N341QS
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
JUST AS WE GOT TO THE AIRPORT AND BEFORE WE GOT TO THE PLANE A EXECUJET VAN STRUCK THE LEFT WING OF N341QS AT 8:56. THE DAMAGE TO THE WING SEEMS MINIMAL BUT THE VAN HAS A BIG DENT. CORRECTIVE ACTION: GAINED ACCESS TO THE AIRCRAFT AND INSPECTED THE DAMAGED AREA AND NOTED DAMAGE IS SUPERFICIAL. ALSO NOTED THAT THE DAMAGE BELOW THE STROBE LIGHT WAS PAINT REMAININGS FROM THE VEHICLE THAT STRUCK THE AIRCRAFT, AND WE WERE ABLE TO REMOVE THAT PAINT. THE STROBE LIGHT NOR THE NAV LIGHT LENSES HAS ANY DAMAGE. FINDINGS SENT TO MCC FOR EVALUATION AND AQHD RECOMENDED A TEMPORARY REPAIR AS PER RFTS-115973 REV.0.
DURING PREFLIGHT FOUND ALL BUT TWO EMERGENCY LIGHTS INOPERATIVE. THE ONLY TWO THAT WORK ARE THE CABIN FLOOR FWD LT & EXTERIOR LIGHT BY THE CABIN DOOR. REMOVED NR 1 EMERGENCY LIGHT POWER SUPPLY & REPLACED WITH NEW EMERGENCY LIGHT POWER SUPPLY IAW AMM 33-50-10. PERFORMED SATISFACTORY OPS CHECKS IAW AMM 33-50-00. REMOVED NR 1 EMERGENCY LIGHT POWER SUPPLY & REPLACED WITH NEW EMERGENCY LIGHT POWER SUPPLY IAW AMM 33-50-10. PERFORMED SATISFACTORY OPS CHECKS IAW AMM 33-50-00.
CORROSION FOUND IN RT WHEEL WELL ON LOWER AFT SPAR CAP. ACCOMPLISHED FORM 8100-9, FIELD REPAIR FR-680-0225-15874 FIELD REPAIR-CORROSION, RT WING REAR SPAR CAP LOWER FORWARD ANGLE RWS 37.
PRIMARY CABIN DOOR WOULD NOT OPEN AFTER LANDING. RED BUTTON WOULD NOT DEPRESS TO OPEN THE DOOR. ATTEMPTED TO HAVE GROUND CREW OPEN THE DOOR FROM THE OUTSIDE. THEY WERE UNABLE TOÿ AND THE SILVER HANDLE ON THE EXTERIOR PART THE DOOR JAMMED INWARD. ATTEMPTED TO USE EMERGENCY CATCH RELEASEÿ IT ALSO IS JAMMED DOES NOT WORK. CREW AND PASSENGERS HAD TO DEPLANE THROUGH EMERGENCY HATCH. CORRECTIVE ACTION: REPLACED DAMAGED SPRING OF THE PRECATCH HANDLE SYSTEM AND REPOSITIONED THE BELLCRANK FITTING P/N 6911329-32 TO AFT OF THE CAM. PERFORMED PRECATCH SYSTEM ADJUSTMENT AND FOUND EVERYTHING WITHIN LIMITS. OPERATED THE DOOR 10 TIMES AND DOOR IS OPERATING PER THE AMM OPS CHECKS. REINSTALLED ALL DOOR PANELING AND REINSTALLED THE EMERGENCY EXIT DOOR ALL WORK DONE IAW CE680 AMM CH 52-10-40 AND 52-20-00.
CABIN PRESSURIZATION CONTROL: DURING CLIMBOUT, WE NOTICED A FLUTTERING/POPPING NOISE FROM ABOUT 1000 MSL TO ABOUT 2000 MSL. IT STOPPED. THEN WE NOTICED THAT THE CABIN WASNT PRESSURIZING AS QUICKLY AS NORMAL. CABIN ALTITUDE WAS ABOUT 4000 CLINBING THROUGH 14,000 FEET, THEN 7000 THROUGH 23,000 FEET. AT THAT POINT WE REQUESTED A DESCENT AND DIVERTED TO SAN JUAN, PR. DURING THE DESCENT, THE CABIN ALTITUDE CONTINUED TO CLIMB. THE CABIN ALTITUDE AMBER ANNUNCIATION CAME ON DESCENDING THROUGH 15,000, AND THE CABIN ALTITUDE RED ANNUNCIATION CAME ON BRIEFLY DESCENDING THROUGH 10,000. THE CABIN PSI DELTA P NEVER GOT ABOVE 5, AND WOULD DECREASE, EVEN DURING LEVEL FLIGHT. WE DECLARED EMERGENCY AND DIVERTED TO SAN JUAN. CORRECTIVE ACTION: WE FOUND THE WATER SEPARATOR DUCT COUPLING PIN S3295-16-10 MISPOSITIONED. REPOSITIONED COUPLING AND SECURED WITH THE REQUIRED CLAMPS IAW CE 680 AMM 21-21-03. ACM OPS CHECK PERFORMED IAW CE 680 AMM 21-21-03.
OVERWEIGHT LANDING: LANDED AT APPROXIMATELY 28,100 POUNDS DUE TO PRESSURIZATION EMERGENCY WITH PASSENGERS. CORRECTIVE ACTION: C/W OVERWEIGHT LANDING INSPECTION IAW CE-680 AMM 05-50-00. OPS CHECK GOOD.
AFTER A NORMAL LANDING IN HOU, A LINEMAN NOTICED OUR RIGHT MLG TRUCK SMOKING WITH A VERY DISTINCT CRACKLING SOUND (ALMOST THE SOUND OF A WOOD LOG BURNING IN A FIRE). THERE WAS ALSO THE SMELL OF BURNING HYDRAULIC FLUID. AFTER ,PERFORMED DETAILED INSPECTION OF R/H MLG TRUCK(#3& #4WHEEL/TIREASSY.) INCLUDING THE FLUID LINES& ASSOCIATED GEAR CONTROL VALVES FOR DAMAGE/FLUID LEAKS. NO FLUID LEAKS, OR OBVIOUS DEFECTS WERE FOUND. PER CUSTOMER REQUEST, REMOVED & REPLACED THE R/H OTBD (#4) BRAKE ASSEMBLY & (#4) WHEEL HUB& TIRE ASSEMBLY, USING SERVICEABLE HARDWARE.REF.CE-680MM 32-10-10,32-42-10& 32-41-20 FOR MX PERFORMED. BRAKE ASSY P/N & S/N REMOVED: 2-1675-1(9914655-3) & 0230A BRAKE ASSY P/N & S/N INSTALLED:2-1675-1(9914655-3) & D1366P W HEEL-HUB& TIRE ASSYP/N & S/N REMOVED:6941060-1& 2024 WHEEL-HUB& TIRE ASSYP/N & S/N INSTALLED:6941060-1& 0494
DURING LH AND RH WING AFT SPAR INSPECTION FOUND CORROSION AROUND SPEED BRAKE HYDRAULIC FITTING AND SP HYDRAULIC FITTING ON RH WING. PERFORMED REPAIR TO RH WING SPAR WEB CORROSION. PER: NETJETS RFTS-112900 N341QS (680-0225) RH WING SPAR WEB CORROSION, REV.0 DATED 17FEB25. PERFORMED REPAIR TO RH CENTER SPAR WS 39.90 UPPER AND LOWER SPAR PASS THROUGH LOCATIONS. PER: TEXTRON REPORT NO: S-680-ATA57/03RD REV- DATED 3/18/2019 REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS.
DURING WING AFT SPAR INSPECTION, FOUND CORROSION AROUND HYDRAULIC FITTINGS ON LH AFT SPAR. DURING BLENDING OF LH WING SPAR FOUND CORROSION UNDER ADDITIONAL FEED THROUGH. DURING ULTRASONIC THICKNESS INSPECTION OF A BLENDED AREA NEAR A FASTENER HOLE ON THE LH AFT SPAR AN ABNORMAL THICKNESS CHANGE INDICATING AN INTERNAL ANOMALY WAS FOUND. PERFORMED REPAIR TO LH WING SPAR WEB CORROSION. PER: NETJETS RFTS-112917 N341QS (680-0225) LH WING SPAR WEB CORROSION, REV.0 DATED 17FEB25. PERFORMED REPAIR TO LH CENTER SPAR WS 39.90 UPPER AND LOWER SPAR PASS THROUGH LOCATIONS. PER: TEXTRON REPORT NO: S-680-ATA57/03RD REV- DATED 3/18/2019 REPAIR OF WING STRUCTURE CORROSION AT TITANIUM BULKHEAD FITTINGS.
MED LOWER CLOSEOUT PANEL CORROSION AND GOUGING.
LH WING AFT SPAR WEB CORROSION.
TAIL CONE HAS CORROSION SURROUNDING LOWER DATA PLATE.
ON TAKEOFF CLIMB OUT, APPROXIMATELY 500 FEET AGL A TURKEY VULTURE IMPACTED THE FRONT LEFT WINDSHIELD CRUSHING THE WINDSHIELD AIR VENT DUCTING. NO STRUCTURAL DAMAGE WAS OBSERVED ON THE LEFT CAPTAIN SIDE WINDSHIELD. AIRCRAFT ENTERED THE TRAFFIC PATTERN AND RETURN TO LAND WITHOUT FURTHER INCIDENT. CORRECTIVE ACTION; REMOVED DENTED LH WINDSHIELD SHROUD. COLD WORKED LH WINDSHIELD SHROUD UNTIL DENT WAS WITHIN LIMITS. INSTALLED LH WINDSHIELD SHROUD. REF. NDT SOLUTIONS WO# 54591 FOR EDDY CURRENT INSPECTION. REF. RFTS-112150 REV. 0 FOR REPAIR. REF. CE 680A AMM 30-40-00. REF. CE 680A SRM 51-00-03.
MAIN DOOR: MAIN CABIN DOOR NOT BALANCED AND OPENS VERY VIOLENTLY. VERY HEAVY/DIFFICULT TO CLOSE. TECH PERFORMED THE COUNTERBALANCE ADJUSTMENT/TECH AND FOUND THE TENSION ON THE CABLES WERE CAUSING THE DOOR TO SLAM DOWN. TIGHTEN THE TENSION OF TME CABLES AND PERFORMED SEVERAL OPERATIONAL CHECKS OF THE MAIN EN'TRANCE DOOR WITH NO DISCREPANCES TO NOTE AT THIS TIME. REF. CE680 AMM 52-10-50
MAIN DOOR CABLE IS LOOSE INSIDE DOOR. CABLE IS ATTACHED, BUT SLACK. INSPECTED CABIN DOOR AND FOUND AFT DOOR COUNTERBALANCE SPRING BROKEN. REMOVED AND REPLACED CABIN DOOR AFT COUNTERBALANCE SPRING WITH A CUSTOMER SUPPLIED NEW PART. PERFORMED RIGGING PROCEDURES FOR THE CABIN DOOR COUNTERBALANCE SYSTEM. OPS CHECK OF MAIN CABIN DOOR OK IAW AMM S2-10-50.
MAIN DOOR CABLE: LEFT SIDE MAIN CABIN DOOR COUNTER BALANCE CABLE WILL NOT RETRACT AND UNABLE CLOSE DOOR FROM INSIDE THE AIRCRAFT. REMOVED MAIN ENTRY DOOR STAIRS, FOUND FORWARD DOOR SPRING BROKEN, NO OTHER DAMAGE NOTED, PUT SPRING AND SOME SCREWS ON ORDER. (JPC 2/25) REMOVED BROKEN COUNTER BALANCE SPRING. INSTALLED CUSTOMER SUPPLIED NEW SPRING, ADJUSTED SPRING TENSION AS REQUIRED, OPS CHECKS OF DOOR GOOD. CLOSED ACCESS TO ANO REINSTALLED STEPS. POST MX CHECKS SATISFACTORY. REF CE-680 AMM 52-10-50.
OPENING THE MAIN CABIN DOOR, AFTER LANDING, BITS OF THE MAIN HINGE BROKE OFF. TECHS WERE UNABLE TO REMOVE THE DAMAGED HINGE HALF AS THE HINGE PIN IS FULLY SEIZED. REMOVED SUPPORT BRACKET & INSTALLED NEW SUPPORT BRACKET REMOVED DAMAGED HINGE HALF & INSTALLED NEW HINGE HALF. REMOVED SEIZED HINGE PIN. INSTALLED NEW HINGE PIN. PERFORMED OPS CHECK OF MAIN ENTRANCE DOOR. NO DISCREPANCIES NOTED. ALL WORK PERFORMED IAW AMM 52-10-20 & SRM 51-40-08.
FIELD REPAIR - CORROSION, VERTICAL STABILIZER, AFT SPAR CAP VFS 174.85 - VFS 238.39. REPORT NO. FR-680-0225-12507 DATED OCTOBER 12, 2023 WITH FAA FORM 8100-9.
AC GENERATION AND CONTROL: SLIGHT ELECTRICAL SMOKE ODOR BEFORE TAKEOFF , FADED WHEN FACING DOWN RUNWAY. DURING TROUBLESHOOTING OF THE RH WINDSHIELD HEAT INOP CAS MESSAGE. WHILE REMOVING RH WINDSHIELD HEAT CONTROLLER, NOTED STRONG ELECTRICAL BURNING SMELL FROM RH WINDSHIELD HEAT CONTROLLER. NO OTHER SMELLS NOTED IN CABIN OR COCKPIT WITH APU OR ENGINES RUNNING. BLEED SOURCES ON AND ALL ELECTRICAL ITEMS ENERGIZED. AFTER REPLACEMENT OF RH WINDSHIELD HEAT CONTROLLER, REFERENCE DISCREPANCY 7, VERIFIED NO ABNORMAL SMELLS PRESENT. WORK PERFORMED IAW CE680 AMM 30-40-10 AND CE680 POH 4-17.
EMER LIGHTS FAIL PREFLIGHT CHECK. WITH BATTERIES OFF AND EMERGENCY LIGHT SWITCH IN ARM, ZERO EMERGENCY LIGHTS TURN ON. WITH THE EMERGENCY LIGHT SWITCH ON, ALL EMERGENCY LIGHTS ILLUMINATE EXCEPT THE OVERHEAD WORK LIGHT AND THE EMERGENCY EXIT LIGHT ABOVE MAIN CABIN DOOR. WITH APU POWER, WITH EMERGENCY LIGHTS IN ARM AND PAX SAFETY SWITCH ON, ZERO EMERGENCY EXIT LIGHTS ILLUMINATE. AFTER RUNNING THE APU FOR 30 MINUTES, THE SAME FAILURE OCCURS.//CORRECTIVE ACTION//R&R FUSE ON #1 EMERGENCY LIGHTING BATTERY PACK. SYSTEM OP-CHECKS GOOD REFF:CE680 AMM 33-50-10. P/N OFF:S2565-5 P/N ON:S2565-5.
CABIN EMERG LIGHT: OVERHEAD CABIN EMERGENCY LIGHTS ON LEFT SIDE, AND MAIN CABIN DOOR EXTERIOR EMERGENCY LIGHT DO NOT ILLUMINATE DURING EMERGENCY LIGHT TEST. VERIFIED DISCREPANCY. CHARGED BATTERIES FOR ONE HOUR. FOUND ALL OTHER LIGHTS WORKING CORRECTLY, INSPECTED AND RESET EACH INERTIA SWITCH. WITH NO CHANGE. REMOVED AND REPLACED #2 EMERGENCY LIGHTING BATTERY PACK IAW CE680 AMM CH 33-50-10 CHARGED BATTERY FOR L HOUR. OPERATIONAL CHECK COMPLETED IAW AMM CH 33-50-00 NO DISCREPANCIES NOTED,
EMERGENCY LIGHTING: WITH THE EMERGENCY LIGHTS IN THE ON POSITION OR THE PAX, SAFETY LIGHT SWITCH ON ALL INTERIOR EMERGENCY SIGNS AND PAX SAFETY LIGHTS FORWARD OF SEATS FIVE AND SIX ARE INOPERATIVE. ALL EXTERNAL EMERGENCY LIGHTS ARE INOPERATIVE. INTERMITTENT CABIN CHIMING OCCURS WHEN THE PAX SAFETY SWITCH IS ON. PERFORMED TC-FLT-33-1001-JIC CESSNA 680 / 680A / 700 / EMBRAER EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE. FOUND FWD DROP AISLE EMERGENCY LIGHT WIRING DAMAGED. REPAIRED WIRING AND RESECURED REF. CE680 IMM 25-92-02. PERFORMED EMERGENCY LIGHT OPERATION CHECK REF. CE680 M/M 33-50-00. OPS CHECK GOOD.
EMERGENCY LIGHTING: CABIN EMER LIGHTS ASSOCIATED WITH BATTERY PACK ONE FOR FORWARD PORTION OF CABIN, ILLUMINATED ON THEIR OWN DURING CRUISE. LIGHTS STAYED ON REGARDLESS OF EMER LIGHT SWITCH POSITION: ON ARM, OR OFF. LIGHTS STAYED ON AFTER ENGINE SHUT DOWN, BATTERIES OFF, AND BATTERIES PHYSICALLY DISCONNECTED. REVIEWED INTERIOR WIRING DIAGRAM 25-92-02 AND LOCATED BATTERY PACK #1 AS SOURCE OF LIGHTS REMAINING ON, RESET G SWITCH FOR BATTERY PACK #1, OPS CHECK GOOD IA W CE680 AMM
EMERGENCY LIGHTING: CABIN, EXTERIOR, AND LAV EMERGENCY LIGHTS FAIL TO ILLUMINATE DURING PREFLIGHT CHECKS. PERFORMED EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE REV. 2 DATED 200CT2022. OPS CHECK GOOD IAW CE-680 AMM 33-50-10.
SMOKE AND AND ODOR IN THE CABIN. APU AND BLEED AIR WERE ON, ENGINES OFF. INSPECTED THE APU EXHAUST FINDING NO OIL OR VISUAL ABNORMALITIES. STARTED THE APU IAW THE POH, RAN THE APU FOR 30 MINUTES WITH THE APU BLEED SELECTED ON WITH NO SMOKE OR ODOR NOTED. SHUT DOWN THE APU. COMPLIED WITH TC-680-21-120905M, DUCT BURN OUT, TASK CARD TC-680-21-120905M. STARTED THE APU AGAIN AND SELECTED THE BLEED ON NOTING NO OIL SMELL OR SMOKE. RAN THE APU FOR 45 MINUETS WITH NO ABNORMALITIES. MCC REQUESTS THE CONDENSER BAG BE REPLACED. GAINED ACCESS TO THE CONDENSER BAG. REMOVED AND INSTALLED THE CONDENSER BAG IAW MM 2215460 & 2341316, 4-404. APU OPERATIONAL CHECK ACCOMPLISHED IAW AMM 49-00-00 WITH NO DEFECTS NOTED.
MAIN DOOR: AMBER CABIN DOOR OPEN CAS MESSAGE WILL NOT CLEAR. WE HAD PLANE PLANE GO DARK. WE OPENED AND CLOSED DOOR 6X TIMES IN A ROW TO RESET, NO LUCK PERFORMED OPS CHECK OF DOOR WARNING SYSTEM IAW CE-680 MM 52-70-00 SEVERAL TIMES, EICAS MESSAGE CLEARED EVERY TIME MCD CLOSED. OPS CHECKS GOOD. NO FURTHER MAINTENANCE REQUIRED.
CORROSION FOUND AROUND THREE LOCK FASTENERS IN CENTER AFT CABIN FLOOR JUST FWD OF OUTFLOW VALVES, FOUND SEVERAL SPOTS OF CORROSION ON STRUCTURE UNDER THE CENTER DROP AISLE PANELS. FINAL REPAIR ERO-966682 REV IR AND 8110-3. VERTICAL REAR SPAR INSPECTION FOUND CORROSION ON RH VERTICAL SKIN NEAR TIP CAP. PERFORMED DOUBLER REPAIR ON RH SIDE OF VERTICAL STABILIZER RH UPPER SKIN IAW AQRD ERO 966683.
ALL LANDING GEAR RETRACTION DID NOT RETRACT-GEAR WOULDNT RETRACT AFTER TAKEOFF. AMBER CAS WOW MIS-COMPARE CAME ON SHORTLY AFTER. **SUPPLEMENTAL INFORMATION - REMOVED & REPLACED LT AFT PCB NZ106 SQUAT SWITCH ASSEMBLY.
VERTICAL STAB AFT SPAR CAP DAMAGE, CORROSION.
BURNING SMELL IN COCKPIT.
REPAIR OF AFT CABIN LIGHTNING STRIKE DAMAGE, S-680-0225/10RD REV-. DATED DECEMBER 20, 2016 WITH FAA FORM 8100-9.
REPAIR OF AFT CABIN LIGHTNING STRIKE DAMAGE.
AFTER APU BLEED AIR SELECTED ON, THERE WAS AN ODOR & HAZY SMOKE IN THE COCKPIT & CABIN. WITH ENGS RUNNING & APU BLEED AIR OFF THE ODOR & SMOKE DISSIPATED. REMOVED STARTER & GENERATOR COOLING DUCT FOUND OIL SOAKED. APU IS LEAKING INTERNALLY. REMOVED APU, PN 3800785-1 & SN P-387 FROM ACFT. INSTALLED APU, PN 3800785-1 & SN P-109, IAW MM 49-10-00. LEAK & OPS CHECKED GOOD.
WHEN APU STARTED & BLEED AIR VALVES OPENED, SMOKE BEGAN TO POUR OUT OF VENTS. SMOKE DISSIPATED WHEN APU BLEEDS CLOSED. WHEN ENG STARTED, NO SMOKE WAS OBSERVED. R & R COALESCER SOCK & COMPLIED WITH ENVIRONMENTAL CONTROL SYS, ECS, DUCT BURN OUT FORM IAW TC-680-21-120905M. OPERATIONAL CHECKED GOOD. NO LEAKS NOTED.
CO-PILOT`S LT BRAKE SPONGY. ON LANDING ROLLOUT, BRAKES WERE APPLIED EVENLY AND ACFT VEERED TO RT AND LT PEDAL FELT SPONGY. BLED LT INBD AND OTBD BRAKES IAW MM 32-42-01, NOTED AIR IN INBD BRAKE. OPS CHECKED GOOD.
WITH THE APU ONLY RUNNING, BLEED AIR WAS SELECTED ON. SMOKE IMMEDIATELY STARTED TO POUR INTO BOTH CABIN AND COCKPIT. SHUTDOWN APU WITHIN 15 SECONDS AND A CONSIDERABLE HAZE OF SMOKE REMAINED HANGING IN AIR. LOCATED OIL COMING FROM AGB VENT LINES OUT EXHAUST. FOUND APU OIL OVERSERVICED. INSPECTED AND CLEANED APU BLEED AIR DUCTING. CLEANED APU AND COWLING. DESERVICED APU OIL TO PROPER LEVEL IAW MM 12-11-03. RAN APU FOR OVER 1 HR WITH BLEED AIR ON TO COMPLETY REMOVE OIL RESIDUE FROM AIR SYS. OPS CHECK GOOD, NO OIL SMELL OR SMOKE PRESENT FROM ENGINES OR APU WITH BLEED AIR ON.
DURING A SCHEDULED INSPECTION OF THE APU COMPARTMENT THE TECH FOUND THE FIRE EXTINGUISHING SYSTEM NOZZLE CRACKED 2.5" AT THE BULKHEAD MOUNTING FLANGE. THIS CONDITION AND PICTURES HAVE BEEN SENT TO UNDER SCR 657016.
DEPARTED, RECEIVED AN AMBER WOW MISCOMPARE MESSAGE. ON GEAR RETRACTION LANDING GEAR DID NOT RETRACT AND RED UNLOCK LIGHT ILLUMINATED. RETURNED LANDING HANDLE DOWN IAW (H-2) PROCEDURE. RED UNLOCK LIGHT WENT OUT AND 3 GREEN LIGHTS ON. NORMAL LANDING. AMBER WOW MISCOMPARE MESSAGE WENT OFF. ALL SYSTEMS OPERATED NORMALLY ON THE GROUND. JACKED ACFT, FOUND NLG SQUAT SWITCH OUT OF ADJUSTMENT. ADJUSTED NLG SQUAT SWITCH TO SPEC IAW MM 32-60-00. OPS CHECK GOOD.
LANDING, HAD AN UNSAFE GEAR INDICATION (NO GREEN LIGHT ON LT MAIN) WE HAD GREEN LIGHTS FOR RT MAIN AND NOSE GEAR AND NO RED UNLOCK LIGHT. RAN GEAR WILL NOT EXTEND CHECKLIST. STILL NO GREEN. JIGGLED LT MAIN GEAR LIGHT AGAIN AND IT CAME ON. FOUND LT GEAR INDICATOR LENSE LOOSE AND BECAME UNSEATED, & 1 EA BULB INOPERATIVE. REPLACED BULBS WITH NEW AND REINSTALLED LENS. RESET GEAR BLOWDOWN LEVER, AND GEAR CONTROL VALVE OVER RIDE VALVE & RESHUTTLED LANDING GEAR SYS & PERFORMED HYD BLEED. SERVICED BLOW DOWN BOTTLE. LANDING GEAR & INDICATION OPS CHECK NORMAL. WORK PERFORMED IAW MM 32-00-00 & 33-10-00.
ON ROTATION THROUGH FIRST POWER REDUCTION ABOUT 2 MINUTES AT HIGH BODY ANGLE, A STRONG OIL BURNING ODOR OCCURRED. WENT AWAY AT THAT TIME. DID NOT HAPPEN ON GROUND OR ANY OTHER TIME DURING FLIGHT. INSPECTED BOTH ENGINE EXHAUSTS AND APU EXHAUST AND FOUND NO OIL IN EXHAUST, REMOVED CLAMPS AT OZONE CONVERTER AND CHECKED FOR OIL AND NO OIL FOUND, REINSTALLED CLAMPS. REMOVED LT AND RT INBD BLANKING PLATES AND CHECKED FOR OIL AND FOUND NO OIL. BOROSCOPED APU INTAKE AND FOUND NO OIL IN INTAKE OF APU. REMOVED AND CLEANED WATER SOCK AND REINSTALLED IAW DUCT BURNOUT PROCEDURE. COMPLIED WITH ECS DUCT BURNOUT IAW TC-680-21-120905M, PERFORMED HIGH POWER ENGINE RUNS AND THROUGHOUT ENGINE RUNS THERE WAS NO BURNING OIL ODOR NOTICED IN THE CABIN. PERFORMED SECOND ENGINE RUN AT HIGH POWER WITH NO DEFECTS NOTED.
75 PERCENT OF BOTTOM HALF OF RT ENGINE COWLING IS MISSING. PERFORMED AIRCRAFT FOREIGN OBJECT DAMAGE INSPECTION IAW MM 5-50-00. NO FURTHER DAMAGE NOTED. PERFORMED ENGINE FOREIGN OBJECT DAMAGE INSPECTION IAW MM 05-50-00. NO DAMAGE NOTED. REMOVED REMNANTS OF THE LOWER COWLING. REMOVED THE UPPER COWL AND CHECKED FOR ADDITIONAL DAMAGE ON UPPER INLET AND TOP OF ENGINE. NO DAMAGE NOTED. CYCLED THRUST REVERSER ON RT ENGINE. OPS CHECKS NORMAL.
ON LT ENGINE, THE THREE SMALL LATCHED ON THE LOWER FRONT OF COWLING WERE FOUND UNLATCHED. ON THE LATCHED ON THE SIDE OF THE COWLING, LATCH 1 (FROM THE FRONT) WAS HANGING DOWN WITH THE TAB IN THE LATCHED POSITION. LATCH 2 THE HOOK WAS FOUND BEHIND THE LATCH BAR. LATCH 3 WAS LATCHED PROPERLY AND LATCH 4 WAS LIKE LATCH 1. INSPECTED COWLING DOOR STRUCTURE, LATCHES, LATCH RECEPTICLES INBD COWL SKIRT, ENGINE ACCESSORIES, WIRING AND PLUMBING WITH NO DEFECTS NOTED IAW MM 71-00-30.
AFTER TAKEOFF AT HIGH POWER SETTING AND RELATIVELY LOW AIRSPEED ON CLIMBOUT, A STRONG ODOR OF FUMES CAME INTO COCKPIT AND CABIN FOR ABOUT 10 MINS. THE APU WAS NOT RUNNING AND ALL ENGINE PARAMETERS WERE NORMAL. ODOR SEEMED TO DISSIPATE DURING CRUISE BUT RETURNED AND WAS LESS INTENSE ON APPROACH AND LANDING. SMELLED MORE LIKE FUEL/EXHAUST AND NOT AN OILY ODOR. CHANGED FUEL NOZZLES ON RT ENGINE. DONE IAW MFG MM 73-10-04. LEAK AND POWER ASSURANCE CHECKED NORMAL. OPS CHECKED NORMAL.
IN CRUISE AT FL230 A STRONG ELECTRICAL ODOR WAS DETECTED IN THE FWD CABIN AND COCKPIT. SECURED INTERIOR ELECTRICAL SWITCH AND ODOR DISSIPATED. FOUND THROTTLE QUADRANT PANEL WIRE CHAFED. REPAIRED PER WM 20-10-07. OPS CHECK GOOD.
ENGINE CHIP DETECT ILLUMINATED IN FLIGHT, REMAINED ON FOR LAST 20 MINUTES OF FLIGHT.
AT FL410 FOR 2.5 TO 3 HOURS - AMBER CAS MSG ACM O'TEMP DISPLAYED & WITHIN 5 SEC AMBER EMERGENCY PRESSURIZATION DISPLAYED - PAX SAID SMOKE & FUMES IN CABIN. REQUESTED LOWER ALTITUDE & DESCENDING THROUGH FL390 BOTH CAS MSGS EXTINGUISHED - VERY LIGHT SMOKE. REPLACED SWITCH WITH NEW IAW THE DIRECTIONS STATED IN SL 680-21-02. OPS CHECK AND LEAK CHECK GOOD.
ON TAKEOFF, UNABLE TO MAKE TAKEOFF, N1OF 95.5 PERCENT UNLESS THE POWER LEVER ON RT ENGINE WAS AT THE FIREWALL STOP. OPS CHECK GOOD ON ENGINE RUN. ALL NUMBERS WITHIN SPECS IAW MM 72-00-00. THROTTLE KNOB SPLIT WITHIN LIMITS.
BRAKES FAILED ON LANDING. REMOVED AND REPLACED BRAKE BLEED VALVE WITH NEW , PERFORMED FUNCTIONAL CHECKED GOOD. I.A.W. 560 M/M 32-42-04. NO LEAKS NOTED P/N 77B62 REMOVED AND REPLACED ANTISKID SERVO VALVE WITH OVERHAULED ASSY. PERFORMED FUNCTIONAL CHECK, CHECKED GOOD I.A.W. 560 M/M 32-42-05. NO LEAKS NOTED.
ANTI-SKID PULSES DURING NORMAL BRAKE USE. RETURNED TO DEPARTURE. [SUP 05-03-07] REMOVED & REPLACED A/S CONTROL BOX IAW CESSNA 560 M/M CHPT 32-42-00.
BRAKES ARE SPONGY AND SLOPPY FEELING DURING LANDING. RT SIDE PULSATED INTERMITTENTLY. [SUP 05-03-07] PERFORMED BRAKE & ANTI-SKID BLEEDING PROCEDURE 3 TIMES ON EACH WHEEL TO ENSURE REMOVAL OF ALL AIR FROM SYSTEM. LEAK CHECK GOOD. TAXIED AIRCRAFT FOR 20 MINUTES AT VARIOUS SPEEDS & BRAKE PRESSURES APPLIED WITH NO FAULTS NOTED. ALL WORK DONE IAW CE560 MM CHAP 32-42-00.
NO BRAKES ON THE COPILOTS SIDE, BRAKE PEDALS VERY SPONGY. PERFORMED BRAKE BLEED IAW CESSNA 560 MM CH 32-42-00. PERFORMED LEAK CHECK. NO LEAKS NOTED.
BOTH CAPTAIN'S AND FO'S BRAKES TEND TO GRAB AND SEEM SOME WHAT SPONGY. IAW CE560MM CHAP 32-42-00 BLED THE COMPLETE BRAKE SYSTEM OPS AND LEAK CHECKS GOOD.
UPON LANDING FELT PULSING IN BRAKE PEDALS AND PEDALS WERE HARD TO PRESS. BRAKE PRESSURE ACCUMULATOR PUMP (NOSE) CYCLES ON APPROXIMATELY EVERY 20-30 SECONDS. PUMP MOTOR SEEMS TO CYCLE ON MORE FREQUENTLY THAN NORMAL. TROUBLE SHOT SYSTEM. DETERMINED BRAKE ACCUMULATOR OVER SERVICED, SERVICED ACCUMULATOR TO PROPER LEVEL OPS CK GOOD ALL WORK DONE I/A/W CITATION ULTRA M/M CHAPTER 12-13-02
LEFT MAIN GEAR WOULD NOT RETRACT ON GEAR RETRACTION (CYCLED GEAR DOWN) 3 GREEN INDICATED. PUT AIRCRAFT ON JACKS, SWUNG GEAR 10 TIMES NO PROBLEMS. FOUND ON 11TH GEAR SWING, GEAR CAME UP BUT GOT GEAR UNSAFE LIGHT WITH GEAR DOWN. FOUND BROKEN WIRE TO LT MAIN GEAR DOWN LOCK SWITCH REPAIRED WIRE AND PERFORMED SWINGS OF SYSTEM NO PROBLEMS FOUND PERFORMED GEAR OPERATIONAL CHECKS IAW CESSNA 560 MM CH 32-00-00 AND 32-31-04.
EMERGENCY LIGHTS WILL NOT EXTINGUISH DUE TO A HARD LANDING. ITEM IS UNDER INVESTIGATION.
LEFT MAIN GEAR WOULD NOT RETRACT DURING GEAR RETRACTION. LEFT MAIN STAYED DOWN WITH GREEN INDICATION & RED GEAR UNSAFE LIGHT ILLUMINATED. ITEM IS UNDER INVESTIGATION.
UPON LANDING BRAKES HAD " HARD PEDALS " ON PILOT'S AND CO PILOTS SIDE. RELEASED BRAKES AND THEN HAD NORMAL BRAKING. FOUND RIGHT GEAR ANTI SKID TRANSDUCER INDICATOR R/S LATCHED WHITE. PULLED RT GEAR TRANSDUCER AND INSP. LOOKED OK. WENT OUT AND TAXI CHECKED BRAKES FOR CONDITION OF BRAKING, CHECKED OK. R & R RT GEAR ANTI-SKID TRANSDUCER. DID ANTI-SKID RESPONSE CHECK PER CE 560 MM 32-42-30 PAGE 201. OPS CHECK GOOD.
HOT ELECTRICAL ODOR COMING FROM THE CABIN. ODOR STARTED AT FL100 AND CONTINUED TO GET WORSE. CREW TURNED DOWN THE HEATER CLOSED FOOT WARMERS, PULLED COFFEE POT OUT OF SLOT. ODOR DID NOT STOP. AT FL180 TO FL200 CREW MADE DECISION TO RETURN TO CLT ON DESCENT BEGAN TO QUIT AT FL100. ODOR WAS GONE ON THE GROUND.
TWO WING DEICE LINES AND CLAMPS LOCATED AT FUSELAGE AND WING LEADING EDGE, CHAFE FUSELAGE SKIN. SUBMITTER STATED SHRINK WRAP AND THERMOPROTECTION TAPE SHOULD BE EXTENDED FORWARD.
TWO WING DEICE LINES AND CLAMPS LOCATED AT FUSELAGE AND WING LEADING EDGE, CHAFE FUSELAGE SKIN. SUBMITTER STATED SHRINK WRAP AND THERMOPROTECTION TAPE SHOULD BE EXTENDED FORWARD.
FOUND 4 INCH VERTICAL CRACK ON LT SKIN OF RUDDER APPROXIMATELY 3 INCHES BELOW HINGE LINE OF TRIM TAB. SKIN REMOVED AND REPLACED. THIS IS THE 5TH INCIDENT OF A LT RUDDER SKIN CRACK.