N305QS
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
IAW PREFLIGHT CHECKS THE EMERGENCY LIGHT SWITCH WAS PLACED TO ON POSITION. NONE OF THE EMERGENCY LIGHT ILLUMINATED. PER DISCUSSION WITH MAINTENANCE A 30 MINUTE CHARGE CYCLE IS NOT AUTHORIZED ON THE DISCREPANCY 5.1: IW PREFLIGHT CHECKS THE EMERGENCY LIGHT SWITCH WAS PLACED TO ON POSITION. NONE OF EMERGENCY LIGHT ILLUMINATED. A 30 MINUTE CHARGE CYCLE IS NOT AUTHORIZED ON THE ACFT. ARRIVED AT ACFT & SELECTED LIGHT SWITCH TO ARM & ON NOTING NO LIGHTS ILLUMINATED. POWERED ACFT & SELECTED LIGHT SWITCH TO ON & ARM NOTING ALL EMERGENCY LIGHTS ILLUMINATED IN BOTH POSITIONS. FOUND PAX SAFETY SWITCH SELECTED ON CAUSING THE LIGHTS TO ILLUMINATE IN ARM POSITION. DESELECTED PAX SAFETY SWITCH & ALLOWED BATTERIES TO CHARGE FOR 2 HOURS IAW AMM 33-50-00. PERFORMED OPS CHECK OF EMERGENCY BATTERIES IAW AMM 33-50-00 WITH NO DEFECTS NOTED. COMPLIED WITH NJA EXERCISE PROCEDURE NOTING ALL LIGHTS REMAIN ON LONGER THAN 10 MINUTES INDICATING BATTERIES ARE AIRWORTHY IAW CMM 33-50-03.
TWO FORWARD RIGHT EXTERIOR , ONE MAIN CABIN ENTRY, THREE MAIN CABIN OVERHEAD EMER LIGHTS REMAINED INOP AFTER 2 30 MINUTE CHARGE CYCLES. REPLACED BATTERY PACKS. OPS CHECK GOOD. IAW MM 33-50-10
MED WAS CLOSED WITH THE KEYLOCK IN THE LOCKED POSITION. THE CABIN DOOR CAS MESSAGE ILLUMINATED. COULD NOT DUPLICATE. MAINTENANCE PERFORMED IAW 52-10-00 AND 52-20-00.
EMERGENCY EXIT LIGHT ON LAV SEAT DOES NOT ILLUMINATE(PRE-FLIGHT) COMPLETED OPS CHECK OF THE EMERGENCY LIGHTING SYSTEM IAW MM 33-50-00. OPS CHECK GOOD AT THIS TIME.
BLENDED CORRODED AREAS ON THE UPPER AND LOWER BRACKETS OF THE UPPER RUDDER HINGE AT THE BONDING STRAP BOLT HOLE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
FOUND CRACK IN THE MID FRAME OF THE NOSE LANDING GEAR WHEEL WELL, CUT OUT CRACKED AREA, PERFORMED NDT, FABRICATED AND INSTALLED REPAIR DOUBLER AND SHIMS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
BLENDED CORRODED AREAS LOCATED ON THE UPPER SURFACE OF THE UPPER WING SKINS LOCATED UNDER AND ADJACENT TO THE LH WING AFT DRAG ANGLE (WING-TO-FUSELAGE FAIRING STRUCTURE), AND THE RH WING MIDDLE AND AFT DRAG ANGLES, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED TREATED AND PRIMED THE CORRODED AREAS FOUND ACCEPTABLE PER TEXTRON STANDARD REPAIR. FABRICATED AND INSTALLED REPAIR DOUBLERS AS REQUIRED IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH & DEVELOPMENT MRO ENGINEERING REPAIR ORDER
REPAIRED THE CORRODED FUSELAGE SKIN AT THE LOWER TCAS ANTENNA CABLE FEED-THROUGH BY BLENDING CORRODED AREAS, PERFORMING NDT AND REPORTING FOR REPAIR DISPOSITION, FABRICATED AND INSTALLED REPAIR DOUBLER IN ACCORDANCE WITH AVIATION QUALITY RESEARCH AND DEVELOPMENT ENGINEERING REPAIR ORDER
MECHANICALLY REMOVED AREAS OF CORROSION LOCATED ON LH ELEVATOR CABLE PULLEY ATTACHMENT BRACKET LOCATED INSIDE BELLY PANEL BAY 154AC AND EXTENDING FORWARD SEVERAL INCHES ONTO FUSELAGE STIFFENER AND DRAIN ATTACHMENT RIVETS PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDED AREAS BY CLEANING, TREATING AND PRIMING PER TEXTRON REPAIR MEMO.
REMOVED 3 AREAS OF CORROSION LOCATED ON LH #1 SPOILER OUTBOARD HINGE BRACKET, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED 2 AREAS OF CORROSION FROM LH WING TRAILING EDGE PANEL 532GB, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED CORROSION LOCATED IN RH MLG WHEEL WELL AT MIDDLE EMERGENCY BRAKE LINE CARRY THRU ON WS 52.00 INBOARD SIDE, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED CHAFFING MARKS ON RH MIDDLE WING ATTACHMENT FITTING, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED CORROSION LOCATED IN LH MLG WHEEL WELL AT MIDDLE EMERGENCY BRAKE LINE CARRY THRU ON WS 52.00 INBOARD SIDE, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
REPAIRED CORRODED AREA IN THE LH MLG WHEEL WELL ON THE AFT WING SPAR LOWER CLIP IN BAY 730DL, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
REPAIRED CORRODED AREAS OF THE AFT TAILCONE SKINS LOCATED UNDER AND ADJACENT TO THE AFT CHIN FAIRINGS, BY R&R THE FAIRINGS, BLENDING CORRODED AREAS, PERFORMING NDT AND REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER
MECHANICALLY REMOVED 1 AREA OF CORROSION FROM LH ELEVATOR CABLE PULLEY BRACKET LOCATED INSIDE LOWER TAIL ACCESS BAY 323AC, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED CORROSION LOCATED ON LH AND RH MLG WHEEL WELL WS 37.00 FWD END, EMERGENCY BRAKE LINE CARRY THRU FITTINGS, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS PER MRO ENGINEERING REPAIR ORDER.
REPAIRED TWO CORRODED AREAS IN THE RH MLG WHEEL WELL ON THE AFT WING SPAR LOWER CLIP, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
REPAIRED CORRODED AREAS AT OF THE LH WING AFT SPAR WEB AFT FACE AT THE #4 SPEED BRAKE PANEL HYDRAULIC LINE CARRY-THRU FITTINGS, PERFORMED NDT, REPORTED FOR REPAIR DISPOSITION, CLEANED, TREATED, AND, PRIMED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
REPAIRED CORRODED AREA OF THE RIGHT WING LOWER SKIN JUST OUTBOARD OF THE MAIN JACKPOINT BY BLENDING AREA, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, CLEANING, TREATING, AND PRIMING REPAIR AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
BLENDED AREA OF CORROSION FROM FUSELAGE SKIN LOCATED AFT OF E-EXIT DOOR OPENING, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS BY CLEANING, TREATING AND PRIMING IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
BLENDED MULTIPLE AREAS OF CORROSION ON THE EMERGENCY EXIT DOOR, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS BY CLEANING, TREATING AND PRIMING IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
MECHANICALLY REMOVED 2 AREAS OF CORROSION FROM LH LOWER WING SKIN TRAILING EDGE JUST INBD OF FLAP ISLAND, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS BY CLEANING, TREATING AND PRIMING IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
DOOR MECHANISM NOT BALANCED. VERY DIFFICULT TO OPEN AND CLOSES VIOLENTLY. ADJUSTED CABIN DOOR CABLES FORWARD AND AFT AFTER FINDING TENSIONS TO BE EXTREMELY HIGH. CABLE TENSIONS SET TO CORRECT RANGE AND OPS CHECK OF MAIN CABIN DOOR IS GOOD. IAW MM 52-10-50.
CORROSION, LH/RH WING, LOWER FORWARD REAR SPAR CAP, W.S. 17-46.
R/H ELEVATOR WEDGE FAIRING SKIN CORROSION BLEND-OUT.
CORROSION AROUND AFT SPAR GEAR EXTEND AND RETRACT FEED-THROUGHS RH WHEEL WELL. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR S-680-ATA-57/03RD.
CORROSION AROUND AFT SPAR GEAR EXTEND AND RETRACT FEED-THROUGHS RH WHEEL WELL. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR S-680-ATA-57/03RD.
CORROSION AROUND AFT SPAR EMERGENCY EXTENSION AND EMERGENCY BRAKE FEED-THROUGHS LH WHEEL WELL. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR S-680-ATA-57/03RD.
TWO FASTENERS (1EA SCREW AND 1EA 1/4 TURN) HAVE GOUGED THE STRUCTURE ABOVE THE EMERGENCY EXIT DOOR P/N 6711141-30.
CABIN EMERG LIGHT: THE EMERGENCY LIGHTS ON BATTERY PACK NUMBER 1 ARE NOT FUNCTIONING PROPERLY. //SIGNOFF// REMOVED WORN CABIN EMERGENCY LIGHT BATTERY PACK P/N: CBS28-1 S/N: 000342 WITH A DOM OF 04/15 AND INSTALLED REPAIRED P/N: CBS28-1 S/N:006929 WITH A DOM OF 11 /18 AFTER INSTALLATION PERFORMED A TOP CHARGE OF THE EMERGENCY LIGHTS BATTERY PACKS AS REQUIRED. WORK PERFORMED IN REFERENCE WITH CE-680 AMM 33-50-10
EMERG LIGHT SWITCH: NO INTERIOR OR EXTERIOR EMERGENCY EXIT LIGHTS ILLUMINATE WITH THE EMERGENCY LIGHT SWITCH IN THE ARMED POSITION AND BATTERY SWITCHES OFF. EMERGENCY EXIT LIGHTS ILLUMINATE WHEN EMERGENCY EXIT LIGHT SWITCH IS IN THE ON POSITION. PERFORMED EMERGENCY BATTERY FUNCTIONAL CHECK !AW CE-680 AMM 33-50-00. FUNCTIONAL CHECK GOOD. NO DEFECTS NOTED AT THIS TIME.
RIGHT SIDE TELESCOPING ROD IS BENT AND THE DOOR WILL NOT CLOSE. GAINED ACCESS TO THE RIGHT SIDE TELESCOPING ROD AND REMOVED AND REPLACED TELESCOPING ROD. IAW CE68 AMM 52-10-30. PERFORMED A SATISFACTORY OPS CHECK, NO DISCREPANCY NOTED AT THIS TIME.
RIGHT ENGINE ENGINE VIBRATION INDICATION: WHILE IN CRUISE FLIGHT (FL330). RIGHT ENGINE BEGIN TO VIBRATE, ACCOMPANIED BY MOMENTARY "ENGINE SHUDOWN" CAS MESSAGE IN CYAN. POWER WAS REDUCED TO 60% N1 WHERE VIBRATION STOPPED. ENGINE VIBRATION QRH WAS ACCOMPLSHED AND FLIGHT CONTINUED WITHOUT FURTHER INCIDENT.//CORRECTIVE ACTION//REMOVED AND REPLACED RIGHT HAND ENGINE DUE TO ENGINE VIBRATION. PN OFF: 30B4258-01 SN OFF: PCE-CG0241
CABIN EMERG LIGHT: WHEN PERFORMING THE EMER LTS TEST, THE SEAT NUMBER 8 CABIN EMERGENCY LIGHT/READING LIGHT DID NOT ILLUMINATE WHEN THE MAIN BATTERY SWITCHES WERE OFF AND THE EMER LTS SWITCH WAS SELECTED TO THE ARM POSITION. TROUBLE SHOOTING SHOWED THAT THE LIGHT WOULD ILLUMINATE WITH AIRCRAFT MAIN BATTERY POWER SELECTED AND THE EMER LTS SWITCH SELECTED TO ON, BUT NOT WHEN MAIN BATTERY SWITCHES WERE SELECTED BACK TO OFF. // SIGNOFF // ARRIVED AND AIRCRAFT AND FOUND THE SEAT #8 EMER. LIGHT, HALF OF THE RH AFT EMER PATH LIGHT, FORWARD OVER WING EMER LIGHT, AND SHARK LIGHT ALL INOP WITH EMER. SWITCH IN ON POSITION AND AIRCRAFT BATTERIES OFF. ALL WORK NORMAL WITH AIRCRAFT BATTERY AND EMER LIGHTS SWITCH ON. CHARGED EMERGENCY BATTERIES USING AIRCRAFT POWER IAW RADIANT POWER CORP. CMM 24-31-05 FOR APPROXIMATELY 2 HOURS. PERFORMED OPERATIONAL TEST OF EMERGENCY BATTERIES AND THE LIGHTS ASSOCIATED WITH EMER. BATTER PACK #3 LASTED ONLY 20 SECONDS. PLACED EMER BATTERY PACK ON ORDER.REMOVED #3 EMER. BATT. PACK IAW CE-680A MM 33-50-10. INSTALLED REPAIRED #3 EMERGENCY BATT. PACK UNIT IAW CE-680 MM 33-50-10. OPS CHECKS GOOD. OLD/NEW PN: CBS28-1 OLD SN: 1761M NEW SN: 006850
MAIN DOOR HANDLE: WHEN THE MAIN DOOR IS CLOSED AND LATCHED IN NORMAL CLOSED POSITION, THE RED BUTTON CAN NOT BE DEPRESSED TO OPEN MAIN CABIN DOOR. THE CREW MADE SURE THAT THE CABIN WAS DEPRESSURIZED AND THE SEAL WAS DEFLATED. WHEN UPWARD PRESSURE ON THE DOOR HANDLE WAS PLACED, THEN THE BUTTON COULD BE DEPRESSED AND THE DOOR OPENED NORMALLY. THE CREW THEN CYCLED THE DOOR AND THE CONDITION REPEATED ITSELF.///SIGN-OFF///PERFORMED THE CABIN DOOR LATCHING/LOCKING SYSTEM ADJUSTMENT PER TEXTRON AMM 52-10-40, REINSTALLED DOOR STEPS AND ADJUSTED THE SPADE FAIRING IAW TEXTRON AMM 52-10-40. OPS CHECK GOOD.
MAIN DOOR HANDLE: WHEN THE MAIN DOOR IS CLOSED AND LATCHED IN NORMAL CLOSED POSITION, THE RED BUTTON CAN NOT BE DEPRESSED TO OPEN MAIN CABIN DOOR. THE CREW MADE SURE THAT THE CABIN WAS DEPRESSURIZED AND THE SEAL WAS DEFLATED. WHEN UPWARD PRESSURE ON THE DOOR HANDLE WAS PLACED, THEN THE BUTTON COULD BE DEPRESSED AND THE DOOR OPENED NORMALLY. THE CREW THEN CYCLED THE DOOR AND THE CONDITION REPEATED ITSELF.///SIGN-OFF///PERFORMED THE CABIN DOOR LATCHING/LOCKING SYSTEM ADJUSTMENT PER TEXTRON AMM 52-10-40, REINSTALLED DOOR STEPS AND ADJUSTED THE SPADE FAIRING IAW TEXTRON AMM 52-10-40. OPS CHECK GOOD.
MAIN CABIN DOOR NEEDS ADJUSTING. THE DOOR LOWERS VERY QUICKLY WITH VERY LITTLE COUNTERBALANCE WEIGHT HOLDING DOOR IN THE CLOSED POSITION. THE CONDITION MAY HAVE CAUSED UPPER STEP PANEL TO COME OFF. CORRECTIVE ACTION: GAINED ACCESS TO MAIN CABIN DOOR SPRING AND CABLES FOUND SATISFACTORY, ADJUSTED CABLES AS REQUIRED. OPERATIONS CHECKED SATISFACTORY IAW CESSNA CE-680 M/M CHAPTER 52-10-00.
FIRST OFFICER COCKPIT WINDOW - PASSING FL 220 RIGHT COCKPIT SIDE WINDSHIELD BEGAN TO CRACK. QRH WAS RUN AND WINDOW CONTINUED TO SLOWLY CRACK UNTIL 3000FT. ALL SWITCHES AND CIRCUIT BREAKERS ARE IN QRH CONFIGURATION. "CORRECTIVE ACTION" REMOVED AND REPLACED WITH NEW THE RH HEATED SIDE WINDOW IAW CE-680 AMM 56-12-00 LEAK AND OPERATIONAL TESTS CHECKED GOOD. NO DEFECTS NOTED.
VERTICAL STAB. AFT SPAR CAP DAMAGE (CORROSION). REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ19154M1 DATED APRIL 12, 2019.
APU TRUSS MOUNT (FLANGE) CORROSION. REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ19152M1 DATED APRIL 12, 2019.
APU TRUSS MOUNT (FLANGE) CORROSION. REFERENCE ENGINEERING MEMO DQ19152M1.
VERTICAL FIN DRAG ANGLE DAMAGE. REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ19155M1 DATED APRIL 15, 2019.
VERTICAL FIN DRAG ANGLE DAMAGE. REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ19155M1 DATED APRIL 15, 2019.
VERTICAL STAB. AFT SPAR CAP DAMAGE (CORROSION). REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ19154M1 DATED APRIL 12, 2019.
ALL LANDING GEAR RETRACTION DID NOT RETRACT - GEAR WOULD NOT RETRACT AFTER TAKEOFF. THE HANDLE WAS LOCKED OUT AND COULD NOT BE MOVED. A SHORT TIME LATER WE RECEIVED A WOW MISCOMPARE CAS MESSAGE. RETURNED TO LANDING AND MESSAGE CLEARED AFTER TOUCHDOWN. ALL SYSTEMS WERE NORMAL AFTER LANDING. // SIGNOFF// JACKED AIRCRAFT SWUNG LANDING GEAR 5 TIMES WITH NO DEFECTS NOTED. CHECKED SERVICE ON NOSE STRUT WITH REFERENCE TO CESSNA 680 MM 12-20-32. SERVICING WAS CORRECT. MCC REQUESTED TO REPLACE NOSE GEAR SQUAT SWITCH. REMOVED SWITCH ASSY P/N 622EN226-6 AND INSTALLED NEW CUSTOMER SUPPLIED SWITCH P/N 622EN226-6 WITH REFERENCE TO CESSNA 680 MM 32-60-00. VERIFIED SQUAT SWITCH RIGGING IS CORRECT. SWUNG GEAR AN ADDITIONAL 5 TIMES WITH NO DEFECTS NOTED. REMOVED AIRCRAFT FROM JACKS
BLENDED THREE AREA OF CORROSION ON THE APU INLET DEFLECTOR SCOOP. FOUND INLET/DEFLECTOR SCOOP NOT REPAIRABLE AND REPLACED WITH NEW.
DURING THE FINAL STAGES OF A HIGH ALTITUDE 3 HOUR FLIGHT WHILE MANEUVERING BELOW 10,000 FEET WITH THE THROTTLES PULLED BACK NEAR IDLE TO DESCEND AND SLOW DOWN A STRONG OILY MUSTY ODOR PERMEATED THE COCKPIT AND CABIN. UPON ARRIVAL AT AIRCRAFT, LEFT AND RIGHT ENGINE OIL LEVELS WERE CHECKED AND FOUND TO BE LOW. APU OIL LEVEL WAS ALSO CHECKED USING THE DIP STICK AND FOUND TO BE OVER SERVICED. GAINED ACCESS TO LEFT AND RIGHT ENGINE BLEED AIR PIPES AND CHECKED FOR OIL RESIDUE IN PIPES, NO RESIDUE WAS NOTED AND REINSTALLED PIPES TO ORIGINAL CONDITION. ACCESSED MAINTENANCE LOG AND IT WAS NOTED THAT THE APU OIL LEVEL WAS SERVICED. GAINED ACCESS TO ACM WATER SEPARATOR AND REMOVED SOCK AND CLEANED IN ACCORDANCE WITH MAINTENANCE MANUAL 12-19-00. REINSTALLED SOCK. SERVICED LEFT AND RIGHT ENGINE OIL WITH 1/2 QUART FOR EACH ENGINE IN ACCORDANCE WITH MAINTENANCE MANUAL 12-11-02. ACCOMPLISHED ENGINE RUN AND NO SMELL WAS NOTED FROM EITHER ENGINE.
RIGHT WING UPPER WING SKIN OTBD OF MIDDLE DRAG ANGLE AFT END UNDERNEATH PAINT AND SEALANT HAS 4 AREAS OF SUSPECTED CORROSION. MECHANICALLY BLENDED LEVEL 1 CORROSION ALONG OUTBD SIDE RH UPPER WING TO FUSELAGE MIDDLE DRAG ANGLE, AFT END, ON WING SKIN P/N 6922680-24, W.S. 37.00. FOUND CORROSION BLENDED AREAS TO BE BEYOND LIMITS IAW SRM 51-70-02. SUBMITTED FINDINGS TO CESSNA ENGINEERING. REPAIRED CORROSION BLENDS ON RH UPPER WING TO FUSELAGE MIDDLE DRAG ANGLE, AFT END, ON WING SKIN P/N 6922680-24, W.S. 37.00 IAW ENGINEERING STRUCTURES REPORT S-680-0088/11RD,
RIGHT WING LOWER FLAP ACCESS PANEL 623AB HAS 1 AREA OF CORROSION. MECHANICALLY REMOVED AREAS OF CORROSION LOCATED ON RIGHT WING LOWER FLAP ACCESS PANEL 623AB P/N 6922693-14 IAW C680 SRM 51-70-02. CORROSION DEFINED AS LEVEL 1 PER C680 MM 51-10-01 TABLE 2 DEFINITIONS AND IS BEYOND BLENDING LIMITS PER C680 SRM 51-70-02. SUBMITTED FINDINGS TO CESSNA ENGINEERING. PERFORMED CORROSION BLEND REPAIRS PER CESSNA/TEXTRON AVIATION MEMO REF: 10510M1 DATED DECEMBER 13,2017.
AIRCRAFT DATA TAG ON LOWER TAIL HAS APPROX 6 AREAS OF CORROSION AROUND PERIMETER OF AIRCRAFT DATA TAG. REMOVED AIRCRAFT DATA TAG LOCATED ON LOWER TAIL. MECHANICALLY REMOVED AREAS OF CORROSION LOCATED UNDERNEATH AIRCRAFT DATA TAG ON SKINS P/N 692029-1 AND 6912030-1 IAW C680 SRM 51-70-02. CORROSION DEFINED AS LEVEL 1 PER C680 MM 51-10-01 TABLE 2 DEFINITIONS AND IS BEYOND BLENDING LIMITS OF .002 PER C680 SRM 51-70-02. SUBMITTED FINDINGS TO CESSNA ENGINEERING. PERFORMED CORROSION BLEND REPAIRS PER CESSNA/TEXTRON AVIATION MEMO REF: 10509M1 DATED DECEMBER 13,2017. REINSTALLED AIRCRAFT DATA TAG WITH 870 SEALANT INCLUDING INSTALLING FASTENERS IN WET WITH 870 SEALANT.
UPON STARTING APU ON GROUND WITH BLEED ON, COCKPIT IMMEDIATELY FILLED WITH SMOKE. RAN APU FOR APPROX 30 MINS, NO SMOKE NOTED IN CABIN, BUT AN OIL ODOR WAS PRESENT. CHECKED OIL SERVICING, NO OIL NEEDED. BORESCOPED APU INLET. REMOVED & INSPECTED WATER SEPARATOR SOCK, NO DEFECTS NOTED. CLEANED & REINSTALLED WATER SEPARATOR. REMOVED APU IAW MM. INSTALLED APU, VERIFIED OIL & FUEL FILTERS ARE INSTALLED. SERVICED WITH 2380. RAN APU, OPERATIONS & LEAK CHECKED GOOD. PERFORMED DUCT BURN IN PROCEDURE. PRESSURIZED ACFT TO MAX DIFF, LEAK CHECKED GOOD OF WATER SEPARATOR. SERVICED OIL AS REQUIRED IAW MM 49-10-00.
RIGHT MLG POSITION INDICATOR, BOTH BULBS INOPERATIVE ON GEAR DOWN SELECTION. FOLLOWED THE CHECKLIST, PULLED MANUAL GEAR RELEASES, PULLED GEAR BLOW DOWN, CHECKED ROTARY TEST, NO GEAR HORN AT FLAP 35, SAFE LANDING. COMPLIED WITH MLG BLOW DOWN BOTTLE RESET & GEAR SWING. R & R UPPER RT MLG INDICATOR LAMP. OPS CHECKED SATISFACTORY IAW MM 32-60-00.
TEMP CONTROL WAS IN AUTO, SELECTED TO CABIN & 72 DEGREES. CABIN WENT VERY HOT QUICKLY & SMELLED LIKE BURNING PLASTIC. DUCT OVERTEMP CABIN AMBER CAS MESSAGE POSTED. RAN THROUGH ABNORMAL CHECKLIST & SAME RESULTS IN MANUAL MODE, COCKPIT & CABIN CONTROL & TURNING OFF BLEED AIR IN BETWEEN. SUPPLY TEMP MAXED AT 310 DEGREES & THEN WENT TO DASHES. E7 & E8 ERROR CODES SHOWED ON TEMP PANEL. EVENT MARKER BUTTON PUSHED. R & R TEMP CONTROLLER ASSEMBLY. OPS CHECKED GOOD IAW AMM 21-22-05.
AFTER LOWERING GEAR, HYDRAULIC VOLUME LOW CAS MESSAGE APPEARED, FOLLOWED BY THE HYDRAULIC PRESSURE LOW LT & RT CAS MESSAGE. COMPLETED THE HYDRAULIC VOLUME LOW EMERGENCY CHECKLIST. EMERGENCY BRAKING WORKED AS EXPECTED. INSPECTION REVEALED PRESSURE PART ON NOSE STEERING UNIT CAME LOOSE. REPLACED SWIVEL AND HOSE IAW MM 32-50-00. ACCOMPLISHED HYDRAULIC SYSTEM BLEED IAW MM 12-12-02, LEAK CHECK, CLEARANCE CHECK, AND OPS CHECKS GOOD. SERVICED BRAKE BOTTLE IAW MM 12-13-01. ACCOMPLISHED BRAKE BLEED PROCEDURE IAW MM 32-42-10.
CLIMBING THROUGH FL 300, THE OUTER PANE OF THE PILOTS SIDE WINDOW SHATTERED. RAN ABNORMAL CHECKLIST & RETURNED TO DEPARTURE. R & R THE PILOT'S SIDE WINDOW IAW MM 56-12-00. OPS & LEAK CHECKED GOOD.
DURING AN INSPECTION, FOUND THE OUTER DOOR FRAME CRACKED UNDER THE TELECOPING ROD ATTACH POINT ON THE AFT OUTER CABIN DOOR FRAME. VERFIED CRACK WITH EDDY CURRENT INSPECTION. REPLACED CABIN DOOR FRAME.
NLG ACTUATOR BOLT IS BROKEN OFF AT AFT END PF ACTUATOR. ELASTOMER IS DAMAGED AND SKIN IS BENT. REMOVED NLG ACTUATOR FAIRING PANEL, FOUND IMPACT DAMAGE TO FAIRING PANEL. DURING FURTHER INSPECTION FOUND THE NOSE FAIRING PANEL ZEE ANGLE DAMAGED. FOUND IMPACT DAMAGE TO THE AFT END OF THE NLG ACTUATOR. FOUND THE REMAINING AFT ACTUATOR PIN AND LT ELASTOCER PARTIALLY INSTALLED IN THE ATTACH FITTING DUE TO PIN SHEARING. REMOVED SHEARED PIN AND CLASTOMERS BEARING FROM THE AFT FITTING. REMOVED COCKPIT SEATS/CENTER PEDEATER COMPONENTS. REMOVED STRINGER IAW SRM 51-40-03. FITTED AND DRILLED OUT NEW CASTING IAW DWG 6711060. INSTALLED NEW CASTING & STRINGER IAW REPAIR DEFINITION 5-680-008806RD. FINISHED FITTING OF NEW NOSE GEAR ACTUATOR CLOSE OUT PANEL. CABLE TENSION & TRAVEL CHECKED. INSTALLED NLG TRUNNION ASSEMBLY. INSTALLED NOSE GEAR ACTUATOR INTO NOSE GEAR ACTUATOR FITTING WITH NEW ELASTOMCRIC BUSHINGS/PIN/SPACE/ NUTS, AND NEW BELT/NUT ONTO TRUNNION SIDE. ADJUSTED CASTER OF NOSE STRUT IAW MM 32-30-30. REINSTALLED PEDISTAL WIRING AND AVIONICAS EQUIPMENT. TRAVEL CHECK & CABLE TENSION CHECK DONE IAW 27-30-00.
RT WHEEL WELL AFT SPAR HAS CORROSION ON OTBD AND INBD SIDE OF LOWER SIDE OF AFT SPAR.
AFTER TAKEOFF, NOSE GEAR DID NOT RETRACT. GEAR HANDLE DID MOVE TO THE UP POSITION. RED "UNLOCK" AND GREEN "NO" WERE ILLUMINATED.
BOTH RIGHT MAIN GEAR INDICATOR LIGHT BULBS ARE INOP. NEITHER LIGHT UP WITH ROTARY TEST. WE DID NOT USE EMER GEAR EXTENSION. QRH FOLLOWED, LANDED UNEVENTFULLY. REMOVED SOCKET, FOUND IT NOT SEATED PROPERLY. INSTALLED NEW BULBS. RESEATED SOCKET AND OPS CHECKED. OPS CHECKED GOOD. WORK DONE IAW MM 33-10-00.
FOUL ODOR INTERMITTENTLY COMING FROM OPERATION OF THE BLEED AIR AND AIR CONDITIINING. BORESCOPED COMPRESSOR OF APU AND FOUND OIL POOLED IN LOWER PART 6 O'CLOCK POSITION. R & R APU.
ON DEPARTURE NOSE GEAR WAS VERY SLOW TO RETRACT . RED UNSAFE + GN NOSE LIGHT WERE ILLUMINATED. AFTER A SHORT TIME NOSE FULLY RETRACTED. ATIS REPORTED WINDS AT 280 AT 29, GUSTING TO 37. JACKED ACFT. C/W SLOW CYCLE TEST. NO DEFECTS NOTED. C/W TIMED CYCLE TEST. GEAR EXTENDS AND RETRACTS IN TIME LIMITS MM CHAPT. 32-00-00 R13. NO DEFECTS NOTED. DURING RETRACTION CHECKS IT WAS NOTED THAT WITH MILD HAND PRESSURE THE NOSE WHEELS CAN BE RESTRAINED FROM CENTERING. CONTACTED CUSTOMER SUPPORT IAW MIDARM CENTERING TORQUE SHOULD BE 500 IN LBS. ORDERED STEERING UNIT. OHMED OUT NLG DOWNLOCK SWITCH AND GNDS OHM CHECK GOOD. DISCONNECTED CONTROL CABLES FROM NOSE WHEEL STEERING POWER UNIT BULLWHEEL. DISCONNECTED HYDR LINES AND ELECTRICAL CONNECTOR ON POWER STEERING UNIT FROM TRUNNION. INSTALLED REPLACEMENT POWER STEERING UNIT ON TOP OF TRUNNION. RECONNECTED CONTROL CABLES TO BULL WHEEL. RECONNECTED HYDR LINES AND ELECTRICAL CONNECTOR. STARTED INSTALLATION OF PULLEY GUIDE PINS. REF MM 32-50-00, REV. 14. COMPLETED NWS UNIT INSTALLATION IAW MM CHAPT. 32-50-00 R12. LEAK AND OPS CHECK GOOD. DOWNJACKED ACFT. TAXI CHECK GOOD.
RUDDER JAMMED AS WE TOOK THE RUNWAY FOR DEPARTURE. ROLL AND PITCH AXIS WERE FREE. ACCOMP RUDDER BIAS, OPS CHECKS IAW AFM 3-175 & OPS MANUAL 2-49, OPS CHECKS GOOD. VERIFIED YAW DAMPER OPS BY ACCOMP AUTOPILOT SERVO DRIVE ADJ/TEST FOR YAW DAMPER ONLY IAW AMM 22-10-02.
ON TAKEOFF ROLL, NO TAKEOFF LIGHT ILLUMINATED. CHECKED THE NO TAKEOFF CONFIGURATIONS PAGE AND THE ROLL SYSTEM WAS DISPLAYED. ILLUMINATED 2 SECONDS AFTER THROTTLE IN T/O DETENT. ROLL SYSTEM CONTROL FAULT CAS DID NOT DISPLAY. CHECKED FOR AIRCRAFT HISTORY AND INTERROGATED CALL FOR FAULTS BUT FOUND NONE, SUGGESTED TO TAKE ACFT TO T/O POWER TO DUPLICATE. NO FAULTS FOUND. ALSO CHECK ALIGNMENT OF THE RACE SPOILER IL WITH BOX, FOUND ALIGNED, NO DEFECTS NOTED. INFORMED MCC CUSTOMER WAS NORMAL AT THIS TIME. ALL WORK ACCOMPLISHED IAW MM 22-12-00 AND 45-40-00.
BIRD STRIKE ON T/O: FRONT LEFT WINDSHIELD AND ABOVE.
DIRTY SOCK ODOR COMING FROM AIR VENTS. (S)
DIRTY SOCK ODOR COMING FROM AIR VENTS. CLEANED WATER SEPARATOR COALESER SOCK IAW MM 21-21-00. OPS CHECK GOOD LEAK CHECK GOOD.
A "FLAPS FAIL" CAS MESSAGE ON FLAP RETRACTION, FLAPS WILL NOT EXTEND. T/S FLAP CONTROL SYS. FOUND A BITE CODE 7 ON THE FLAP CONTROLLER, MEANING AN INTERNAL FAILURE OF THE UNIT. REMOVED AND REPLACED FLAP CONTROLLER. RESET FLAP SYS. FUNCTION CK OF FLAP CONTROLLER AND OPS CK OF FLAPS GOOD AT THIS TIME REF MM 27-51-00
ON TAKEOFF ROLL, THE RIGHT ENGINE N1 WAS 1/2 PERCENT BELOW TARGET, ABORTED TAKEOFF. ITEM IS UNDER INVESTIGATION.
LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF, HYDRAULIC PRESSURE LIGHT DID NOT ILLUMINATE. GEAR INDICATION WAS 3 GREEN AND NO RED. REMOVED AND REPLACED SUSPECTED FAULTY LANDING GEAR CENTER BYPASS VALVE AND PRESSURE RELIEF VALVE. PERFORMED LANDING GEAR RETRACTION AND EXTENSION, SYSTEM CHECKED GOOD. ALL WORK PERFORMED IAW CESSNA560 MM CHAPTER 29-11-06 AND 32-30-00.
DURING APPROACH AT IAH, LT MAIN LANDING GEAR DID NOT INDICATE DOWN AND LOCKED. PERFORMED ABNORMAL CHECK LIST AND BLEW GEAR DOWN, STILL DID NOT HAVE INDICATION. AIRCRAFT LANDED SAFELY AT IAH.
LEFT MLG INDICATOR LIGHT DID NOT ILLUMINATE ON GEAR EXTENSION ON FINAL TO IAH. PERFORMED EMERGENCY CHECKLIST AND BLEW GEAR DOWN.