N393GH

Part: STRUT — LEAKING (NLG) · airframe 5,702 hrs · 4,370 cycles

AFTER TAKEOFF THE CREW REPORTED THAT AFTER THE LG WAS RETRACTED THAT THE NLG DEPLOYED TO THE DOWN POSITION. TROUBLESHOOTING & INSPECTION FOUND THAT THE NLG HAD AN INTERNAL LEAK. THE INTERNAL LEAK IN THE STRUT WAS PREVENTING THE STRUT FROM FULLY EXTENDING AFTER TAKEOFF & THIS PREVENTED THE STRUT FROM ENGAGING GEAR UPLOCK HOOK. THE STRUT ASSEMBLY WAS REMOVED & AN OVERHAULED ASSEMBLY WAS INSTALLED. RETURNED TO SERVICE.

Part: RADAR — INTERFERENCE · airframe 5,604 hrs · 4,310 cycles

INTERMITTENT ISSUE WITH COMM STATIC. EXTENSIVE TROUBLESHOOTING WAS COMPLETED. THIS RADIO STATIC ISSUE HAD EVERYONE STUMPED. EVENTUALLY THE SOURCE OF THE STATIC WAS TRACKED DOWN TO A RF INTERFERENCE COMING FROM THE RADAR UNIT. NO CREW REPORTS ON ANY FAULTS IN OPERATION OF THE RADAR UNIT DURING THE COMM STATIC ISSUES. SEVERAL RADAR UNITS, 4 EACH, WERE INSTALLED WITH SN`S LESS THAN 3000 & EACH UNIT HAD EITHER BEEN REPAIRED OR OVERHAULED, BUT EACH EXHIBITED THE SAME RF INTERFERENCE WITH THE COMM RADIOS. IT WAS RESEARCHED & DISCOVERED THAT THE RADAR UNITS PN 622-8440-003 WITH A SN LESS THAN 3000 WERE CAUSING THE RF INTERFERENCE. A RADAR UNIT PN 622-8440-003 SN 3750 WAS INSTALLED & NO FURTHER RADIO STATIC INTERFERENCE HAS BEEN REPORTED.

Part: TRIM SWITCH — FAILED (HORIZ STAB) · airframe 5,514 hrs · 4,240 cycles

THE EMER STAB TRIM WAS INTERMITTENTLY WORKING IN THE DOWN POSITION. TROUBLESHOOTING FOUND THE EMER TRIM SWITCH TO BE FAILING & REQUIRED REPLACEMENT. THE DEFECTIVE SWITCH WAS REMOVED & A NEW SWITCH INSTALLED. FUNCTIONAL CHECKS WERE SATISFACTORY.

Part: RADAR — DEFECTIVE · airframe 5,376 hrs · 4,141 cycles

THE CREW REPORTED THAT THEY HAD INTERMITTENT RADAR FAULT ANNUNCIATIONS FOLLOWED BY RADAR THUMPING NOISE. TROUBLESHOOTING DETERMINED THE WEATHER RADAR PN 622-8440-003, SN 3680 WAS DEFECTIVE. THE RADAR UNIT WAS REPLACED WITH A REPAIRED UNIT.

Part: CVR — NO TEST (COCKPIT) · airframe 5,350 hrs · 4,125 cycles

THE CREW REPORTED THAT THE COCKPIT VOICE RECORDER WOULD NOT TEST. TROUBLESHOOTING FOUND THE CVR DEFECTIVE. THE UNIT WAS REPLACED WITH AN OVERHAULED CONDITION.

Part: SWITCH — DEFECTIVE (AIRSPEED) · airframe 5,104 hrs · 3,975 cycles

FLIGHT CREW REPORTED THAT DURING DESCENT TO LANDING, NORMAL PITCH TRIM OPERATED MUCH SLOWER THAN NORMAL. MX TROUBLESHOT THE NORMAL PITCH TRIM OPERATION AND FOUND THE 250 KT AIRSPEED SWITCH IN THE NR 1 ADC DEFECTIVE.

Part: PRINTED CKT BOARD — DEFECTIVE (EXTERNAL POWER) · airframe 4,954 hrs · 3,852 cycles

CREW EXPERIENCED SEVERAL INTERMITTENT PROBLEMS WITH EXTERNAL POWER. FOUND DIODE ON CIRCUIT CARD P182 GOING TO PIN 36. PCB P182 WAS REPLACED WITH NEW AND FUNTIONAL CHECKS WERE SATISFACTORY.

Part: PCB — DEFECTIVE · airframe 4,925 hrs · 3,826 cycles

THE FLIGHT CREW REPORTED THE THE "PLT WARN" CIRCUIT BREAKER POPPED DURING FLGHT. THE CIRCUIT BREAKER DID NOT RESET AFTER 1 ATTEMPT. TROUBLESHOOTING ISOLATED THE PROBLEM DOWN TO THE A172 PCB, PN 128-364086-1. THE PCB WAS REPLACED WITH A REPAIRED UNIT IAW THE WDM 33-41-01. FUNCTIONAL CHECKS WERE SATISFACTORY.

Part: TRANSMITTER — INTERMITTENT (TE FLAPS) · airframe 4,896 hrs · 3,803 cycles

CREW REPORTED AN INTERMITTENT FLAP ASYMMETRY INDICATION ISSUE . DISCREPANCY WAS NOT DUPLICATED WHILE ACFT WAS IN MX FOR TROUBLESHOOTING AND THUS MADE IT VERY DIFFICULT TO CORRECT. CONFIRMED THAT THE LT INBD FLAP POSITION TRANSMITTER WAS DEFECTIVE. UNIT REPLACED AND RIGGED. FUNCTIONAL CHECKEDS SATISFACTORY.

Part: ALTIMETER — DEFECTIVE (STANDBY) · airframe 4,581 hrs · 3,564 cycles

CREW REPORTS THE STAND-BY ALTIMETER STICKS INTERMITTENTLY. REMOVED THE DEFECTIVE STAND-BY ALTIMETER SN AG554. INSTALLED AN O/H STAND-BY ALT. PN 122-382142-13, SN AG922. FUNCTIONAL CHECKS SATISFACTORY.

Part: PRESSURE SWITCH — DEFECTIVE (FUEL SYSTEM) · airframe 4,233 hrs · 3,350 cycles

THE CREW REPORTED THAT THE LT FUEL BOOST PUMP, LOW PRESSURE INDICATION WAS SLOW TO REACT TO PREFLIGHT TESTING. TROUBLESHOOTING IDENTIFIED THE LT FUEL LOW PRESSURE SENSOR SWITCH WAS DEFECTIVE. THE SWITCH WAS REPLACED WITH NEW FUNCTIONAL CHECK SATISFACTORY.

Part: COMPUTER — DEFECTIVE (AUTOPILOT) · airframe 4,219 hrs · 3,341 cycles

CREW REPORTED THAT THE AUTO-PILOT PITCH TRIM FAIL ANNUNCIATOR ILLUMINATED WITH THE AUTO-PILOT ENGAGED. TROUBLESHOOTING FOUND THE NR 1 FCC, PN 822-1019-313, SN 262Y DEFECTIVE. INSTALLED A MODIFIED FCC. FUNCTIONAL CHECKS SATISFACTORY.

Part: ACTUATOR — FAULTY (RUDDER TRIM) · airframe 4,191 hrs · 3,320 cycles

THE CREW REPORTED THAT DURING PREFLIGHT CHECKS THAT THE RUDDER TRIM WOULD NOT TEST WHILE ON AIRCRAFT BATTERY POWER, BUT WOULD TEST WITH EXTERNAL POWER APPLIED TO AIRCRAFT. TROUBLESHOOTING FOUND THAT THE TRIM ACTUATOR WAS DEFECTIVE. REMOVED THE RUDDER TRIM ACTUATOR P/N 45AS61014-111 (105) S/N 981002. INSTALLED A REPAIRED UNIT PER THE BEECH 400A AMM 27-20-00-201. FUNCTIONAL CHECKS WERE SATISFACTORY.

Part: COMPUTER — DEFECTIVE (STALL WARNING) · airframe 4,003 hrs · 3,185 cycles

THE CREW REPORTED THE LT STALL SYSTEM TEST WOULD NOT MOVE THE NEEDLE ON AOA GAUGE, TROUBLESHOT THE STALL SYSTEM AND FOUND THE STALL WARNING COMPUTER TO BE DEFECTIVE. REMOVED S/N 22886 AND INSTALLED AN INSPECTED STALL COMPUTER P/N 0020BG1 S/N 22957. FUNCTIONAL CHECKS SATISFACTORY.

Part: POSITION SWITCH — DEFECTIVE (TE FLAP) · airframe 3,846 hrs · 3,080 cycles

CREW REPORTED THE SPEED BRAKES WERE INOP IN FLIGHT. TROUBLESHOT AND FOUND THE RT FLAP FOLLOW-UP SWITCH TO BE DEFECTIVE. REMOVED THE DEFECTIVE UNIT S/N 38A6. INSTALLED AN OVERHAULED UNIT. FT OK.

Part: RCCB — DEFECTIVE (ELECTRICAL SYS) · airframe 3,647 hrs · 2,949 cycles

THE CREW REPORTED THE LT BUS TIE CIRCUIT BREAKER TRIPPED DURING THE PREFLIGHT CHECKS. TROUBLESHOOTING FOUND THAT THE LEFT BUS TIE RCCB P/N 45AS88810-003 S/N 001194 TO BE DEFECTIVE. INSTALLED A NEW RCCB, FUNCTIONAL CHECKS SATISFACTORY (RCCB = REMOTE CONTROLLED CIRCUIT BREAKER).