N513QS

Part: PIN — LACK OF LUBE (ZONE 800) · airframe 9,190 hrs · 6,079 cycles

AFTER LANDING WE WERE UNABLE TO OPEN THE MAIN CABIN DOOR FROM THE INSIDE. WHEN PUSHING THE RED BUTTON AND TRYING TO LIFT THE HNDLE, IT WOULD ONLY RAISE ROUGHLY 1/4 INCH AND REMAIN LOCKED. AT THE SAME TIME THE YELLOW CABIN DOOR OPEN LIGHT WAS CYCLING ON AND OFF. IT TOOK SEVERAL MINUTES AND MULTIPLE ATTEMPTS BEFORE IT FINALLY OPENED. AFTER THE PX LEFT WE CYCLED THE DOOR MULTIPLE TIMES. THE ISSUE THEN BECAME THAT THE DOIR HANDLE WOULD OPERATE NORMALLY UNTIL IT MOVE ABOUT HALF WAY UP, THEN IT HIT SIGNIFICANT RESISTENCE REQUIRING MUCH MORE FORCE TO GET IT TO RAISE THE REST OF THE WAY FOR THE DOOR TO OPEN. CORRECTIVE ACTION: RELUBRICATED DOOR PINS. OPS CHECK GOOD. IAW CESSNA CE-680A AMM 52-10-00.

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 8,713 hrs · 5,785 cycles

CABIN EMERG LIGHT: EMERGENCY LIGHT UND SEAT 10 IS INOP. SEE STEPS FOR TROUBLESHOOTING. DISASSEMBLED FORWARD RIGHT COUCH/SIDE FACING SEAT TO GAIN ACCESS TO EMERGENCY LIGHT ASSY. REMOVED LIGHT PN CLE319-01-30 SN 239001194 AND INSTALLED NEW LIGHT PN CLE319-01-30 SN 202400000015364. RE ASSEMBLED SEAT. PERFORMED OPS CHECKS OF EMERGENCY LIGHT SYSTEM. OPS CHECK GOOD. WORK IAW CE-680A MM 33-50-00. OK TO RETURN TO SERVICE.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 7,204 hrs · 4,729 cycles

1 HYDRAULIC PUMP: IN FLIGHT WE GOT A RUMBLING FEELING FOR ABOUT 5 MIN. THE. GOT A HYD PRESS LOW L AMBER CAS MESSAGE. WHEN WE PUT THE LANDING GEAR DOWN WE GOT THE HYD VOLUME LOW AMBER CAS MESSAGE. FOUND LH HYDRO PUMP FAILED, REMOVED LH AND RH HYDRO PUMPS IA W CE680A 29-10-05 SEE DISCREPANCY 12 AND 13 FOR R&R PERFORMED FLUSH AND BLEEDING OF HYDRO SYSTEM IAW CE680A AMM 12-10-30 PERFORMED OPS AND LEAK. CHECK IAW CE680A AMM 29-10-00 OPS CHECK AND LEAK CHECK GOOD

Part: PUMP — FAULTED (RT ENGINE) · airframe 6,192 hrs · 4,125 cycles

ON APPROACH, WHITE SMOKE CABIN & COCKPIT. RAN QRH , DID NOT DETERMINE SOURCE OF SMOKE. BORESCOPED LT ENG 1ST STAGE HPC & 4TH STAGE HPC, NO DEFECTS IAW EMM 72-00-00. PERFORMED ENG CONSUMPTION RUN, ENG RAN APPROX 1 HOUR, NO DEFECTS, SMOKE, OR ODORS IAW EMM 71-00-00. BORESCOPED RT ENG, 1ST STAGE HPC & 4TH STAGE HPC IAW EMM 72-00-00. DURING ENG RUN, RT ENG OIL LEVEL FLUCTUATING. R & R OIL PUMP. INSTALLED ORIGINAL REPAIRED AGB & PERFORMED ENG RUNS & LEAK CHECKS, NO DEFECTS IAW EMM 71-00-00, 72-60-01, AND 79-20-05. MX FOUND AN AIR RESTRICTION ORIFICE IN APU BLEED LINES, BROKEN PIECE OF ORIFICE WENT DOWNSTREAM & RESTED ON ACM HEAT EXCHANGER. R & R DAMAGED APU BLEED LINE & REMOVED DEBRIS FROM EXCHANGER.

Part: BATTERY — DEFECTIVE (EMERGENCY LIGHTS) · airframe 6,071 hrs · 4,047 cycles

CABIN EMERG LIGHT: WHEN TESTING EMERGENCY LIGHTING SYSTEM, THE EMERGENCY LIGHTS WOULD NOT COME ON IN EITHER THE ARM OR ON POSTION. THEN WHEN EXCERCISING THE EMERGENCY LIGHTING SWITCH, MOST OF THE EMERGENCY LIGHTS ILLUMINATED, BUT THEN WOULD NOT TURN OFF WITH THE EMERGENCY LIGHT SWITCHNIN OFF POSTION AND NO OTHER POWER APPLIED ON AIRCRAFT. AFTER CYCLING THE BATTERY SWITCHES ON AND THEN OFF, WE WERE ABLE TO GET MOST OF EMERGENCY LIGHTS TO WORK NORMALLY EXCEPT THE FOLLOWING EMERGENCY LIGHTS STILL WILL NOT ILLUMINATE WITH EMERGENCY LIGHT SWITCH IN ON OR ARM POSITION: OVERHEAD READING LIGHT IN LAVATORY WILL NOT ILLUMINATE. FLOOR LIGHT IN LAVATORY WILL NOT ILLUMINATE. LEFT WING INSPECTION LIGHT WILL NOT ILLUMINATE. RIGHT WING INSPECTION LIGHT WILL NOT ILLUMINATE. REMOVED # 1 EMER BATT DUE TO NOT HOLDING A CHARGE AND INSTALLED A REPAIRED UNIT IAW AMM CH33-50-06 OP'S CK GOOD, REMOVED #2 ERNER BATT DUE TO NOT HOLDING A CHARGE AND INSTALLED A NEW UNIT IAW AMM CH33-50-06 OP'S CK GOOD, REMOVED #3 ERNER BATT DUE TO NOT HOLDING A CHARGE AND INSTALLED A NEW UNIT IAW AMM CH33-50-06 OP'S CK GOOD, REMOVED #4 ERNER BATT DUE TO NOT HOLDING A CHARGE AND INSTALLED A MODIFIED UNIT IAW AMM CH 33-50-06 OP'S CK GOOD.

Part: WIRE — BROKEN · airframe 5,672 hrs · 3,767 cycles

FLOOR EMERG EXIT LIGHT: EMER FLOOR LIGHT UNDER SEAT #8 IS INOP. AC WAS POWERED UP FOR 10+ MIN, CONDITION DIDN'T CLEAR. "CORRECTIVE ACTION" REPAIRED TWO BROKEN WIRES AT SEAT 8 EMERGENCY LIGHT CONNECTOR. FUNCTION TEST OF EMERGENCY FLOOR LIGHT PASSES.

Part: CANISTER — CRACKED (LT WING) · airframe 4,365 hrs · 2,884 cycles

DURING DESCENT, A FAINT SMELL OF FUEL WAS NOTICED IN CABIN FOR APPROXIMATELY 30 SECONDS. FOUND FUEL POOLING IN FLAP JACK SCREW TUBE(OUTBOARD TUBE) ON LH INBOARD FLAP WITH EVIDENCE OF JACK SCREW DAMAGE. ALSO NOTED JACK SCREW DAMAGE IN MID FLAP INBOARD JACK SCREW TUBE WITH WATER POOLING AS WELL. REMOVED L/H WING MID-FLAP INBOARD ACTUATOR CAN WELD ASSEMBLY. REMOVED L/H WING INBOARD FLAP OUTBOARD ACTUATOR CAN WELD ASSEMBLY IAW CE-680A SRM 51-40-05. FOUND WELD CANS INSTALLED INCORRECTLY RESULTING IN CONTACT WITH FLAP DRIVE JACK SCREWS (INVERTED). UPON REMOVAL OF WELD CANS FROM A/C FOUND CRACKS AT MOUNTING FLANGE WELDS ON WELD CAN ASSEMBLIES. P/N OFF 6922622-1 S/N OFF NSN NSTALLED NEW LH MIDFLAP INBOARD AND OUTBOARD FLAP ACTUATOR CANS IAW CESSNA CE680A SRM 51-40-05. P/N'S OFF AND ON - 6922622-1. AFTER INSTALLATION OF L/H MID-FLAP INBOARD & OUTBOARD FLAP ACTUATORS, OPERATED FLAPS THROUGH SEVERAL CYCLES & VISUALLY VERIFIED FLAP JACKSCREWS TRAVEL FREE & CLEAR OF BOTH CAN WELD ASSEMBLIES. REF CE-680A 27-50-00-5 FOR MX PERFORMED.

Part: CANISTER — DAMAGED · airframe 4,365 hrs · 2,884 cycles

FUEL STORAGE: DURING DESCENT FAINT SMELL OF FUEL WAS NOTICED IN CABIN FOR APPROXIMATELY 30 SEC THEN DISAPPEARED . UPON POST FLIGHT INSPECTION NOTICED FUEL ODOR COMING FROM LEFT BATTERY COMPARTMENT, NO LEAKS NOTED. "CORRECTIVE ACTION" REMOVED L/H WING MIDFLAP INBOARD ACTUATOR CAN WELD ASSEMBLY. REMOVED L/H WING INBOARD FLAP OUTBOARD ACTUATOR CAN WELD ASSEMBLY IAW CE-680A SRM 51-40-05. FOUND WELD CANS INSTALLED INCORRECTLY RESULTING IN CONTACT WITH FLAP DRIVE JACK SCREWS. UPON REMOVAL OF WELD CANS FROM A/C FOUND CRACKS AT MOUNTING FLANGE WELDS ON WELD CAN ASSEMBLIES. P/N OFF 6922622-1 S/N OFF NSN INSTALLED NEW LH MIDFLAP INBOARD AND OUTBOARD FLAP ACTUATOR CANS IAW CESSNA CE680A SRM 51-40-05. P/N'S OFF AND ON - 6922622-1.

Part: BATTERY BOX — ODOR · airframe 4,365 hrs · 2,884 cycles

DURING DESCENT FAINT ODOR OF FUEL WAS NOTICED IN CABIN FOR APPROXIMATELY 30 SEC THEN DISAPPEARED . UPON POST FLIGHT INSPECTION NOTICED FUEL ODOR COMING FROM LEFT BATTERY COMPARTMENT, NO LEAKS NOTED.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 3,960 hrs · 2,624 cycles

REPAIR OF CORROSION AND CHAFING ON HORIZONTAL UPPER AND LOWER SKINS. TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ27201M1 DATED 09/30/2020. HORIZONTAL STABILIZER UPPER AND LOWER SKIN DAMAGE (CHAFING/CORROSION).

Part: DOUBLER — CRACKED (NLG WW) · airframe 3,960 hrs · 2,624 cycles

REPAIR TO NOSE LANDING GEAR WHEEL WELL CRACKS. TEXTRON AVIATION STANDARD REPAIR SR-680A-ATA53-25890 DATED 06/01/2020, STANDARD REPAIR CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75. WITH FAA FORM 8100-9 DATED 06/01/2020.

Part: COWLING — DAMAGED (ZONE 400) · airframe 3,569 hrs · 2,357 cycles

RIGHT LOWER COWL DRAIN MAST FASTENERS HOLES OVER SIZED REF ENGINEERING MEMO DQ24931RRL1 DATED MARCH 2, 2020

Part: CLOSEOUT PANEL — CRACKED (RT AILERON) · airframe 179 hrs · 115 cycles

RT AILERON CENTER COVE CLOSEOUT PANEL IS CRACKED. ACCOMPLISHED REMOVAL OF RT AILERON IAW MM 57-60-05. ACCOMPLISHED REMOVAL OF RT AILERON CENTER COVE CLOSEOUT ANGLE IAW SRM 51-40-05. REMOVED RT LOWER ANGLE ASSEMBLY IAW SRM 51-40-05. ACCOMPLISHED INSTALLATION OF NEW ANGLE ASSEMBLIES, UPPER, LOWER AND SHROUD CENTER IAW SRM 51-40-05. AILERON CLOSE OUT PANEL. . AILERON TRAVEL CHECK OPS CHECK GOOD, NO DEFECTS NOTED IAW MM 27-10-00. VERIFIED AILERON TRAVEL CHECK.

Part: TUBE — BROKEN (RT ENG P3 LINE)

RIGHT HAND ENGINE OUTBOARD BLEED AIR VALVE P3 LINE FOUND BROKEN AT WELDED 'L' FITTING. BY VISUAL INSPECTION, SUSPECTED CAUSE IS VIBRATION AND FATIGUE AND POSSIBILITY OF FLAW IN WELD.

Part: LONGERON ASSY — CRACKED (LT ENG T/R)

FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY, ABOUT 2 INCHES FROM BUMPER. LONGERON ASSEMBLY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED.