N313QS
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
BLENDED MULTIPLE AREAS OF CORROSION ON THE UPPER AND LOWER SKINS OF THE HORIZONTAL STABILIZER, NEAR LT AND RT TIP CAP, LH AND RH IB ELEVATOR HINGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, PRIMED, AND TOPCOATED AREAS.
MECHANICALLY REMOVED 1 AREA OF CORROSION AND 1 AREA OF BARE METAL LOCATED ON LH HORIZONTAL STAB UPPER SKIN NEAR INBOARD ELEVATOR HINGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. FABRICATED AND INSTALLED REPAIR DOUBLERS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED 2 AREAS OF CORROSION LOCATED INSIDE LH HORIZONTAL STAB ELEVATOR COVE, LOWER SPAR CLIP BETWEEN INBOARD AND MIDDLE ELEVATOR HINGE ATTACHMENTS, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED 1 AREA OF CORROSION ON THE UPPER AFT CORNER OF THE CUT OUT OF THE E-EXIT ON FUSELAGE SKIN, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED CORROSION LOCATED ON RH WING AFT SPAR, AFT FACE OF SPAR WEB BELOW SPOILER PANEL #9 AROUND PRESSURE AND RETURN HYDRAULIC LINE CARRY THROUGH FITTINGS, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED 1 AREA OF CORROSION AND 1 AREA OF BARE METAL LOCATED ON LH HORIZONTAL STAB UPPER SKIN NEAR INBOARD ELEVATOR HINGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. FABRICATED AND INSTALLED REPAIR DOUBLERS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
CORROSION FOUND WHERE LT AND RT WING AND FUSELAGE MEET.
CORROSION FOUND WHERE LT AND RT WING AND FUSELAGE MEET.
CORROSION FOUND ON TAIL AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATA PLATE. PERFORMED EDDY CURRENT INSPECTION FOR CRACKS AND CORROSION ON BLENDED AREAS LOCATED ON AFT FUSELAGE AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATE PLATE. PERFORMED ULTRASONIC REMAINING THICKNESS INSPECTION ON BLENDED AREAS LOCATED ON AFT FUSELAGE AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATE PLATE. COMPLIED WITH RFTS-115434 TAILCONE SKIN CORROSION DOUBLER REPAIR.
CORROSION FOUND ON TAIL AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATA PLATE. PERFORMED EDDY CURRENT INSPECTION FOR CRACKS AND CORROSION ON BLENDED AREAS LOCATED ON AFT FUSELAGE AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATE PLATE. PERFORMED ULTRASONIC REMAINING THICKNESS INSPECTION ON BLENDED AREAS LOCATED ON AFT FUSELAGE AROUND AIRCRAFT DATA PLATE AND JUST AFT OF DATE PLATE. COMPLIED WITH RFTS-115434 TAIL CONE SKIN CORROSION DOUBLER REPAIR REV. 0 DATED 31OCT25.
LIGHTS CONNECTED TO THEIR RESPECTIVE EMERGENCY LIGHTING BATTERY PACK FAILED TO OPERATE AFTER TWO 30 MINUTE CHARGING SESSIONS. THE TWO LOWER SIDES OF MAIN CABIN DOOR FRAME, ONE ABOVE EMERGENCY EXIT, ONE ON BULKHEAD BEHIND SEAT 9. CORRECTIVE ACTION: REMOVED AND REPLACED ALL EMERGENCY BATTERY PACKS IA W CE680 AMM 33-50-10. PERFORMED RECHARGE PROCEDURE AND OPS CHECK. OPS CHECK GOOD EXCEPT FOR OUTSIDE FWD OVERWING EMER LIGHT NOT ILLUMINATING. SEE DISCREPANCY 6.
REPAIRED CORRODED AREAS OF THE VERTICAL STABILIZER SKINS LOCATED NEAR THE UPPER EDGE AND ONE NEAR THE FORWARD EDGE BY BLENDING, PERFORMING NDT, REPORTING FOR REPAIR DEPOSITION, CLEANING, TREATING, PRIMING AND FABRICATING AND INSTALLING REPAIR DOUBLERS IAW AEROSPACE QUALITY RESEARCH & DEVELOPMENT MRO ENGINEERING REPAIR ORDER.
EMERG EXIT SIGN/LIGHT: THE AFT LAV EMERGENCY EXIT SIGN IS INOP. THE AFT DIVIDER OVERHEAD EMERGENCY EXIT SIGN IS INOP. CORRECTIVE ACTION: CHECKED THE EMERGENCY POWER SUPPLY BATTERY #4 FUSE AND FOUND IT BURNT. PERFORMED WIRING CHECK AND FOUND WIRES GOING TO THE EXIT SIGN ON THE BOTTOM OF THE TOILET SEAT PINCHED. GAINED ACCESS AND REPAIRED THE DAMAGED WIRES AS REQUIRED. REPLACED THE EMERGENCY POWER SUPPLY BATTERY #4 FUSE PN: AGC5. PERFORMED OPS CHECK AND THE OPS CHECK WAS SATISFACTORY. CLOSED ACCESS AND RETURNED THE AIRCRAFT TO ITS ORIGINAL CONFIGURATION. WORK WAS DONE IRW CE-680 SPM 20-30-15 AND AMM 33-50-00.
DURING DESCENT FROM FL350 WITH ANTI-ICE ON THE ENGINE CONTROL FAULT R AMBER CAS MESSAGE ILLUMINATED. FAULT MESSAGE WAS RESET AFTER PUSHING THE FADEC RESET. REMOVED PN HG1153CA04, SN 08053096 DUE TO "RH ENG CONTROL FAULT" CAS MESSAGE. INSTALLED A REPAIRED UNIT AND COMPLETED LEAK AND OPS CHECKS WITH NO FAULTS. WORK DONE WITH REFERNCE TO AMM. INSTALLED UNIT. WORK DONE WITH REFERENCE TO AMM 34-12.00
ON PREFLIGHT, ALL EMERGENCY LIGHTS INTERIOR AND EXTERIOR DO NOT ILLUMINATE WITH THE EMER LTS SELECTED ON. IN ARM, AFT EMERGENCY EXIT LIGHTS DO NOT ILLUMINATE. MET WITH CREW AND VERIFIED DISCREPANCY. GAINED ACCESS TO #4 EMER LIGHT POWER SUPPLY AND INSPECTED CONNECTIONS FOR SECURITY OF INSTALLATION AND DAMAGE WITH NO DEFECTS FOUND. PERFORMED G SWITCH RESET PROCEDURE WITH NO SUCCESS. UPON FURTHER INSPECTION OF #4 POWER SUPPLY FOUND FUSE BLOWN. REMOVED AND REPLACED #4 EMER POWER SUPPLY FUSE AND PERFORMED EMERGENCY LIGHTS OPS CHECK AND NETJETS AVIATION, INC TASK CARD TC-FL T-33-1001. WITH NO DEFECTS NOTED, EMERGENCY LIGHTS SYSTEM OPS CHECK GOOD. AFTER PERFORMING CHARGE FOR 60 MIN, PERFORMED ANOTHER OPS CHECKS AND FUSE BLEW AGAIN. REPLACED #4 EMER POWER SUPPLY FUSE. REPOSITIONED EMER LIGHT POWER SUPPLY #2 AND #4 AND THE ORIGINAL #2 POWER SUPPLY IN THE #4 POSITION BLEW ITS FUSE. REINSTALLED #2 POWER SUPPLY TO ORIGINAL LOCATION WITH NEW FUSE. REINSTALLED #4 EMER LIGHT POWER SUPPLY TO ITS ORIGINAL POSITION. CHECKED FOR POWER AND GND AT CP UF008, CONSTANT 28V AND GOOD GROUND. GAINED ACCESS TO CP JI 108V AND DISCONNECTED CP J 1108 TURNED EMER LIGHT SWITCH TO ON, ALL EMER LIGHTS ILLUMINATED WITH NO ISSUES EXCEPT THE LAV AREA LIGHT THAT ARE CONTROLLED BY THE #4 EMER POWER SUPPLY. VERIFIED POWER AT PLUG PII08V FOUND GOOD POWER AT PINS A,B,E,G, F, K. INSPECTED THE WIRING JNVOL VED WITH THE #4 EMERGENCY BA TIER Y PACK AND FOUND THAT THE TOILET DISCONNECT HARNESS (PI0L2V) WIRES WERE PINCHED UNDER THE LAV MOUNTING BRACKET AND WERE CUT. REMOVED DAMAGED WIRES AND INSTALLED NEW WIRES, CONNECTOR, AND PINS AW CITATION ST AND ARD PRACTICES MANUAL CH 20-30-25 AND CESSNA AIRCRAFT COMPANY MODEL 680 IMM & !PC CH 25-92-02. OPS CHECKED GOOD. ORIGINAL SUBMISSION DATE: 8-28-2023.
REPAIRED CRACKED INBOARD END RIB OF THE RH HORIZONTAL STABILIZER, LOWER FLANGE AT RBL 8.8, PER REPAIR -2 OF TEXTRON REPAIR DEFINITION S-680-ATA55/08RD REVISION â BY NDT MAPPING CRACK, TRIMMING CRACKED AREA, FABRICATING AND INSTALLING REPAIR PIECES.
DEPARTED APF, APU OFF FOR TAKEOFF. LEVELED OFF AT 2000 FT PER CLEARANCE & NOTICED A HOT BURNING OIL ODOR, REDUCED POWER AT 2,000 FT TO KEEP A SLOW AIRSPEED, ODOR BEGAN TO EASE. VISUAL INSP SHOWED NO OIL ON ENG COWLINGS OR UNDER APU. OIL LEVELS CHECKED GOOD. RAN APU, NO ODOR NOTED, PERFORMED ENG RUN & SIGHT ODOR. REPLACED SOCK & ENG RUNS AGAIN. & ODOR SLIGHTLY OBSERVED AFTER LT ENG START. REMOVED DUCTS FROM WATER SEPARATOR & NOTICED ODOR. REMOVED BLEED DUCTS & CLEANED. FOUND NO OILY RESIDUE, SLIGHT ODOR. REINSTALLED BLEED DUCTS. CLEANED TIRE DUCT & PERFORMED BURN OUT PROCEDURE AGAIN, NO ODOR. PERFORMED DUCT BURN OUT, R & R WATER SEPARATOR CONDENSER BAG IAW AMM 21-51-00. NO DEFECTS NOTED.
APU BLEED AIR: COULD NOT CONTROL CABIN TEMP BELOW 80 DEGREES. STARTED APU AND SELECTED BLEED AIR ON. ODOR OF BURNT OIL ENTERED CABIN AND THEN BLEED SELECTED OFF. ON GROUND BEFORE FLIGHT THERE WAS NO ODOR W BLEED AIR ON. APU WAS STARTED AFTER SLOWING AIRCRAFT AT 20,000 FT. // SIGNOFF// REMOVED ACM PT#2206610-L SN 498 AND INSTALLED A SERVICEABLE UNIT FROM N339QS PT# 2206610-1 SN 974, REMOVED ACM EXHAUST DUCT PT# 6915050-41 NSN AND INSTALLED A NEW EXHAUST DUCT PT# 6915050-41 NSN , REMOVED TEMP CONTROL VL V PT#27241287-L 4 SN 9BA243F AND INSTALLED AN OVHLD VLV PT# 27241287-14 SN L 0BC370F, WHILE DOING LK AND OP'S CHECK FOUND THE WATER SEPARATOR LEAKING FROM CLAMP JOINT, REMOVED WATER SEPARATOR PT# 2341316-2 SN 758 AND INSTALLED AN OVHLD UNIT PT# 23413 16-2 SN 622 LA W HONEYWELL OPERATION AND MAINTENANCE MANUAL 2215460 & 23413 16, CE680 AMM CH 21-22-05, 21-21-03
EMERGENCY LIGHTING: WHEN DOING THE EMERGENCY LIGHT CHECK, THE ONLY LIGHTS WORKING ARE THE EXIT LIGHT OVER THE MAIN CABIN DOOR, THE OVERHEAD LIGHT BETWEEN SEATS 3 AND 5 AND THE OVERHEAD LIGHT OVER SEAT 9. THE DOORFRAME EXIT SIGNS, THE AISLE LIGHTING, THE DIVIDER EXIT SIGN AND ALL THE LIGHTS ON THE STARBOARD SIDE ARE NOT WORKING. PERFORMEDTC-FLT-33-1001 EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE REV 0 DATED 15DEC2021. NO DEFECTS NOTED. OPS CHECKS GOOD.
CABIN EMERG LIGHT: RIGHT SIDE CABIN EMERGENCY LIGHTS INOP. LEFT SIDE OPERATES NORMALLY. // SIGNOFF// RAN APU FOR 1 HOUR TO CHARGE THE EMERGENCY BATTERIES. PREFORMED OPS CHECK OF THE EMERGENCY LIGHTS AND NO DEFECTS FOUND JAW SOVEREIGN 680 AMM 33-50-00
ANTISKID FAIL AMBER CAS: ON CLIMB OUT WE HAD A FLICKERING AMBER ANTISKID FAIL CAS MESSAGE. THE CHECKLIST HAD US TURN IT OFF SINCE THE MESSAGE WOULD NOT CLEAR. WE LANDED IN THE OFF POSITION. // SIGNOFF // REMOVED THE ANTI-SKID CONTROLLER AND INSTALLED SERVICEABLE CONTROLLER FROM N324QS, PERFORMED ANTI-SKID CONTROLLER OPERATONAL CHECK JAW CE680 MM 32·42·00. OPS CHECK GOOD. NO FAILS NOTED. PERFORMED FUNCTIONAL CHECK OF THE ANTI"SPIN SYSTEM IAW CE680,MM 32·42·00. FUNCTIONAL CHECK GOOD. NO FAILS OR FAULTS NOTED.
BLENDED CORRODED AREAS OF THE LOWER SURFACE OF THE RH LOWER WING SKIN, BELOW THE AFT SPAR CAP NEAR THE MAIN LANDING GEAR WHEEL WELL AREA, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPLACED BLENDED FASTENERS AS REQUIRED, TREATED, PRIMED, AND TOP COATED REPAIR AREAS PER TEXTRON REPAIR MEMO.
RIGHT INBOARD MLG TIRE: BRAKE FROZEN. TIRE DAMAGED.
RIGHT INBOARD MLG TIRE: BRAKE FROZEN. TIRE DAMAGED. WE FOUND THAT THERE WAS ICE BUILD-UP 0F THE RT INBOARD BRAKE. AFTER REMOVING THE ICE WE WERE ABLE TO TURN THE WHEEL AND WE CONFIRMED THAT THE TIRE WILL NEED TO BE REPLACED. WE REMOVED THE MLG WHEEL ASSY REF CE-680 AMM 32-11-02. WE INSPECTED THE BRAKE ASSEMBLY NO DAMAGE NOTED THE RT INBOARD BRAKE ASSEMBLY. WE ALSO CONFIRMED THAT THE BRAKE ACTUATES NORMALLY. WORK DONE IAW CE-680 AMM 32-42-00. INSTALLED AN OVERHAULED MLG WHEEL ASSEMBLY REF CE-680 AMM 32-41 -02. PER MCC REQUEST WE TAXIED THE AIRCRAFT TO VERIFY THAT THE BRAKES WERE NOT STICKING AND NO FURTHER DEFECTS NOTED.
VERTICAL STAB HAS 1 AREA OF VERIFIED CORROSION ON LH SPAR CLIP BELOW UPPER RUDDER HINGE. FOUND DURING 6 MONTH INSPECTION. REMOVED LEVEL 1 CORROSION FROM VERTICAL STAB LH SPAR CLIP BELOW UPPER RUDDER HINGE IAW CESSNA 680 SRM 51-70-02. FOUND BLENDED AREA TO BE BEYOND SRM LIMITS IAW CESSNA 680 SRM 51-70-02. SUBMITTED FINDINGS TO TEXTRON ENGINEERING FOR REPAIR. PERFORMED TEXTRON FIELD REPAIR FR-680-0140-7699 REV - DATED: 02/18/2020.
ALL LANDING GEAR RETRACTION DID NOT RETRACT - WHEN NOSEWHEEL CAME OFF THE GROUND ON TAKEOFF, THE MASTER WARNING LIGHT ILLUMINATED. THE GEAR HANDLE WOULD NOT MOVE AND "WOW MISCOMPARE" AMBER CAS MESSAGE DISPLAYED. "CORRECTIVE ACTION" TROUBLESHOT LANDING GEAR SYSTEM. UPON JACKING AIRCRAFT,FOUND NLG GEAR LOWER BARREL ASSEMBLY WAS STUCK HALF WAY UP THE UPPER BARREL CAUSING THE NLG SQUAT SWITCH NOT TO ENGAGE TO THE IN-AIR POSITION. SERVICED NLG TO WITHIN LIMITS PER CESSNA 680 MM 12-20-32.
DURING CLIMB OUT, AT APPROXIMATELY FL 350 IN MCT THRUST, THERE WERE SEVERAL ENGINE COMPRESSOR STALLS ON THE RT ENGINE. DURING THE STALLS THE ITT EXCEEDED 900. THE STALLS WERE SEVERE ENOUGH TO CAUSE THE AIRPLANE TO YAW. THE STALLS WENT AWAY WHEN POWER WAS REDUCED. REMOVED AND REPLACED THE RT ENGINE.
SHORTLY AFTER STARTING THE APU AND SELECTING BLEED ON, A GRAYISH SMOKE COULD BE SMELLED AND SEEN THROUGHOUT THE CABIN AND COCKPIT. SMOKE DISSIPATED AFTER APU SHUT DOWN.
AT CRUISE FL340, THE AIRPLANE MADE A LOUD POP, THEN A BANG, FOLLOWED BY A VIBRATION , YAW, AND ITT OVERTEMP/ N1 OVERSPEED ON THE RIGHT ENGINE. BOTH POWER LEVERS REDUCED IMMEDIATELY. BOTH ENGINE PARAMETERS INDICATED NORMAL RANGES. FLIGHT RETURNED TO DEPARTURE AIRPORT AND LANDED WITHOUT INCIDENT. POST FLIGHT REVEALED NO EXTERIOR DAMAGE. SWAPPED LT & RT BLEED AIR CONTROL PCBS. REMOVED RT HPRSOV & INSTALLED NEW HPRSOV IAW AMM 36-00-00. ALL LEAK & OPS CHECKED WERE PERFORMED SATISFACTORY.
EMERGENCY EXIT DOOR SKIN HAS SEVERAL AREAS OF CORROSION AROUND PERIPHERY NEAR COMPOSITE RING. FOUND DURING PAINT PROCESS. REMOVED SEAL AND COMPOSITE RINGS AND BLENDED CORROSION. CORROSION FOUND TO BE BEYOND LIMITS. REMOVED THE EMERGENCY EXIT DOOR, AND INSTALLED NEW DOOR.
FAIRING DAMAGE.
VERTICAL STABILIZER LEFT AND RIGHT SKIN DAMAGE.
HORIZONTAL STABILIZER LEFT AND RIGHT UPPER AND LOWER SKIN DAMAGE.
VERTICAL FIN REAR SPAR DAMAGED.
LEFT ELEVATOR SKIN CORRODED.
VERTICAL STAB LEADING EDGE UPPER LEFT EDGE DELAMINATED.
RUDDER HINGE BRACKET CORRODED.
BULKHEAD BOND ASSY. DAMAGED, DOUBLER CRACKED, NICKED AND DEBONDED.
CORROSION DAMAGE FOUND ON LT UPPER WING SKIN. REPAIRED IAW STRUCTURES REPORT NR: S-680-0140/06RD.
CORROSION FOUND AT DISCRETE LOCATIONS ON THE STR AND TAILCONE SKINS. REPAIRED IAW STRUCTURES REPORT S-680-0140/04RD.
CORROSION FOUND AT MULTIPLE SITES ON THE LT & RT VERTICAL STABILIZER SKINS. REPAIRED IAW STRUCTURES REPORT NR: S-680-014/05RD.
GEAR WOULD NOT RETRACT, GEAR HANDLE COULD NOT BE MOVED. AFTER ACFT WAS JACKED BROUGHT UP CDMS TO LANDING GEAR PAGE. WITH NO HYD TRIED TO PULL GEAR HANDLE BUT HANDLE WOULD NOT PULL FROM DOWN POSITION. VIEWED CDMS & CORRECT COMMANDS WHERE PRESENT POWER & GND TO ALLOW HANDLE TO PULL. REMOVED SCREWS SECURING HANDLE & MOVED ASSEMBLY FWD, HANDLE WOULD STILL NOT PULL. TAPPED ON THE SIDE OF THE GEAR HANDLE ASSEMBLY & THEN WAS ABLE TO PULL HANDLE TO UP POSITION. APPLIED HYD & GEAR SWINGS WERE NORMAL. WHEN HANDLE WAS PULLED OUT & THEN SNAPPED BACK INTO PLACE BY QUICKLY RELEASING HANDLE TO UP POSITION. GEAR HANDLE ASSEMBLY WAS PLACED ON ORDER. GEAR CONTROL HANDLE REMOVED PN 721101-5, SN 025. JACKED ACFT & APPLIED HYD. INSTALLED CUSTOMER SUPPLIED SERVICEABLE GEAR HANDLE ASSEMBLY PN 9912550-1, SN M5469 IAW MM CHAP 32-30-10. PERFORMED GEAR OPERATIONAL CHECKS IAW MM CHAP 32-00-00. OPERATIONS CHECKED GOOD. DOWN JACKED & SERVICED HYD.
GEAR WOULD NOT RETRACT, GEAR HANDLE COULD NOT BE MOVED. REMOVED GEAR HANDLE & BENCH CHECKED SOLENOID OPERATION. APPLIED POWER & GND, HANDLE REMAINS LOCKED DOWN. INTERMITTENTLY HANDLE WILL UNLOCK. SOLENOID COIL HAS EXCESSIVE RESISTANCE. GEAR HANDLE ASSEMBLY IS FAULTY. REMOVED LG CONTROL ASSEMBLY PN 721101-5, SN 077 & INSTALLED LG CONTROL ASSEMBLY PN 049801-001, SN 025. LG OPERATIONAL CHECK GOOD IAW MM 32-30-10.
DURING A SCHEDULED INSPECTION WE TRIED TO INSTALL A NEW FILTER ELEMENT. THE ELEMENT WOULD NOT SIT INTO THE BOTTOM OF THE FILTER HOUSING BOWL. THE FILTER WAS REJECTED & RED TAGGED BY THE TECHNICIAN & RETURNED TO THE MATERIALS DEPARTMENT. WE HAD IN THE PAST REJECTED THIS SAME PN FILTER FOR THE SAME DEFECT & SUBMITTED SCRS TO A/C MANUFACTURER & AN SDRS TO THE FAA. A/C MANUFACTURER CLAIMS TO HAVE PURGED THEIR STOCK OF THIS DEFECTIVE FILTER ELEMENTS. THIS ELEMENT IS LOT NUMBER 395141, MFG DATE 4/13. THIS PROBLEM HAS BEEN REPORTED TO A/C MANUFACTURER UNDER SCR REPORT NUMBER 677262.
APPROXIMATELY 20 MIN INTO FLIGHT AT FL430, CREW NOTICED A HOT SMELL. 5 MINUTES LATER A WHITE GRAY SMOKE ENTERED THE COCKPIT & CABIN. THE PRESS SOURCE SELECT KNOB WAS SELECTED TO L IAW ENVIRONMENTAL SMOKE CHECKLIST. SMOKE DISSIPATED DURING DESCENT & LANDING OVER 20 MIN PERIOD EN ROUTE TO ALTERNATE AIRPORT. REMOVED RT ENG SN PCE CG0286 & INSTALLED A SERVICEABLE ENG PCE-CG0027. PERFORMED OPERATIONAL CHECKS, LEAK CHECKS & 5 POINT ENG CALIBRATION RUN WITH NO DEFECTS NOTED. ALL WORK PERFORMED IAW CE-680 MM 71-00-10, 71-00-20, 71-00-30 & PWC 306C EMM 71-00-00.
SMOKE IN CABIN AT FL 430. DURING CLIMBOUT ABOUT 14,000 APU SYS FAIL ANNUNCIATOR CAME ON AND APU SHUTDOWN. APU GEN HAD BEEN OFF, BUT BLEED AIR ON. APPROX 30 MINUTES LATER, LEVEL AT FL 430 ADVISED OF A LITTLE SMOKY IN CABIN. FINE GREY ENVIRONMENTAL SMOKE/HAZE OBSERVED IN CABIN WITH BURNED OIL ODOR. INITIATED 3,000 FPM DESCENT, THROTTLES IDLE AND SMOKE DISSIPATED WITHIN 5 MINUTES. DID NOT RE-OCCUR. REMOVED LT ENG AND INSTALLED SERVICEABLE ENGINE. PERFORMED OPS & LEAK CHECKS AND 5 POINT ENGINE CALIBRATIONS WITH NO DEFECTS OR OIL ODOR OR SMOKE NOTED. ALL ENGINE PARAMETERS ARE WITHIN LIMITS AT THIS TIME. ALL WORK PERFORMED IAW AMM 71-00-10, 71-00-20, 71-00-30 AND EMM 72-00-00. COMPLETED SEVERAL OPS CHECKS OF APU WITH NO DEFECTS NOTED.
NOSE GEAR MADE LOUD BANGING NOISE UPON GEAR RETRACTION, SHOOK GLARE SHIELD. NOSE STRUT WITHIN LIMITS RETRACTION GUIDES SEEM TO ALIGNED CORRECTLY. CYCLED GEAR, UNABLE TO DUPLICATE. CHECKED SERVICE OF NOSE STRUT FOUND LOWER CHAMBER TO BE LOWER AT 15 PSI. FOUND LT NOSE WHEEL TO EXCESSIVELY SPIN POSSIBLE CAUSING NOISE AFTER GEAR RETRACTION. REMOVED LT NLG WHEEL, CLEANED BEARINGS. PACKED BEARINGS AND INSTALLED NLG WHEEL ASSY WITH NEW GREASE SEALS REF MM 32-41-10. SERVICED NLG STRUT FLUID AND GAS CHARGE IAW MM 32-20-00, REV 19. NLG CLEARANCE CHECKED GOOD. SERVICE RESEVIOR AND LOWERED ACFT FROM JACKS.
GETTING AN INTERMITTENT ACRID "DIRTY SOCK" ODOR IN CABIN DURING FLIGHT WITH APU OFF. R & R THE WATER SEPARATOR COALESCER IAW MM 21-21-03, 21-50-00. THE OPS AND LEAK CHECKS ARE SATISFACTORY. THERE WAS NO EVIDENCE OR ANY OIL IN THE WATER SEPARATOR.
UPON CLIMBING TO CRUISE ALTITUDE, BRIEF ODOR OF "HEAT" WAS NOTED IN THE COCKPIT. FOLLOWED LATER BY THE PASSENGERS WHO ALERTED THE CREW TO WHITE SMOKE COMING FROM BACK OF THE CABIN. A DIVERSION WAS DECLARED AND UPON REDUCTION OF POWER, SMOKE SOMEWHAT ABBATED AND WAS NON EXISTENT BY THE TIME PLANE TAXIED TO FBO. INSPECTED ECU AND FOUND TURBINES TO BE LOCKED UP AND HEAVY BURNED OIL ODOR IN COALESCER SOCK. CONFIRMED A BAD ECU WOULD CREATE THE CONDITIONS DESCRIBED. R & R ECU IAE MM 21-51-00. R & R COALESCER SOCK IAW MM 12-19-00. ENVIRONMENTAL AND PRESSURIZATION OPS CHECK GOOD ON ENGINE RUN.
WHILE PERFORMING THE 2B INTERNAL WING INSP, FOUND THAT THE LT AND RT ELECTRICAL CONNECTOR BLANKING PINS WERE FALLING OUT BECOMING FOD IN THE CTR FUEL TANK. CONNECOTRS ARE LOCATED IN FUEL ACCESS PANELS 175AB AND 176AB, ON THE FWD WALL.
NOSE GEAR FAILED TO RETRACT INITIALLY DURING GEAR UP CYCLE COMMAND. AFTER 30 SECONDS NOSE GEAR CONTINUED UP CYCLE AND STOWED WITH LIGHT OUT. GREEN AND RED NOSE GEAR INDICATIONS PRESENT DURING EVENT. PERFORMED MULTIPLE OPS CHECKS. INSPECTED CONNECTOR. APPLIED COLD TEMP SPRAY TO CONNECTIONS AND SWITCHES. COULD NO DUPLICATE FAULT. FOUND NOSE STRUT REQUIRED SERVICE. SERVICED STRUT.
DEPARTED PDX RAISED GEAR FOLLOWED BY LOUD BANG, VIOLENT SHAKING. INDICATIONS WERE RED UNLOCK LT AND NOSE WHEEL GREEN LT. SERVICED NOSE STRUT WITH FLUID AND AIR. ADJUSTED NOSE LT AND RT LANDING GEAR SQUAT SWITCHES. GEAR SWING AND OPERATIONAL CHECKS SATISFACTORY. WORK WAS ACCOMPLISHED IAW MM 32-20-00 AND 32-60-00.
AFTER TAKE-OFF, LANDING GEAR WOULD NOT RETRACT.
ABORTED TAKE OFFDUE TO HP FAIL LT CAUTION LIGHT. INSTALLED NEW LEFT HP DIFFERENTIAL PRESSURE SWITCH (SD001). PERFORMED OPERATIONAL CHECK AND LEAK CHECK IAW CE-680 MM 36-10-00. CHECKED GOOD.
AFTER TAKEOFF WHEN GEAR WAS RETRACTED RIGHT MAIN LIGHT AND RED GEAR UNSAFE REMAINED ILLUMINATED. RECYCLED GEAR DOWN NORMAL INDICATION AND LANDED A/C. ITEM IS UNDER INVESTIGATION.
AFTER TAKEOFF WHEN GEAR WAS RETRACTED, ALL 3 GREEN LIGHTS EXTINGUISHED THE RED GEAR UNSAFE STAYED ILLUMINATED THEN THE RIGHT MAIN LIGHT REAPPEARED. RECYCLED GEAR AND ALL LIGHTS EXTINGUISHED. REMOVED PRINTED CIRCUIT BOARD PLB2-4 BOARD FROM ZONE 245 AND INSTALLED NEW PLB IAW CITATION ULTRA MM CH 25-41-02. PERFORMED GEAR FUNCTIONAL CHECK WITH NO DEFECTS NOTED IAW CITATION ULTRA MM CH 32-01-00.
ON COMPLETION OF THE SPOILER TEST THE LT ENGINE QUITS. OPERATED SPEED BRAKES THRU SEVERAL CYCLES, VERIFIED 85 PERCENT SWITCHES RETRACT THE SPEED BRAKES, PERFORMED SEVERAL SLAM CHECKS OF LEFT AND RIGHT ENGINES. NO DEFECTS NOTED, SPEED BRAKES AND ENGINE THROTTLE CONTROL SYSTEMS OPERATE NORMALLY AT THIS TIME. ALL WORK PERFORMED IAW CE 560 M/M 27-61-00 AND 76-11-00.
POWER BRAKE LOW PRESS AND ANTI-SKID INOP LIGHT REMAINED ILLUMINATED ON MASTER CAUTION PANEL AFTER GEAR WAS LOWERED; BRAKES FELT SOFT, HAD TO USE EMERGENCY BRAKE TO COMPLETELY STOP THE AIRCRAFT. ITEM IS UNDER INVESTIGATION.
DURING TAXI OUT FOR DEPARTURE CO-PILOT FELT THE BRAKES MOMENTARILY DISENGAGED. PILOT TOOK CONTROL AND HAD SAME EXPERIENCE. AIRCRAFT RETURNED TO BLOCK. PERFORMED ANTI-SKID SYSTEM CHECK ON GROUND AND SYSTEM PERFORMED NORMALLY.
PILOT REPORTED AFT J-BOX CB ANNUNCIATOR ILLUMINATED IN-FLIGHT. FOUND BAGGAGE HEAT AND APU AUX HYD PUMP CONTROL CB'S LOCATED IN AUX DC J-BOX TRIPPED. USED AN INSP MIRROR AND FOUND NO OBVIOUS WIRING DEFECTS. AFTER SEVERAL HRS OF SYS T/S AFT J-BOX CB ANNUNCIATOR ILLUMINATED. SMOKE WAS EMITTING FROM AUX J-BOX, ALL SYSTEMS WERE SHUT DOWN, FIRE WAS EXTINGUISHED. DURING AUX J-BOX REMOVAL, THE SELF-LOCKING NUT SECURING TERMINAL LUG OF MAIN POWER CABLE WAS FOUND LOOSE. HEAT GENERATED FROM ADDED RESISTANCE TRIPPED CB'S AND CAUSED FIRE. AUX J-BOX PREVIOUSLY REMOVED 1-97 TO ACCOMPLISH SB 29-9. PHASES 1-5 COMPLETED 2-98.