COULD NOT BE PRESSED. R & R RUDDER BIAS CONTROL VALVE, REMOVED PN 5307-1, SN 1763C. WOULD NOT PASS OPS CHECK, ANNUNCIATOR WOULD NOT COME ON WHEN BREAKER PULLED BUT WOULD COME ON WHEN T/R DEPLOYED. REPLACED RUDDER BIAS CONTROL VALVE, WITH O/H VALVE. LEAK AND OPS CHECKED GOOD. ALSO REMOVED AND REPLACED RUDDER BIAS ACTUATOR IAW REQUEST, REMOVED PN 6660613-12, SN: 5655. LEAK AND OPS CHECKS GOOD IAW MM 27-20-05.

Part: LEAD — BURNED (STARTER GEN) · airframe 5,179 hrs · 4,000 cycles

THE APU WAS OPERATING AND BLEED AIR WAS ENGAGED, PRESSED THE ENGINE START BUTTON FOR NR 2 ENGINE, AFTER FUEL WAS INTRODUCED DURING THE START, THE APU DROPPED OFFLINE AND OUR ENGINE AVIONICS SCREENS MOMENTARILY WENT BLANK. DETECTED A FAINT ODOR OF SMOKE. AFTER THE ENGINE START WAS COMPLETED THE ODOR OF SMOKE INCREASED, SAW CABIN FILLING WITH SMOKE. IT APPEARED TO BE COMING OUT OF THE WEMAC ABOVE SEAT NR 7. BATTERY. TEMP WAS AROUND 90 DURING THE START SEQUENCE. NO ABNORMALITY NOTED IN THE TAIL SECTION. FOUND APU STARTER GENERATOR "B" TERMINAL LEAD END MELTED AND WELDED TO TERMINAL STUD. REMOVED AND REPLACED APU STARTER GENERATOR AND REMOVED AND REPLACED APU "B" TERMINAL LEAD. OPERATED APU AND BOTH ENGINES FOR 30 MINUTES. NO SMOKE WAS PRESENT IN THE CABIN AT ANY TIME. LEAK AND OPERATIONAL CHECKED SATISFACTORY. ALL WORK DONE IAW MM 24-31-02.

Part: UNKNOWN — SMOKE (CABIN) · airframe 5,112 hrs · 3,947 cycles

HEAVY SMOKE ENTERED AFT CABIN TO THE COCKPIT WHEN THE APU BLEED WAS TURNED ON. THE CABIN GOT HOT AND A RUMBLING NOISE WAS HEARD. THE ACFT WAS SHUTDOWN. PERFORMED APU RUNS. PERFORMED ECU OPS CHECKS WITH NO DEFEFCTS NOTED. RAN APU BLEED AIR TO FULL HOT AND FULL COLD IN AUTO AND MANUAL MODES WITH NO SMOKE IN COCKPIT OR CABIN AT ANY TIME DURING 1 HOUR APU RUNS. REINSPECTED APU OIL LEVEL AND FOND SAME AS WHEN STARTED RUNS. ALL WORK PERFORMED IAW AMM 21-10-00, 21-51-00 AND 49-00-00.

Part: PUMP — INOPERATIVE (HYD PACK) · airframe 4,859 hrs · 3,750 cycles

LOW BRAKE PRESSURE ANNUNCIATOR ILLUMINATED, ACTIVATED ANTI-SKID INOPERATIVE. CIRCUIT BREAKER WAS NOT POPPED. R & R THE HYD POWER PACK MOTOR PUMP AND FILTER IAW MM 32-44-20. BLED BRAKES AND OPS CHECKED. OPS & LEAK CHECKS GOOD.

Part: CHANNEL — CRACKED (FWD CARGO DOOR) · airframe 4,731 hrs

DURING A SCHEDULED INSPECTION, FOUND THE FWD BAGGAGE DOOR HINGE ASSY CRACKED IN SEVERAL PLACES. TWO CRACKS IN SUPPORT CHANNEL 66120720-2 AND ONE CRACK ON CHANNEL 6612069-11.THE CRACKS WERE FOUND BY VISUAL INSPECTION. THIS AIRCRAFT HAD SB560XL-52-13 INSTALLED AT THE FACTORY.

Part: HINGE BRACKET — CRACKED (RT ELEVATOR) · airframe 4,731 hrs

DURING A SCHEDULED MX, FOUND THE RT ELEVATOR HINGE BRACKET CRACKED ON THE LOWER FLANGE. REMOVED THE BRACKET ASSY AND FOUND THE UPPER FLANGE WAS CRACKED USING EDDY CURRENT INSPECTION.

Part: HINGE BRACKET — CRACKED (LT ELEVATOR) · airframe 4,731 hrs

DURING A SCHEDULED MX, FOUND ON THE LT ELEVATOR HINGE BRACKET CRACKED ON THE LOWER FLANGE. REMOVED THE BRACKET ASSY AND FOUND THE UPPER FLANGE WAS CRACKED USUING EDDY CURRENT INSPECTION.

Part: SKIN — CRACKED (TAIL CONE) · airframe 4,731 hrs · 3,643 cycles

TAILCONE SKIN CRACK DAMAGED AT APU HEAT SHIELD ATTACHMENTS. COMPLETED MFG REPAIR DEFINITION ATA53/03RD.

Part: CIRCUIT BREAKER — TRIPPED (ANTI SKID SYS) · airframe 4,148 hrs · 3,195 cycles

POWER BRAKE CIRCUIT BREAKER TRIPPED OFF DURING TAKEOFF, GIVING A ANTI-SKID INOPERATIVE CAUTION. INSPECTED POWER BRAKE PUMP. ANTI SKID ROTARY TEST GOOD. NO FAULTS FOUND ON FAULT DISPLAY UNIT. TAXIED ACFT AND NO DEFECTS NOTED, REF MM 32-42-00.

Part: SERVO — FAILED (BLEED VALVE) · airframe 2,787 hrs · 2,161 cycles

LEFT EEC FAILED IN FLIGHT, THE THROTTLE WOULD NOT RESPOND IN AUTOMATIC OR MANUAL MODE, IT WAS STUCK IN FLIGHT IDLE. AFTER FOLLOWING TAB O1, PERFORMED AN ENGINE FAILURE PRECAUTIONARY SHUTDOWN. PERFORMED FUEL CONTAMINATION CHECK AND INSPECTION OF LT ENGINE FUEL FILTER. NO DEFECTS NOTED. INSTALLED NEW FUEL FILTER AND ORINGS.TROUBLESHOT TO DEFECTIVE BLEED VALVE TORQUE MOTOR. REMOVED AND REPLACED TORQUE MOTOR WITH NEW. PERFORMED ALL REQUIRED NEW CHECKS. OPS AND LEAK CHECKS GOOD. WORK PERFORMED PER ENGINE MM 73-10-05, 75-30-01 AND 71-00-00.