N750GM

ATA 5344

Part: HINGE — BROKEN (ZONE 100) · airframe 12,469 hrs · 6,471 cycles

DURING FLIGHT PILOTS REPORTED AN AMBER CASS MESSAGE FUEL DOOR OPEN AND THEY ALSO EXPERIENCED VIBRATION DURING THE FLIGHT. SINGLE POINT DOOR HINGE FOUND BROKEN. IT IS LIKELY THAT THE DOOR WAS NOT LATCHED PROPERLY PRIOR TO FLIGHT CAUSING THE DAMAGE.

ATA 3222

Part: STRUT — DISCHARGED (ZONE 700) · airframe 12,246 hrs · 6,364 cycles

AFTER TAKEOFF, THE PILOT ATTEMPTED TO RETRACT THE LANDING GEAR AND THE LAND GEAR DID NOT RETRACT. THE NOSE LANDING GEAR WAS SERVICED. GEAR AND GEAR RETRACTION OPERATIONAL CHECKS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE

ATA 2720

Part: RUDDER — MALFUNCTIONED (ZONE 300) · airframe 12,062 hrs · 6,285 cycles

THE CREW REPORTED THAT AFTER 50 MINUTES THE RUDDER TRIM BEGAN TO TURN TO THE LEFT & THEN TO THE RIGHT

ATA 2720

Part: ACTUATOR — MALFUNCTIONED (ZONE 300 RUDDER) · airframe 12,059 hrs · 6,282 cycles

THE PILOT REPORTED UPON DEPARTURE WHETHER TURNING RIGHT OR LEFT, THE UPPER RUDDER / AIRCRAFT SWAYED LEFT AND RIGHT BEFORE CORRECTING

ATA 3436

Part: GPWS — WARNING MESSAGE (ZONE 200) · airframe 11,864 hrs · 6,190 cycles

PILOT REPORTED A EGPWS AND WIND SHEAR FAIL EICAS MESSAGE

ATA 3230

Part: NONE — NONE · airframe 9,868 hrs · 5,344 cycles

AIRCRAFT ARRIVED IN WICHITA WITH VENT LINE AND EMERGENCY EXTEND LINE DISCONNECTED FROM THE EMERGENCY GEAR EXTENDED BOTTLE. THE MAINTENANCE MANUAL WAS NOT FOLLOWED WHEN THE GEAR BOTTLE WAS LAST INSTALLED, AND BOTH LINES TO THE EMERGENCY GEAR BLOW-DOWN BOTTLE WERE NOT CONNECTED. PER THE MAINTENANCE TRACKING SYSTEM OF THE CUSTOMERS, THE LAST TIME THIS BOTTLE WAS IN MAINTENANCE WAS 21/JAN/2022 BY BRIAN K ELWICK A&P 3280426. SEE MAINTENANCE MANUAL STEPS BELOW B. INSTALL PNEUMATIC STORAGE BOTTLE (REFER TO FIGURE 201). WARNING: FOR AIRPLANES THAT HAVE THE PRESSURE GAGE INSTALLED DIRECTLY TO THE BOTTLE, DO NOT INSTALL THE GAGE FITTING TOO DEEP INTO THE BOTTLE. THE FITTING CAN OBSTRUCT THE AIRFLOW IF YOU ACTUATE THE BLOWDOWN. NOTE: IF A REPLACEMENT CONTROL VALVE ASSEMBLY HAS BEEN INSTALLED, REMOVE FITTINGS FROM EXISTING VALVE ASSEMBLY AND INSTALL IN REPLACEMENT VALVE ASSEMBLY IN SAME MOUNTING ORIENTATION, USING NEW O-RINGS AND BACKUP RINGS. (1) PLACE PNEUMATIC STORAGE BOTTLE IN MOUNTING POSITION AND SECURE TOP OF BOTTLE TO PLATE ASSEMBLY BY INSTALLING SCREWS. (2) SECURE RETAINING CLAMP AROUND BOTTLE AND TIGHTEN CLAMP NUT. NOTE: IF BLEED VALVE WAS REMOVED TO FACILITATE REMOVAL/INSTALLATION, INSTALL BLEED VALVE AT THIS TIME USING NEW SEALS AS APPLICABLE. (3) IDENTIFY AND CONNECT VENT LINE, PRESSURE LINE AND GAGE LINE TO FITTINGS ON PNEUMATIC BOTTLE. (4) POSITION CONTROL CABLE THROUGH STORAGE BOTTLE LEVER STOP BRACKET AND INSTALL CABLE STOP. INSTALL CABLE CLAMPS AND ADJUST CABLE PER PROCEDURE IN PNEUMATIC STORAGE BOTTLE CONTROL CABLE REMOVAL/INSTALLATION. (5) SERVICE THE PNEUMATIC STORAGE BOTTLE. FOR BOTTLE SERVICING PROCEDURE, REFER TO CHAPTER 12, HIGH PRESSURE PNEUMATIC SERVICE VALVES - SERVICING, AND LANDING GEAR AND BRAKE EMERGENCY PNEUMATIC SYSTEMS - SERVICING. (6) PLACE THE AIRPLANE ON JACKS. REFER TO CHAPTER 7, JACKING - MAINTENANCE PRACTICES. (7) PERFORM A CHECK OF THE GEAR BLOWDOWN SYSTEM. REFER TO THE SECTION GEAR BLOWDOWN OPERATIONAL TEST IN THE TOPIC, LANDING GEAR HYDRAULIC SYSTEM - ADJUSTMENT. (8) CHECK FOR LEAKAGE AT FITTINGS, VALVE AND LINES. (9) CLOSE LEFT NOSE COMPARTMENT DOOR. (10) REMOVE AIRPLANE FROM JACKS AND INSTALL REMOVED ACCESS PANELS.

ATA 2210

Part: NONE — NONE · airframe 9,516 hrs · 5,192 cycles

DURING APP THE PILOT REPORTED THAT ON THE EICAS THAT THE FGC AMBER CAS BEGAN TO FLICKER. DURING THIS TIME THEY ALSO EXPERIENCED A PRIMARY TRIM FAILURE. WHEN AIRCRAFT LANDED, THE PRIMARY PITCH TRIM AND FGC WERE TROUBLESHOT AND THE FUNCTIONAL TEST PERFORMED AND MAINTENANCE WAS UNABLE TO DUPLICATE THE FAULT.