N671QS
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 LAV SERVICE VEHICLE IMPACTED THE RIGHT ENGINE WHILE MANEUVERING TO SERVICE THE LAV PERFORMED PRELIMINARY INSPECTION OF DAMAGE TO RIGHT COWL. 2 ENGINE 1 MEASUREMENTS SENT TO MCC JT 03/23/25 TOOK PICTURES AND MEASURETS ,SENT TO MCC AND AQRD FINAL RFTS HAS YOU PUT ADHESIVE IN DELAMLNATFON AND SAND.PARTS ON ORDER ETA21DO 3/24/25 PERFORMED TEMPOARY REPAIR TO RIGHT ENGINE COWL FN ACCORDANCE WITH RFTS-113376 REV O DATED 24MAR2025.
EMERGENCY LIGHTS WORK AS NORMAL UNTIL THE PAX SAFETY SWITCH IS TURNED OFF, THEN THE REAR EMERGENCY LIGHTS AND EXIT SIGNS STAY ON. REMOVED AND REPLACED RELAY KC006 EMER LT PWR LOSS RELAY FOR TROUBLESHOOTING REF CE-680A M/M 24-60-05 DID NOT FIX SQUAWK ITEM NEEDS FURTHER TROUBLESHOOTING. REMOVED AND REPLACED KC007 EMER LIGHT PILOT CONTROL RELAY IAW MM 24-60-05 AND MM 33-20-00 OPS CHECK GOOD.
RH VERTICAL STABILIZER SKIN CORROSION. REMOVED CORROSION, VERIFIED NO CRACK INDICATIONS, AND MEASURED REMAINING MATERIAL THICKNESS. FOUND TO BE MAJOR IN SCOPE. ACCOMPLISHED AQRD ENGINEERING REPAIR ORDER ERO-977263.
CORROSION ON LEFT VERTICAL STABILIZER SKIN JUST BELOW TOP CAP. LOCATED UNDERNEATH FILLET SEAL COVERING SEAM BETWEEN PARTS. REMOVED CORROSION, VERIFIED NO CRACK INDICATIONS, AND MEASURED REMAINING THICKNESS OF MATERIAL. SUBMITTED TO ENGINEERING AND FOUND TO BE MINOR IN SCOPE. REPLACED ALL SURFACE TREATMENT AND PROTECTION IAW NJA RFTS-109082 AND CE-680A MM 51-20-01.
LH AND RH HORIZONTAL SKIN CORROSION AND SPLICE PLATE CORROSION
APU SMOKE: APPROXIMATELY 2 MINUTES AFTER APU START WITH BLEED AIR ON SMOKE FILLED CABIN. BLEED AIR OFF AND SMOKE DISSIPATED. /// CORRECTIVE ACTION /// REMOVED AND REPLACED APU ASSY PER CE680A AMM 49-10-00 OPS AND LEAKS CHECKS GOOD.
COCKPIT SMOKE: ON THE GROUND WITH MAIN CABIN DOOR OPEN, SHUT DOWN APU MOMENTARILY. ON RE-START, SMOKE CAME FROM COCKPIT AREA AND QUICKLY FILLED CABIN. NO DISCERNABLE, OIL, ELECTRICAL OR OTHER NORMAL SMELL. SHUT DOWN APU AND ALL ELECTRICS AND LEFT AIRPLANE FOR SMOKE TO CLEAR. PERFORMED OPS CHECK OF APU WITH NO DEFECTS NOTED. RAN APU FOR APPROX 45 MINUTES, NO SMOKE OR FUMES NOTED INSIDE OR OUTSIDE AIRCRAFT. BORESCOPED APU INLET AND EXHAUST FOR OIL OR DEBRIES, NO DEFECTS OR LEAKS FOUND. OPS CHECK GOOD AT THIS TIME
ENGINE FIRE R CAS RT ENGINE FIRE DETECTION LIGHT. RT ENG FIRE DETECT LIGHT ILLUMINATED ON CLIMB OUT APPROX 10000-12000 FT FOR 1 SEC. HAD 1 AURAL RT ENG FIRE CALL & RED CAS MSG ILLUMFOR LESS THAN 1 SEC. ALL INDS IMMEDIATELY CHECKED & ENG PARAMETERS NORMAL. ALL INDS NORMAL, NO SECONDARY INDS OF FIRE. NO OTHER OCCURRENCE DURING & REMAINDER OF FLT, ALL NORMAL. REMOVED THE NR 3 GEA 7100 AND INSTALLED A REPAIRED UNIT IAW MM 31-40-15. LOADED THE SOFTWARE INTO THE GEA AND PERFORMED THE G5000 INTEGRATED AVIONICS SYSTEM- ADJUSTMENT TEST IAW MM 34-60-00. PERFORMED THE GARMIN GEA 7100 ENGINE/AIRFRAME INTERFACE UNIT 3 FDR TEST PROCEDURE IAW MM CHAPTER 31-30-00. OPS CHECKED GOOD.
RIGHT ENG FIRE DETECTION LIGHT ILLUMINATED ON CLIMB OUT APPROX 4000-5000 FT FOR ONE SECOND. RECEIVED 1 AURAL RT ENG FIRE CALL & RED CAS MSG FOR LESS THAN 1 SECOND. IMMEDIATELY CHECKED ENG PARAMETERS. ALL INDS NORMAL, NO SECONDARY INDS OF A FIRE. ALL INDS NORMAL REMAINDER OF FLT. PERFORMED ARES DOWNLOAD & SENT TO MANUF.FOR REVIEW. REMOVED PCB & FOUND A CLEAR THICK SUBSTANCE ON CONNECTOR FACES. CLEANED CONNECTIONS IAW SPM 20·30-05. PERFORMED SATIS WIRING CHECKS FROM PCB TO RT ENG FIRE DETECTOR ASSY. NSTALLED PCB & CONNECTOR IAW MM 24-60-35. OPS CHKED GOOD. PERFORMED A SATIS ENG FIRE SENSOR VISUAL CHK OF RT ENG LOOP IAW HM 26-10-00.
RIGHT ENGINE FIRE DETECTION LIGHT: ON CLIMB OUT AT FL210 WE RECEIVED ONE AURAL RT ENGINE FIRE CALL AND THE RED CAS MESSAGE APPEARED FOR ABOUT 1 SECOND. ALL ENGINE INDICATIONS NORMAL AND NO OTHER INDICATIONS ON REMAINDER OF FLIGHT. COULD NOT CONFIRM DISCREPANCY. PERFORMED BITE TEST WITH NO DEFECTS NOTED. DOWNLOADED AND FORWARDED ARES TO TEAM 680A THEY RECOMMEND WIRING CHECKS BETWEEN JZ208 AND PT40B PIN 97. WIRING CHECKS PER CESSNA SPM 20·30·15 REVEALED NO DEFECTS. NEXT TROUBLESHOOTING RECOMMENDED WAS SWAP OF FIRE AND SMOKE PCBS. SWAPPED FIRE AND SMOKE PCBS NZ108 AND NZ208 IAW CE-680A AMM 24-60-35. PERFORMED OPERATIONAL TEST, NO DEFECTS NOTED.
ENGINE FIRE R RED CAS: INFLIGHT AT FL410 AND MCT , RED RIGHT ENG FIRE CAS CAME ON MOMENTARILY. A FEW MOMENTS LATER IT CAME ON AGAIN MOMENTARILY. ATTEMPTED OPS CHECK OF FIRE DETECT SYSTEM FOUND NO DEFECTS. DOWNLOADED ARES DATA AND SENT TO TEXTRON FOR REVIEW. DATA REVEALED THE PCB NZ208 DID NOT SEE NOR DID IT OUTPUT A FIRE SIGNAL. CHECKED WIRING FROM NZ208 TO GEA#3 AND FOUND NO DEFECTS. SWAPPED SMOKE DETECT PCB'S NZ208 AND NZ108 FOR CUSTOMER CONVENIENCE PER TEAM 680. ALL OPS CHECKS GOOD, REVEALING NO DEFECTS. REF CE680A WDM 26-10-30 AND CE680A AMM 26-10-00 NEW PCB LOCATIONS
FIRE DETECTION: AT FL 400 HAD RIGHT ENGINE FIRE CAS AND AUDIBLE WARNING. IT ONLY CAME ON FOR APPROXIAMATELY 2 SECONDS WITH ONLY ONE AUDIBLE WARNING. ALL ENGINE INDICATIONS WERE NORMAL. // SIGNOFF // TRIED RETRIEVINQ THE ARES DOWNLOADS ON EJM RAMP. COULD NOT CONNECT TO THE ARES SYSTEM DUE TO THE ACFT CONNECTED WITH THE EJM WIFI. TAXIED ACFT OUT TO THE RUN UP PAD & CONNECTED WITH THE ARES SYSTEM. FOUND THE LAST EVENT RECORDED ON THE ARES SYSTEM WAS 3-23-21. CONTACTED TEAMLATITUDE TO CHECK SYSTEM FOR DATA FROM THIS ACFT. THEY CONFIRMED NOTHING SINCE 3-23-21. RETURNED TO EJM & CONTINUED T/S ENGINE FIRE R CAS MSG. CHECKED THE PCB NZ208 CONNECTION, PINS & WIRING. NO DEFECTS FOUND. CONTINUED WIRING CHECKS FROM THE GEA #3 & PCB NZ208. NO DEFECTS FOUND. FAULT IS NOT LISTED IN THE CMC ONLY LISTED AS A CAS MSG. CONTACTED TEAMLATITUDE WITH INFO ON THE GEA#3~PCB-NZ208-& WIRNG CHECKS. THEY GOT RECCOMENDATIONS OF REPLACINGTHE NZ208 WITH THE WIRING CBECKS BEING SATISFACTORY & NO ARES DATA TO RESEARCH THE FAULT. RECEIVED NEW FIRE / SMOKE PCB. REMOVED FROM STATIC SHIELD WRAP. FOUND THE TOO AFT CORNER DAMAGED. REPORTED FINDINGS TO MCC ADAM. HE PLACED ANOTHER PCB ON ORDER. ETA ARRIVAL 1235 4-11-21. SHIPMENT DELAYED. LOOKING INTO GETTING A SERVICEABLE UNIT FROM CMH HANGER TO CONTINUE MX . RELOCATED ACFT TO THE SIANATURE FLT SUP RAMP, DUE EJM CLOSES 2100. RECEIVED A SERVICEABLE PCB FROM ACFT N626QS. INSTALLED SERVICEABLE FIRE I SMOKE PCB INTO NZ208. ACCOMPLISHED SYSTEM OPS CHECKS .SVSTEM CKS ARE_GOOD & NO FAULTS & NO CAS MSG'S. RESTORED ALL CONNECTIONS & ACCESS. WORK DONE WITH REF TO CE680A AMM 24-60-35 & 26-25-00.
FOUR DENTS NOTED TO UNDERSIDE OF LH INBOARD WING AND TWO DENTS NOTED TO LH INBOARD LEADING EDGE REPAIRED BY ACCOMPLISHMENT OF FR-680A-0206-8911 REVISION A DATED 22 FEB 2021 WITH 8100-9 DATED 23 FEB 2021. DENTS, LH WING, UPPER SKIN, LOWER SKIN, LEADING EDGE, CWS 90.
AT FL430 THE AMBER PRESSURIZATION FAULT CAS ILLUMINATED. WE INITIATED THE QRH PROCEDURE AI3. THE CHECKLIST CALLS FOR THE PRESSURIZATION AUTO/MANUAL BUTTON TO BE CYCLED. UPON CYCLING THE BUTTON THE CABIN CLIMBED TO 14000 FT. FROM FL430 TILL LANDING THE PRESSURIZATION SYNOPTIC GAVE ERRONEOUS READINGS SUCH AS EXCESSIVE CLIMBING OR DESCENDING, EXCESSIVE CABIN PRESSURE AND NO CABIN ALTITUDE. UPON LANDING THE CABIN DIDN'T DEPRESSURIZE AND THE EMERGENCY ABNORMAL CHECKLIST AIRPLANE PRESSURIZED ON THE GROUND CHECKLIST L1 WAS COMPLETED. AT FL430 THE AMBER PRESSURIZAION FAULT C AREAS SHOWED CABIN PRESSURE NEVER DROPPED BELOW 13900' NO FURTHER ACTION REQUIRED WROTE CABIN PRESSURE IN ERROR SUPPOSED TO BE (CABIN ALTITUDE NEVER EXCEEDED 13870'). COMPLETED CABIN PRESSURE CHECKS, IAW CE680A MM 21-30-00-5. NO PRESSURIZATION FAULT CAS MESSAGE SEEN. REMOVED PART NO: 011-02635-00 REMOVED SERIAL NO: 2BY005900. REMOVED INOPERABLE GEA NR 3 AND INSTALLED A SERVICEABLE REPAIRED UNIT ABOVE, IAW 31-30-00.
LEFT BRAKE TRAVELS ALMOST TO THE STOP BEFORE BRAKE IS EFFECTIVE. BRAKES APPEAR TO BE NEW & NO LEAKS WERE DETECTED, FLUID LEVEL REMAINS CONSTANT. PERFORMED LEAK CHECK ON ENTIRE BRAKE SYS, NO LEAKS NOTED. VERIFIED SPONGY BRAKE ON LT PILOTS SIDE. BLED ANTI-SKID BRAKE SYS, BRAKE & MASTER CYLINDER, CHECKED GOOD. TAXI CHECKED ACFT & OPS & LEAK CHECKED GOOD IAW MM 32-42-00.
SHORTLY AFTER TAKEOFF A VERY LOUD SINGLE POP OR BANG WAS HEARD & WAS FOLLOWED BY A RUSHING AIR NOISE FROM BEHIND THE COCKPIT AREA. SOON AFTER THE WING ENG ANTI-ICE WAS TURNED OFF & THE NOISE STOPPED IMMEDIATELY. UPON INSPECTION WE FOUND THAT THE BLEED AIR TUBE TEE ASSEMBLY WAS FOUND CRACKED AROUND THE FITTING FOR THE BLEED AIR TEMP SENSOR. THE TEE ASSEMBLY WAS REPLACED WITH A NEW UNIT.
WHEN GEAR WAS SELECTED UP, THE UNLOCK LIGHT REMAINED ON ACCOMPANIED BY THE HYDRALIC PRESSURE LIGHT. INSPECTED LANDING GEAR , NO DEFECS NOTED. PERFORMED GEAR SWINGS AND DUPLICATED PROBLEM, NOTICED LT MLG UPLOCK ACTUATOR SWITCH NOT CONTACTING UPLOCK HOOK WHEN GEAR IS RETRACTED CREATING AN UNSAFE INDICATION IN COCKPIT. INSPECTED UPLOCK HOOK AND ACTUATOR AND FOUND NO DEFECTS. FOUND UPLOCK HOOK SPRING ASSY DIRTY AND NOT ALLOWING HOOK TO RELEASE. CLEANED AND LUBURICATED UPLOCK HOOK ASSEMBLY AND PERFORMED GEAR SWINGS. OPS CHECKED GOOD, RESTORED AIRCRAFT TO ORIGINAL CONFIGURATION.
RIGHT BRAKE MAKING A LOUD MOANING AND CHATTERING NOISE. ALSO GRABS WHEN APPLYING BRAKES. COMPLIED WITH VISUAL INSPECTION OF RT BRAKE. NO FAULTS FOUND. FOUND WEAR INDICATOR MEASURING 0.20", FOUND PRESSURE AT BOTH BRAKES NORMAL. COMPLIED WITH TAXI CHECK FOUND BRAKING NORMAL. REMOVED RT WHEEL, CLEANED, & INSTALLED WHEEL. COMPLIED WITH TAXI CHECK. BRAKING NORMAL AT ALL SPEEDS. WORK ACCOMPLISHED IAW MM 32-42-01.
DURING SCHEDULED MX THIS ECU SUPPORT BRACKET WAS FOUND CRACKED IN 2 PLACES. ONE CRACK IS 1.80 INCHES LONG, THE SECOND CRACK IS .80 INCHES LONG. THIS IS THE SECOND SUPPORT BRACKET TO BE INSTALLED ON THIS ACFT. WE HAVE SEEN SIMULAR SUPPORT BRACKET CRACKS ON OTHER ACFT. A SERVICE CONDITION REPORT AND PICTURES HAS BEEN SUBMITTED TO MFG UNDER SCR 610072.
AIR DUCT OVER HEAT CABIN (ENVIRONMENTAL DUCT OVERTEMP) REACHED A TEMP OF 325C AND WAS INCREASING AND SMOKE IN THE CABIN IN-FLIGHT. FOLLOWED CHECKLIST Q4 AND TEMP DECREASED TO 208C.
AIR DUCT OVER HEAT CABIN (ENVIRONMENTAL DUCT OVERTEMP) REACHED A TEMP OF 325C AND WAS INCREASING AND SMOKE IN THE CABIN IN-FLIGHT. FOLLOWED CHECKLIST Q4 AND TEMP DECREASED TO 208C. TROUBLESHOT "AIR DUCT O' HEAT CABIN" LIGHT, CABIN SUPPLY AIR UNCONTROLLABLE IN MANUAL MODE, FOUND TEMP CONTROL VALVE FOILED, R & R CABIN TEMP CONTROL VALVE WITH AN O/H UNIT IAW MM CH 21-31-00. OPS CHECKED GOOD.
ADC NR 1 FAILED.
AFTER GEAR RETRACTION, GEAR UNLOCK LIGHT REMAINED ILLUMINATED. UPON PULLING AND RESETTING HYD PRESS CIRCUIT BREAKER, NOISE WAS HEARD FROM NOSE AND MALFUNCTION CLEARED. TROUBLESHOOTING FOUND LT MAIN GEAR UPLOCK HOOK INTERMITTENTLY BINDING. CLEANED AND LUBED UPLOCK MECHANISM. GEAR SWINGS AND OPS CHECKS NORMAL. REF MM 32-01-00.
AFTER T/O, RECEIVED A GEAR UNSAFE LIGHT FOLLOWED BY STAB MISCOMPARE AND HYD PRESSURE LIGHT ILLUMINATED. INSPECTED UPLOCK SWITCHES AND FOUND THE NOSE SWITCH OUT OF ADJUSTMENT. ADJUSTED NOSE GEAR UPLOCK SWITCH IAW MM CHAP 32-30-05. PERFORMED GEAR SWING. OP CHECKS GOOD.
AFTER TAKEOFF, GEAR UNLOCK LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION FOLLOWED BY STAB MISCOMPARE, GEAR, HYD PRESSURE CAUTION LIGHTS. ADJUSTED BOTH MLG UPLOCK SWITCHES IAW MM 32-30-05. REPOSITIONED ADEL CLAMPS FOR ANTI SKID WIRING HARNESS ON BOTH MLG TRAILING LINKS. GEAR SWING OPS CHECK GOOD AT THIS TIME. C/W OPS CHECK OF FLAP/HORIZONTAL STAB SYSTEM. OPS CHECK GOOD AT THIS TIME.
WHILE FLYING AT FL400 A LOUD (THUNK) WAS HEARD COMING FROM THE BACK. THE GEAR UNSAFE LIGHT ILLUMINATED WITH HYD PRESS STEADY. ADJUSTED NOSE GEAR UPLOCK HOOK AND UP LOCK SWITCH IAW MM 32-30-05 GEAR SWING OPERATIONAL CHECK GOOD.
DURING GEAR RETRACTION RED UNLOCK LIGHT STAYED ILLUMINATED. REMOVED AND REPLACED LANDING GEAR CONTROL HANDLE IAW MM 32-30-01 ALSO REMOVED AND REPLACED LANDING GEAR PCB IAW MM 24-51-02. C/W LANDING GEAR FUNCTIONAL CHECKS IAW MM 32-01-00. OPERATIONAL CHECKS GOOD.
DURING GEAR RETRACTION RED UNLOCK LIGHT STAYED ILLUMINATED, FOLLOWED BY STAB MISCOMPARE AND HYD PRESS CAUTION LIGHTS. WITH GEAR EXTENDED UNLOCK LIGHT WENT OUT. WHILE COMPLETING HYD PRESS CHECKLIST (GEAR RETRACTED), A LOUD THUNK WAS HEARD IN THE L WING ROOT AREA WHEN THE HYD CONTROL CB WAS PULLED. CB WAS RESET, GEAR WAS EXTENDED. THERE WERE NO UNUSUAL BUFFET OR FLIGHT CHARACTERISTICS DURING THE FLIGHT. REMOVED AND REPLACED LANDING GEAR CONTROL HANDLE IAW MM 32-30-01. ALSO REMOVED AND REPLACED LANDING GEAR PCB IAW MM 24-51-02. C/W LANDING GEAR FUNCTIONAL CHECKS IAW MM 32-01-00. OPERATIONAL CHECKS GOOD.
AFTER TAKEOFF, THE GEAR UNSAFE LIGHT ILLUMINATES AFTER THE GEAR HANDLE IS PLACED IN THE UP POSITION. THE HYD PRESS AND STAB MISCOMPARE ANNUNCIATOR ALSO ILLUMINATE. PULLING THE HYD CONT CB, DOES NOT DROP ANY LANDING GEAR ASSEMBLIES OR EXTINGUISH THE UNLOCK LIGHT. TROUBLESHOT TO THE RT UPLOCK ACTUATOR, SPRING TOO WEAK TO ENGAGE HOOK FULLY. REMOVED AND REPLACED SPRING. OPS CHECK GOOD IAW MM CH 32-30-05
GEAR WOULD NOT RETRACT AFTER TAKEOFF. R & R LT UPLOCK ACTUATOR WITH NEW. FOUND HYD RELIEF VALVE OUT OF TOLERANCE, REPLACED WITH OVERHAULED UNIT FROM PNEUDRAULICS RS PD6R469J, PRESSURE SWITCH & LT MLG ACTUATOR WITH SERVICEABLE UNIT FROM CESSNA ICT RS CNQB9181 WORK PERFORMED IAW MM.
AFTER TAKEOFF UPON FLAP RETRACTION THE "STAB MISCOMPARE ANNUNCIATOR LIGHT" ILLUMINATED. REPLACED SWITCHES SC050 AND SC051 PER MM 27-90-40. GROUND OPERATIONAL CHECK GOOD
UPON GEAR RETRACTION - GEAR UNLOCK LIGHT WOULD NOT EXTINGUISH. REMOVED AND REPLACED ALL THREE UP LOCK SWITCHES WITH NEW PER CESSNA 560XL MAINT. MANUAL CHAP 32-30-05 & 32-60-02. SYS GROUND OPS CHECKED GOOD.
PILOTS SIDE RT PEDAL WENT TO THE FLOOR ON LANDING. REMOVED AND INSTALLED OVERHAULED MASTER CYCLINDER ON PILOTS SIDE. RT PEDAL. ALL WORK DONE IAW CESSNA 560 M/M 32-42-02.
PILOT'S SIDE (LT) LEFT FOOT BRAKE PEDAL GOES TO FLOOR. 09-27-07 REMOVED AND REPLACED PILOTS LT AND RT BRAKE PEDAL MASTER CYLINDER IAW C-560XL MAINT. MANUAL 32-42-02. OPS AND LEAK CHECKED GOOD.
BLUE GEAR FLUID LEAKING OUT OF NOSE GEAR AND A HALF CUP OF FLUID HAS POOLED IN LT AVIONICS BAY. STARTED SMOKING WITH BATTERY SWITCH ON. PULLED CIRCUIT BREAKERS. [07-23-07] FOUND BRAKE PUMP FILTER BOWL O-RING BLOWN & SMOKING WAS A SKYDROL MIST COMING FROM BOWL WHEN UNDER PRESSURE. REPLACED O-RING & BLED BRAKES IAW CE560XL M/M CHAP 32-42-00. OPS CHECK & LEAK CHECK GOOD.
DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABILIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER # 242686
AFTER TAKEOFF, FOUND LANDING GEAR WOULD NOT RETRACT, DIVERTED AIRCRAFT TO GTF AND LANDED SAFELY. JACKED UP AIRCRAFT AND ADJUSTED LT MLG SQUAT SWITCH IAW CESSNA 560XL MAINTENANCE MANUAL CHAPTER 32-61-00. SERVICED LT & RT MLG OLEO'S IAW CESSNA 560XL MM CHAPTER 12-14-00, INSPECTED WIRING IN LT WHEEL WELL, LANDING GEAR CONTROL UNIT AND LANDING GEAR CONTROL VALVE IAW CESSNA-560XL M/M CHAPTER 32-32-02. SYSTEM OPS CHECKED GOOD.
PERFORMED AILERON WING CABLE INSPECTION PER CESSNA ASL560XL-27-12, FOUND CABLES CHAFED/BROKEN BEYOND MANUFACTURER'S LIMITS. REMOVED AND REPLACED LEFT AND RIGHT WING AILERON CABLES IAW CESSNA 560XL MM CHAPTER 27-10-03.
FOUND NOSE GEAR ACTUATOR EXTEND LINE JAM NUT LEAKING. UPON REMOVAL OF JAM NUT, FOUND JAM NUT NOT TO HAVE INDENTION MILLED FOR RETAINER, PN ME28773-04, AND O-RING NAS 1612-9A. AREA HAS NOT BEEN DISTRUBED SINCE PAINT AT FACTORY DUE TO PAINT ON FASTENERS. SUBMITTER STATED PART COULD HAVE BEEN MISMARKED AT MANUFACTURER OR IN STORES AT FACTORY. (X)