N627QS

Part: SKIN — DEBONDED (ZONE 500) · airframe 5,559 hrs · 3,679 cycles

DISBONDS ON THE UPPER WINGS BETWEEN THE OUTBOARD END OF STRINGERS AND THE COMMON SKIN DOUBLERS. THE SKIN AND COMMON DOUBLERS MAY ALSO EXHIBIT A GRADUAL DEVIATION FROM CONTOUR IN THESE REGIONS. THE EXTEND OF THE DEFECT IS LOCATED USING ULTRASONIC INSPECTION AND CORRECTED BY ADDING FASTENERS AND ADHESIVE TO THE DISBONDED AREAS. REFERENCE FIELD REPAIR SR-680A-ATA57-47522 DATED 05/MAR/2025.

Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 5,236 hrs · 3,489 cycles

DENT DISCOVERED ON TOP OF LEFT WING.2). FLAP: RIGHT FLAP HAS A NOTICEABLE DENT ON THE TOP DISCOVERED DURING PREFLIGHT INSPECTION. PERFORMED PERMANENT REPAIR IAW RFTS-112809 AND SPM 20-50-00.

Part: WIRE — PULLED (EMERGENCY LIGHTS) · airframe 4,682 hrs · 3,120 cycles

LAV FLOOR EMERGENCY LIGHT INOP. PERFORMED THE "EMERGENCY LIGHTS FAIL PREFLIGHT TEST" PROCEDURE FROM THE QRH. LIGHT REMAINED INOP. FOUND LAV FLOOR EMERGENCY LIGHT CONNECTOR WIRING PIN PULLED FROM CONNECTOR. REINSTALLED PIN OPS CHECK GOOD

Part: STINGER — CORRODED (ZONE 200) · airframe 2,085 hrs · 1,360 cycles

STINGER UPPER NUTPLATE DRAG ANGLES ARE CORRODED AT NUTPLATES.

Part: NONE — CHIPPED (ZONE 700) · airframe 2,085 hrs · 1,360 cycles

LH MLG AXLE PLATING DAMAGE (CHIPPED)

Part: NONE — NONE · airframe 1,648 hrs · 1,089 cycles

MAIN EXIT SIGN/LIGHT: MAIN CABIN EXIT LIGHTS ALL REMAIN ON AFTER SHUTDOWN. // SIGNOFF // RESET COCKPIT INERTIA SWITCH IAW CE-680AMM 33-50-11 OPS CHECKS GOOD.

Part: NONE — NONE · airframe 1,631 hrs · 1,077 cycles

LAV EMERG LIGHT: ON INITIAL EMER LIGHT TEST, FOUND LAV EMER FLOOR LIGHT IMOP. // SIGNOFF// POWERED ON A/C AND CONFIRMED SQWAK REMOVED TOILET FRONT PIECE TO ACCESS FLOOR STRIP CONNECTOR, FOUND CONNECTOR PF2010 PIN PUSHED BACK, REINSERTED PIN AND REINSTALLED TOILET PANEL TURNED ON EMERGENCY LIGHTS AND FLOOR STRIP LIGHT ALONG WITH ALL THE OTHER LIGHTS CAME ON, LEFT A/C POWERED ON FOR 2 HOURS TO LET EMERGENGY BATTERIES CHARGE WORK ACCOMPLISHED JAW C36B0A MM33-50-00 OPS CHECK GOOD.

Part: SKIN — CHAFED (ZONE 100) · airframe 1,608 hrs · 1,059 cycles

THE FUSELAGE LOWER SKIN (PN: 7411392-12) WAS CHAFED IN TWO AREAS FROM CONTACT WITH THE ANTI-ICE CROSSFLOW VALVE. THE VALVE IS REPOSITIONED PER TEXTRON AVIATION SB680A-30-10. CHAFE DAMAGE REPAIRED PER TEXTRON AVIATION SR-680A-53-22175, FAA FORM 8100-9 SUBMITTAL LETTER NO. 19-1711 DATED 7/19/2019.

Part: G SWITCH — FAILED (EMERGENCY EXIT) · airframe 1,232 hrs · 803 cycles

EMERGENCY EXIT SIGN/LIGHT: EMERGENCY LIGHTS WILL NOT TURN OFF WITH SWITCH IN OFF POSITION. LIGHTS ARE OVER THE MAIN CABIN DOOR (WHITE), 2 (RED) SIDE WALL LIGHTS NEXT TO MAIN CABIN DOOR AND UNDER SEAT FACING MAIN CABIN DOOR (WHITE).RESET "G" SWITCH IN COCKPIT PEDESTAL. EMERGENCY EXT LIGHTS EXTINGUISHED. OPS CHECKED GOOD. REF CE-680A M/M 33-50-11.

Part: PIVOT — CRACKED (HORIZ STAB) · airframe 14,248 hrs · 11,337 cycles

FOUND DURING INSPECTION: HORIZONTAL STAB AFT PIVOT FITTING CRACKED. P/N 6631102-31.

Part: FITTING — CRACKED (HORIZ STAB) · airframe 11,261 hrs

DURING A SCHEDULED INSPECTION, FOUND THE HORIZONTAL STABILIZER ATTACH FITTING CLIP CRACKED IN TWO PLACES. THE CRACKS WERE IN THE CUT OUT RADIUS ABOUT .12 INCH LONG. CLIP WAS SENT TO FOR EVALUATION. A REPORT WAS FILED UNDER SCR 708902.

Part: UNKNOWN — SMOKE (COCKPIT & CABIN) · airframe 10,989 hrs · 8,728 cycles

SMOKE WAS OBSERVED IN THE COCKPIT & CABIN. ODOR WAS ALSO OBSERVED.

Part: CONTROL CABLE — FRAYED (TAIL CONE)

WHILE TROUBLESHOOTING, AN AUTO PILOT PORPOISE DISCREPANCY, THE TECH PULLED ON A PRIMARY RUDDER CABLE IN THE TAIL CONE AND IT SNAPPED. THE CABLE HAS BEEN BROKEN EXCEPT FOR A FEW STRANDS. IT APPEARS THE CABLE WAS NOT RIDING IN A PULLEY AND WAS CHAFING ON THE UPPER CABLE GUARD. INCORRECT ROUTING MAY HAVE BEEN THE ROOT CAUSE FOR THE POTENTIAL FAILURE. 2 SETS OF EYES AR CRITICAL WHEN WORKING ON PRIMARY FLIGHT CONTROL SYS AND CRITICAL ACFT COMPONENTS.

Part: UNKNOWN — ODOR (CABIN) · airframe 9,077 hrs · 1,760 cycles

APPROX 1 HR INTO A FLIGHT, AT 41,000 AND IN NORMAL CRUISE MODE. CO-PILOT AND PILOT COULD DETECT AN ODOR OF FUEL. WENT TO BACK OF PLANE WHERE FOUR OTHER CREW MEMBERS COULD DETECT IT AS WELL. DURING DESCENT IT WASN'T AS NOTICABLE AT LOW POWER SETTINGS. INCREASED POWER AT INTERMEDIATE LEVEL OFFS, THE ODOR WOULD RETURN. TRIED TO ISOLATE THE ODOR BETWEEN THE LT & RT PRESSURE SOURCE BUT COULDN'T NOTICE ANY DIFFERENCE. PERFORMED ENGINE RUNS WITH BLEEDS ON TO SIMULATE WRITE-UP. NO FUMES WERE DETECTED AT THIS TIME UTILIZING A MULTIGAS DETECTOR SET ON THE JET A FUEL SETTING & RUNNING BOTH ENGINES AT ALL POWER SETTINGS.

Part: WATER SEPARATOR — ODOR (COCKPIT) · airframe 8,245 hrs · 6,501 cycles

DISTINCT EXHAUST ODOR IN COCKPIT AT TAKE OFF WITH APU ON AND APU BLEED AIR ON. WITH BLEED AIR OFF THE ODOR IS REDUCED. IN FLIGHT THERE IS AN EXHAUST ODOR (NOT AS DISTINCT). IT IS REDUCED WHEN EITHER PRESS SOURCE IS SELECTED. FOUND APU OIL OVERSERVICED. REMOVED OIL TO CORRECT LEVEL. IAW MM 12-11-03. INSPECTED WATER SEPARATOR/ COALESCER SOCK FOUND RESIDUAL OIL & DIRTY ODOR. REPLACED SOCK "NEW". MX IAW MM 21-51-00. FOUND APU FLOW DIVIDER TEE B-NUT - LEAKING FUEL AT APU PRIMARY FUEL MANIFOLD. TIGHTENED B-NUT. MX IAW MM 49-30-06, OPS CHECK GOOD.

Part: GYRO — INOPERATIVE (COCKPIT) · airframe 8,138 hrs · 6,424 cycles

AT FL 430, WITH PFD 2 SELECTED (RT SEAT FLYING) LT PFD COMMAND BAR TURNED BLUE ALONG WITH ALL TREND BARS AND COURSE INDICATORS. THE RED AIRSPEED TAPE DISSAPEARED AND THE ATTITUDE GYRO TURNED TO GRAY, VICA, BLUE AND BROWN. REPOSITIONED THE NR 1 PFD TO THE MFD POSITION, AND THE MFD TO THE NR 1 PFD POSITION IAW THE MM 34-25-01. OPS CHECK OF BOTH UNITS GOOD. MONITORED SYS FOR SEVERAL HOURS WITH NO DEFECTS NOTED.

Part: INDICATOR — MALFUNCTIONED (FUEL QTY) · airframe 7,466 hrs · 5,887 cycles

AFTER TAKE OFF (L) FUEL GUAGE ANNUNCIATOR ILLUMINATED. FUEL LOAD INITIALLY SHOWED 1000 LBS HIGH, THEN STABILIZED SHOWING 1000 LBS LOW AND REMAINED THERE.

Part: FLOW VALVE — INOPERATIVE (FUEL SYSTEM) · airframe 7,447 hrs · 5,872 cycles

MOVING THE FUEL TRANSFER SWITCH FROM LT TO OFF CAUSES THE L/R LOW PRESS ANNUN. TO ILLUMINATE MOMENTARY & TURN THE L/R FUEL BOOST PUMP ANNUN. ON. TROUBLESHOT TO RT MOTIVE FLOW VALVE. R & R VALVE IAW MM CH 28-21-06. OPS & LEAK CHECK GOOD.

Part: ACTUATOR — INOPERATIVE (MLG) · airframe 7,250 hrs · 5,715 cycles

LEFT GREEN DOWN AND LOCKED ANNUNCIATOR ILLUMINATED INTERMITTENTLY IN FLIGHT. HYDRAULIC PRESS LIGHT DID NOT ILLUMINATE. ALL OTHER INDICATIONS NORMAL. INSTALLED REPAIRED ACTUATOR IAW THE MM 32-30-04. OPS CKED GOOD

Part: INDICATOR — UNKNOWN (FUEL SYSTEM) · airframe 7,044 hrs · 5,546 cycles

AT BEGINNING OF TAKEOFF ROLL THE RT FUEL QUANTITY INDICATOR DROPPED TO ZERO AND THE RT FUEL GAUGE ANNUNCIATOR AND MASTER CAUTION ILLUMINATED. STARTED APU AND WAITED 15 MIN. CHECKED SIGNAL CONDITIONER LED'S NO FAULTS DISPLAYED. STARTED ENGINES & TAXIED ACFT. MONITORED RT FUEL GAUGE, NO FAULTS, ALL INDICATIONS NORMAL. SUMPED FUEL FROM TANKS, FUEL REMOVED CONTAINED A SMALL AMOUNT OF WATER. RAN ENGINES & TAXIED AGAIN. DURING TAXIING EXECUTED SEVERAL AGGRESSIVE STEERING MANEUVERS. NO FAULTS FOUND OR DISPLAYED. PERFORMED AN ADDITIONAL COMPLETE SHUTDOWN FOLLOWED BY ANOTHER FULL START OF ENGINES. NO FAULTS FOUND OR DISPLAYED ON SIGNAL CONDITIONER. REINSTALLED ACCESS PANELS.

Part: CONTROL CABLE — BROKEN (TAIL)

DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED. THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIES OF "S" PULLEYS MOUNTED IN THE HORIZ STAB. SHOULD MAKE THIS A TIME CHANGE ITEM. (K)

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 6,387 hrs · 4,986 cycles

BOTH L/R FUEL GAUGE ANNUNCIATORS ILLUMINATED ON TAKEOFF. TAKEOFF WAS ABORTED. FUEL QTY GAUGES BOTH READ ZERO. GAINED ACCESS TO LT/RT WING ROOT ELECTRICAL CONNECTORS FOR MOISTURE NONE FOUND. INSPECTED FUEL SIGNAL CONDITIONER FOR FAULT BITES NONE FOUND.

Part: PROBE — READS LOW (FUEL SYSTEM) · airframe 6,135 hrs · 4,787 cycles

ON TAKEOFF ROLL, MASTER CAUTION CAME ON, REJECTED TAKEOFF, LT FUEL GAUGE ANNUNCIATOR LIGHT ON. CONNECTED TEST SET, FOUND PROBE NR 6 READING LOW. REMOVED NR6 PROBE, CLEANED AND REINSTALLED, PROBE NOW READING IN SAME RANGE AS OTHER PROBES, C/W WET CAL IAW MM CH 28-41-00. OPS CHECKED GOOD. LEAK CHECKED GOOD.

Part: ACTUATOR — LEAKING · airframe 6,031 hrs · 4,718 cycles

ON TAKEOFF, GOT A STAB MISCOMPARE LIGHT AND THE HYDRAULIC PRESS LIGHT. REPLACED ACTUATOR DUE TO EXCESS LEAKAGE IN ACTUATOR IAW 560XL M/M 23-40-00. OPS AND LEAK CHECK GOOD.

Part: BRAKE — STUCK (MLG) · airframe 5,498 hrs · 4,271 cycles

LT BRAKE IS STICKING CAUSING CONTROL ISSUES WHILE TAXIING. INSTALLED AN OVERHAULED BRAKE IN LT POSITION IAW MM CH 32-42. INSTALLED AN OVERHAULED METERING VALVE IN LT POSITION IAW THE MM CH 32-42.

Part: PUSHROD — CHAFED (PAX DOOR) · airframe 1,758 hrs · 1,376 cycles

DURING ROUTINE INSPECTION FOUND MAIN ENTRY DOOR PUSHROD (OPENING/CLOSING) RUBBING AGAINST THE CUTOUT IN THE DOOR STRUCTURE. ADJUSTED PUSHROD TO PREVENT CHAFING, PERFORMED BLEND OUT REPAIR TO CABIN DOOR FORMER IAW MFG REPAIR DEFINITION REPORT NR S-560XL-5227/01RD.