N602QS
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
HAD TO MANUALLY EXTEND GEAR DUE TO NOT EXTENDING NORMALLY.NO HYD SYS AVAILABLE. RAN QRH & MANUAL GEAR EXTENSION WORKED. GEAR CONTROL CIRCUIT BREAKER PULLED PER QRH. PERFORMED GVI OF HYD SYS & FOUND HYD SYS OVERSERVICED & BLOWDOWN BOTTLE UNDERSERVICED. PERFORMED INSPECTIONS OF PCB NZ016 HYD CONTROL & WIRING CHKS OF HYD MANIFOLD, NO SHORTS TO GROUND & CONTLNUITY AS REQUIRED. VERIFIED ALL CONDITONS WERE FREE FROM DEFECT CONCERNING 32-27 &. 29-04 R & R HYD PCB NZ016 IAW AMM 24-50-03, R & R, BLED, & OPS CHECKED HYD VALVE IAW AMM 29-11-06, SWUNG GEAR & CYCLED ALL HYD COMPONETS. PERFORMED ENG RUNS & VERIFIED HYD OPS GOOD. SERVICED GEAR BLOWDOWN BOTTLE TO WITHIN LIMITS IAW AMM 12-13-01. NO FURTHER DEFECTS.
EXTENDING THE FLAPS FOR APPROACH, DID NOT WORK. MLG & SPEED BRAKES INOP. BROKE OFF APPROACH. MANUALLY EXTENDED GEAR IAW QRH & DID A NO FLAP APPROACH & NO FLAP LANDING QRC. DIVERTED TO AN AIRPORT WITH LONGER RUNWAY. NO ANNUNCIATORS CAME ON DURING EVENT. NO INDICATIONS OF A LEAK & RESERVOIR SHOWED NORMAL. MAIN BRAKE SYSTEM WORKED. PERFORMED GVI , HYD SYS, FOUND HYD SYS OVERSERVICED, BLOWDOWN BOTTLE TO BE UNDERSERVJCED. SAFTEY WIRE INTACT. R & R HYD PCB NZ016 IAW AMM 24·50-03, REMOVED, REPLACED, BLED, & OPS CHECKED HYD VALVE IAW AMM 29-L1S06. SWUNG GEAR AND CYCLED ALL. HYD COMPONENTS. PERFORMED ENGINE RUNS AND VERIAED HYDS OPS. SERVICED BLOWDOWN BOTTLE IAW AMM 12-13-01. NO FURTHER DEFECTS.
THE MAIN CABIN HANDLE REQUIRES EXCESSIVE FORCE TO OPEN AND CLOSE. TROUBLESHOT MED TO DIRTY AND DRY INNER AND OUTER DOOR HANDLE ASSEMBLIES. SET UP SUPPUES. CLEANED WITH ISOPROPYL BOTH ASSEMBLES. LUBED AS REQUIRED. VISUAL AND OPERATIONAL TESTS SATISFACTORY. ALL WORK IAW MM:12-20-52, 52-10-00
MAIN DOOR PRECATCH: MAIN CABIN DOOR PRECATCH WILL NOT RELEASE WHEN TRYING TO OPEN MAIN CABIN DOOR. //SIGNOFF// TECHS ROUND THAT THE PRE-CATCH WAS NOT RETRACTING FULLY WHEN THE HANDLE IS PULLED AND IS CATCHING THE DOOR WHEN IT TRIES TO OPEN. TECHS REMOVED THE FWD PAX DOOR TRIM TO GAIN ACCESS TO THE PRE-CATCH ASSEMBLY. TECHS ADJUSTED THE CABLE FROM THE LOWER SIDE TO LIMITS AND THE PRE-CATCH RELEASES THE DOOR EVE,Y TIME NOW THAT THE PLAY HAS BEEN REMOVED. OPS TEST OR THE PAX DOOR AND PRE-CATCH FOUND SATLSFACTO,Y. TECHS RESTORED ACCESS TO THE PAX DOOR FWD TRIM. REFERENCE: 560 XL AMM 52-10·01
EMERG EXIT DOOR: EMER EXIT ANNUNCIATOR WITH ASSOCIATED MASTER CAUTION ILLUMINATED PASSING THROUGH 2500FT ON CLIMB OUT. ANNUNCIATOR REMAINED ON UNTIL TOUCHDOWN. FOUND GAP BETWEEN EMERGENCY EXIT DOOR UPPER LATCH PIN AND PROXIMITY SWITCH TO BE WELL BEYOND .040" LIMITS. ADJUSTED PROXIMITY SWITCH AND OBTAINED A .026" GAP IAW C560XL MM 52-20-01.
CABIN EMERG LIGHT: ALL THREE EXIT SIGNS DO NOT ILLUMINATE WITH EMER LIGHT SWITCH ON OR PASS SAFETY SWITCH ON. CHECKED CONNECTORS FOR PROPER FITMENT, FOUND THAT THE AFT ENTRY DOOR SHROUD EXIT SIGN WAS NOT PROPERLY SEATED. RESEATED THE CONNECTOR ON THE AFT ENTRY DOOR SHROUD . NO PARTS REQUIRED. FT ON ALL THREE EXIT SIGNS ARE GOOD AT THIS TIME. WORK PERFORMED IAW C560XL SPM 20-30-20.
DURING INSPECTION FOUND FUSELAGE STRINGER 15L IS CRACKED ON THE AFT END OF THE TAIL CONE SECTION AT F.S. 580.00. TRIMMED DAMAGED STRINGERE AND PERFORMED A DOUBLER REPAIR IAW APPROVED DATA.
EMERGENCY LIGHTING: DROPPED AISLE LIGHTS, LEFT FORWARD HALF, THE MAJORITY OF THEM ARE INOP. IT APPEARS THE SECTION BETWEEN SEAT 3 AND 5 ARE INOP. // SIGNOFF/ REPAIRED WIRING CONNECTION TO AISLE LIGHT STRIP AT SEAT 3 REF CE560XL SPM 20-30-20 & OPS CKED EMERG EXIT DROPPED AISLE LIGHTS NORMAL REF CE560XL AMM 33-50-00
MAIN CABIN DOOR ANNUNCIATOR IS ILLUMINATED WITH AN ASSOCIATED VENT DOOR SIX PACK LIGHT. WHEN THE VENT DOOR IS MANUALLY CLOSED, VENT DOOR, SIX PACK LIGHT EXTINGUISHERS, BUT CABIN DOOR ANNUNCIATOR REMAINS ON WITH THE MAIN CABIN DOOR CLOSED & LOCKED. BOTTOM FORWARD LOCK FLAG IS PARTLY OUT OF VIEW. LOCATED & ADJUSTED FLAG AS NEEDED. INSTALLED STEPS TO VERIFY THAT FLAGS ARE ALL ABLE TO BE SEEN WHEN DOOR IS LOCKED. OPS CHECK GOOD. WORK PERFORMED IAW AMM 52-10-01. REMOVED OLD CABIN DOOR PCB & INSTALLED INSPECTED DOOR PCB, OPS CHECK GOOD IAW AMM 24-51-02 & 52-10-00. OPS CHECKED DOOR VENT SYS, DOOR VENT CLOSED, 6 PACK EXTINGUISHED & CABIN DOOR OPEN ANNUNCIATOR EXTINGUISHED. OPS CHECKED GOOD.
FOUND CORROSION AROUND FASTENER HOLE ON LH WING UPPER SKIN AT WS 64.073. REPAIRED IAW NETJETS RFTS 108114 REV.0 DATED 16MAY2023. THIS IS A PERMANENT REPAIR
INSTALLED AIR CYCLE MACHINE (ACM) HEAT EXCHANGER THAT UNDERWENT A MAJOR REPAIR DUE TO BOTH HEAT EXCHANGERS BEING DAMAGED. HEAT EXCHANGER UNIT WAS REPAIRED UNDER THE FOLLOWING REFERENCES: AQRD RS-890517 REV C DATED 06/14/2020, AQRD RS-890517-1 REV C DATED 06/14/2020, AQRD EWO-2700 REV IR DATED 12/15/2021, AND FAA 8110-3 DATED 6/15/2020 SIGNED BY DERT-710086-SW.
MAIN DOOR HANDLE: MAIN CABIN DOOR HANDLE VERY HARD TO LATCH CLOSED. SEEMS TO BE BINDING. // SIGNOFF// VERIFIED MED IS DIFFICULT TO LATCH. LUBED ALL PINS IN DOOR. DOOR STILL HAS A CATCH WHEN LATCHING. REMOVED FIXED STAIRS. PERFORMED GVI OF DOOR PULLIES. NOTICED AT POINT AT HANDLE BARREL HAS FRICTION_ LUBED POINTS OF CONTACT DOOR NOW LATCHES SMOOTHLY. WERT PERFORMED WITH REFERENCE TO CITATION 560 XL AMM 52-10-02
MAIN CABIN DOOR HANDRAIL DOES NOT LOCK THE DOOR IN THE DOWN POSITION. HANDRAIL CAN BE MOVED ALMOST STRAIGHT DOWN AND DOES NOT STOP IN CORRECT POSITION. PIN MISSING IN HANDRAIL LOCKING ASSYMBLY. FOUND PIN HARDWARE ON GROUND. REINSTALLED ORIGINAL ROLL PIN AND PERFORMED OPS CHECKS OF MAIN ENTRY DOOR. OPS CHECKED GOOD. WORK DONE IAW MM 52-10-00.
CABIN DOOR PRECATCH WILL NOT RELEASE CABIN DOOR. // SIGNOFF// ADJUSTED CABIN DOOR PRECATCH IAW CESSNA 560XL MM 52-10-01. OPS CHECK GOOD AT THIS TIME.
MAIN DOOR HANDLE: MAIN DOOR HANDLE IS VERY DIFFICULT TO OPEN FROM BOTH OUTSIDE AND INSIDE THE AIRCRAFT. GAINED ACCESS TO MAIN DOOR HANDLE. INSPECTED, CLEANED AND LUBRICATED THE DOOR HANDLE AND LINKAGES, OPERATIONAL TEST OF MAIN DOOR CHECKED GOOD IAW CE-560XL MM 52-10-00, NO DEFECTS NOTED. CLOSED UP ACCESS.
EMERGENCY LIGHTING: ON POST FLIGHT FOUND THAT ALL OF THE LEFT FORWARD DROPPED AISLE LIGHTING SYSTEM IS NOT WORKING. // SIGNOFF// INSPECTED LH AISLE DROP LIGHTING ELECTRICAL CONNECTOR AND FOUND MOLEX CONNECTOR DISCONNECTED AND 1 WIRE PULLED FROM THE ELECTRICAL CONNECTOR AIRFRAME SIDE. EXTRACTED PIN FROM DROP AISLE LIGHTING CONNECTOR AND CRIMPED BACK ON TO PULLED WIRE IAW CE-560XL SPM 20-30-25. RESEATED CONNECTOR AND PERFORMED SUCCESSFUL OPERATIONAL TEST OF THE AISLE LIGHTING AS REQUIRED. WORK DONE IRW CE-560XL IMM 25-92-1 2.
NO RESISTANCE ON MAIN DOOR WHEN OPENING FROM THE OUTSIDE. EXTREMELY HARD TO PULL DOOR IN WHEN CLOSING FROM THE INSIDE. CORRECTIVE ACTION: OPERATED CABIN DOOR MULTIPLE TIMES AND VERIFIED SQUAWK. MEASURED PRECATCH PLUNGER RETRACTION INTO HOUSING AND VERIFIED PLUNGER IS FLUSH WITH HOUSING WITH PRECATCH BUTTON PUSHED, IAW 560XL MM 52-10-00. NOTICED WITH CLOSING CABIN DOOR, DOOR HAD EXCESSIVE TENSION CAUSING DOOR TO RETRACT HALFWAY AUTOMATICALLY WHEN INITIALLY CLOSING THE DOOR. DOOR STEPS AND OPERATED DOOR. DOOR OPERATED CORRECTLY AND PRECATCH WORKS GOOD. WORK DONE IAW 560XL MM52-10-03.
MAIN CABIN DOOR IS VERY HEAVY TO OPEN FROM BOTH OUTSIDE & INSIDE. CONFIRMED WRITE UP CHECKED SPADE DOOR AND TELESCOPING RODS, BOTH CHECKED GOOD, REMOVED STEPS AND OPERATED DOOR, FOUND THAT DOOR WOULD START TO COME UP BUT THEN STOP, BUT WHEN PUSHED UP THE SPRINGS WOULD CATCH THEN EXPAND COUNTER BALANCE SPRINGS EXPECT SPRINGS TO HAVE CRACKS. REMOVED AND REPLACED COUNTER BALANCE SPRINGS IAW CESSNA CE-560XL MM CH 52-10-03. OPS CHECKED SATISFACTORY.
DURING TAKEOFF AND CLIMB COPILOTS RIGHT OUT BOARD PEDAL COULD NOT BE MOVED. WITH AUTO PILOT AND YAW DAMP OFF FROM COPILOTS SIDE RIGHT RUDDER (OUTBOARD PEDAL) COULD NOT BE MOVED. FROM PILOT SIDE INFLIGHT WITH AUTO PILOT AND YAW DAMP OFF RIGHT PEDAL COULD WHEN PUSHED BE MOVED BUT SEEMED VERY STIFF AND MUCH HARDER TO PUSH THAN THE LEFT PEDAL. ONCE WE RETURNED FOR LANDING RUDDER FUNCTION SEEMED TO PERFORM NORMAL DURING TAXI BACK TO RAMP. DISCONNECTED NWS BUNGEE FROM STEERING ARM, CONNECTED AFTER PEDAL STIFFNESS TEST. PERFORMED RUDDER PEDAL STIFFNESS TEST IAW MM 27-20-05. FOUND ALL PEDALS IN BOTH DIRECTIONS BREAKING OUT AT 19-20 LBS. NO GRAININESS OR INCONSISTENCY FOUND IN RUDDER PEDAL MOVEMENT, IAW THE MANUAL, THE ACTUATOR IS ACCEPTABLE. REPLACED THE RUDDER BIAS ACTUATOR, DETENSIONED RUDDER BIAS CABLE, RUDDER BIAS ACTUATOR, TENSIONED RUDDER BIAS CABLE AND SAFETIED TURNBARREL. PERFORMED RUDDER BIAS OPS CHECK AND RUDDER PEDAL STIFFNESS TEST. RUDDER PEDAL BREAKOUTS IMPROVED TO 16-17 LBS. WITHIN MM LIMITS. LEAK CHECKED RUDDER BIAS ACTUATOR BLEED AIR FITTINGS. ORIGINAL SUBMISSION DATE. 02/13/2019
RIGHT ENGINE OIL PRESSURE INDICATION NOT READING, RIGHT ENGINE OIL PRESSURE DROPPED TO ZERO IN FLIGHT. ABNORMAL CHECK LIST REQUIRED ENGINE SHUTDOWN. ENGINE ITT TEMP NORMAL AND ENG OIL TEMP NORMAL. INSPECTED RIGHT ENG OIL LEVEL AND FOUND TO BE 1 QUART LOW BUT NO INDICATION OF ANY OIL LOSS. R&R RIGHT ENGINE
RIGHT WING, TOP SPAR HAS A COUPLE OF AREAS OF SUSPECTED CORROSION ON THE LT AND RT STRAKES NEAR THE COMPOSITES. FABRICATED AND INSTALLED REPAIR DOUBLERS.
THE MAIN ENTRY DOOR HAS A GOUGE ON THE INNER SURFACE OF THE DOOR SKIN IN THE FWD COUNTERBALANCE SPRING BAY. THERE IS A DENT ON THE EXTERIOR SURFACE AT THE SAME LOCATION.
THE HF ANTENNAE IS DETACHED FROM THE VERTICAL STABILIZER AND IS HANGING FROM TOP OF FUSELAGE. TECH DISCOVERED DAMAGE TO TAILCONE WHILE PERFORMING MEL PROCEDURE. REMOVED HF ANTENNA SUPPORT SLEEVE & ELBOW AND INSTALLED HF ANTENNA, HF ANTENNA SUPPORT SLEEVE, ELBOW, AND APPROVED ALTERNATE PN HF ANTENNA TENSION UNIT. OPS CHECKS NORMAL. COMPLETED REPAIR PROCEDURE FOR DAMAGE AREA 3, 5 AND 6 STEPS 1-5. COMPLIED WITH ERO 851404, REV IR TAIL CONE REPAIR PROCEDURES FOR DAMAGE AREAS 1, 2, 4 STEPS 5-9. COMPLIED WITH REPAIR PROCEDURES FOR DAMAGE AREAS 3, 5, 6 STEPS 6-9. REINSTALLED TAIL CONE, WORK PERFORMED IN REF WITH MM 53-10-15. PARTS REPLACED: TENSION UNIT ANTENNA, PN: 5ARM300-11C-5LN, ELECTRIC CABLE, PN: 14379-
LEFT BRAKE PEDAL ON LT SEAT HAS NO PRESSURE. LT WEAR PIN WILL MOVE WHEN LT BRAKE ON THE RT SEAT IS PRESSED. FOUND PILOT'S LT MIDDLE BRAKE CABLE BROKEN. R & R CABLE WITH NEW IAW MM 32-44-10. RIGGED & SAFETIED CABLE, TAXI CHECKED GOOD AT THIS TIME.
LEFT MAIN TIRE FAILED ON LANDING ROLL OUT. SUSPECT FAILURE OF ANTISKID. LT BRAKE APPEARS TO HAVE LOCKED UP. R & R LT BRAKE WITH OVERHAULED UNIT IAW MM 32-42-01. PERFORMED BLEED OF LT BRAKE IAW MM 32-42-00. OPS & LEAK CHECKED GOOD.
WITH EQUAL PRESSURE APPLIED TO BOTH BRAKE PEDALS, ACFT PULLS HARD TO THE LEFT. FOUND THAT BRAKES HAD A BROKEN RETURN SPRING AT LT POWER BRAKE METERING VALVE ACTUATION ARM. R & R SPRING, OPS CHECKED GOOD IAW MM 32-44-10.
DURING A SCHEDULED INSPECTION, BRAKE METERING VALVE AND THE RT FORWARD CABLE WAS FOUND TO BE DEFECTIVE, FRAYED, APPROXIMATELY 18 INCHES FROM CLEVIS WHERE IT ATTACHES TO THE BRAKE PEDAL. THERE WERE NO SIGNS OF THE CABLE CONTACTING ANY STRUCTURAL MEMBERS OR IN AN AREA THAT A PULLEY WOULD CAUSE A SHARP BEND. IT WAS NOTED THAT THE CABLE FRAYING OCCURRED IN A STRAIGHT RUN. THE OTHER RT CABLE WAS CHANGED AS A PRECAUTIONARY MEASURE.
NOSE GEAR DID NOT RETRACT AFTER TAKEOFF. GREEN NOSE GEAR LIGHT ON AND RED GEAR UNLOCK LIGHT ON. NO OTHER INDICATIONS. SELECTED GEAR DOWN GOT ALL 3 GREEN DOWN AND LOCKED AND NO RED AND LANDED. JACKED ACFT. RETRACTED GEAR, FOUND NLG WOULD PARTIALLY RETRACT THEN WOULD FAIL TO EXTEND POSITION ONCE MLG WERE UP AND LOCKED. RANG OUT NLG UPLOCK SWITCH. FOUND PINS D AND E OPEN. SHOULD BE NORMALLY CLOSED. R & R NLG UPLOCK SWITCH. ADJUSTED SWITCH IAW MM 32-30-05. PERFORMED LANDING GEAR FUNCTIONAL CHECK. SYS CHECK GOOD IAW MM 32-01-00. REMOVED MULE ON STICK. DOWN JACKED ACFT.
AFTER TAKEOFF, BROUGHT GEAR UP AND NOTICED A THUMPING SOUND LIKE A TIRE HITTING SOMETHING SPINNING DOWN, SAW THE HYDRAULIC ANNUNCIATOR FLASHING ON AND OFF, WITH THE RED GEAR UNLOCK LIGHT ALSO FLASHING ON AND OFF. ALL THREE GREEN GEAR LIGHTS WERE OUT. EXTENDED GEAR AND THE NOISE WENT AWAY, RECEIVED THREE GREEN GEAR LIGHT ON AND RED GEAR UNLOCK LIGHT WENT OUT. RETURNED AND LANDED WITH NO OTHER PROBLEMS. DURING GEAR SWING, GEAR WOULD NOT REMAIN UP AND WOULD CREATE A THUMPING SOUND. INSPECTED UPLOCKS TO FIND RIGHT UPLOCK SWITCH FAULTY. REMOVED AND REPLACED RIGHT UPLOCK SWITCH WITH NEW SWITCH IAW MM 32-30-05. RIGGED UPLOCK SWITCH. OPERATIONAL CHECKED NORMAL.
LEFT HORIZONTAL STAB SPIGOT FITTING CORRODED.
WHEN EXTENDING THE GEAR FOR LANDING, THE LEFT MAIN DOWN LIGHT DID NOT ILLUMINATE AND THE UNSAFE LIGHT DID NOT EXTINGUISH. RAN ROTARY TEST AND ASSURED THAT ALL GEAT INDICATORS WERE WORKING, AND EXTENDED FLAPS BEYOND 15 DEGREES AND RECEIVED WARNING HORN. AFTER ABOUT 1 MINUTE, GEAR DOWN INDICATOR LIGHTS ILLUMINATED AND GEAR UNSAFE LIGHTS EXTINGUISHED. THERE WAS NO ACCOMPANYING GEAR MOVEMENT NOISE JUST PRIOR TO WHEN THE LIGHTS INDICATED DOWN. REMOVED LT MAIN GEAR ACTUATOR. INSTALLED NEW ACTUATOR AND SLOW CYCLED GEAR. HYD SYS CHECKED LEFT GEAR CAMBER. CAMBER CHECKED GOOD. ACTUATOR INSTALLED WITH NEW ATTACH HARDWARE. ALL WORK IAW 32-30-04 OF MM. OPS CHECK AND LEAK CHECKED GOOD.
WHEN EXTENDING THE GEAR FOR LANDING, THE LEFT MAIN DOWN LIGHT DID NOT ILLUMINATE AND THE UNSAFE LIGHT DID NOT EXTINGUISH. AFTER ABOUT ONE MINUTE, THE GEAR DOWN INDICATOR LIGHTS ILLUMINATED AND THE THE GEAR UNSAFE LIGHTS EXTINGUISHED.
GEAR WARNING HORN INTERMITTENT. HORN DIDN'T WORK DURING ROTARY TEST WITH APU. SHUT ALL ELECTRICAL OFF, DISCONNECTED BATTERY, RETRIED WITH BATTERY POWER AND HORN DIDN'T WORK. RETRIED WITH APU AND HORN CAME ON AFTER 15-20 SECONDS. REPLACED THE RT THROTTLE SWITCH BANK AND RIGGED SWITCHES IAW MM CH 76-11-00. GEAR WARNING HORN OPS CHECKED GOOD.
ATTITUDE AND HEADING ON CO-PILOTS PFD FAILED SHORTLY AFTER TAKEOFF. REMOVED INTERMITTENT AHRU NR 2. INSTALLED A REPAIRED AHRU NR2. SYS OPS CHECKED GOOD. WORK DONE IAW AMM 34-21-01.
SMOKE IN CABIN. APU WAS RUNNING FOR APPROX 5 MINS WITH BLEED OFF. NOTICED NO SMOKE. TURNED BLEED ON AND AFTER APPROX 2 MINS HAD SMOKE IN THE CABIN. LATER WE RAN BOTH ENGINES WITH NO APU AND DID NOT NOTICE ANY SMOKE. FOUND OIL IN APU AIR INLET. REMOVED WATER SOCK, CLEANED, AND CLEANED DUCT. INSTALLED WATER SEPARATOR IAW MM 12-19-02. RAN BOTH ENGINES AND SMOKE IN CABIN OR COCKPIT.
ENROUTE, LT TAIL DEICE FAIL LIGHT ILLUMINATED. SELECTED OFF THEN MANUAL IAW THE ABNORMAL CHECKLIST WITH NO CHANGE . ACFT WAS AT FLT 270 DURING FAILURE.
EEC MANUAL LIGHT ILLUMINATED ON NR 2 ENGINE DURING DESCENT FOLLOWED BY LOSS OF THRUST AND CONTINUOUS COMPRESSOR STALLS. AFTER DOWNLOADING DCU FILES AND SENDING TO MANUFACTURER. REMOVED REPLACED AND OPS CHECK GOOD OF RT BLED AIR TORQUE MOTOR IAW MM 73-20-03, 75-30-01 AND 71-00-00.
AFTER TAKEOFF AND GEAR RETRACTED, THE GEAR UNLOCK LIGHT REMAINED ILLUMINATED. RAN CHECKLISTS AND NOSE GEAR EXTENDED WHEN HYD CTRL CB WAS PULLED. LOWERED GEAR AND LANDED NORM. POST FLIGHT REVEALED FLAT NOSE STRUT AND FLUID LEAKAGE. DISASSEMBLED NOSE STUT AS NESSISERY INSTALLED SEAL KIT CPDL32-1 AND ASSEMBLED REF CMM 32-20-01 REV 7. SERVICED WITH SKYDROL AND NITROGEN IAW MM 12-14-00. INSPECTED UPLOCK DOORS, AND ACTUATORS FOR GENERAL CONDITION ALL OK COMPLETED 5 FAULT FREE CYCLES.
AFTER TAKEOFF AND GEAR RETRACTED, THE GEAR UNLOCK LIGHT REMAINED ILLUMINATED.
DURING TAKEOFF ROLL RT ENGINE ANTI-ICE ANNUNCIATOR ILLUMINATED WITH SWITCH IN THE OFF POSITION. TAKEOFF ABORTED. TROUBLESHOT ENGINE ANTI-ICE SYSTEM, PERFORMED ENGINE ANTI-ICE SYSTEM, FUNCTIONAL CHECK PER CESSNA 560XL MAINT MANUAL 30-11-00-710 SYSTEM FUNCTIONS PROPERLY AT THIS TIME.