N301QS

Part: SPAR CAP — CORRODED (WING) · airframe 11,342 hrs · 7,663 cycles

CORROSION, LH AND RH WINGS, LOWER REAR SPAR CAPS, WS 33 TO 36. ACCOMPLISHED REPAIR DEFINITION NO. FR-680-0010-4784, MAJOR REPAIR, FIELD REPAIR - CORROSION, LH AND RH WINGS, LOWER REAR SPAR CAPS, WS 33 TO 36 DATED OCT.31, 2018 - AND FAA FORM 8100-9 DATED OCT.31, 2018 WEIGHT AND BALANCE WAS NOT AFFECTED.

Part: FITTING — DAMAGED (RUDDER ACTUATOR) · airframe 10,284 hrs · 6,919 cycles

RUDDER BIAS ACTUATOR UPPER GIMBAL MOUNT IS CONTACTING STRUCTURE. FOUND UPPER RUDDER BIAS ACTUATOR HAVING ENLONGATED BOLT HOLES. MEASURED DAMAGED HOLE ON RUDDER BIAS FITTING P/N 6960556-49 MOUNTING HOLE.MEASURED DAMAGED HOLE ON RUDDER BIAS FITTING MOUNTING HOLES AND CLEANED REPAIR USING ACETONE. APPLIED ALODINE AND INSTALLED BUSHING WET WITH EPOXY PRIMER IAW AEROSPACE ERO-898765 REV IR DATED JULY 6, 2017.

Part: TORQUE TUBE — CORRODED (RUDDER) · airframe 10,284 hrs

FOUND RUDDER LOWER TORQUE TUBE TO HAVE INTERNAL CORROSION. FOUND DURING RUDDER INSTALLATION AFTER PAINT. REQUEST ADDITIONAL TIME FOR THE REMOVAL OF THE SEIZED RUDDER TORQUE TUBE AND FOR TRAVEL CHECK OF RUDDER. REMOVED LOWER RUDDER TORQUE TUBE AND INSTALLED CUSTOMER SUPPLIED NEW LOWER RUDDER TORQUE TUBE. VERIFIED PROPER RUDDER TRAVELS. DONE IAW MM 27-20-00.

Part: UNKNOWN — ODOR (CABIN) · airframe 10,016 hrs · 6,733 cycles

10 MINUTES AFTER REACHING CRUISE ALTITUDE, AN OILY SMOKE ODOR IN THE CABIN AND DISCOVERED THAT THE CABIN WAS VERY SMOKEY. DURING DIVERSION THE SMOKE CLEARED AND CAME BACK SEVERAL TIMES BEFORE LANDING. INSPECTED ACM DUCTS FOUND NO OIL RESIDUE. RAN ENGINES WITH ECS ON AND OBSERVED NO FOUL ODORS RELATED TO OILY SMOKE. COMPILED WITH NJA ECS DUCT BURN OUT PROCEDURE.

Part: SKIN — DAMAGED (AILERON) · airframe 9,359 hrs · 6,276 cycles

AIRCRAFT HAS HAIL DAMAGE. EVALUATED HAIL DAMAGE IAW SRM 51-00-03. FOUND AILERONS & ELEVATOR DAMAGE OUT OF LIMITS & SENT OUT FOR REPAIRS. REMOVED & REINSTALLED REPAIRED AILERONS & ELEVATORS IAW MM 57-60-00 & 55-20-00. LT & RT AILERON WAS BALANCED IAW SRM CHAPTER 51-60-01 & WAS FOUND TO BE WITHIN BALANCE LIMITS AT THIS TIME. LT & RT ELEVATOR WAS BALANCED IAW SRM CHAPTER 51-60-02 & WAS FOUND TO BE WITHIN LIMITS AT THIS TIME.

Part: FILTER ELEMENT — MISMANUFACTURED · airframe 6,974 hrs

DURING A SCHEDULED INSPECTION, REMOVED THE HYD CASE FILTER ELEMENT. TRIED TO INSTALL A NEW FILTER ELEMENT IN THE FILTER HSG BOWL, IT WOULD NOT SEAT TO THE BOTTOM OF THE BOWL. UPON FURTHER INSPECTION WE FOUND THAT THE FILTER ELEMENT OUTSIDE DIAMETER WAS LARGER THAN THE FILTER BOWL INSIDE DIAMETER. THIS FILTER ELEMENT WAS RETURNED TO MFG FOR EVALUATION AND A SERVICE CONDITION REPORT WAS SENT TO MFG UNDER REPORT 662147.

Part: FILTER ELEMENT — MISMANUFACTURED · airframe 6,974 hrs

DURING A SCHEDULED INSPECTION, REMOVED THE HYD CASE FILTER ELEMENT. TRIED TO INSTALL A NEW FILTER ELEMENT IN THE FILTER HOUSING BOWL, IT WOULD NOT SEAT TO THE BOTTOM OF THE BOWL. UPON FURTHER INSPECTION, FOUND THAT THE FILTER ELEMENT OUTSIDE DIAMETER WAS LARGER THAN THE FILTER BOWL INSIDE DIAMETER. THIS FILTER ELEMENT WAS RETURNED TO MFG FOR EVALUATION AND A SERVICE CONDITION REPORT WAS SENT TO MFG UNDER REPORT NR 662148.

Part: FILTER ELEMENT — MISMANUFACTURED · airframe 6,974 hrs

DURING A SCHEDULED INSPECTION, REMOVED THE HYD CASE FILTER ELEMENT. TRIED TO INSTALL A NEW FILTER ELEMENT IN THE FILTER HOUSING BOWL, IT WOULD NOT SEAT TO THE BOTTOM OF THE BOWL. ON FURTHER INSPECTION, FOUND THAT THE FILTER ELEMENT OUTSIDE DIAMETER WAS LARGER THAN THE FILTER BOWL INSIDE DIAMETER. THIS FILTER ELEMENT WAS RETURNED TO MFG FOR EVALUATION AND A SERVICE CONDITION.

Part: TUBE — CRACKED (APU BAY) · airframe 6,178 hrs

DURING A SCHEDULED MX CHECK, FOUND THIS TUBE ASSY CRACKED ABOUT HALF WAY AROUND THE FIREWALL FLANGE AT THE WELD.

Part: DIFFUSER — CRACKED (RT ENGINE) · airframe 6,178 hrs

DURING SCHEDULED MX, FOUND RT ENGINE INLET LIP DIFFUSER TUBE CRACKED. WHEN WE WERE REPLACING THIS TUBE WE FOUND THIS FLANGE WAS CRACKED 1.75 INCHES FROM THE END OF THIS PART. THE ENGINE INLET PN 6952100-5 HAS 3 OF OF THESE FLANGES THAT MAKE A COMPLETE CIRCLE AROUND THE INLET LIP. THE OTHER FLANGES WERE CRACK FREE. THE FLANGE CRACK WAS LOCATED AT THE 1 O'CLOCK POSITION ON THE INLET. AN SCR AND PICTURES HAVE BEEN SENT TO MFG UNDER SCR REPORT NR 627082.

Part: CONTROL HANDLE — INOPERATIVE (MLG) · airframe 6,007 hrs · 4,064 cycles

AFTER TAKEOFF, LANDING GEAR HANDLE WOULD NOT MOVE OUT OF THE DOWN POSITION. THERE WERE NO ASSOCIATED CAS MESSAGES. ALL 3 LANDING GEAR WERE LOCKED DOWN WITH GREEN LIGHTS-- NO RED. REPLACED LANDING GEAR CONTROL HANDLE IAW MM CH 32-30-10. OPS CHECKS GOOD.

Part: GENERATOR — BURNED (RT A/C) · airframe 5,595 hrs · 3,788 cycles

AFTER STARTING THE RT ENGINE WE NOTICED THE RT WINDSHIELD HEAT INOPERATIVE CAS MESSAGE WAS DISPLAYED. SHORTLY AFTER THAT, DETECTED ELECTRICAL SMOKE AND THE LINE CREW WERE MOTIONING FOR US TO SHUT THE ENGINES DOWN. FOUND RT ENGINE A/C GENERATOR BURNED UP. REMOVED GENERATOR AND INSTALLED AN O/H EXCHANGE UNIT IAW MM 24-20-10. OPS CHECKED NORMAL.

Part: I/O MODULE — INOPERATIVE · airframe 5,311 hrs · 3,575 cycles

CYAN "AHRS BASIC" LOSS OF RT DATA. NR 2 N1/ITT/FUELFLOW/QTY/FUELTOTAL DASHED LINES & NR 2 DC VOLTS/AMPS & BATTERY VOLT/AMPS & BATTERY TEMP. AMBER RADAR ALT LIGHT. SWAPPED GEN I/O CARDS & RELOAD SOFTWARE. RT SIDE DID NOT COME UP, SHOWED DASHES ON ENG INDICATORS AND BATTERY. PUT CARDS BACK IN ORIGINAL POSITIONS, RELOADED SOFTWARE NOW HAD CARD IS IN MAU NR 3. POWERED ON SYS & VERIFIED FAILURE IS CURRENTLY ON LT SIDE SYS. REMOVED NR 3 AND NR 4 GENERIC I/O MODULES, RESTORED MODULES TO ORIGINAL POSITIONS. REMOVED NR 4 GENERIC I/O MODULE, INSTALLED MODIFIED MODULE IAW MM 34-17-00. LOADEDED MODULE SOFTWARE IAW MM 34-23-10. OPS CHECKED GOOD. EICAS DISPLAY AND MESSAGES VERIFIED NORMAL.

Part: ACTUATOR — INOPERATIVE · airframe 5,009 hrs · 3,388 cycles

IMMEDIATELY AFTER TAKEOFF, PRIMARY TRIM AND AUTOPILOT FAILED. SECONDARY TRIM OPERATED NORMAL. R & R PRIMARY STAB ACTUATOR WITH AN O/H UNIT. R & R ACTUATOR CONTROL UNIT WITH AN O/H UNIT. COMPLIED WITH ALL RIGGING PROCEDURES AND OPS CHECK. OPS CHECK GOOD. NO DEFECTS NOTED. WORK PERFORMED IAW MM CH 27-40-00 AND 27-40-00.

Part: CONTROLLER — FAILED (TE FLAPS) · airframe 4,441 hrs · 3,024 cycles

FLAPS FAILED IN ZERO POSITION. R & R FLAP CONTROLLER ASSY IAW MM 27-51-00. OPS CKS GOOD.

Part: SWITCH — OUT OF ADJUST (BRAKE SYSTEM) · airframe 3,428 hrs · 2,368 cycles

DURING T/O ROLL AT 60-70 KTS THE RED "NO TAKEOFF" AND AMBER PARKING BRAKE LOW PRESSURE CAS MSG ILLUMINATED. T/O WAS ABORTED. PARKING BRAKE HANDLE WAS IN THE RELEASED (DOWN) POSITION. ADJUSTED PARKING BRAKE SWITCH MM. CHAPTER 32-42-70. OPS CHECKS NORMAL.

Part: ACTUATOR — OUT OF ADJUST (STAB TRIM) · airframe 2,787 hrs · 1,920 cycles

AUTOPILOT DISCONNECTS AND AUTOPILOT (FAIL A CAS) MSG COMES ON ONCE THE NOSEDOWN TRIM (PRIMARY) SETS TO +1.2. C/W HORIZONTAL STABILIZER TRIM ADJUSTMENT AND TEST IAW CE680 M/M 27-40-00. ADJUSTED ACTUATOR AS REQUIRED. TRAVEL AND OPS CHECK GOOD.

Part: SERVO — MALFUNCTIONED · airframe 2,785 hrs · 1,917 cycles

AUTO PILOT DISCONNECTS IN FLIGHT BY ITSELF. REMOVED AND REPLACED AILERON SERVO IAW MM 22-10-00. C/W AUTOPILOT SERVO DRIVE ADJUSTMENT AND TEST IAW MM 22-10-02. OPS CHECK GOOD.

Part: LAMP — SMOKE (CHART LIGHT) · airframe 2,615 hrs · 1,813 cycles

CAPTAINS YOKE MOUNTED CHART LIGHT SMOKES WHEN TURNED OFF. REPLACED CAPTAINS YOKE MOUNTED (CHART) MAP LIGHT ASSY WITH A NEW LIGHT ASSY IAW MM 27-13-00. OPS CHECKED GOOD.

Part: CONTROL CABLE — MISINSTALLED (SPOILER) · airframe 2,343 hrs · 1,610 cycles

ROLL SPOILER CABLE P/N S3779-4P233.7M WAS ROUTED INCORRECTLY OVER LOW FRICTION PULLEY. CABLE WAS FOUND ROUTED THROUGH TOOLING HOLE IN BRACKET P/N 6960236-17 RATHER THAN ENGAGING PULLEY. THE BRACKET TOOLING HOLE EXHIBITED WEAR FROM THE CABLE RIDING (CUTTING) INTO THE TOOLING HOLE.

Part: INDICATOR — ERRATIC (COCKPIT) · airframe 2,136 hrs · 1,454 cycles

COPILOTS AIRSPEED ERRATIC ON TAKE OFF ROLL FOUND INSECT LODGED IN RT PITOT TUBE. REMOVED RT PITOT TUBE FROM MOUNT AND REMOVED OBSTRUCTION WITH DRY NITROGEN. REINSTALLED PITOT TUBE AND PERFORMED PILOTS AD CO-PILOTS COMBINED LEAK RATE CHECK AND NR 1 AND 2 PFD ALT., AIRSPEED AND MACH AIRSPEED CORRELATION I.A.W. CE680 M/M CH. 34-11-00-700. ALL CHECKS GOOD.

Part: LANDING GEAR — UNKNOWN (RIGHT) · airframe 1,977 hrs · 1,353 cycles

RT GEAR WOULD NOT INDICATE DOWN (RED UNLOCK LIGHT ON, NO RT GREEN GEAR LIGHT ). ON DOWNWIND GEAR BLEW DOWN SUCCESFULLY (3 GREEN LIGHT) LANDED WITHOUT INCIDENT. REMOVED AND REPLACED RT MAIN ACTUATOR IAW CE680 M/M 32-30-40. OPS CHECKED GOOD.

Part: CARBON SEAL — LEAKING (RT ENGINE) · airframe 1,822 hrs · 1,257 cycles

RT ENG OIL PRESSURE BEGAN DROPPING AT FL310. ONCE IT REACHED BELOW 35 PSI THE THROTTLE WAS BROUGHT TO IDLE. ONCE THE OIL PRESSURE REACHED 15, THE THROTTLE WAS PUT INTO CUTOFF. ALL CAS MESSAGES AND EICAS INDICATIONS WERE PRESENT. EMER CL D5, B1 THEN CZ PROCEDURES WERE FOLLOWED. REMOVED RT ENG AC ALT. REMOVED SEAL P/N 30B46458-01. INSTALLED NEW SEAL P/N 307B458-01. INSTALLED AC ALT CLEANED OIL FROM COWLING. RESERVICED OIL. RAN ACFT TO POWER. OPS AND LEAK CK GOOD ALL IAW MM 72-60-01.

Part: O-RING — LEAKING (HYDRAULIC SYS) · airframe 1,371 hrs · 936 cycles

REPEAT DISCREPANCY AT CRUISE ABOUT 45 MINUTES INTO FLIGHT HYD LEVEL LOW EICAS MESSAGE APPEARED. OBSERVED HYD VOLUME AT 110 CU IN FOLLOWED CHECKLISTS, UNLOADED HYD PUMPS. DIVERTED, ABLE TO CONSERVE ENOUGH FLUID TO EXTEND GEAR NORMALLY THEN UNLOADED HYD PUMPS AGAIN. NO OTHER HYD SYS ACTUATED AFTER EICAS MESSAGE. AFTER LANDING OBSERVED RED FLUID HAD LEAKED OUT OF ACCESS PANEL ON BOTTOM OF RT PYLON. REMOVED AND REPLACED O-RING AND RETAINER FOR RT PYLON HYD FILTER AND SERVICED HYD RESERVOIR IAW MM, ALSO REPLACED LOW PRESS SWITCH O-RING IAW MM. KEEP BLOWING OUT LOW PRESSURE SWITCH O-RING, REMOVED AND REPLACED RT PYLON MANIFOLD FILTER ASSY LEAK, OPERATIONALLY CHECKS GOOD.

Part: PRESSURE SWITCH — LEAKING (HYD SYS) · airframe 1,368 hrs · 934 cycles

WHILE DESCENDING TO LAND, HYD VOLUME LOW CAS MESSG POSTED. VISUAL CHECK NOTED HYD PRESS AT 300 PSI. VOLUME WAS DOWN TO 110 CU IN. HYD VOL LOW CHECKLIST CONSULTED. AIRCRAFT WAS SLOWED TO GEAR EXTENSION SPD AND GEAR WAS EXTENDED. LANDING GEAR EXTENDED. HYDRAULIC VOLUME DECREASED TO 40 CU IN AND PRESS WENT TO ZERO AFTER BOTH HYD PUMPS WERE UNLOADED. HYD RESIDUE WAS ALONG RT ENG. LANDING WAS NORMAL. EMER BRAKE WAS USED. TROUBLESHOT HYD LEAK TO RT HYD LOW PRESS SW IN RT PYLON. INSTALLED NEW PACKING. SERVICED HYD SYSTEM BLED SYSTEMS. RAN AIRCRAFT. PRESSURE AND LEAK CHECKS GOOD. WORK PERFORMED IAW CHAPTERS 32-42-10 AND 12-12-06 OF THE M/M.

Part: DISPLAY — BURNED (COCKPIT) · airframe 786 hrs · 528 cycles

RIGHT PFD / DU NR 4, ATTITUDE FAIL, HEADING FAIL, EVENTUALLY DU BLACKED OUT. FUMES IN THE COCKPIT. DU CAME BACK ON BEFORE LANDING. TROUBLESHOT TO BAD DU NR 4. REPLACED DU NR 4 AND DOWNLOADED FILES TO DU NR 4 IAW CE680 M/M 34-23-00. OP'S CHECK GOOD.