N311QS
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
REPAIRED CORRODED AREAS OF THE LOWER AFT FUSELAGE TAILCONE SKINS LOCATED UNDER AND ADJACENT TO THE AFT CHIN FAIRING AREAS BY BLENDING CORRODED AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER.
REPAIRED SEVERAL CORRODED AREAS ON THE VERTICAL STABILIZER AFT SPAR RH CAP BY BLENDING, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS AND SHIMS.
REPAIRED CORRODED AREAS OF THE LOWER FORWARD SPAR CAPS OF THE LH & RH WINGS, LOCATED IN THE MAIN LANDING GEAR WHEEL WELLS, BY REMOVING FASTENERS AS REQUIRED, BLENDING CORRODED AREAS, PERFORMING NDT AND REPORTING FOR REPAIR DISPOSITION, TREATING & PRIMING REPAIR AREAS AND INSTALLING FASTENERS IN ACCORDANCE WITH TEXTRON FIELD REPAIR .
BLENDED CORROSION ON THE UPPER SURFACE OF THE UPPER WING SKIN OF THE RH WING, LOCATED ADJACENT TO AND UNDERNEATH THE AFT DRAG ANGLE (WING-TO-FUSELAGE FAIRING AREA), BY REMOVING THE AFT DRAG ANGLE, BLENDING CORRODED AREAS, PERFORMING NDT AND SUBMITTING RESULTS FOR REPAIR DISPOSITION. TREATED, PRIMED AND TOPCOATED BLENDED AREAS AND REINSTALLED THE DRAG ANGLE PER TEXTRON FIELD REPAIR FR-680-0196-12031.
MAIN DOOR PRECATCH LEVER: LEVER EXTENDED AND WILL NOT RETRACT. VISUALLY VERIFIED PRECATCH SYSTEM IS NOT WORKING PROPERLY. GAINED INTERNAL ACCESS TO PRECATCH SYSTEM AND NOTED CAM OVERCENTERED AND BEHIND STRIKE PLATE OF PLUNGER. ADJUSTED CAM AS REQUIRED AND INSTALLED NEW TENSION SPRING IAW MM 52-10-40. OP CHECK GOOD. ORIGINAL SUBMISSION DATE: 12/1/2022
FUEL PRESSURE INDICATION: WHILE CROSSFEEDING FROM L TANK, FUEL PRESS LOW L. CASS MESSAGE CAME ON MOMENTAIRLY FOLLOWED BY FUEL BOOST PUMP ON L CASS MESSAGE. FUEL BOOST PUMP ON R CASS MESSAGE THEN CAME ON ALSO.//CORRECTIVE ACTION// REMOVED AND REPLACED LEFT BOOST PUMP ASSY WITH AN OVERHAULED ASSY IAW CE680 MM 28-20-10, OPS AND LEAK CHECKS GOOD,
LEFT EMERGENCY LIGHT AFT OF MCD: MULTIPLE EMERGENCY LIGHTS INOP. LEFT EXTERIOR FUSELAGE AFT OF MAIN CABIN DOOR. INTERIOR CEILING LIGHT OVER SEAT 3 AND 5. INTERIOR LIGHT OVER SEAT NONE. // SIGNOFF// REMOVED AND REPLACED PINS IN PL089V DUE TO BEING BURNT AND SHORTING. OPERATIOMANL TEST CARRIED OUT ON EMERGENCY LIGHTS, OPS TEST GOOD. REF MODEL 680 MM 33-50-10, 33-50·00, W/M 25-92-06 AND 33-50-01,
REMOVED LH UPPER AND LOWER BRAKE LINES AND BULKHEAD FITTINGS FROM LH WING, MIDDLE SPAR, AFT SIDE. BLENDED CORROSION FROM LH WING, MIDDLE SPAR, AFT SIDE. EVALUATED REMAINING THICKNESS AND FOUND AREA TO BE OUT OF SRM LIMITS PER CESSNA 680 SRM 51-70-02. SUBMITTED TO TEXTRON ENGINEERING. RE-EVALUATED AREA WITH TEXTRON REPAIR DEFINITION S-680-ATA57/03RD REV -, SUBJECT: REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS, DATED: 03/18/2019, AND FOUND AREA AROUND LOWER BULKHEAD FITTING TO BE WITHIN THIS REPAIR LIMITS. FOUND AREA AROUND UPPER BULKHEAD FITTING TO BE OUT OF LIMITS. REMOVED RH UPPER AND LOWER BRAKE LINES AND BULKHEAD FITTINGS FROM RH WING, MIDDLE SPAR, AFT SIDE. BLENDED CORROSION FROM RH WING, MIDDLE SPAR, AFT SIDE. EVALUATED REMAINING THICKNESS AND FOUND AREA TO BE OUT OF SRM LIMITS PER CESSNA 680 SRM 51-70-02. SUBMITTED TO TEXTRON ENGINEERING. RE-EVALUATED AREA WITH TEXTRON REPAIR DEFINITION S-680-ATA57/03RD REV -, SUBJECT: REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS, DATED: 03/18/2019, AND FOUND AREA AROUND LOWER BULKHEAD FITTING TO BE WITHIN THIS REPAIR LIMITS. FOUND AREA AROUND UPPER BULKHEAD FITTING TO BE OUT OF LIMITS. REPAIRED LH AND RH WING CENTER SPAR AT THE HYDRAULIC FEED THRUS IN MLG WHEEL WELLS PER AEROSPACE QUALITY AND RESEARCH DEVELOPMENT ERO-104821 TITLED LH/RH WING CENTER SPAR WEB CORROSION REPAIR REV. IR. DATED MAY 06, 2021 AND SUPPORTED BY FAA FORM 8110-03 DATED MAY 06, 2021. REPAIR DOCUMENTED ON FAA FORM 337 DATED 06 MAY 2021.
REMOVED RH EMERGENCY BRAKE BULKHEAD FITTING FROM RH WING, RIB AT RWS 37. BLENDED CORROSION FROM FWD INBOARD WEB ON RIB AT RWS 37. EVALUATED REMAINING THICKNESS AND FOUND AREA TO BE OUT OF SRM LIMITS PER CESSNA 680 SRM 51-70-02. SUBMITTED TO TEXTRON ENGINEERING. RE-EVALUATED AREA WITH TEXTRON REPAIR DEFINITION S-680-ATA57/03RD REV -, SUBJECT: REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS, DATED: 03/18/2019, AND FOUND IT TO BE WITHIN THIS REPAIR LIMITS. PERFORMED REPAIR STEPS FOR THIS AREA CONTAINED IN THIS TEXTRON STANDARD REPAIR. RE-INSTALLED RH EMERGENCY BRAKE BULKHEAD FITTING. LEAK CHECK RH EMERGENCY BRAKE LINE AND BULKHEAD FITTING.
BLENDED CORRODED AREAS ON THE LEFT AND RIGHT HAND WINGS AFT SPARS LOWER SPAR CAPS, LOCATED IN THE MAIN LANDING GEAR WHEEL WELL AREAS, PERFORMED ULTRASONIC AND EDDY CURRENT INSPECTIONS AND REPORTED FOR REPAIR DISPOSITION. TREATED AND PRIMED REPAIR AREAS IAW TEXTRON REPAIR MEMO.
CORROSION FOUND ON VERTICAL STAB AFT SPAR. FOUND DURING 1 ADDITIONAL AREA OF CORROSION FOUND ON RT SIDE OF VERTICAL STAB SPAR CLIP JUST BELOW RUDDER MIDDLE HINGE. PERFORM TEXTRON ENGINEERING FIELD REPAIR ON VERTICAL STAB SPAR. MECHANICALLY BLENDED 6 TOTAL AREAS OF CORROSION ON VERTICAL STABILIZER AFT SPAR RT AND LT ANGLE CLIP AND SPAR WEB, IAW CESSNA 680 SRM 51-70-02. CORROSION DETERMINED TO BE LEVEL 2 CORROSION.
SPOT OF CORROSION ON LT WING INBOARD FWD, JUST BEHIND LEADING EDGE. NOTED DURING 57-00-00-2101-LT FOUND 48 ADDITIONAL CORROSION AREAS AFTER FWD DRAG ANGLE REMOVAL AND CLEAN-UP. 5 HI-LOC'S ON LT WING UPPER WHERE FWD AND MIDDLE DRAG ANGLES WERE REMOVED REQUIRE REPLACEMENT DUE TO PITTING ON FASTENERS HEADS. MECHANICALLY REMOVED CORROSION LOCATED ON OUTBOARD EDGE OF LT WING UPPER FWD DRAG ANGLE AND ADDITIONAL CORROSION LOCATED UNDERNEATH FWD AND MIDDLE DRAG ANGLES. PROTECTED BARE METAL WHERE CORROSION DEPTHS DID NOT EXCEED C680 SRM 51-70-02 LIMITATIONS. REPAIRED BLENDED AREAS ON LT WING INBOARD UPPER SKIN NEXT TO FORWARD DRAG ANGLES, PER TEXTRON FIELD REPAIR, FR-680-0196-8574 REV A. TITLED: FIELD REPAIR-CORROSION DAMAGE, WING, UPPER SKINS, LT WS 37, DATED: 11/17/2020.
FOUND SEVERAL AREAS OF CONFIRMED CORROSION UNDER SEVERAL NUTPLATES ON THE V-STAB AT THE FOLLOWING LOCATIONS: 341DL 7 NUTPLATES, 341CL 5 NUTPLATES,341BL 5 NUTPLATES, 341DR 3 NUTPLATES,341CR 5 NUTPLATES, 341AL 1 NUTPLATE. REMOVE NUTPLATES AND BLEND CORROSION. PREP, TREAT AND PRIME AFTER NDT. BLENDED SEVERAL AREAS OF CORROSION UNDER SEVERAL NUTPLATES ON THE V-STAB AT THE FOLLOWING LOCATIONS: 341DL 7 NUTPLATES, 341CL 5 NUTPLATES, 341BL 5 NUTPLATES, 341DR 3 NUTPLATES, 341CR 5 NUTPLATES, 341AL 1 NUTPLATE. FOUND CORROSION TO BE OUT OF LIMITS, PER CESSNA 680 SRM 51-10-01 AND 51-70-02. SUBMITTED TO TEXTRON. REPAIRED CORROSION, PER TEXTRON MEMO DQ27778M1 DATED: NOVEMBER 11, 2020. CORROSION REMOVED WAS CONSIDERED TO BE LEVEL 2, PER NETJETS GMM 2.2.2.
SPOT OF VERIFIED CORROSION IN LT WHEEL WELL ON AFT SPAR, LOWER SPAR CLIP. MECHANICALLY REMOVED 1 SPOT OF VERIFIED CORROSION IN LT WHEEL WELL ON AFT SPAR LOWER SPAR CLIP. FOUND CORROSION BLENDS EXCEEDING C680 SRM 51-70-02 AND SUBMITTED FINDINGS TO TEXTRON ENGINEERING. REPAIRED CORROSION BLEND, IAW TEXTRON ENGINEERING FIELD REPAIR FR-680-0196-8561 REV- , TITLED FIELD REPAIR-CORROSION, CENTER WING, LT AND RT REAR SPAR CAPS, WS 35 TO WS38, DATED 11/03/2020 SUPPORTED BY FAA FORM 8100-9.
SPOTS OF VERIFIED CORROSION IN RT WHEEL WELL ON AFT SPAR, LOWER SPAR CLIP. MECHANICALLY REMOVED 1 SPOT OF VERIFIED CORROSION IN RT WHEEL WELL ON AFT SPAR LOWER SPAR CLIP. FOUND CORROSION BLENDS EXCEEDING C680 SRM 51-70-02 AND SUBMITTED FINDINGS TO TEXTRON ENGINEERING. REPAIRED CORROSION BLEND, IAW TEXTRON ENGINEERING FIELD REPAIR FR-680-0196-8561 REV- , TITLED FIELD REPAIR-CORROSION, CENTER WING, LT AND RT REAR SPAR CAPS, WS 35 TO WS38, DATED 11/03/2020 SUPPORTED BY FAA FORM 8100-9.
REPAIRED FIVE CHAFFED AREAS AROUND E-EXIT WEB AND FRAME IN STRINGER 3 SURROUNDING AREAS OF THE INTERIOR FUSELAGE AT FS 409.26 AND FS 426.26 BY INSTALLING REPAIR DOUBLERS AND SHIMS PER ENGINEERING REPAIR ORDER.
FOUND DURING PRELIMINARY INSPECTION. LT PYLON AFT CHANNEL ASSEMBLY IS CRACKED. FABRICATED AND INSTALLED REPAIR DOUBLER. ATTACHED TO MODIFIED EXISTING CHANNEL ASSEMBLY. ATTACHED TO PYLON TRAILING EDGE. ALL WORK ACCOMPLISHED IAW AQRD ERO-957932 REV IR AND APPROVED WITH 8110-3 DATED 5/8/19.
REPAIR OF OVERSIZED DOOR ROD PIN HOLE IN LEFT AND RIGHT MLG TRUNNIONS. REPORT NR S-680-0196/06RD DATED SEPTEMBER 29, 2017 WITH FORM FAA 8100-9.
LEFT AND RIGHT MLG DOOR CORROSION. MEMO DQ9710M1 DATED: OCTOBER 3, 2017.
LEFT AND RIGHT AFT WING SPAR WEB BULKHEAD FITTING CORRODED.
LEFT INBOARD FLAP CORRODED.
LANDING GEAR WOULD NOT RETRACT, GEAR HANDLE STUCK IN UP POSITION. REMOVED FAILED GEAR HANDLE AND INSTALLED NEW. C/W GEAR SWING. OPERATIONAL CHECK GOOD. WORK COMPLIED WITH IAW MM 32-10-00.
ABRUPT THUMP FOLLOWED BY RED GEAR UNLOCK LIGHT OCCURRED AT CRUISE AT FL410. TROUBLESHOT TO NOSE LANDING GEAR UPLOCK SWITCH BARLY CONTACTING UPLOCK ROLLER. ADJUSTED NLG UPLOCK SWITCH AND OPS CHECK GOOD IAW MM 32-60-00.
WHEN SELECTING AVIONICS ON, WE HEARD A NOISE LIKE A FAN BLADES HITTING SOMETHING, THEN WE SMELLED THE ODOR OF SOMETHING BURNING. TURNED AVIONICS BACK OFF AND WHEN TURNING ON AVIONICS BACK ON AGAIN WE RECEIVED "MAU 2 FAIL" CAS MESSAGE. COULD NOT DUPLICATE FAN NOISE/SMELL OR MAU 2 FAILURE. CYCLED AVIONICS POWER MULTIPLE TIMES AND FOUND NO DEFECTS. REMOVED DISPLAYS NR 2 AND NR 3 AND VISUALLY INSPECTED AREAS AROUND GLARE SHIELDS FANS AND EFIS DISPLAY FANS WITH NO INDICATIONS OF WIRING OR OTHER OBJECTS CONTACTING THE FAN BLADES. VACUUMED DUST OUT OF EFIS/GLARE SHIELD FANS. REINSTALLED NR 2 AND NR 3 DISPLAYED AND PERFORMED FUNCTIONAL TEST WITH NO DEFECTS NOTED.
AT 200 FT AGL THE FUEL BOOST PUMP RT CAS MESSAGE CAME ON. CREW SELECTED RT BOOST PUMP ON. AT 100 FT AGL FUEL PRESS LOW RT CAS MESSAGE CAME ON. ON LANDING ROLL OUT THE RT ENG FAILED & ATTEMPTED TO RELIGHT BUT WOULD NOT RELIGHT. SHUT THE ENG DOWN MANUALLY. R & R RT BOOST PUMP HIGH & LOW PRESSURE SWITCHES. PERFORMED SUPPLY & MOTIVE FLOW FUEL PRESSURE CHECKS, WITH NO DEFECTS NOTED. PERFORMED LEAK & OPS CHECKS & ENG RUNS IAW EMM 71-00-00. ALL ENG PARAMETERS ARE WITHIN EMM LIMITS.
RED CAS MESSAGE BATTERY O TEMP LIGHT ILLUMINATED ON TAKEOFF ROLL. TEMP, BATTERY, WENT UP TO +71 C. COMPLIED WITH APPROPRIATE EMERGENCY CHECKLIST. THE CYAN BATTERY OFF LT CAS MESSAGE DID NOT DISPLAY. CFR SAID THEY COULD SMELL ODOR & BURNING FROM LT BATTERY COMPARTMENT. REMOVED AND REPLACED BOTH MAIN BATTERIES. OPS CHECKED GOOD. WORK DONE IAW MM 24-31-00.
AFTER TAKEOFF, CLIMBING THROUGH 2000 MSL, AMBER ANTI-SKID FAIL CAS ILLUMINATED. COMPLETED ABNORMAL CHECKLIST, CAS DID NOT CLEAR. POWERED ACFT & PERFORMED OPERATIONS CHECK OF THE ANTI-SKID WITH NO DEFECTS NOTED. INTERROGATED CMC & ALL DATA PARAMETERS WHERE WITHIN LIMITS WITH NO DEFECTS OR FAULT MESSAGES. GAINED ACCESS TO SPEED TRANSDUCES ON MLG & INSPECTED TRANSDUCER, WIRING HARNESS & CONNECTIONS WITH NO DEFECTS NOTED. PERFORMED TAXI CHECK & OPERATED ANTI-SKID SYS WITH NO DEFECTS NOTED & NO CAS MESSAGES. WORK DONE IAW AMM 32-40-00.
GEAR WOULD NOT RETRACT ON CLIMB-OUT AND THE GEAR HANDLE WOULD NOT MOVE. WHILE CONFIGURING FOR LANDING THE "WOW MISCOMPARE" CAS MESSAGE ILLUMINATED. R & R NLG UPPER AND LOWER BARREL ASSEMBLIES IAW CMM CHAP 32-20-01 R 1. OPS CHECKED GOOD. UPPER BARREL ASSY PN 6742180-2, SN 239, HRS 2190.7, CYC 1466.
FUEL FILTER BYPASS L CAS ILLUMINATED IN FLIGHT, EMERGENCY DECLARED. REMOVED & INSPECTED LT FUEL FILTER ELEMENT. NO DEBRIS OR FOREIGN MATERIAL FOUND IN ELEMENT OR IN BOWL. PERFORMED LT ENGINE START & IMMEDIATELY RECEIVED A FUEL FILTER BYPASS "L" CAS MESSAGE WITH NEW FILTER ELEMENT INSTALLED. R & R LT FUEL FILTER DELTA 'P' SWITCH. GROUND RAN OF BOTH ENGINES WITH NO ABNORMAL CAS MESSAGES. IAW MM 73-10-03 OTHER FUEL FILTERS & FUEL SAMPLES CHECKED GOOD. NO DEBRIS.
THE ENG CONTROL FAULT R FAILED AT FL430. DID NOT FLY THROUGH ANY WEATHER. DASHES ON EVERYTHING RT SIDE. ON POWERING DOWN THE AMBER MAU 2 FAIL CAME ON. REMOVED AND REPLACED CUSTOM I/O MODULE OPS CHECKS GOOD IAW MM 34-17-00.
UPPER FWD LATCH OF REAR BAGGAGE DOOR POPPED OPEN IN FLIGHT. INSPECTED DOOR LATCH, PINS, AND LOCKS. FOUND DOOR TO OPERATE AS REQUIRED WITH NO DEFECTS NOTED.
DURING CRUISE AP A FAIL CAS MSG POSTED FOLLOWED 30 SECONDS LATER BY AP B FAIL CAS MSG.
DURING CRUISE AP A FAIL CAS MESSAGE POSTED FOLLOWED 30 SECONDS LATER BY AP B FAIL CAS MESSAGE. BOTH MESSAGE REMAINED ON THE RESET OF THE FLIGHT REVIEWED CDMS FAULTS, FOUND PITCH TRIM FAULT ON LAST FLIGHT. REMOVED AND REPLACED HORIZONTAL STAB TRIM CONTROL UNIT. IAW MM CHAPTER 27-40-00. EICAS STAB RIGGING CHECKS GOOD. OPS CHECKS GOOD.
DURING CRUISE, AP A FAIL CAS MESSAGE POSTED FOLLOWED 30 SECONDS LATER BY AP B FAIL CAS MESSAGE. BOTH MESSAGES REMAINED ON THE RESET OF THE FLIGHT REPEAT WRITE-UP. REVIEWED CDMS FAULTS, FOUND PITCH TRIM FAULT ON LAST FLIGHT. REMOVED AND REPLACED HORIZ STAB TRIM CONTROL UNIT IAW MM CHAPTER 27-40-00. EICAS STAB RIGGING CHECKS GOOD. OPS CHECKS GOOD.
AFTER TAKEOFF, POSITIONED GEAR HANDLE UP. THE MAINS CAME UP BUT THE NOSE DID NOT RETRACT AND THE RED UNLOCK LIGHT STAYED ILLUMINATED. (S)
AFTER TAKEOFF, POSITIONED GEAR HANDLE UP. MAIN CAME UP BUT NOSE DID NOT RETRACT AND THE RED UNLOCK LIGHT STAYED ILLUMINATED. RECYCLED GEAR AND SAME THING HAPPENED. AFTER ABOUT 10 MIN THE NOSE GEAR RETRACTED. JACKED ACFT, 3 GREEN, CYCLED GEAR SEVERAL TIMES. NLG WOULD NOT RETRACT AND MAINS WOULD. CLEANED DOWNLOCK SWITCH CONNECTOR. NO HELP. REMOVED "RETRACT" HYD LINE NEAR ACTUATOR, NO FLUID EXPELLED WHEN SELECTED UP. REATTACHED LINE. REVIEWED HYD SCHEMATIC IN FLIGHT SAFETY NORMAL. RETRACTION HYD FLUID GOES INTO POWER STEERING UNIT TO CTR NOSE GEAR WHEELS THEN GETS PARTED TO RETRACTION SIDE OF ACTUATOR. REMOVED "CENTER" HOSE TO NWS UNIT AND GOT FLUID FLOW WHEN SELECTING RETRACT. RECONNECTED 'CENTER" HOSE. DISCONNECTED "RETRACT" HOSE FROM NWS UNIT. NO FLUID FLOW WHEN RETRACTING. ORDERED NEW UNIT PN 9914650-2 AND PROTRACTOR KIT PN: CJMDX32-003. REMOVED NWS UNIT P/N 9914650-2, SN 0218 AND INSTALLED A NWS UNIT, S/N 0270. RETRACTED GEAR 10 TIMES. ALL RETRACTION AND INDICATIONS OPS CHECK NORMAL AS REQUIRED. C/W NWS TEST (CENTERING PRIOR TO RETRACTION). OPS CHECKS GOOD. C/W NWS TEST (ELECTRICAL AND DISCONNECT). OPS CHECKS GOOD. INSTALLED PROTRACTOR. CONFIRMED NWS DRIVE HAS 1.95" IN BOTH DIRECTIONS. TIGHTENED ADJUSTMENT SCREWS ON PIVOT ARMS AGAINST SECTOR TO .16" ON BOTH SIDES. NWS TRAVELS R90 DEGREES, L70 DEGREES AND CTRS AT 4 -7 DEGREES. RIGGING IS REQUIRED. FOUND CABLE TENSIONS ON TOP OF NOSE WHEEL STEERING UNIT NOT WITH SPEC. (16LBS FOR .0625 INCH CABLE)GAINED ACCESS TO MIXER ASSY. FOUND CABLE ON LT SIDE FROM LT SIDE OF MIXER ASSY. OUT THROUGH FWD PRESSURE BULKHEAD TO BE OFF OF ITS PULLEY. REMOVE CTR FLOOR PANELS FWD. OF PEDESTAL. REMOVED LWR MIXER ASSY COVER. REMOVED ABOVE PULLEY AND CORRECTLY ROUTED CABLE. RE-INSTALLED MIXER ASSY COVER. FOUND CABLE TENSION ON ABOVE PULLEY VERY LOOSE. ADJUSTED BOTH LT AND RT CABLES WHICH RISE OUT OF MIXER ASSY. TO CORRECT CABLE TENSIONS. APPLIED ELEC / HYDR POWER AND OPERATED NOSE WHEEL STEERING. FOUND NWS STEERING TO NOT CTR, WAS STILL OFF BY ABOUT 4 DEGREES. TRAVEL IS STILL 90 DEGREES RT, 70 DEGREES LT. CALLED MFG HELP DESK WAS ADVISED TO RELIEVE HYDR AND ACCUMULATOR PRESSURE AND SEE IF LWR OLEO WOULD GO LT AND RT TO ITS' STOPS. INSPECTED CONTROL ASSY (TILLER) AND ITS COMPONENTS BY REMOVING LT COCKPIT KICK PANEL. NO UNUSUAL DEFECTS WERE NOTED, TILLER IS A SEALED UNIT , NO BINDING NOTED ON EXTERIOR COMPONENTS, INCLUDING RETURN SPRING AND CONTROL SHAFT. RE-INSTALLED LT COCKPIT KICK-PANEL. INSPECTED ALL STEERING COMPONENTS IN NOSE WHEEL WELL AND COCKPIT, NO BINDING WAS NOTED AND ALL CABLE TENSIONS WERE GOOD. PLACED NEW NWS STEERING UNIT ON ORDER. REMOVED NWS UNIT P/N 9914650-2 SN 0270. INSTALLED NEW UNIT OF SAME PN, SN0269. CABLES NEED TO BE INSTALLED AND HYD LINES. NEED TO BE INSTALLED AND OPS CHECK NEED TO BE PERFORMED AT THIS TIME. INSTALLED NWS STEERING CABLES AND HYD LINES. INSTALLED ALL REQUIRED COTTER PINS. RIGGED NOSE WHEEL STEERING CABLE AS REQUIRED. COMPLIED WITH NWS SYS BLEEDING. COMPLIED NWS OPS CHECKS, OPS CHECK GOOD. NO LEAKS NOTED. JACKED ACFT AND COMPLIED WITH GEARS SWINGS. GEARS WERE SWUNG 8 TIMES IN 2 SEPERATE OPS CHECKS. OPS CHECK GOOD AT ALL TIMES. WORK PERFORMED IAW MM CHAPTERS, 32-50-00, AND 32-20-00. CHECKED HYD RESERVOIR AND SERVICED AS REQUIRED.
GEAR WILL NOT RETRACT AFTER TAKEOFF. "WOW MISCOMPARE" AMBER MESSAGE IN FLIGHT INTERMITTENTLY. WENT OUT BEFORE LANDING. ONLY ON FOR ABOUT 15 SECONDS. NOSE STRUT NOT EXTENDING COMPLETELY. NITROGEN SERVICE LOW AT UPPER AND LOWER SERVICE PORT. RESERVICED NOSE STRUT TO 285 PSI. UPPER AND 40 PSI LOWER. OPERATIONAL CHECK GOOD IAW MM 32-20-00.
FIRST OFFICER BRAKE PEDALS HAD NO PRESSURE CAPTAIN BRAKE PEDALS SEEMED TO HAVE NORMAL PRESSURE. PERFORMED ANTI-SKID BRAKE BLEED, BRAKE PEDALS CHECKED GOOD AFTER BLEED I/A/W MODEL 560 MM 32-42-00.
AFTER TAKEOFF, NOTICED GEAR UNLOCK LIGHT WITH HYDRAULIC PRESSURE ON ANNUNCIATOR. RAN CHECK LIST. WHEN GEAR CONTROL CIRCUIT BREAKER PULLED LT MAIN FELL WITH GREEN LIGHT. MATCHED CONDITION WITH GEAR HANDLE AND RT MAIN AND NOSE WHEEL FELL WITH GREEN LIGHTS. USED EMER GEAR BOTTLE AND LANDED. REPLACED HYDRO RELIEF VALVE PER 560 MM, CH 29-11-06. LEAK AND OPS CHECKS GOOD
UPON DEPARTURE AND GEAR RETRACTION THE GEAR UNSAFE LIGHT ILLUMINATED ON AND HYD PRESS LIGHT ILLUMINATED. WITH ACCELERATION NOISE INCREASED ABNORMALLY, AS IF ONE OR MORE GEAR REMAINED DOWN. REMOVED LT MAIN GEAR ACTUATOR & INSTALLED A RENTAL ACTUATOR THAT WAS INSPECTED BY CESSNA AIRCRAFT COMPANY CRS CNQR18C IAW 560 M.M. CHAP. 32-31-04.
AFTER TAKEOFF THE GEAR UNLOCKED LIGHT AND THE HYDRAULIC PRESS ON LIGHT REMAINED ILLUMINATED AFTER RETRACTING THE LANDING GEAR. REMOVED & REPLACED LT UPLOCK ACTUATOR ASSY SPRING AND LT UPLOCK SWITCH. CYCLED GEAR MULTIPLE TIMES. OPS CHECKS GOOD IAW CE560 MM 32-31-05.
AFTER TAKEOFF THE GEAR UNLOCKED LIGHT REMAINED ILLUMINATED. THE LANDING GEAR HANDLE WAS CYCLED TWICE WITH NORMAL INDICATIONS. INSPECTED GEAR & C/W GEAR SWINGS, ALL OPERATIONS & INDICATIONS WERE NORMAL NO DEFECTS NOTED AT THIS TIME. ALL WORK ACCOMPLISHED IAW CE560 MM CHAPTER 32-30-00 & 32-30-00 FOR TROUBLESHOOTING.
ON CLIMBOUT, AFTER GEAR AND FLAP RETRACTION, THE (HYD PRESS ON) AND RED (GEAR UNLOCKED) LIGHTS REMAINED ON. PERFORMED PROCEDURE K-2 IN EMEG/ABNORMAL PROCEDURE AT STEP 2 WHEN THE LANDING GEAR CONTROL C/B WAS PULLED THE LT MAIN GEAR EXTENDED, CONFIRMED AURALLY, AND LT GEAR GREEN LIGHT CAME ON. RED (GEAR UNLOCKED) AND (HYD PRESSON) LIGHTS REMAINED ILLUMINATED. AT STEP 3 WHEN THE FLAP CONTROL C/B WAS PULLED, THE (HYD PRESS ON) LIGHT EXTINGUISHED. WHEN THE LANDING GEAR C/B WAS RESET THE LT MAIN GEAR RETRACTED AND RED (GEAR UNLOCKED) LIGHT EXTINGUISHED. FLIGHT RETURNED TO DEPARTURE AIRPORT. ALL HYD AND FLIGHT CONTROL SYSTEM FUNCTIONED NORMALLY DURING GEAR AND FLAP EXTENSION. (M2B) PERFORMED LANDING GEAR SLOW C
STANDBY AIRSPEED INDICATOR FAILED TO DISPLAY AIRSPEED DURING TAKEOFF ROLL, FOUND AIRSPEED FLEXIBLE HOSE KINKED ON THE STANDBY AIRSPEED/ALTIMETER. ROUTED HOSE IN A PROPER ORIENTATION TO AVOID KINKS. PERFORMED THE AIRSPEED CALIBRATION FOR THE STANDBY AIRSPEED/ALTIMETER IAW THE CESSNA 560 MAINTENANCE MANUAL 34-11-25. CHECKS GOOD.
MASTER WARNING LIGHT ILLUMINATED DURING T/O (AT APPROX 80-90 KIAS), THE RT OIL PRESSURE LIGHT ILLUMINATED AND EXTINGUISHED WHEN POWER WAS REDUCED TO IDLE. RAN ACFT, COULD NOT DUPLICATE PROBLEM. REMOVED RT OIL PRESSURE SWITCH P/N 9912178-3 S/N 1291. INSTALLED NEW SWITCH P/N 9912178-3 S/N 1382. RAN ACFT OPS AND LEAK CHECK GOOD, ALL IAW CE-560 MM 79-31-01.
AFTER TAKEOFF GEAR WOULD NOT RETRACT. ATC REPORTED THAT OUR TRANSPONDER DID NOT APPEAR ON (IT WAS SELECTED TO ALT). AFTRE CLIMBING THROUGH 2000 FT A LOUD CLUNK AND POP WAS HEARD. GEAR THEN RETRACTED NORMALLY. GEAR HANDLE WOULD NOT MOVE UNTIL (POP) WAS HEARD. ITEM IS UNDER INVESTIGATION.
ON TAKEOFF ROLL THE RT FUEL LOW PRESSURE LIGHT ILLUMINATED OR HYD FLOW LOW LIGHT IS ILLUMINATED. PERFORMED SATISFACTORY POWER RUNS. OPERATED THRUST REVERSERS, FLAPS AND SPOILERS. PERFORMED A SATISFACORY FUEL CROSS FLOW AND BOOST PUMP CHECKS, REFERENCE MM 31-51-01 AND AFM.
LANDING GEAR HANDLE WOULD NOT MOVE TO ALLOW GEAR RETRACTION AFTER TAKEOFF. ITEM IS UNDER INVESTIGATION.
ON TAXI INTO FBO, PARTIAL BRAKE PRESSURE LOST WITH PWR BRAKE LOW PRESSURE AND ANTI SKID INOP ANNUCIATOR LIGHTS ON. TRIED TURNING ANTI-SKID OFF, AND ALL BRAKE PRESSURE LOST. TURNED ANTI-SKID ON RECLAIMED PARTIAL PRESSURE. TROUBLESHOT A/S BRAKE SYS, REPLACED BRAKE CONTROL RELAY, BROKE METER RELAY, BRAKE LOW PRESS SWT FOUND FLUID IN LOWER BRAKE VENT LINE, INSP LT AND RT BRAKE SHUTTLE VLV'S, FOUND FLUID IN BRAKE LINES, RESEALED LT AND RT BRAKE SHUTTLE VLV'S, REINSTALLED, REINSTALLED BRAKE LINES, BLED A/S BRAKE SYSTEM, OPS CHK/LK CHKS GOOD IAW M/M CH'S 12-12-02, 32-42-00, AND CMM CH 32-46-43 CWRRO61D.
R-SIDE R-BRAKE PEDAL GOES FLAT TO THE FLOOR. BLED BRAKES IAW CE560 MM CHP 32-42-00, OPS AND LEAK CHECKED GOOD.
THE RIGHT HAND SIDE BRAKE PEDALS NEED TO BE DEPRESSED FULLY AND THEN PUMPED TO RECEIVE ADEQUATE BRAKING ACTION. ON THE LAST LANDING, BRAKE PEDALS WERE PUSHED TO FLOOR THEN PUMPED. BLED BRAKE SYSTEM PER CHAPTER 32-42-00 OF THE CITATION 560 MM, OPERATIONAL AND LEAK CHECK GOOD.
LEFT BRAKE APPEARS TO GRAB LEFT WITH VERY LITTLE BRAKE APPLICATION, AIRCRAFT RETURNED TO BLOCK. TROUBLESHOT AND FOUND LEFT SIDE BRAKE FAULTY, REPLACED LT BRAKE ASSEMBLYIAW CESSNA MM CHAPTER 32-42-01.
ON TAKE OFF FROM EWR GEAR WAS STUCK IN DOWN POSITION ACCOMPLISHED AIR TURN BACK TO EWR. ITEM IS UNDER INVESTIGATION.