N372QS
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
ON DEPARTURE WE RECEIVED AP FAIL A CAS MESSAGE. REENGAGED AP AND RECEIVED AP FAIL B CAS MESSAGE ALSO. WE FOUND THE PRIMARY STAB TRIM TO BE INOPERATIVE WITH NO PRIMARY STAB TRIM FAIL CAS MESSAGE. WE USED SECONDARY TRIM AND LANDED WITHOUT ISSUE. REMOVED ELEVATOR TRIM TAB CABLE ASSEMBLY TO PERFORM VISUAL INSPECTION AND DEEM SERVICEABLE. NO DISCREPANT NOTED. PROVIDED NJA MCC WITH PHOTOS OF COMPLETE CABLE. REINSTALLED SERVICEABLE CABLE AS OUTLINED IN TEXTRON AVIATION MODEL 680 MM, CHAPTER 27-40-00. SUCCESSFULLY COMPLETED STABILIZER TAB CABLE RIGGING IAW MM 27-40-00. TENSION SET TO 32 POUNDS FOR 85 DEGREES F TO COMPENSATE FOR AMBIENT TEMPERATURE. SUCCESSFULLY COM
AFTER PARKING AND SETTING THE BRAKE THE RIGHT BRAKE CALIPER WAS SMOKING WITH BRAKES SET AND RELEASED. PERFORMED GVI OF BOTH RT MLG BRAKES AND WHEEL ASSEMBLIES WITH NO LEAKS OR DEFECTS NOTED. SET BRAKES AND LET SIT FOR 30 MINUTES WITH NO DEFECTS AND PUMPED BRAKES NUMEROUS TIMES WITH AUX PUMP RUNNING AND NO DEFECTS NOTED. SYSTEM OPS AS SHOULD IAW MM 32-42-00 WITH NO LEAKS NOTED.
MAIN DOOR DOES NOT GO DOWN ALL THE WAY. IT STAYS UP ABOUT AN INCH AND WHEN THE PASSENGERS STEP ON IT, IT DROPS THAT INCH UNTIL THE ARMS ARE FULLY EXTENDED. CABLE TENSION NEED TO BE ADJUSTED ACCOMPLISHED THE CABLE TENSION , INSPECTED FOUND CABLE TO MUCH TENSIONED . LOOSE THE LOCK PINS AND RELEASED THE CABLE TENSION UNTIL THE CORRECT TENSION RESECURED THE RAIL LOCK PINS. REINSTALLED THE THE MAIN ENTRY DOOR STEPS & ACCOMPLISHED MULTIPLE TIMES THE OPERATION OPENING AND CLOSING THE MAIN ENTRY DOOR NO DEFECT NOTED. COMPLIED WITH THE MAIN ENTRY DOOR STEPS LIGHT CHECK GOOD. WORK DONE IN REF CE-680 AMM 52-10-30
MECHANICALLY BLENDED HIGH SPOTS ON A GOUGE ON THE RH WING LEADING EDGE APPROXIMATELY 3.25 INCHES OTBD OF THE START OF THE LEADING EDGE. POLISHED AND RETURNED AREA TO ORIGINAL SURFACE FINISH IAW CESSNA 680 SPM 51-70-02 AND NETJETS ENGINEERING RFTS-114953 REV. 0 TITLE: N372QS (680-0201) RH WING LEADING EDGE GOUGE. DATED 10 SEP 2025.
UPON OPENING DOOR WE HEARD A LOUD GRINDING/BINDING NOISE ON DOOR DOWNWARD DESCENT, DOOR IS DIFFICULT TO LOCK DOWN AND REQUIRES EXCESSIVE FORCE TO LIFT HANDLE OVER DETENT TO CLOSE. VERIFIED. T/S DOOR AND FOUND CLOSING HANDLE PUSHROD TO BE OUT OF ADJUSTMENT. ADJUSTED CLOSING HANDLE PUSHROD. OPS CHECK OF DOOR SATISFACTORY. WORK DONE IAW AMM 52-10-30
WHILE IN A DESCENT FROM FL 410 TO FL 340 ZERO, WITH THE THRUST LEVERS AT IDLE, THERE WAS A VIBRATION FROM THE RIGHT ENGINE AND THE ENGINE SHUTDOWN R CYAN MESSAGE ILLUMINATED. MOVED THE RIGHT THROTTLE OUT OF IDLE AND THE ENGINE SHUTDOWN R CYAN MESSAGE EXTINGUISHED. THE ENGINE OPERATED NORMALLY AND WE LANDED WITHOUT INCIDENT. GAINED ACCESS TO THROTTLE QUADRANT. PERFORMED RIG CHECK OF THROTTLE QUADRANT IAW AMM 76-10-00. RIG CHECKS SATISFACTORY. ALL VALUES WERE WELL WITHIN LIMITS. CLOSED ACCESS. THROTTLE QUADRANT OPERATIONAL CHECKS SATISFACTORY,
REPEAT WRITE UP. BEGAN DESCENT FROM 43,000FT. THROTTLE WAS AT OR NEAR IDLE. AT 43,000FT WE FELT A COMPRESSOR STALL WHILE OBSERVING A RIGHT ENGINE ROLL BACK FOLLOWED BY A BLUE CAS MESSAGE ENG SHUTDOWN R. WITHIN 5-10 SECONDS THE ENGINE AUTOMATICALLY RESTARTED. EVENT MARKER WAS PRESSED (17:00Z) AND THE FLIGHT CONTINUED WITH NO OTHER ABNORMAL INDICATIONS. REMOVED RT FCU & INSTALLED REPAIRED LISTED BELOW IAW AMM 73-10-02. SWAPPED EECS IAW AMM 73·20-02. PERFORMED UNCAPPED AND CAPPED POWER ASSURANCE TEST AND FOUND TEST FAILED. TROUBLESHOT TO RH EEC NOT MIRRORED. MIRRORED LH AND RH EECS IAW MM 77-40-01. VERIFIED EEC MIRRORING. ALL LEAK AND OPERATIONAL CHECKS SATISFACTORY. POWER ASSURANCE TEST SATISFACTORY.
RIGHT ENGINE ENGINE COMPRESSOR STALL: AT APPROX. 42000FT IN THE DECENT, A COMPRESSOR STALL WAS FELT FOR ABOUT 5-10 SECONDS, AIRCRAFT VIBRATION WAS FELT AND LOUD BANGING NOISE WAS HEARD. THE R ENGINE SHUTDOWN BLUE ADVISORY MESSAGE WAS ALSO DISPLAYED WITH N1, N2 AND ITT INDICATIONS DECREASING RAPIDLY. THE ENGINE SEEMED TO BE COMPLETELY SHUTDOWN FOR ABOUT 10-20SECS WHEN WE DECIDED TO PUSH THE THRUST LEVER FORWARD WHICH SEEMED TO RELIGHT THE ENGINE. THE EVENT MARKER BUTTON WAS PRESSED AND THE FLIGHT WAS CONTINUED TO A SAFE LANDING WITH NO OTHER ABNORMAL INDICATIONS. CORRECTIVE ACTION: PERFORMED FAULT ISOLATION 3, TABLE 101, FIG 103 IAW PW306C MM REV 51 DATED 4 NOV 2024. FOUND FAULTY FUEL DUMP CONTROL VALVE SEE SQUAWK 3.3 FOR RESOLUTION. RESOLUTION: SIGNED OFF: 05/05/2025 BY: LYLE SHOOK REMOVED FWD UPPER BAGGAGE COMPARTMENT FADEC CONNECTORS ACCESS PANEL. STEP: 1 DESCRIPTION: COMMENTS: REINSTALLED FWD UPPER BAGGAGE COMPARTMENT FADEC CONNECTORS ACCESS PA SIGNED OFF: 05/05/2025 BY: KEVIN BARNETT INSPECTOR: 05/05/2025 BY: LYLE SHOOK DURING TROUBLESHOOTING PROCEEDURES FIG(103) FOUND FAULTY FUEL DUMP VALVE THAT WILL REQUIRE REPLACEMENT. REMOVED FUEL TRANSFRER TUBE FROM DUMP VALVE TO WASTE EJECTOR CANISTER. COMMENTS: REINSTALLED FUEL TRANSFRER TUBE FROM DUMP VALVE TO WASTE EJECTOR CANIST SIGNED OFF: 05/05/2025 BY: KEVIN BARNETT INSPECTOR: 05/05/2025 BY: LYLE SHOOK ITEM: 3 #2 ENGINE STEP: 2 DESCRIPTION: REMOVED FUEL START AND DUMP VALVE PN 26240-7 SN 9959517303 REPLACED FUEL START AND DUMP VALVE WITH INSPECTED PN 26240-7 SN 0937. PERFORMED SATISFACTORY LEAK AND OPERATIONAL CHECKS IAW PW306C MM REV 51 DATED 4 NOV 2024.(TASK 73-10-05). COMMENTS: SIGNED OFF: 05/05/2025 BY: KEVIN BARNETT INSPECTOR: 05/05/2025 BY: LYLE SHOOK COMPLIED WITH NETJETS TASK # T2PL6D00CMNF, RIGHT ENGINE COMPRESSOR STALL. REMOVED AND REPLACED THE RIGHT-HAND ENGINE START DUMP VALVE. REMOVED ONE EACH START/DUMP VALVE P/N 26240-07 S/N 9959517304 AND INSTALLED ONE EACH INSPECTED DUMP VALVE P/N 26240-07 S/N 0937. PERFORMED OPERATIONAL AND LEAK CHECKS. THE OPERATIONAL CHECK WAS GOOD WITH NO LEAKS NOTED. ALL WORK COMPLIED WITH IAW THE PW306C MAINTENANCE MANUAL CHAPTER 73-10-05. ORIGINAL SUBMISSION DATE: 5/2/2025
MAIN ENTRY DOOR INTERIOR GRAB HANDLE CAME OFF WHILE CLOSING DOOR. ATTACHING HARDWARE IS BROKEN OFF ALONG WITH PART OF THE STEP STRUCTURE AND IS INSIDE THE DOOR NOW. SEE ATTACHED PHOTOS. CORRECTIVE ACTION: REATTACHED HANDLE STAND OFFS. INSTALLED NEW STEP ASSEMBLY HARDWARE. OPS CHECK GOOD. IAW CE680 SPM 20-40-00 AND CE680 IPC 52-10-02.
R&R FASTENERS, BLENDED CORRODED AREAS OF THE AFT WING SPAR LOWER CAP LOCATED IN THE LH MAIN LANDING GEAR WHEEL WELL, PERFORMED NDT, REPORTED FOR RESULTS REPAIR DISPOSITION. RE-INSTALLED EXISTING HI-LOK'S WITH NEW COLLARS. APPLIED ALODINE, PRIMER, TOPCOAT AND CIC TO BLENDED AREAS IAW NJA ENGINEERING RFTS.
THE MAIN CABIN DOOR HAND RAIL REQUIRES EXCESSIVE FORCE TO LOCK THE STEPS IN PLACE. ONCE LOCKED IN PLACE, HAND RAIL AGAIN NEEDS EXCESSIVE FORCE TO BE ABLE TO RAISE THE DOOR. FEELS LIKE SOMETHING WILL BREAK IF TENSION DOES NOT GET ADJUSTED. ADJUSTED CLOSING HANDLE OVERCENTER PUSHROD AS REQUIRED PER CE-680 AMM 52-10-30. PERFORMED NUMEROUS OPERATIONAL CHECKS WITH NO DEFECTS NOTED.
UPON TAKE OFF, RETRACTED MLG, ALL 3 RETRACTED, THE MLG UNLOCK LIGHT DID NOT EXTINGUSH. COMPELETED UNLOCK QRH CHECKLIST, NLG DID NOT EXTEND. COMPLETED MLG WILL NOT EXTEND QRH CHECKLIST, UNSUCCESSFUL. PROCEDED TO LAND WITH NLG IN UP POSITION. PERFORMED GEAR SWINGS IAW AMM 32-00-00. REMOVED AND REINSTALLED EXISTING NLG. SERVICED NLG TIRES & STRUT IAW MM 32-20-00, 32-60-00, 12-13-02, 12-20-32. REMOVED & REINSTALLED BAGGAGE/APU FIRE BOTTLE IAW CESSNA 680 AMM 26-20-30. REMOVED AND REINSTALLED NOSE WHEEL STEERING ACCUMULATOR IAW AMM 32-50-00. REMOVED AND REINSTALLED NOSE AVIONICS COMPONENTS & RACKS TO FACILITATE REPAIR PERFORMED ON SQK 43-4 OF THIS WORK ORDER. ALL R&R IAW AMM 34-21-00, 34-17-00, 34-43-00, 34-41-00, 34-12-00, 34-11-00, 31-20-05, 24-60-40, AND 24-32-00. R & R LT NOSE SKIN WITH NEW, LT NLG DOORS WITH NEW. RADOME BULKHEAD WITH NEW FRAME & WEB: & LT & RT LOWER DRAG ANGLES WITH NEW IAW SRM 51-40-06, 51-40-03, 51-40-11, 51-40-0.
A FEW SECONDS AFTER ROTATION AND LANDING GEAR RETRACTION WE RECEIVED A ?HYDRAULIC VOLUME LOW? AND ?HYDRAULIC PRESSURE LOW L-R? AMBER EICAS MESSAGES AND A RED LANDING GEAR ?UNLK? LIGHT WITH A RH MLG GREEN LIGHT ON THE GEAR INDICATORS. WE REQUESTED TO STAY AT 5000? AND KEPT OUR SPEED BELOW 200KTS. RUN THE QRH CHECKLIST FOR THE LOW HYDRAULIC VOLUME, COMPLIED WITH ALL THE SPEED AND FLAP 15¿ RESTRICTIONS. RUN A GENESIS RUNWAY ANALYSIS. BLEW DOWN THE LANDING GEAR USING THE EMERGENCY PNEUMATIC SYSTEM, LANDED ON THE RUNWAY UNDER 24000LBS AND USED THE EMERGENCY BRAKE SYSTEM TO STOP THE PLANE. *** CORRECTIVE ACTION *** INSPECTED RIGHT MAIN LANDING GEAR IN THE LOCATION OF THE HYDRAULIC LEAK. FOUND THE RIGHT GEAR RETRACT LINE LEAKING HYDRAULIC FLUID. REMOVED RIGHT MAIN ACTUATOR GEAR RETRACT LINE P/N AS116-06K0166 S/N: N/A. INSTALLED HOSE ASSEMBLY P/N AS116-06K0166 S/N: N/A PER 680 MM. CHAPTER 20-10-05.
CABIN EMERG LIGHT: CABIN INTERIOR EMERGENCY LIGHT OVER WORK TABLE DOES NOT ILLUMINATE DURING EMERGENCY LIGHT CHECK. THE LIGHT DOES ILLUMINATE WITH MAIN DC POWER. (PRE FLIGHT) // SIGNOFF // PERFORMED EMER UGHTING OPS CHECK, DOME UGHT OVER WORK TABLE DID NOT ILLUMINATE. ALLOWED BATTERY PACK TO CHARGE AND LIGHT WOULD ILLUMINATE BUT BATTERY WAS WEAK. REMOVED #1 BATTERY PACK AND REPLACED WITH REPAIRED UNIT. OPS CHECKED EMER UGHTING SYSTEM IAW CESSNA 680 AMM 33-50-00. NO DEFECTS NOTED
MAIN CABIN DOOR NOT PROPERLY COUNTER WEIGHTED. DOOR FALLS ALL THE WAY OPEN WHEN NOT COMPLETELY CLOSED. DOOR IS HARD TO BRING UP TO CLOSE FROM INSIDE CABIN. // SIGNOFF// GAINED ACCESS TO COUNTER BALANCE ASSEMBLY AND FOUND THE FWD SPRING UNDER TENSIONED. ADJUSTED TENSION AS REQUIRED AND OPS CHECK GOOD. MX CW IN REF TO CE-680 AMM 52-10-50
MAIN DOOR: MAIN CABIN DOOR COUNTERWEIGHT NEEDS ADJUSTMENT. DOOR WILL NOT STAY CRACKED AND FALLS 1 QUARTER TRAVEL. PREFORMED OPS CHECK WITH NO DEFECTS NOTED AND OPS CHECH GOOD ALL WORKCDONE IAW CE-680 AMM: 52-10-00
7 AREAS OF VERIFIED CORROSION ON RH AFT SPAR IN MLG WELL. BLENDED 7 AREA OF CORROSION IN RH GEAR WELL, AFT LOWER SPAR. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED FINDINGS AND FOUND AREA TO BE BEYOND LIMITS. REPAIRED AREA OF LEVEL 2 CORROSION PER AQRD ERO-104549 REV. IR, TITLE N372QS N372QS AFT WING SPAR REPAIR DATED: FEB 12 2021 .
4 AREAS OF VERIFIED CORROSION ON LH AFT SPAR IN MLG WELL. BLENDED 4 AREA OF CORROSION IN LH GEAR WELL, AFT LOWER SPAR. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED FINDINGS AND FOUND AREA TO BE BEYOND LIMITS. REPAIRED AREA OF LEVEL 2 CORROSION PER AQRD ERO-104549 REV. IR, TITLE N372QS N372QS AFT WING SPAR REPAIR DATED: FEB 12 2021 .
EMERGENCY LIGHTING CONSISTING OF AFT OVER WING LIGHT, EXIT SIGN ON BULKHEAD SEAT NINE, EXIT SIGN OVERLAP, SEAT LAV OVERHEAD LIGHT ALL INOPERABLE WITH THE EMERGENCY SWITCH IN ARM AND MAIN BATTERIES OFF. ALSO WITH SWITCH IN ON POSITION AND MAIN BATTERIES OFF NO EMERGENCY LIGHTS COME ON. CORRECTIVE ACTION: REPLACED NR 1, 2, 3, 4 EMERGENCY BATTERY CHARGING SYSTEMS. REMOVED AND INSTALLED P/N"S CBS28-1. REMOVED S/N NR 1 006771, NR 2 2755M, NR 3 2052M, NR 4 1702M DUE TO INTERNAL FAILURE AND INSTALLED REPAIRED EMERGENCY BATTERY CHARGER SYSTEM P/N CBS28-1 S/N NR 1 0062891, NR 2 005817, NR 3 005624, NR 4 005873.
FOUND DURING CABIN INTERNAL ZONAL INSPECTION, FOUND SEVERAL SPOTS OF CORROSION ON STRUCTURE UNDER THE CENTER DROP AISLE PANELS. PERFORMED AQRD REPAIR ERO-966932 REVISION A DATED SEP 10 2020 AT FUSELAGE FLOOR F.S. 157.
CABIN AND COCKPIT TEMPERATURE CONTROL VALVE INTERNAL AND EXTERNAL COMPONENTS ARE VERY LOOSE AND MOVING DURING VALVE OPERATION. FOUND WHILE PERFORMING TASK 21-61-00-7100 COCKPIT AND CABIN MANUAL TEMPERATURE CONTROL OPERATIONAL CHECK. PART NUMBERS OF THE CABIN AND COCKPIT TEMP CONTROL VALVES ARE THE SAME.
MAU 1 FAIL AMBER CAS ILLUMINATED - MAU 1 FAIL AMBER CAS MESSAGE ILLUMINATED IN FLIGHT A FL400 DURING CRUISE. ****CORRECTIVE ACTION**** REPLACED POWER SUPPLY MODULE ASSY.
CORROSION DISCOVERED ON AFT BAGGAGE DOOR HINGES. REMOVED CORROSION VIA MECHANICAL MEANS. RECOMMEND REDUCING THE INSPECTION INTERVAL OR USING AN IMPROVED PRIMER IN THAT AREA.
BRAKES WEAKER THAN NORMAL AT HIGH SPEEDS. SEEMS MAX BRAKING NOT AVAILBLE WHEN APPLYING MAX BRAKE PEDAL PRESSURE. BRAKING ACTION NORMAL AT TAXI SPEEDS. INSPECTED BRAKES FOR WEAR & LEAKS - OK. PERFORMED FUNCITONAL CHECK OF POWER BRAKE SYS FOUND LT BRAKE PRESSURES OUT OF LIMITS. BLED BRAKES - PERFORMED ANTI-SKID FUNCTIONAL TEST. LT BRAKE PRESSURES WITHIN LIMITS AFTER BLEEDING. OPS AND LEAK CHECKS GOOD IAW MM 32-42-00.
AFTER DEPARTURE GEAR HANDLE PLACED IN UP POSITION. NOSE GEAR RETRACTED NORMALLY " LIGHT OUT ". UNLOCK RED LIGHT REMAINED ILLUMINATED AS MAIN LT AND RT GEAR CYCLED UP AND DOWN APPROX 3 TIMES WHEN MAIN GEAR CYCLED DOWN " GREEN ' DOWN LOCK LIGHT. INSPECTED AND NOTED NOSE GEAR STRUT IS FLAT PREVENTING PROPER OPERATION OF THE NOSE GEAR SQUAT SWITCH. REPACKED NOSE STRUT AND COMPLETED SATISFACTORY FUNCTIONAL CHECKS IAW MM 32-20-01.
GEAR HANDLE PLACED IN UP POSITION, MAIN LT AND RT GEAR CYCLED UP AND DOWN APPRX 3 TIMES.
AFTER DEPARTING CMH THE AP FAIL B MSG FLICKERED THEN ILLUMINATED SOLID.
AFTER DEPARTING, THE AP FAIL B MESSAGE FLICKERED THEN ILLUMINATED SOLID. TROUBLESHOT AUTOPILOT SYS USING DIAGNOSTIC MX SYS. NO FAULTS FOUND SYSTEM CHECKS GOOD IAW MM 45-40-00.
RT MAIN GEAR UPLOCK FAILED. HAD A GEAR UNLOCK LIGHT ON WITH A HYDRAULIC PTRS ON LIGHT. RAN THE HYDRAULIC PRES ON CK LIST AND WHEN WE PULLED THE GEAR CONTROL (CB) AS DIRECTED THE RT MAIN GEAR EXTENDED. THE GEAR HANDLE WAS THEN PLACED IN THE GEAR DOWN POS. RESET THE (CB) AND GOT 3 GREEN LIGHTS, NO DIVERT. REMOVED FAULTY RT MAIN GEAR UPLOCK SWITCH P/N S430087. INSTALLED NEW SWITCH P/N 65430087. OP CHECK GOOD, ALL WORK PERFORMED IAW CESSNA CE-560 MAINT MANUAL CHAP'S 32-61-00 AND 32-60-00, FOR DETAILS REF FAS W/O 07-183
LT ENGINE SHUT ITSELF DOWN FOLLOWING SPEED BRAKE TEST. THROTTLE WAS AT IDLE. FOUND LT ENGINE IDLE SET TOO LOW AND THROTTLE LINKAGE OUT OF RIG. RIGGED LT ENGINE THROTTLE LINKAGE AND ADJUSTED LOW IDLE. OPS CHECKS GOOD IAW MM 71-00-00.
LT ENGINE WOULD NOT MAKE TAKEOFF POWER SHORTLY AFTER LIFTOFF. DURING SPEED BRAKE CHECK, ENGINE SHUT DOWN WHEN THROTTLE PULLED BACK TO IDLE. PERFORMED ENGINE BLEED AIR LEAK CHECK, NO LEAKS NOTED. ADJUSTED FUEL CONTROL/ FLOW DIVIDER INTERCONNECT ROD IAW THE MM CHAPTER 71-00-00. OPERATIONAL CHECKS WERE NORMAL.
WHILE ON APPROACH TO LAND NOTICED TWO ANNUNCIATORS, POWER BRAKE LOW PRES AND ANTI SKID INOP. BRAKE FAILURE. RAN CHECKLIST AND LANDED WITHOUT BRAKES. ON POST FLIGHT ALL FLUID LEVELS AND PRESSURE WERE NORMAL. DISCONNECTED P9 CONNECTOR TO CHECK FDC GROUND AT PIN O OF 59. GROUND PRESENT, RECONNECTED P9 FOLLOWED ANTI-SKID TROUBLE SHOOTING CHART CESSNA MM 32-42-00 NO FAULT FOUND. SYSTEM OPS CHECKED GOOD.
SMOKE IN COCKPIT FROM RT EYEBALL VENT. TURNED OFF DEFOG FAN PER CHECKLIST, SMOKE DISSIPATED. REPLACED CABIN DEFOG BLOWER WITH OVERHAULED P/N 5703-4, S/N 0809 IN ACCORDANCE WITH CESSNA 560 M/M 21-21-00 REV 21. OPS CHECKS GOOD.
NR 1 ENGINE FLAMEOUT AFTER START, REPEATED START AND AGAIN FLAMEOUT AFTER ABOUT 1 MIN. RAN ENGINE FOUND NR 1 ENGINE FAILED SLAM CHECK, RE-RIGGED FUEL CONTROL ON NR 1 ENGINE, OPS CHECK OF POWER OF DAY, SLAM CHECK, ACCELERATION, AND HIGH IDLE WERE GOOD IAW CESSNA 560 M/M DATA REFERENCE 71-01-03.
LEFT ENGINE SHUTS DOWN WHEN THROTTLE MOVED FROM CRUISE TO IDLE SETTING. ITEM IS UNDER INVESTIGATION.
POWERED UP AIRCRAFT FOR PREFLIGHT. FMS SCREEN STAYS BLACK AND SMOKE WAS COMING OUT FROM UNDER FMS. FOUND FMS GNS-XL. CONTACTED EMPIRE. REMOVED AND REPLACED GNS-XL IAW CE560 MM 34-61-03. OPS CHECK IAW GNS-XL FLIGHT MANAGEMENT SYSTEM OPERATOR'S MANUAL.
LEFT FIRE WARNING LIGHT ILLUMINATED ON TAXI IN. INSPECTED COCKPIT INDICATION LIGHTS AND COULD NOT FIND ANY FAULTS. INSPECTED L/H ENGINE FIRE LOOP & FOUND 2 CLAMPS PINCHING INSULATORS & MAKING CONTACT WITH FIRE LOOP. REMOVED CLAMPS & INSULATORS. REINSTALLED ISOLATORS & CLAMPS AND REPOSITIONED FIRE LOOP SO NO CONTACT WAS MADE WITH CLAMPS. ALL WORK PERFORMED I/A/W CESSNA 560 M/M CHAPTER 26-11-01. FUNCTIONALLY TEST GOOD. NO DEFECTS NOTED
LEFT ENGINE EXCEEDED 95LB OIL PRESSURE WHEN COMPUTED TAKEOFF POWER SET ON TAKEOFF. REMOVED OIL FILTER AND INSTALLED NEW OIL FILTER. PERFORMED OPERATIONAL CHECK, AND LEAK CHECK. NO LEAKS NOTED. ADJUSTED THE OIL PSI REGULATOR VALVE, OPS CHECK GOOD, LEAKED CHECK OK. ALL WORK PERFORMED IAW CHAPTER 79-20-01 OF THE P&WC JT15D MM.
DURING PHASE 1-4 INSP, FOUND RT FLAP ACTUATOR TO HAVE THE CYLINDER TO ATTACH BASE BOLT HEAD SHEARED OFF. THE HEAD OF THE BOLT WAS STILL ATTACHED TO THE SAFTEY WIRE (THE ACTUATOR WAS NOT LEAKING AND STILL WORKING). IT APPEARS THAT THE BOLT HAD BEEN BROKEN FOR A WHILE, DUE TO THE DIRT AND GRIME AROUND AREA. THIS IS NOT THE FIRST TIME WE HAVE SEEN THIS ON THE FLAP ACTUATOR, AT LEAST TWO OTHERS THAT WE HAVE FOUND.
RT MAIN LANDING GEAR INDICATOR LIGHT IS INOPERATIVE, BLEW THE GEAR DOWN PER THE CHECKLIST. THREE GREEN LIGHTS NOW APPEAR ON AND TEST CORRECTLY AFTER LANDING. - REPLACED GEAR POSITION INDICATING BULBS PER CESSNA 560 MM CHAPTER 33-13-10, PERFORMED GEAR RETRACTION AND EXTENSION TESTS PER CESSNA 560 MM CHAPTER 32-30-00 FOUND NORMAL. SERVICED BOTTLE WITH NITROGEN PER CESSNA 560 MM CHAPTER 12-10-00.
UPON INSPECTION OF RIGHT WING DE-ICE BOOT, DETERMINED THE AERODYNAMIC FILLER UNDER THE BOOT HAD DEBONDED FROM THE LEADING EDGE. AFTER REMOVAL OF THE DE-ICE BOOT AND REMAINING FILLER, THE LEADING EDGE SKIN WAS FOUND TO HAVE NUMEROUS CORROSION PITS. THE PITS RANGED FROM .003 INCH IN DEPTH TO .012 INCH IN DEPTH. AFTER REMOVAL OF CORROSION, DEPTH HAD INCREASED TO BETWEEN .007 INCH AND .017 INCH DEEP. (X)