N307QS
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
STARTING DESCENT OUT OF 24000 GEAR LEVER IN UP POSITION GEAR UNLOCK LIGHT ILLUMINATED. LANDING GEAR EXTENDED AS NORMAL BEFORE LANDING AND UNLOCK LIGHT EXTINGUISHED. REPEAT WRITEUP. FOUND LEFT UPLOCK SWITCH HAS HIGH RESISTANCE THROUGH UP CONTACTS REF WDM 32-30-01-02, REINSTALLED CLAMPS AS NEEDED. VERIFIED PROPER NLG STRUT SERVICING FOUND 279 PSI IN THE UPPER AND 41PSI IN THE LOWER, AND FOUND 9.75 IN OF STRUT EXTENSION, IAW CE680 AMM 12-20-32. PERFORMED NOSE LANDING GEAR (NLG) CASTER CHECK PER AMM 32-30-30 NO DEFECTS NOTED. - REMOVED AND REPLACED LEFT MAIN GEAR UPLOCK SWITCH IAW CE680 AMM 32-60-00, COMPLETED RIGGING CHECK AND SAFETIED AS REQUIRED. OPS CHECK GOOD.
TABLE LIGHT BETWEEN SEAT 3 AND 5 DOES NOT ILLUMINATE ON EMERGENCY LIGHT TEST WITH SWITCH IN THE ARM OR ON POSITION ON EMERGENCY BATTERY POWER. CORRECTIVE ACTION: REMOVED AND REPLACED #2 EMERGENCY BATTERY IAW CE680A MM 33-50-10. LIGHTS OPS CHECKS GOOD.
THE SEAT LIGHT ABOVE SEAT 9 DOES NOT ILLUMINATE DURING THE EMERGENCY LIGHT TEST IN EITHER THE ARMED OR ON SWITCH POSITION AND POWERED BY EMERGENCY BATTERY POWER. CORRECTIVE ACTION: REMOVED AND REPLACED #2 EMERGENCY BATTERY IAW CE680A MM 33-50-10. LIGHTS OPS CHECKS GOOD
DURING FIRST FLIGHT PREFLIGHT, THE EMERGENCY LIGHTS WOULD NOT ILLUMINATE PROPERLY. THE MAIN CABIN DOOR LIGHTS FAILED. THE OVER GALLEY LIGHT FAILED. THE LIGHT IN THE FIRST SET OF CLUB SEATS FAILED AND ALL THE FLOOR LEVEL EMERGENCY LIGHTING FAILED. REPEAT WRITE UP. REPLACED NR 1 EMERGENCY LIGHTING BATTERY PACK WITH A NEW ONE AND CLOSED ACCESS. OPS CHECKS GOOD. FOUND LIGHTS FOR NR 3 BATTERY PACK FAILED OPS CHECK. REPLACED NR 3 EMERGENCY LIGHTING BATTERY PACK WITH A NEW ONE. OPS CHECKS GOOD. CHARGED BATTERY IAW MM 33-50-10.
DURING FIRST FLIGHT PREFLIGHT, THE EMERGENCY LIGHTS WOULD NOT ILLUMINATE PROPERLY. THE MAIN CABIN DOOR LIGHTS FAILED. THE OVER GALLEY LIGHT FAILED. THE LIGHT IN THE FIRST SET OF CLUB SEATS FAILED AND ALL THE FLOOR LEVEL EMERGENCY LIGHTING FAILED. PERFORMED TASK CARD, TC-FLT-33-1001, EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE. ALL BATTERIES FOUND AIRWORTHY PER CMM 33-50-03. MCC FOUND NO RECENT HISTORY REQUESTS NO FURTHER ACTION.
THE RED PUSH BUTTON ON THE MAIN CABIN DOOR WORKS INTERMITTENTLY. SOMETIMES IT WILL NOT PRESS IN UNLESS YOU PULL DOWN ON THE MAIN CABIN DOOR HANDLE. IT FEELS LIKE IT IS CATCHING ON SOMETHING AND THERE IS AN AUDIBLE CABLE NOISE THAT IS NOT USUALLY NOTICEABLE. CORRECTIVE ACTION: CLEANED DEBRIS OUT OF LATCH HANDLE INTERNALS AND RELEASE PIN, PLUNGER ASSEMBLY BEFORE LUBING. CHECKED ALL SPRINGS, PUSHRODS, BELL CRANKS, IDLER TUBE AND LATCH TUBES WITH NO DEFECTS NOTED. PERFORMED OPERATIONAL CHECKS OF THE CABIN DOOR, OPS CHECK GOOD. WORK IN REF. 680 AM M 52-10-40.
FOUND CORROSION ON RH AFT SPAR NEAR WS 37.00 ATTACHMENT BRACKET. MECHANICALLY BLENDED 15 AREAS OF CORROSION ON RH WING AFT SPAR. IAW CESSNA 680 SRM 51-70-02 AND SRM 51-10-01. FOUND BLENDED AREAS TO BE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02. DETERMINED CORROSION TO BE LEVEL 1 PER NETJETS GMM 2.1.2 AND MILD TO MODERATE PER CESSNA 680 SRM 51-10-01. COMPLIED WITH NETJETS RFTS-113687 REV.0 TITLE: N307QS (680-0130) RH WING AFT SPAR CORROSION DATE: 08 MAY 2025.
FOUND 1 SMALL AREA OF CORROSION ON LH WING OUTBD FLAP, INBD FLAP ATTACH FITTING AND 2 SMALL AREAS OF CORROSION ON LH WING MIDDLE FLAP, INBD FLAP ATTACH FITTING. MECHANICALLY BLENDED 1 AREA ON LH WING OUTBD FLAP, INBD FLAP ATTACH HINGE FITTING/BRACKET AND 2 AREAS ON LH WING MIDDLE FLAP, INBD FLAP ATTACH FITTING/BRACKET. FOUND TO BE LIGHT SURFACE CORROSION, MINIMAL MATERIAL LOSS WHICH IS WITHIN C680 SRM 51-70-02 LIMITATIONS NOT EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. ALODINED, PRIMED AND APPLIED TOPCOAT TO BLENDED AREAS IAW C680 SRM 51-20-01. PER GMM 2.1.2.
FOUND 3 AREAS OF CORROSION ON LH AFT WING SPAR, FWD FACE AND 1 AREA ON AFT SPAR LOWER CLIP. MECHANICALLY REMOVED 3 AREAS OF CORROSION LOCATED INSIDE LH MLG WHEEL WELL INBD OF BAY 730DL, AFT SPAR WEB AND 1 AREA ON LOWER SPAR CLIP INSIDE BAY 730DL AND 1 ADDITIONAL AREA LOCATED ON UPPER SPAR WEB ALSO INSIDE BAY 730DL. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS AQRD ENGINEERING RFTS-113683 REV.0 , TITLE: N307QS (680-0130) LH WING AFT SPAR CORROSION, DATE: 18APR25. THIS IS A MINOR/PERMANENT REPAIR.
LH AND RH FWD FUSELAGE CHIN FAIRINGS HAVE CORROSION EXTENDING FROM THEM. MECHANICALLY BLENDED 6 AREAS OF CORROSION ON LH AND RH CHIN FAIRING FUSELAGE SKIN. IAW CESSNA 680 SRM 51-70-02 AND SRM 51-10-01. FOUND BLENDED AREAS TO BE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02. DETERMINED CORROSION TO BE LEVEL 1 PER NETJETS GMM 2.1.2 AND MILD TO MODERATE PER CESSNA 680 SRM 51-10-01. COMPLIED WITH NETJETS RFTS-113714 REV.0 TITLE: N307QS (680-0130) FORWARD CHIN FAIRING FUSELAGE SKIN CORROSION DATE: 23APR2025. THIS IS CONSIDERED A MINOR REPAIR.
FOUND 1 AREA OF CORROSION AROUND MED FWD SHEAR TIE. MECHANICALLY BLENDED 1 AREA OF CORROSION AROUND MED FWD SHEAR TIE IAW CESSNA 680 SRM 51-70-02 AND SRM 51-10-01. AFTER NDT TESTING, DETERMINED BLENDED AREA TO BE WITHIN ALLOWABLE DAMAGE AT THIS TIME PER CESSNA 680 SRM 51-70-02. RESTORED EXTERIOR PAINT SCHEME IAW CESSNA 680 SPM 20-50-00.
RUDDER BIAS: AS POWER WAS APPLIED DURING TAKEOFF, A NO TAKE OFF AURAL WARNING WAS SOUNDED. ON THE NO TAKE OFF PAGE, A RUDDER BIAS WITH ASTRIX WAS PRESENT. A LOW SPEED ABORT WAS COMPLETED. GROUND SPEED DID NOT EXCEED 30 KNOTS. ATTEMPTS TO CLEAR THE MESSAGE FAILED. CORRECTIVE ACTION; REMOVED SUSPECTED DEFECTIVE RUDDER VARIABLE BIAS ACTUATOR. INSTALLED OVERHAULED UNIT. PERFORMED OPERATIONAL CHECKS TO FIND NO DEFECTS AT THIS TIME. REF: CE-680 AMM 27-20-10.
AFTER CLOSING MAIN CABIN DOOR WHILE RESTOCKING. WHEN TRYING TO OPEN MAIN CABIN DOOR TO GO OUTSIDE, RED PUSH BUTTON ON HANDLE WOULDN`T DEPRESS. TRIED MULTIPLE TIMES & FINALLY USED THE AUXILIARY LOCK BUTTON RELEASE TO UNLOCK HANDLE FOR MOVEMENT. CLOSED DOOR AGAIN RETRIED OPENING SAME RESULT. WHILE INSPECTING THE MED NOTICED THAT THE INTERIOR HANDLE HAD EXCESSIVE PLAY. WHEN APPLIING PRESSURE WHILE ENGAGING RED PUSH BUTTON, BUTTON WOULDNT PUSH IN. INSPECTED INNER LATCHING/LOCKING HANDLE, FOUND BOLT ATTACHING INNER LATCHING/LOCKING HANDLE TO TORQUE TUBE WAS LOOSE. REMOVED, CLEANED & REINSTALLED BOLT W/ATTACHING HARDWARE. IAW AMM 52-10-40, & SPM 20-10-45, & 20-10-65. OPS CHECK GOOD. NO DEFECTS NOTED.
LEFT ENGINE ENGINE OVERTEMP: LEFT ENGINE TEMP CLIMBED TO 930 ON TAKEOFF IN THE T/O DETENT. REDUCED POWER TO MCT DETENT AND THE TEMP REDUCED SLIGHTLY BUT WAS STILL ABOVE 920. TOTAL TIME OVER 920 WAS ABOUT 1 MINUTE. REMOVED LEFT ENGINE DUE TO ITT EXCEEDANCE. INSTALLED AN INSPECTED ENGINE IN LEFT POSITION OF AIRCRAFT. ACCOMPLISHED ENGINE FUEL SYSTEM DEPRESERVATION. COMPLIED WITH ENGINE GROUND RUNS, LEAK AND OPERATIONAL CHECKS INCLUDING CHECKS1 THROUGH 8 OF THE EMM TABLE 501, 71-00-00. NO DISREPANCIES NOTED. ALL PARAMETERS WITHIN LIMITS. IAW AMM71-00-10, 71-00-20, 71-00-30 AND EMM 71-00-00. ORIGINAL SUBMISSION DATE; 6/26/2023
MAIN DOOR LOCK: DURING THE ROTARY TEST OVERSPEED DETENT, THE DOOR LOCK SOLENOID DID NOT MAKE A CLICK. WE CLOSED THE MAIN CABIN DOOR AND TRIED THE OVERSPEED TEST AGAIN. THE DOOR HANDLE REMAINED UNLOCKED. // SIGNOFF// ACCESSED WIRE HARNESS BETWEEN DOOR AND FUSELAGE AND WHILE PERFORMING THE ROTARY TEST, GENTLY MANIPULATED HARNESS AND VERIFIED LOCKING SOLENOID DID NOT ENGAGE OR DISENGAGE. REMOVED MED STEP ASSEMBLY FROM MED REF CE680 MM 52-10-20, NOTING MULTIPLE SCREWS WERE CORRODED IN PLACE AND REQUIRED EXTRA TIME FOR EXTRACTION. FOUND BOTH WIRES GOING TO MED LATCH SOLENOID WERE BROKEN. VERIFIED WIRES WERE BROKEN TO SHORT FOR REPAIR. REMOVED FAULTY LATCH SOLENOID P/N 70R10461-2 S/N 0160 AND INSTALLED CUSTOMER SUPPLIED NEW SOLENOID P/N 70R10461-2 S/N 1056 REF CE680 IPC 52-70-00. POWERED UP AIRCRAFT ON GPU POWER. VERIFIED AFTER INITIAL POWER UP THAT THE CABIN DOOR OPEN CAS MSG POSTED. CLOSED MED AND LATCHED HANDLE, NOTING DOOR OPEN CAS MSG EXTINGUISHED. PERFORMED OVERSPEED ROTARY TEST REF CE680 AFM, NOTING MED LATCH SOLENOID ENGAGED AND DISENGAGED AS COMMANDED. PERFORMED TEST MULTIPLE TIMES WITH SAME RESULTS. NO FAULTS OR DEFECTS NOTED. POWERED DOWN AIRCRAFT AS REQUIRED. INSTALLED MED STEP ASSY AND RELATED PANELS REF CE680 MM 52-10-20
MAIN DOOR PRIMARY SEAL: DOOR SEAL INFLATED ON GROUND WITH ONLY APU RUNNING (MED WOULD NOT CLOSE)//CORRECTIVE ACTION// REMOVED AND REPLACED ACOUSTIC SEAL INFLATION VALVE LEAKS AND OPS CHECK GOOD REF 680 MM SECTION 36-10-10. PN OFF 5303-2A SN 3026 PN ON 5303-2A SN 5249A
BAGGAGE FIRE RED CAS: BAGGAGE FIRE RED CAS IN CLIMB THROUGH 40,000FEET. COMPLIED WITH QRH AND ACTIVATED BOTH BAGGAGE FIRE BUTTON AND SEC BAG BOTTLE BUTTON. ASSOCIATED CYAN FIRE BOTTLE LOW BAG-APU MSG DISPLAYED THEREAFTER. FIRE DEPARTMENT DID NOT LOCATE ANY FIRE UPON INSPECTION. EMERGENCY DECLARED.//CORRECTIVE ACTION// REMOVED DEFECTIVE FWD SMOKE DETECTOR PN 473597-17 S/N SEA2570 INSTALLED NEW SMOKE DETECTOR PN 473597-17 S/N SEA1111 IAW 680 AMM 26-10-40 OPS CHECK GOOD REMOVED DEFECTIVE AFT SMOKE DETECTOR PN 473597-17 S/N 2571 INSTALLED NEW SMOKE DETECTOR PN 473597-17 S/N SEA0605 IAW 680 AMM 26-10-40 OPS CHECK GOOD REMOVED SPENT APU FIRE BOTTLE PN 33100028-2 SN 5628281 INSTALLED OVERHAULED APU FIRE BOTTLE PN 33100028-2 SN 58246B1 IAW CE-680 AMM 26-20-30 OPS CHECK GOOD. REMOVED SPENT BAGGAGE FIRE BOTTLE PN 9914712-6 SN 10225H1 INSTALLED SERVICABLE FIRE BOTTLE PN 33100028-2 SN 11301H1 IAW CE-680 AMM 26-20-30 OPS CHECK GOOD.
LEFT ENGINE ENGINE OVERTEMP: ON TAKEOFF LEFT ENGINE ITT WENT YELLOW 920 DEGREES AND STAYED THERE UNTIL POWER WAS REDUCED. LEFT ENGINE ITT RAN APPROXIMETLY 40 DEGREES HIGHER THEN RIGHT ENGINE AFTER THAT.//CORRECTIVE ACTION// REMOVED LH ENGINE PRECOOLER PRSOV AND CLAMPS AND INSTALLED NEW CUSTOMER SUPPLIED UNITS, OPS AND LEAK CHECK GOOD WITH NO DEFECTS NOTED, REF CE680 MM 36-10-00,
MAIN DOOR HANDLE: HAVE TO USE A EXCESSIVE FORCE TO LOCK THE HANDLE IN THE DOWN POSITION.///SIGN-OFF///ADJUSTED MCD IAW CE 680AMM 52-10-30. OPS CHECK GOOD.
REPAIRED CORRODED AFT LOWER TAILCONE SKINS LOCATED ADJACENT AND UNDER THE AFT FUSELAGE-TO-WING CHIN FAIRING BY: R & R AFT CHIN FAIRINGS, BLENDING CORRODED AREAS, PERFORMING NDT, TREATING BLENDED AREAS, AND FABRICATING AND INSTALLING REPAIR DOUBLERS AND SHIMS, AS REQUIRED PER TEXTRON FIELD REPAIR.
BENDED CORRODED AREA AT FS 548.5 RIB WEB LOCATED AT BONDING STRAP ATTACHMENT, PERFORMED NDT AND REPORTED RESULTS FOR REPAIR DISPOSITION. CLEANED, TREATED, PRIMED AND APPLIED CIC TO REPAIR AREA, IAW TEXTRON REPAIR MEMO.
VERY STRONG UNIDENTIFIABLE CHEMICAL ODER/FUME STARTED MOMENTS AFTER REDUCING POWER DURING DECENT FROM 20000FT. WE PUT ON OUR O2 MASKS AND ODER STILL REMAINED AFTER SHUTDOWN WHEN WE REMOVED OUR MASKS. ANTI ICE WAS NOT USED. APU WAS OFF. SIGNOFF RAN NR 1 ENGINE AND OPERATED CABIN TEMP FROM HOT TO COLD SERVERAL TIME. UNABLE TO DUPLICATED ISSUE. RAN NR 2 ENGINE AND OPERATED CABIN TEMP FROM HOT TO COLD SERVERAL TIMES UNABLE TO DUPLICATE ISSUES. RAN NR 2 AND NR 1 AT THE SAME TIMES AND OPERATED CABIN TEMP FROM HOT TO COLD SERVERAL TIMES UNABLE TO DUPLICATE ISSUE CW TC 680-21-120905M ENVIROMENTAL CONTROL SYSTEM (ECS) DUCT BURN OUT TO ENSURE THE ENVIROMENTAL DUCTS AND COALESER AND FREE OF OIL CONTAMINATION IAW AMM 21-51-00 REPLACED COALESER BAG.
FMS 2 BLACKED OUT AND WOULD NOT RETURN, FOLLOWED BY A STRONG ELECTRICAL ODOR IN COCKPIT, FOLLOWED BY RIGHT MCDU CIRCUIT BREAKER POPPING. RAN ENVIRONMENTAL SYSTEM ODOR CHECKLIST, WITH PRESS SOURCE SELECTOR ON L, ODOR DISSIPATED. TS AND FOUND RIGHT MCDU IS CAUSING BREAKER TO OPEN SWAPPED MCDU'S AND ISSUE FOLLOWED TO LEFT SIDE. VISUALLY INSPECTED LEFT AND RIGHT CR PANEL, MCDU'S PFD, AND MFD'S CONNECTIONS AND WIRING NO DEFECTS FOUND, ALL WORK DONE PER AMM 24-60-20, 23-80-00 AND 34-23-00 REPLACED RIGHT MCDU WITH REPAIRED UNIT AND PERFORMED SATISFACTORY OPS CHECK. WORK DONE PER AMM 23-80-00.
FOUND SEVERELY CORRODED FWD WEDGE PANEL OF THE RUDDER FAIRING ASSEMBLY. REPLACED PART WITH NEW P/N 6912670-5 PER SRM 51-20-01, 51-40-03, 51-40-04 AND SPM 20-40-20.
FOUND CORRODED WING SKIN UNDER THE OVERWING FUEL FILLER CAP ADAPTER ASSEMBLY. BLENDED THE CORRODED AREAS, PERFOMED ULTRASONIC THICKNESS AND EDDY CURRENT CRACK INSPECTION. TREATED AND PRIMED BLENDED AREAS.
RIGHT ELEVATOR HAS MULTIPLE AREAS OF CORROSION AROUND MID AND INBD STATIC WICK BASES. REMOVED THE CORROSIONR IAW SRM 51-70-02. CORROSION IS BEYOND ALLOWABLE LIMITS AND THE ELEVATOR MUST BE REPAIRED.
ALL RIGHT SIDE COLD MESSAGES ILLUMINATED. CHECKLIST ACCOMPLISHED. MESSAGES EXTINGUISHED AFTER CROSS FLOW SELECTED. LATER, ENGINE CONTROL FAULT LT AND WINDSHIELD HEAT INOPERATIVE ILLUMINATED SIMULTANEOUSLY. BOTH CHECKLISTS WERE ACCOMPLISHED. WARNINGS STAYED ON. SHORTLY AFTER, FUEL BOOST PUMP ON ILLUMINATED. CHECKLIST ACCOMPLISHED. SHORTLY BEFORE TURNING ONTO ILS FINAL THERE WAS AN AURAL AND PHYSICAL THUMP. LT ENGINE QUIT. SINGLE ENGINE APPROACH AND LANDING ACCOMPLISHED UNEVENTFULLY. TROUBLESHOOTING REVEALED THE LT ENGINE HP BLEED AIR COUPLING FAILED, ALLOWING HP BLEED AIR TO ESCAPE INTO ENGINE COWLING COMPARTMENT. FOUND THE LT ENGINE EEC ENDURED AN OVERTEMP RESULTING IN ENGINE SHUTDOWN. INSPECTED ENGINE IAW 2K FAULT ISOLATION. LT ENGINE UPPER COWLING DAMAGE NOTED AND DOCUMENTED. ACCOMPLISHED REPLACEMENT OF THE LT ENGINE EEC AND HP BLEED AIR COUPLING. OPS, LEAK AND POWER ASSURANCE CHECKED SATISFACTORY. COMPLETED REPLACEMENT OF RT ENG INBD PRSOV DUE TO ALL RT ANTI-ICE COLD CAS MESSAGE. ANTI ICE OPS & LEAK CHECKS GOOD. IAW AMM 36-10-00, EMM 72-00-00 & 73-20-02. ACCOMPLISHED A GENERAL VISUAL CHECK OF THE AIRCRAFT:. PERFORMED A DETAILED INSPECTION OF THE AIRCRAFT LANDING GEAR, PAYING PARTICULAR ATTENTION TO MAIN WHEEL WELL, DOORS, AND ACTUATORS, UPLOCK, SURROUNDING AREAS, LINES AND HARNESSES. ADDITIONALLY, CHECKED ALL FLIGHT CONTROLS FOR PROPER OPERATION AND SERVICING OF ALL GAS AND FLUIDS AS REQUIRED. AIRCRAFT: INSPECTED AND FOUND SAFE FOR INTENDED FLIGHT. INSPECTED COWLING PER ERO·917285. COMPLIED WITH AQRD ERO-917285 EVALUATION OF LEFT ENGINE TOP COWLING.
APU TRUSS MOUNT (FLANGE) CORRODED.
AFT LT AND RT BULKHEAD SPAR FITTING CORRODED.
RUDDER TORQUE TUBE BRACKET CORRODED.
VERTICAL STABILIZER SPAR CAP AND VERTICAL STABILIZER SKIN CORROSION.
RUDDER LOCKED UP IN FLIGHT. AT LANDING STAGE AFTER 5 HR FLIGHT AUTOPILOT YAW DAMP OFF, REALIZED RUDDER COMPLETELY LOCKED UP. COULD NOT MOVE AT ALL. UPON MAIN GEAR TOUCHDOWN RUDDER RELEASED & OPERATED NORMALLY THROUGH ROLLOUT & TAXI IN. MOVES FREELY ON GND. ACCOMPLISHED VERIFYING OPERATION OF THE RUDDER GUST LOCK. NO DEFECTS FOUND. OPS CHECK GOOD. RAN THE AIRCRAFT TO VERIFY OPERATION OF THE RUDDER BIAS SYSTEM. FOUND THE RUDDER MOVEMENT STIF IN NORMAL (SYSTEM ON) AND MOVED FREELY IN OVERRIDE. FOUND A LEAK AT THE FORWARD SIDE OF THE RUDDER BIAS ACTUATOR. ACCOMPLISHED REMOVING AND REPLACING THE RUDDER BIAS ACTUATOR IAW CESSNA 680 M/M CH 27-20-10. RAN THE AIRCRAFT OPERATIONAL CHECK GOOD AND LEAK CHECK GOOD.
AFTER TAKEOFF, LANDING GEAR HANDLE WAS SELECTED UP. GEAR REMAINED DOWN WITH THREE GREEN & RED UNLOCKED LIGHT CAME ON. AFTER APPROXIMATELY ONE MINUTE, GEAR CAME UP & ALL THE LIGHTS WENT OUT. JACKED ACFT & CYCLED LANDING GEAR WITH NO FAULTS. CHECKED MLG OLEOS & NOSE STRUT NITROGEN PRESSURE & FOUND THE NOSE STRUT PRESSURE LOW AT 265 PSI. SERVICED NOSE STRUT TO CORRECT PRESSURE. CYCLED LANGING GEAR SYS, OPS CHECKED GOOD IAW MM 32-00-00.
AFTER TAKEOFF AND AT GEAR RETRACTION, HYD FLUID LET LOOSE IN NOSE AREA. GEAR DID NOT RETRACT CORRECTLY AND FELL AGAIN TO DOWN POSITION. UNLOCK AND 3 GREEN LIGHTS ILLUMINATED. HYD VOLUME LOW CAS MESSAGE ILLUMINATED. HYD PRESSURE LOW CAS MESSAGE ILLUMINATED. BOTH OF THOSE QUANTITIES READ "ZERO". "HYD VOLUME LOW" EMERGENCY CHECKLIST WAS COMPLETED. GEAR WAS BLOWN TO DOWN POSITION, EMERGENCY BREAK WAS EMPLOYED. INSPECTED NLG. FOUND NWS CENTERING HYD FLEX LINE RUPTURED. R & R NWS CENTERING HYD FLEX LINE WITH NEW UNIT. FOUND LARGE AMOUNT OF HYD FLUID DRIPPING FROM BELLY OF ACFT. REMOVED PANELS,144AR, 154AC, 154BC, 164AC, 164BC, 166AC, 165AC, 176AC, 175AC, AND 315AL AND CLEANED PANELS AND AREAS UNDER PANELS. REINSTALLED ALL REMOVED PANELS. SERVICED HYD SYSTEM AS REQUIRED. PERFORMED A FULL ACFT HYD SYSTEM BLEED AS REQUIRED. OPS CHECK OF LANDING GEAR AND NWS SYSTEM GOOD AT THIS TIME.
APPROACHING THE RUNWAY AND DESCENDING TO PATTERN ALTITUDE THE GEAR WAS SELECTED DOWN. 2 GREEN LIGHTS ILLUMINATED FOR THE MAINS AND A RED LIGHT WERE DISPLAYED. WE LEVELED OFF AT PATTERN ALTITUDE AND STAYED IN THE TRAFFIC PATTERN. APPROX 15 SECONDS AFTER THE GEAR WAS SELECTED DOWN, 3 GREEN LIGHTS WERE DISPLAYED. CONTINUED AND LANDED NORMALLY. JACKED ACFT PERFORMED MULTIPLE GEAR SWINGS. ALL CHECKED GOOD. INSPECTED DOWNLOCK SWITCH AND WIRING. ALL CHECKED GOOD. CONTACTED AMCC ADVISED US TO REPLACE SWITCH. R & R DOWNLOCK SWITCH IAW THE MM 32-30-30. OPS CHECKED OK.
AFTER TAKEOFF AT GEAR RETRACTION, NOSE GEAR LIGHT REMAINED GREEN AND NOSE GEAR DID NOT RETRACT, UNLOCK RED LIGHT ILLUMINATED MAINS OPERATED NORMALLY. IAW EMERGENCY CHECKLIST, EXTENDED GEAR AND 3 GREEN LIGHTS, NO UNLOCK RED. NOSE WHEEL STEERING UNIT WOULD NOT PASS GEAR UP CENTERING TEST. REMOVED & REPLACED NWS UNIT, RIGGED NWS UNIT, OPERATIONALLY CHECKED GOOD. IAW MM 32-50-00, & LEAK CHECKED GOOD.
AFTER 30 MINUTES ON OXYGEN AT FL410, RT SIDE O2 MASK STOPPED DELIVERING O2 IN ALL MODES. LT SIDE O2 MASK RESULTED IN SAME. GAUGE READ 1600 NR ON PREFLIGHT AND INDICATED 1400 NR AT FAILURE. OUTSIDE GAUGE ALSO READ 1400 NR. PERFORMED OXYGEN CYLINDER/REGULATOR INSP CHECK. OXYGEN REGULATOR IS SAFETY ON AND NO LEAKS FOUND, PERFORMED OXYGEN SYS CHECK IAW MFG OPERATION HANDBOOK (AFM), OPERATION CHECK NORMAL. SERVICED OXYGEN SYS IAW MM (REV 15) 12-16-00 (REV 12).
AT LEVEL OFF AT FL 410, "WINDSHIELD HEAT INOP L" CAS MESSAGE CAME ON. CHECKLIST COMPLETED FOR THAT AND SOON AFTER LT WINDSHIELD CRACKED. PERFORMED TEST OF WINDSHIELD CONTROLLER. OPS CHK GOOD. REMOVED CRACKED WINDOW. INSPECTED CONNECTIONS & WIRING TO WINDOW. NO DEFECTS NOTED. CLEANED & PREPPED WINDOW FRAME. INSTALLED REPLACEMENT WINDOW, PERFORMED. LEAK CHK. LEAK CHK GOOD. OPS CHK GOOD. WORK DONE IAW MM 56-11-00 (REV 14).
AFTER TAKEOFF, GEAR HANDLE WOULD NOT COME OUT OF DETENT TO GO UP AND RAISE THE GEAR.
RE-RIGGED NOSE GEAR SQUAT SWITCH. CYCLED GEAR, OPS CHECK GOOD. WORK DONE IN REF TO MM CH 32-60-00. CHECKED NLG STRUT SERVICING IAW AMCC. SERVICING CHECK GOOD. RESERVICED NG CHARGE IN NOSE STRUT IN REF TO MM CH 32-20-00.
UPON LANDING GEAR RETRACTION, NOSE GEAR MADE LOUD "CLUNKING" NOISE. LT MAIN GEAR LIGHT REMAINED ON. THE RED UNSAFE LIGHT REMAINED ON.
LANDING GEAR RETRACTION, NOSE GEAR MADE LOUD "CLUNKING" NOISE, NOSE GEAR GREEN LIGHT WENT OUT. RT MAIN GEAR LIGHT WENT OUT. LT MAIN GEAR LIGHT REMAINED ON. THE RED UNSAFE LIGHT REMAINED ON WITH THE GEAR HANDLE IN THE UP POSITION. JACKED ACFT AND FOUND NOSE STRUT NOT FULLY EXTENDED WITH WHEELS CLEAR OF GROUND REPACKED NOSE GEAR OLD WITH NEW SEAL KIT PN CPD680-32-3 OPS AND LEAK CHECK GOOD REF CMM 32-20-01.
RUDDER TRIM INOP. CANNOT ADJUST TRIM. REPLACED RUDDER TRIM ROTARY SWITCH IAW WIRING MM 27-20-01 OP'S CHECK GOOD. C/W OVERSPEED CHECK IAW MM 5-50-00 STEP 4 B,C,D AND E NO DEFECTS NOTED IAW AAIP UNSCHEDULED MAINTENANCE CHECK.
UPON GEAR RETRACTION RED (UNLOCK) STAYED ON. CYCLE GEAR DOWN (3) GREEN, LANDING UNEVENTFUL. [07-23-07] PERFORMED FUNCTIONAL TEST OF MASTER WARNING SYSYTEM IAW HAWKER 800XP MM. 31-50-00. FUNCTIONAL CHECKS NORMAL NO DEFECTS NOTED.
BOTH PIC ANS SIC BRAKE PEDALS GO HALF WAY TO THE FLOOR BEFORE THERE IS ANY PRESSURE. PRESSURE CHECKED BRK SYS REACHED 800 PSI. OPS CHECKED SHUTTLE VALVES, OPERATING PROPERLY. OHMS CHECKED WIRING HARNESS AT PN001 AT BRAKE CONTROL BOX AND BOTH WHEEL TRANSDUCERS PASSED CHECKS. SWAPPED BRAKE PACKS. BLED BRAKES, TAXIED AIRCRAFT AND OBSERVED NORMAL BRAKE OPERATION MM 32-42-00.
BRAKES SPONGY ON TAXI AND PULL TO THE RIGHT FROM CO-PILOTS SIDE. PERFORMED ANTI-SKID SYSTEM BLEEDING PROCEDURE 3 TIMES PEDALS ARE FIRM AND EVEN DURING TAXI FROM BOTH PILOTS AND COPILOTS POSITIONS. OPS CHECK GOOD IAW CESSNA 560 M/M 32-42-00.
UPON LANDING PILOT'S BRAKE DID NOT ENGAGE UNTIL PEDALS WERE FULLY DEPRESSED FORWARD. COPILOTS SIDE WAS OK. DURING TAXI PILOTS BRAKE FELT "MUSHY" AND REQUIRED FULL DEFLECTION TO BRAKE. FOUND HYDRAULIC FLUID ON PILOTS FLOORBOARD. VISUAL INSPECTION FOUND PILOTS LEFT MASTER CYLINDER LEAKING LOWER FITTING BASE NUT. REMOVED FITTING AND INSTALLED NAS 16124A O-RING AND NEW BACKUP RING BLED ANTI-SKID BRAKE SYSTEM IN ACCORDANCE WITH CESSNA 560 MM CHAPTER 32-42-00 PARA 4B. SERVICED RESERVOIR AND TAXI CHECKED AIRCRAFT.
PIC'S BRAKES LOST PRESSURE DURING LANDING ROLLOUT. SIC'S BRAKES WORK NORMALLY. PERFORMED BRAKE BLEED PROCEDURE TO BOTH LT & RT BRAKES. BRAKES OPERATE NORMAL AT THIS TIME. ALL WORK DONE IAW CESSNA 560 MM 32-42-00.
UPON LANDING PILOT'S (LEFT SIDE) BRAKES VERY SOFT AND SPONGY. TRAVEL ALMOST TO THE STOPS BEFORE FIRM PRESSURE IS FELT. PUMPED UP TO NEAR NORMAL PRESSURE BUT SYSTEM WILL NOT SUSTAIN NORMAL BREAKING PRESSURE. COPILOT'S BRAKES NORMAL. INSPECTED BRAKE RESERVOIR, ACCUMULATOR AND BRAKES ASSY FOR LEAKS, WEAR INDICATORS; PILOT, CO-PILOT BRAKE PEDALS FOR LEAKS, NO DEFECTS NOTED, APPLIED POWER TO AIRCRAFT AND CHECKED BRAKES FOR OPERATION, NO DEFECTS NOTED FROM PILOTS OR CO-PILOTS. CONFERRED WITH TECH SERVICES, RETURN TO SERVICE IS OK. BLED BRAKES IAW 560 M/M 32-42-00, OPS CHECKS NORM. NO DEFECTS NOTED.
UPON INSPECTION OF WING DE-ICE BOOTS, DETERMINED THE AERODYNAMIC FILLER UNDER THE BOOT HAD DEBONDED FROM THE LEADING EDGE SKIN. AFTER REMOVAL OF DEICE BOOT AND REMAINING FILLER, THE LEADING EDGE SKIN WAS FOUND CORRODED. THE LEFT WING LEADING EDGE HAD A PIT .031 INCH DEEP AND APPROXIMATELY .1250 INCH DIAMETER. THE RIGHT WING HAD NUMEROUS CORROSION PITS RANGING FROM .005 INCH TO .022 INCH DEEP. (X)
UPON INSPECTION OF WING DE-ICE BOOTS, DETERMINED THE AERODYNAMIC FILLER UNDER THE BOOT HAD DEBONDED FROM THE LEADING EDGE SKIN. AFTER REMOVAL OF DEICE BOOT AND REMAINING FILLER, THE LEADING EDGE SKIN WAS FOUND CORRODED. THE LEFT WING LEADING EDGE HAD A PIT .031 INCH DEEP AND APPROXIMATELY .1250 INCH DIAMETER. THE RIGHT WING HAD NUMEROUS CORROSION PITS RANGING FROM .005 INCH TO .022 INCH DEEP. (X)