N323QS
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
ENROUTE AT FL410 R ENGINE OIL PRESSURE BEGAN SLOWLY DECAYING UNTIL THE OIL PRESSURE LOW R CAS ILLUMINATE, FOLLOWED SHORTLY BY A ENGINE VIBRATION R CAS.WE SUBSEQUENTLY SHUT DOWN THE RIGHT ENGINE IAW QRH AND DIVERTED TO KAPA.
AFTER TOUCHDOWN WHEN APPLYING BRAKES GRADUALLY BETWEEN 70 AND 80KTS THE LEFT MAIN BRAKE STARTS GRABBING AND SHIMMERING NOTICEABLY. WHEN BELOW ANTI SKID SPEED NO GRABBING NOR SHIMMERING IS OCCURRING. INSPECTED LT INBD AND OTBD BRAKE, WHEEL ASSEMBLIES AND SURROUNDING AREA WITH NO DEFECTS NOTED. REMOVED LH INBOARD AND OUTBOARD WHEEL ASSEMBLIES AND REMOVED GREASE FROM BRAKE ASSEMBLES. REMOVED EXCESSIVE BRAKE DUST FROM BRAKE ASSEMBLIES WITH NITROGEN. INSTALLED LH INBOARD AND OUTBOARD WHEEL ASSEMBLIES. ALL WORK REF. MM 32-41-00 AND 32-41-20.
MECHANICALLY BLENDED 8 AREAS ON RT H-STAB LOWER SKIN ON THE AFT EDGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED , TREATED, PRIMED AND TOP COATED AREAS PER NETJETS REQUEST FOR TECHNICAL DISPOSITION REPORT.
MULTIPLE EMERGENCY LIGHTS IN THE CABIN AND EXTERIOR NOT ILLUMINATING WHEN EMERGENCY LIGHT SWITCH IN THE ARMED POSITION. RAN APU FOR 45 MINUTES TO CHARGE BATTERY PACKS, WITH NO SUCCESS. REMOVED # 1 EMERGENCY BATTERY, REMOVED #1 EMERGENCY BATTERY, INSTALLED REPAIRED CUSTOMER SUPPLIED EMERGENCY BATTERY. REMOVED RT NR 2 BATTERY PACK. INSTALLED CUSTOMER SUPPLIED REPAIRED BATTERY. REMOVED RT NR 3 BATTERY PACK. INSTALLED REPAIRED CUSTOMER SUPLLIED BATTERY PACK. REMOVED NR 4 BATTERY . INSTALLED REPAIRED CUSTOMER SUPPLIED BATTERY, OPS CHECKED GOOD, RESTORED ACCESS IN REFERENCE TO AMM 33-50-10.
FORWARD CABIN EMERGENCY LIGHTS DO NOT ILLUMINATE WITH THE SWITCH IN THE ON POSITION. AFT CABIN EMERGENCY LIGHTS DO ILLUMINATE. CORRECTIVE ACTION: TROUBLESHOT EMERGENCY LIGHTING SYSTEM AND VERIFIED THAT THE CABIN DOOR EXIT LIGHT AND FWD RH WORK SURFACE LIGHT WERE NOT ILLUMINATING. REMOVED #1 EMERGENCY BATTERY FOR TROUBLESHOOTING. PERFORMED EMERGENCY LIGHTING BATTERY PACK CAPACITY TEST IAW CESSNA 680 AMM 33-50-10 AND DETERMINED THAT THE #1 EMERGENCY BATTERY IS INOP. REFER TO SQK 2-2 OF THIS WO# DBZHA FOR REPLACEMENT OF EXISTING #1 EMERGENCY LIGHT BATTERY AND INSTALLATION OF THE CUSTOMER SUPPLIED EMERGENCY LIGHT BATTERY AND FUNCTION CHECK. SEE SQK 3-1 OF THIS WO# DBZHA FOR ADDITIONAL TROUBLESHOOTING PER NETJETS MCC.
FOUND 8 NUTPLATES WITH CORROSION LOCATED INSIDE OF PANEL 154BC. NUT PLATES HOLD ON THE MED SPADE DOOR. REMOVED EXISTING MED SPADE DOOR AND 8 NUTPLATES FOR ACCESS. MECHANICALLY BLENDED AREAS OF CORROSION IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FOR NOMINAL THICKNESS. REPAIRED LEVEL 2 CORRODED STRUCTURE FOUND ON MAIN ENTRANCE SPADE DOOR NUTPLATE DOUBLER LOCATED INSIDE PANEL 154BC IAW WITH NETJETS RFTS-113008 REV.0 TITLED: N323QS (680-0134) BELLY FAIRING SUPPORT CORROSION, DATE: 25FEB25.
FOUND THE EMERGENCY EXIT DOOR CORRODED OUTER SKIN ALONG CONTOUR RING EDGE AREA, REMOVED CONTOUR RINGS AND FOUND ADDITIONAL AREAS OF CORROSION. SENT DOOR OUT FOR REPAIRS. NOTE: EMERGENCY EXIT DOOR P/N 6911251-4.
REMOVED RH MIDDLE FLAP ASSEMBLY TO WORK CORROSION ON FWD, OUTBD LUG. MECHANICALLY REMOVED RH MIDDLE FLAP ROLLER, OUTBD LUG CORROSION, INBD SURFACE IAW C680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW NETJETS ENGINEERING RFTS-113063 REV. 0 TITLE: N323QS (680-0134) RH MIDDLE FLAP ROLLER LUG CORROSION, DATE: 25FEB25.
MECHANICALLY REMOVED 2 AREAS OF CORROSION FROM RH WING AFT SPAR, FWD FACE IN RH MLG WHEEL WELL. EVALUATED AND FOUND BLENDED AREAS WERE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS ENGINEERING RFTS-113108, REV.0, TITLE: N323QS (680-0134) LH AND RH WING AFT SPAR CORROSION, DATE: 18MAR25.
MECHANICALLY REMOVED 4 AREAS OF CORROSION LOCATED ON TAILCONE SERVICE DOOR FRAME ASSEMBLY WITH ADDITIONAL 4 AREAS OF CORROSION AFTER FRAME ASSEMBLY WAS REMOVED IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FOR NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS ENGINEERING RFTS-113054 REV.0 TITLE: N323QS (680-0134) TAILCONE SERVICE DOOR FRAME CORROSION, DATE: 25FEB25.
MECHANICALLY REMOVED 3 AREAS OF CORROSION LOCATED IN LH MLG WHEEL WELL, AFT SPAR, LOWER CLIP IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW NETJETS AQRD ENGINEERING RFTS-113108 REV.0 TITLE: N323QS (680-0134) LH AND RH WING AFT SPAR CORROSION, DATE: 18MAR25
BLENDED 5 AREAS OF CORROSION LOCATED ON EXTERIOR FUSELAGE SKIN ALONG THE SEAM NEXT TO THE PILOT DV WINDOW IN ZONE 243 ALONG SEAM, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
REMOVED NUT PLATES FROM PANELS LANDS TO ACCESS CORROSION AND MECHANICALLY REMOVED ALL AREAS OF CORROSION BEHIND VERTICAL STABILIZER PANELS 341ER, 341DR, 341CR, 341BR, AND 341AR, 341AL, 341BL, 341CL, AND 341DL, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS. INSTALLED NEW NUT PLATES.
REPAIRED 2 AREAS OF CORROSION LOCATED ON LH HORIZONTAL STABILIZER UPPER SKIN FORWARD OF PANEL 351AC, BY BLENDING CORROSION, PERFORMING NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS ENGINEERING ORDER BY CLEANING, TREATING, AND PRIMING AREAS.
REPAIRED THE LH UPPER WING SKIN LOCATED UNDER AND ADJACENT TO THE AFT DRAG ANGLE (WING-TO-FUSELAGE FAIRING STRUCTURE) BY BLENDING CORROSION, PERFORMING NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER TEXTRON FIELD REPAIR BY CLEANING, TREATING, AND PRIMING AREAS.
MECHANICALLY BLENDED CORROSION FROM CORROSION FROM CENTER STRINGER UNDER PANELS 154AC AND 154BC, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
MECHANICALLY BLENDED CORROSION FROM LH OVER-WING FUEL ADAPTER LAND., PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED AREAS OF CORROSION LOCATED ON UPPER EXTERIOR FUSELAGE SKIN IN ZONE 254, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
MECHANICALLY REMOVED 1 AREA OF CORROSION LOCATED ON RH GEARWELL AFT SPAR, FWD FACE, LOWER CLIP, INBD OF WS 37.00 IAW C680 SRM 51-70-02. FOUND CORROSION BLEND TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 LIMITATIONS EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLEND IAW TEXTRON ENGINEERING FIELD REPAIR FR-680-0134-14777 REV- TITLE: FIELD REPAIR-CORROSION,RH WING, AFT SPAR, LOWER CAP WS 18.50-23, DATE: 21FEB2025. PERFORMED INITIAL HI-LOK BOLT HOLE INSPECTION, HOLES #118-120 USING NDT EDDY CURRENT AS INSTRUCTED IN ORIGINAL REPAIR TABLE 2 SPECIAL INSPECTION REQUIREMENTS. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: (SPECIAL INSPECTION REQUIREMENTS) COMPONENT 6922435-4 RH FWD ANGLE, WS 18.50-23, FIGURE 4, TECHNIQUE BHET2, INITIAL HOURS 14,736.1, RECURRING HOURS 6,000.
BLENDED CORRODED AREA ON THE RH UPPER WING SKIN, JUST AFT OF THE LEADING EDGE AND OUTBOARD OF THE WING WALK, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED 6 AREAS OF CORROSION ON THE RH LOWER OUTBOARD WING SKIN, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED CORRODED AREAS FROM THE OUTBOARD ROLLER LUG OF THE RH WING MIDDLE FLAP, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
REMOVED EMERGENCY BRAKE LINES AND CARRY THROUGH FITTINGS FROM RH AND LH RIBS AT WS 37, BLENDED CORRODED AREAS, PERFORMED, NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED 15 AREAS OF CORROSION ON LH UPPER WING IN ZONES 551 AND 552 (OUTBOARD WING) PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED 6 AREAS OF CORROSION ON LH UPPER WING (INBOARD WING) PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
MECHANICALLY REMOVED CORROSION LOCATED AROUND RH OVERWING FUEL FILLER, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAID AREAS PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
BLENDED ONE AREA OF CORROSION FROM LH LOWER WING FORWARD OF THE AILERON, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING, AND PRIMING AREAS.
MECHANICALLY REMOVED CORROSION LOCATED AROUND LH OVERWING FUEL FILLER, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED AREAS PER TEXTRON REPAIR MEMO BY CLEANING, TREATING, AND PRIMING AREAS.
FAILED TO TEST ON PREFLIGHT. LIGHTS DO NOT ILLUMINATE IN ARM POSITION. LIGHTS FUNCTION NORMALLY WHEN SELECTED ON. PERFORMED EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE. OPS CHECK GOOD. IAW TC-FLT-33-1001.
MAIN DOOR PRE CATCH NOT FLUSH WITH PANEL. ON LAST LEG DOOR WOULD NOT CATCH. CORRECTIVE ACTION: EVALUATED THE PRECHATCH SYSTE. SYSTEM IS COMPLETELY FUNCTIONAL 5/5 CHECKS SATISFACTORY . HANDLE DOES NOT SIT FLUSH AS REPORTED . FROM EVALUATION IT LOOKS AS IF THE HANDLE IS MATING AGAINST THE PLASTIC AT THE LOWER PORTION OF THE HANDLE BEFORE IT IS AT THE TOP OF THE HANDLE , CAUSING IT TO STICK OUT SLIGHTLY AT THE TOP, THERE IS NO OBSTRUCTION AND DOES NOT CAUSE THE SYSTEM TO NOT WORK. GAINED ACCESS AND PERFORMED AN ADJUSTMENT OF THE PRE CATCH HANDLE PLATE SCREW, ADJUSTMENT WAS ONLY ABLE TO BE MINOR TO BE WITHIN AMM LIMITS . AFTER REASSEMBLY OF THE STAIRS , FOUND THE ADJUSTMENT MADE VERY LITTLE DIFFERENCE, THERE IS NO ADJUSTMENT ON THE HANDLE ITSELF IN REGARDS TO THE STAIRS AS WELL AS NO TOLERANCE LISTED IN AMM.MCC ADVISED IF DOOR IS RIGGED WITHIN AMM LIMITS , CLEAR ITEM. CONFIRMED PRECATCH IS IN PROPER RIGG. REASSEMBLED MED STEPS. PERFORMED ANOTHER OPS CHECK OF THE SYSTEM. CHECKS SATISFACTORY .REF CESSNA 680 52-10-40
THE MAIN CABIN DOOR HAS APPROXIMATELY TWO TO THREE INCHES OF PLAY IN IT WHEN IT IS FULLY DOWN AND LOCKED. FOUND THE OVER CENTER PUSHROD LOOSE. RESECURED THE PUSHROD AND OPERATED THE DOOR SEVERAL TIMES AND FOUND IT SATISFACTORY. WORK DONE IAW CE-680 AMM 51-10-30
NJA CORROSION FOUND ON LEFT-AFT-VERTICAL-STAB SPAR CAP. ACCOMPLISHED TEXTRON AVIATION ENGINEERING MEMO DQ41418M1 DATED 10/5/2023.
APU (EXCEPT GENERATOR): IN FLIGHT AT 25,000FT WITH APU ON WITH MAX AIR SELECTED , A STRONG ODOR IN CABIN . TURNED APU OFF AND ODOR VERY SLOWLY DISSIPATED. ODOR DID NOT SMELL ELECTRICAL OR OILY. COMPUED WITH NJA TASK CARDS, THE COALESCER WAS A LLTTLE DIRTY ⢠CLEANED SOCK AND HOUSING, REINSTALLED ASSY. INSPECTED APU WITH BORESCOPE ⢠NO DEFECTS NOTED. RAN EACH BLEED AIR SOURCE INDEPENDENTLY (R ENG, LENG AND APU) FOR SEVERAL MINUTES. RAN BLEED AIR SYSTEM MIRRORING PILOTS CONFIGURATION DURING THE SQUAWK. NOT ABLE TO DUPUCATE ANY TYPE OF ODOR AT THIS TIME. IT IS NOTED THAT BOTH ENGINES WERE PREVIOUSLY REPLACED PRIOR TO THIS WRITE-UP, WHICH IS SUSPECTED TO BE THE CAUSE OF THE ODOR. REF NJA TC·C68-21·1001 AND TCC68-49-1001.
FOUND CORROSION GOING UNDER RH WING AFT DRAG ANGLE. FOUND ADDITIONAL 80 AREAS OF CORROSION UNDER DRAG ANGLE. MECHANICALLY REMOVED 94 AREAS OF CORROSION FROM RH WING AFT DRAG ANGLE AREA IAW CESSNA 680 SRM 51-70-02. EVALUATED REMAINING THICKNESS AND FOUND TO BE OUT OF LIMITS. SUBMITTED TO TEXTRON ENGINEERING FOR REPAIR. WITH THE AMOUNT OF MATERIAL LOSS, TEXTRON ENGINEERING WANTED THE SKIN REPLACED. REMOVED RH WING UPPER IB TRAILING EDGE SKIN P/N UNKNOWN S/N UNKNOWN DUE TO LEVEL 2 CORROSION. INSTALLED NEW CUSTOMER SUPPLIED RH WING UPPER IB TRAILING EDGE SKIN P/N 6922681-70 S/N 29476585. CESSNA 680 SRM 51-40-03, 51-40-06, 51-40-08 AND CSMP 20-40-20.
BLENDED CORROSION ON LOWER FUSELAGE SKIN AROUND TCAS ANTENNA CARRY THRU CONNECTORS. FOUND CORROSION TO BE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02. REPAIRED CORROSION ON LOWER FUSELAGE SKIN AROUND TCAS ANTENNA CARRY THRU CONNECTOR PER TEXTRON REPAIR MEMO DQ 29978 M1, SUBJECT: "680-0134 LOWER FUSELAGE SKIN DAMAGE", DATED: 05/13/2021.
MECHANICALLY BLENDED CORROSION FROM RUDDER COVE ON VERTICAL STAB AFT SPAR RH CLIP IAW CESSNA 680 SRM 51-70-02. REFER TO SQK 103-2 OF THIS WO FOR NDT. EVALUATED REMAINING THICKNESS AND FOUND TO BE OUT OF LIMITS. SUBMITTED INFO TO ENGINEERING. COMPLIED WITH TEXTRON ENGINEERING REPAIR MEMO DQ29867M1 SUBJECT: VERTICAL STABILIZER AFT SPAR CAP CORROSION, DATED: MAY 4, 2021. WORK PERFORMED IAW CESSNA 680 SRM 51-20-01, 51-40-03 AND SPM 51-30-10.
MECHANICALLY REMOVED CORROSION LOCATED ON VERTICAL STAB, AFT SPAR, LH SPAR CLIP JUST BELOW LOWER CROSS MEMBER. FOUND CORROSION EXCEEDING C680 SRM 51-70-02 LIMITATIONS AND SUBMITTED TO TEXTRON ENGINEERING FOR REPAIRS. REPAIRED CORROSION IAW TEXTRON ENGINEERING MEMO DQ29983M1 SUBJECT: 680-0134 N323QS, RRL VERTICAL STABILIZER LH AFT SPAR CLIP DATED MAY 14, 2021.
REMOVED CRACKED RUDDER TORQUE TUBE P/N UNKNOWN FROM RUDDER P/N 6933000-19 S/N 0134 AND INSTALLED NEW CUSTOMER SUPPLIED RUDDER TORQUE TUBE P/N 6933025-55 PER CESSNA 680 SRM 51-40-03, 51-40-06, 55-40-09, CSPM 20-40-20.
BLENDED 2 AREAS OF CORROSION ON UPPER AFT EDGE OF RH VERTICAL STAB SKIN. FOUND CORROSION REMOVED TO BE BEYOND LIMITS PER CESSNA 680 SRM 51-70-02. REPAIR CORROSION PER TEXTRON REPAIR MEMO DQ29966M1, SUBJECT "RIGHT-HAND VERTICAL STABILIZER SKIN CORROSION", DATED: 05/12/2021.
BLENDED 1 AREA OF CORROSION ON TOP OF LT HORIZONTAL STAB JUST FORWARD OF WEDGE PANEL 351AC (INBOARD OF THE LT ELEVATOR) PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. TREATED, PRIMED, AND TOP COATED PER TEXTRON ENGINEERING MEMO.
MAIN CABIN DOOR HEAVY TO CLOSE. CABIN DOOR MAKES NUMEROUS CREAKING NOISES AS IT CLOSES. REMOVED AND REPLACED BOTH LUBRICATED SPRINGS DUE TO BROKEN AND CRACKED SPRINGS. RIGGED CABLE TENSIONS, OPERATIONS CHECK GOOD, DOOR CLOSES MUCH EASIER. ALL WORK DONE, IAW CH 52-10-50 OF 680 MODEL.
SHORT FINAL GOING TO EGE AIRPORT. APROX 8000 FT. EMERGENCY PRESS, ACM BLEED LEAK, BAGGAGE HEAT FAIL AND POSSIBLE ACM OVER TEMP MESSAGE COME ON AND WENT OUT. ELECTRICAL BURNING SMELL, WAS NOTICED SHORTLY AFTER. LANDED UN EVENTFULLY. RAN CHECK LIST FOR ACM BLEED LEAK CHECKLIST. // SIGN OFF // REMOVED AND CLEANED SOCK. SOCK DID NOT LOOK DIRTY OR OILY, REINSTALLED.INTERROGATED CMC AND FOUND PC CARD JC108 L BLEED AIR MONITOR PIN 39 STATUS WAS "OVERHEAT". RH SIDE CARD INDICATED "NORMAL ALONG WITH ALL THE OTHER BLEED AIR PC CARDS.PERFORMED DUCT BURN OUT TASK CARD. WHILE ON STEP 1. D. ACM OVERTEMP WITH EMER PRESS ILLUMINATED AND THE APU AUTO SHUT DOWN. NO SMELL IN CABIN NOTED. CALLED TEAM 680 ADVISED TO BORESCOPE THE HEAT EXCHANGER AND LOOK FOR DEBRIS.I WOULD GET A ACM OVERHEAT SWITCH COMING PN 927223-2-3 IM NOT SURE WHICH PC CARD IS INSTALLED A -21 OR A -26, DEPENDING ON SB680-30-03R1, BUT MAYBE GET A PC CARD COMING AS WELL PN 6918625-26 OR -21 REMOVED ACM TEMP SENSOR, INSTALLED NEW TEMP SENSOR AND ATTEMPTED DUCT BURN IN TC. SAME OUTCOME AS BEFORE BUT WITH ACM BLEED LEAK MESSAGE. WE BELIEVE THAT WHAT WE SAW YESTERDAY WAS IN FACT THE LEAK MESSAGE AND NOT THE OVERTEMP. INSPECTED BLEED LOOP AROUND ACM AND FOUND SENSE LINE BRACKET BROKEN AND LOOP SITTING ON THE ACM DUCTING REPLACED BROKEN BRACKETS ON BLEED LEAK DETECTION SENSING ELEMENT WITH NEW ONES, P/N: 6914170-20 AND P/N: 6914190-3. REF. CE680 MM 36-20-10. DUCT DUCT BURN OUT COMPLETED ON LINE 4 OF THIS WORK ORDER. OPS/LEAK CHECKS GOOD. NO BURNING OR ANY OTHER UNUSUAL SMELLS NOTED. REPLACED BROKEN BRACKETS ON BLEED LEAK DETECTION SENSING ELEMENT WITH NEW ONES, P/N: 6914170-20 AND P/N: 6914190-3. REF. CE680 MM 36-20-10. DUCT DUCT BURN OUT COMPLETED ON LINE 4 OF THIS WORK ORDER. OPS/LEAK CHECKS GOOD. NO BURNING OR ANY OTHER UNUSUAL SMELLS NOTED. SPOKE WITH BRYSON SKILES AND VERIFIED HEAT EXCHANGER WAS BORESCOPED AND NO DEBRIS WERE FOUND.
SHORT FINAL GOING TO AIRPORT. APROX 8000 FT. EMERGENCY PRESS, ACM BLEED LEAK, BAGGAGE HEAT FAIL AND POSSIBLE ACM OVER TEMP MESSAGE COME ON AND WENT OUT. ELECTRICAL BURNING SMELL, WAS NOTICED SHORTLY AFTER. LANDED UN EVENTFULLY. RAN CHECK LIST FOR ACM BLEED LEAK CHECKLIST.
BLENDED CORRODED AREA ON THE LOWER HINGE BRACKET OF THE MIDDLE RUDDER HINGE ON THE VERTICAL STABILIZER, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPLACED CORRODED PART WITH NEW HINGE PLATE P/N 6931050-60 PER CESSNA 680 SRM 51-40-03, 51-40-06, 51-40-08 AND CSPM 20-40-20.
BLENDED, PERFORMED NDT AND TREATED CORRODED AREAS ON THE LH HORIZONTAL STABILIZER SPAR CAP IAW REPAIR MEMO.
BLENDED, PERFORMED NDT AND TREATED CORRODED AREAS ON THE LT WING AFT SPAR LOWER CAP, LOCATED BEHIND ACCESS PANEL 730DL, IAW REPAIR MEMO.
1) HYDRAULIC FLUID LEAK - COMPLETE LEFT AND RIGHT HYDRAULIC FLUID LOSS OCCURRED AFTER TAKEOFF WITH GEAR RETRACTED. POSTFLIGHT REVEALED HYDRAULIC FLUID COMING FROM RIGHT ENGINE DRAIN MAST. NO HYDRAULIC FLUID VISIBLE AROUND LEFT OR RIGHT MAIN LANDING GEAR. 2) EMERGENCY LANDING GEAR BLOW DOWN WAS PERFORMED DUE TO TOTAL LOSS OF HYDRAULIC FLUID. 3) OVERWEIGHT LANDING - AIRCRAFT LANDED OVERWEIGHT AT 28,300 POUNDS TO FULFILL EMERGENCY LANDING PROCEDURES FOR TOTAL HYDRAULIC FAILURE. 4) EMERGENCY BRAKE HANDLE WAS PULLED DURING PERFORMANCE OF TOTAL HYDRAULIC FLUID LOSS EMERGENCY.
RAISED LANDING GEAR AND THE NOSE GEAR DID NOT RETRACT, AS INDICATED BY A GREEN NOSE GEAR LIGHT, THE RED UNLOCK LIGHT, AND AERODYNAMIC NOISE WITH THE GEAR HANDLE SELECTED UP. WE CYCLED THE GEAR AND IT EXTENDED AND RETRACTED NORMALLY. GEAR EXTENSION FOR LANDING WAS NORMAL. R&R STEERING CONTROL UNIT PN 9914650-2 0322
CLIMBING THROUGH FL400, AN ODOR WAS NOTICED BY CREW, FOLLOWED BY VISUAL SMOKE IN BOTH THE CABIN AND COCKPIT. SHORTLY AFTER, TWO AMBER CAS MESSAGES FOR ACM OVERTEMP AND EMERGENCY PRESSURIZATION ILLUMINATED. EMERGENCY DESCENT WAS ACCOMPLISHED ALONG WITH COMPLIANCE WITH THE CHECKLIST. DIVERTED. REMOVED AND REPLACED THE RT MASS FLOW SHUTOFF VALVE DUE TO BEING FAILED IN THE CLOSED POSITION. OPS AND LEAK CHECKED GOOD IAW AMM 21-10-00, VERIFIED OPERATIONAL OF ECU /ACM WITH ENGINES AND APU RUNNING WITH NO SMOKE OR ACM OVERHEAT MESSAGES.
NLG FRAME CRACK. ACCOMPLISHED ENGINEERING LETTER DQ11281M1 DATED FEB 23, 2018, 680-0134 NLG RIGHT SIDE FRAME (P/N 6713072-31) CRACK.
IN FLIGHT, WITH WING ANTI-ICE ON, A STRONG ODOR IN COCKPIT AND CABIN. NOT VERY EVIDENT WITH ONLY ENGINE STAB ANTI-ICE ON. APU WAS OFF. ALSO EXPERIENCED TO A LESSER DEGREE DURING GROUND CHECK. REMOVED THE LT ENGINE DUE TO CAUSING STRONG ODOR IN COCKPIT AND CABIN & INSTALLED A NEW SERVICEABLE ENGINE. PERFORMED AN OPS CHECK AND LEAK CHECK WITH NO DISCREPANCIES NOTED. ALL WORK PERFORMED IAW AMM 71-00-10, 710-00-30, 71-00-10 AND EMM 71-00-00.
IN FLIGHT, WITH WING ANTI-ICE ON, STRONG ODOR IN COCKPIT AND CABIN. NOT VERY EVIDENT WITH ONLY ENGINE STAB ANTI-ICE ON. APU WAS OFF. ALSO EXPERIENCED TO A LESSER DEGREE DURING GROUND CHECK.
CORROSION ON THE MAIN CABIN DOOR FORWARD HINGE HALF.
FOUND CORROSION ON TAIL STRINGER AREA. REPAIRED IAW ERO-8588679.
DURING SCHEDULED INSPECTION WE FOUND THAT BLEED AIR TUBE PN 6955300-9 CRACKED AT THE APU FIREWALL BULKHEAD TO BLEED AIR TUBE ASSEMBLY ATTACH FLANGE. THE CRACK WAS TWO TO THREE INCHES LONG LOCATED AT THE WELD BETWEEN FLANGE & TUBE ASSEMBLY. A NEW TUBE ASSEMBLY WAS ORDERED & INSTALLED. WE HAVE FOUND THIS SAME DEFECT ON ACFT IN THE PAST.
UPON GEAR RETRACTION WITH THE HANDLE IN THE UP POSITION. THE RED, UNLOCK, LIGHT ILLUMINATED. PERFORMED THE APPROPRIATE CHECKLIST ITEM & ACTION RETURNED FOR LANDING WITHOUT FURTHER INCIDENT. VISUALLY INSPECTED LT, RT & NOSE UP LOCK SWITCHES, NO DEFECTS NOTED. CHECKED SWITCHES FOR PROPER ADJUSTMENT. NOSE UP LOCK ADJUSTED WITHIN LIMITS THE LT & RT SWITCHES WERE OUT OF ADJUSTMENT, SHORT. ADJUSTED BOTH TO 0.57 INCHES PERFORMED GEAR SWINGS, NORMAL INDICATIONS EACH TIME. THE RED UNLOCK LIGHT DID NOT ILLUMINATE ONCE UP & LOCKED. DOWN JACKED ACFT. SERVICED HYD RESERVOIR AS REQUIRED, OPERATIONS CHECKED GOOD. WORK DONE IAW MM 32-60-00 & 12-12-02.
NLG FAILED TO RETRACT AFTER TAKE OFF. RED UNLOCK LIGHT ILLUMINATED. HEARD FOUR BUMPS AND FELT THROUGH AIRFRAME. RED ITEMS CHECKLIST COMPLETED WITH A NORMAL UNDERWEIGHT LANDING. JACKED ACFT. CHECKED OPERATION OF LANDING GEAR. NOSE GEAR RETRACTED NORMAL. NOSE GEAR UNSAFE LIGHT STAYED ON ALONG WITH A BUMPING NOISE FROM THE NLG AREA. CHECKED NOSE GEAR UP SWITCH FOUND SWITCH PLUNGER STICKING. LUBED SWITCH, OPERATES SATISFACTORILY. REMOVED NLG UPLOCK SWITCH, AND REPLACED WITH NEW SWITCH IAW MM 32-60-00. OPS CHECKED GOOD.
NOSE GEAR FAILED TO RETRACT AFTER TAKE OFF. RED UNLOCK LIGHT WAS ILLUMINATED. HEARD FOUR BUMPS AND FELT THEM THROUGH THE AIRFRAME. RED ITEMS CHECKLIST WAS COMPLETED WITH A NORMAL UNDERWEIGHT LANDING. JACKED ACFT. CHECKED OPERATION OF LANDING GEAR. NOSE GEAR RETRACTED NORMAL. NOSE GEAR UNSAFE LIGHT STAYED ON ALONG WITH A BUMPING NOISE FROM THE NOSE WHEEL AREA. CHECKED NOSE GEAR UP SWITCH FOUND SWITCH PLUNGER STICKING. LUBED SWITCH NOW NOSE GEAR OPERATES SATISFACTORILY. CONTACTED MX COORDINATOROF FINDINGS. REMOVED NLG UPLOCK SWITCH AND REPLACED WITH NEW SWITCH. INSTALLED NEW SWITCH IAW MM 32-60-00. OPS CHECKED GOOD.
RED UNLOCK LIGHT REMAINED ON AFTER NORMAL GEAR RETRACTION. NO ABNORMAL SOUNDS AND ALL 3 GREEN LOCK LIGHTS WENT OUT. FOLLOWED CHECK LIST. NORMAL GEAR EXTENTION WITH NO ABNORMAL SOUNDS. R & R NLG ELECTRICAL HARNESS IAW MM 32-20-00. PERFORMED LANDING GEAR OPS CHECK IAW MM 32-00-00. CHECKED TAXI LIGHT IAW MM 33-41-00. NO DEFECTS NOTED AT THIS TIME.
GEAR UNSAFE LIGHT ON WHEN GEAR WAS SELECTED UP. NOSE GEAR KEPT BANGING AS IF CYCLING UNTIL GEAR HANDLE WAS SELECTED DOWN. MAIN GEAR RETRACTED AND EXTENDED NORMALLY. PERFORMED INITIAL MLG OPS CHECK, GEAR CYCLED GOOD IAW MM 32-00-00 (REV 31). CHECKED NOSE GEAR FREE FULL CABLE RIG-CHECKED GOOD IAW MM 32-30-70. NLG STRUT EXTENSION CHECK 9.8" CHECKED UPLOCK RIG CHECKED GOOD IAW MM 32-60-00. FROZE NLG, LT MLG, AND RT MLG UPLOCK SWITCHES CHECKING FOR CHANGE IN RESISTANCE VALUES WHEN EXERCISING SWITCHES BETWEEN UP/DOWN POSITIONS. NO FAULTS NOTED.
EMERGENCY ESCAPE HATCH INSPECTION. FOUND A SMALL AREA OF CORROSION APPROX 2.5" X 0.750", ALONG LOWER EDGE. CORROSION IS UP TO 0.016" IN DEPTH. FOUND AN ADDITIONAL SMALL AREA OF CORROSION APPROX 0.5" IN SIZE ALONG AFT CENTER EDGE. CORROSION IS UP TO 0.007" IN DEPTH ALL SKINS HAVE A NOMINAL THICKNESS OF 0.190". PERFORMED NDT EVALUATION. REPAIRED CORROSION IAW EA-0120. PERFORMED NDT INSPECTIONS FOR CRACKS AND MATERIAL THICKNESS AFTER REPAIR. NO CRACKS NOTED AND FOUND TO BE WITHIN MINIMUMS. PERFORMED EDDY CURRENT ON BLENDED AREAS PER NDT ET 01. FOUND NO CRACK INDICATIONS. PERFORMED ULTRASONIC THICKNESS INSPECTION ON BLENDED AREAS OF E-EXIT DOOR EDGING PER NDT UT 01.
WHILE IN CRUISE FLIGHT, THE LT AND RT AMBER FUEL BOOST ON CAS MESSAGES ILLUMINATED. RAN THE APPROPRIATE CHECKLIST WITH NO CHANGE NOTED. PRIOR TO CAS MESSAGES ILLUMINATING, HAD BEEN IN CROSSFEED. CROSSFEED WAS OFF APPROX 1 MINUTE BEFORE CAS MESSAGES ILLUMINATED. OPERATED ACFT ENGINES, OPERATED THE THROTTLES AT ALL SETTINGS, TRANSFERED FUEL LT TO RT AND RT TO LT, CROSSFEED CHECKED GOOD AT ALL THROTTLE SETTINGS. MANUALLY TURNED ON BOOST PUMPS LT AND RT, NO DEFECTS NOTED. DISCREPANCY DID NOT DUPLICATE ON GROUND, SHUT ENGINES AND POWERED DOWN. WORK DONE IAW MM 28-20-10.
MLG RED UNLOCK LIGHT ILLUMINATED DURING CLIMBOUT AT 28,000 FT. NO ABNORMALITIES PRIOR TO UNLOCK LIGHT. MLG EXTENDED NORMALLY. FOUND LT UPLOCK SWITCH IS DEFECTIVE. REMOVED LT MLG UPLOCK SWITCH & INSTALLED NEW SWITCH IAW MM 32-60-00. RIGGED LT UPLOCK SWITCH. OPS CHECKS ALL SWITCHES, OPS CHECKED GOOD IAW MM 32-80-00.
DURING REPAIR OF THE LT WING L/E, FOUND CORROSION IN AN AREA THAT IS NOT ACCESSIBLE WITHOUT REMOVING RIVETS AND THE DIFFUSER TUBE. THESE AREAS WERE BLENDED AND PRIMERED USING REPAIR DATA FROM MFG. THIS SITUATION WOUDL HAVE CONTINUED TO CORRODE WITHOUT ANY INDICATION HAD MX NOT BEEN NEEDED IN THIS AREA FOR OTHER REASONS.
AFTER GEAR RETRACTION, RED "GEAR UNSAFE" ANNUNCIATOR DID NOT EXTINGUISH. THE NOSE GEAR SOUNDED AS THOUGH IT WAS RETRACTED, BUT THEN THERE WAS HEARD APPOX. 6 LOUD BANGS IN SUCCESSION AS NOSE GEAR ATTEMPTED TO RECYCLE ITSELF, ACCOMPANIED BY A COINCIDENTAL FLICKERING "GEAR UNSAFE" ANNUNCIATOR. NOSEGEAR THEN STOWED, WITH NO UNSAFE INDICATIONS. R & R NOSE GEAR UPLOCK ACTUATOR. R & R SHUTTLE VALVE. PERFORMED SEVERAL SATISFACTORY GEAR SWINGS. OPS AND LEAK CHECKED GOOD. WORK PERFORMED IAW MM 32-30-50.
DEPARTED, WHEN WE SELECTED THE GEAR UP WE HEARD 3 LOUD BANGS FROM THE NOSE GEAR , SAW THE NOSE GEAR DOWN AND GEAR UN-SAFE LIGHT WHERE FLASHING THEN ALL WENT OUT. GEAR EXTENSION NORMAL WITH 3 GREEN INDICATION. RETURNED TO IAD WITH OUT INCIDENT. FOUND A WIRE STRAND SHORTING PIN A OF P G001 (NOSEGEAR UPLOCK SWITCH) TO GROUND. REMOVED WIRE STRAND. CHECK NOSEGEAR STRUT SERVICE, FOUND LOWER CHAMBER LOW. SERVICED NOSE STRUT IAW MM CH 32-20-00. PERFORMED SEVERAL GEAR SWINGS, OPS CHECKED GOOD IAW MM CH 32-00-00.
AFTER GEAR RETRACTION, NOSE GEAR BANGED UP AND DOWN FOR 15 TO 20 SECONDS. COULD BE FELT AND HEARD IN CABIN. GEAR CAME DOWN NORMAL. FOUND STRUT WOULD NOT EXTEND FULLY DUE TO PRESSURE LOSS IN LWR CHAMBER. DISASSEMBLY & REPACKED STRUT WITH NEW SEAL, NUT, PISTON, & SPACER. REASSEMBLED, INSTALLED & SERVICED NOSE STRUT. REF CMM 32-20-01 & MM 32-20-00. OPS CHECKS AND GEAR SWINGS SATIS.
LG INDICATED "UNSAFE" DURING RETRACTION.
REMOVED AND REPLACED NLG UPLOCK SWITCH (P/N S3177-1, NSN). PERFORMED OPS CHECKS AND SWITCH RIGGING. WORK DONE IAW MM CH 32-60-00.
DURING LANDING, AT 50 KTS WHEN APPLYING BRAKES, AIRCRAFT PULLS HARD TO THE LT AND DURING TAXI IN LT BRAKE GRABS WHEN LIGHTLY APPLYING LT BRAKE. WE TAXIED AIRCRAFT AGAIN WITH ANTISKID ON. PLANE PULLS LT. WHEN BRAKES USED AND WITH ANTISKID OFF PLANE PULLS TO THE RT WHEN BRAKES ARE USED. BLED BRAKES IAW MM 32-42-00 REPAIRED BAD SPLICE ON PIN Y OF PLUG J65 IN LT WHEEL WELL IAW WD 32-40-01. REPLACED CONNECTOR P65 IAW WD 91-10-00. OPERATIONAL CHECKED GOOD BY FLIGHT CREW NO DEFECTS NOTED. P/N : ON/OFF MS3126F20-39P S/N: ON/ OFF NA.
ON LANDING, PILOT HAD NO BRAKE PRESSURE ON THE RT SIDE, BRAKE PRESSURE CAME UP SUDDENLY AFTER 3 SECONDS. FOUND BRAKE RESERVOIR LEVEL HALF WAY ON UPPER SIGHT GAGE, SERVICED BRAKE RESERVOIR IAW CESSNA 560 MM CHAPTER 12-10-02. BLED BRAKE SYSTEM AND PERFORMED ANTI-SKID FUNCTIONAL TEST IAW CESSNA 560 MM CHAPTER 32-42-00, NO DEFECTS OR LEAKS NOTED.
BRAKE PUMP RUNS CONTINUOUSLY WHEN BRAKES ARE APPLIED. LOW BRAKE PRESS ANNUNCIATOR ILLUMINATES.
FOUND THE LEFT ENGINE THRUST REVERSER CONTROL LINKAGE HAD CUT INTO THE OUTER PROTECTIVE COVER OF THE MOTIVE FLOW FUEL HOSE. THE FUEL HOSE ASSY WAS REPLACED AND THE T/R CONTROL LINKAGE SAFETY WIRE REPOSITIONED TO PREVENT IT FROM CHAFING THE HOSE.