N45GL

Part: ACTUATOR — FAILED (NLG)

ON LANDING IN AKN, NOSE GEAR DOWN AND LOCK LIGHT FAILED TO ILLUMINATE. FERRY TO ANCHORAGE AFTER VERIFYING GEAR DOWN AND LOCKED, GREEN LIGHT CAME ON DURING TAXI OUT. COULD NOT DUPLICATE FAILURE ON GROUND. REPLACED NOSE GEAR ACTUATOR FOR T/S. (M)

Part: RELAY — CONTAMINATED (MLG)

ON APPROACH TO LANDING IN ANCHORAGE, THE PILOT SELECTED LANDING GEAR DOWN TWICE WITH NO EFFECT. THE GEAR WAS EXTENDED MANUALLY AND THE LANDING WAS WITHOUT INCIDENT. MAINTENANCE CONFIRMED THAT THE HYDRAULIC PUMP RELAY WAS FREEZING, HIGH MOISTURE CONTENT IN UNIT, AND REPLACED SAME. (M)

Part: CONNECTOR — DAMAGED (MLG)

AT LANDING IN ANCHORAGE, PILOT REPORTED MLG WAS SLOW TO GO DOWN, THE LANDING GEAR WARNING HORN WOULD NOT SILENCE AND INTRANSIT LIGHTS REMAINED ON WITH THREE GREEN SAFE LIGHTS ALSO ON. MAINTENANCE COULD NOT DUPLICATE. REPLACED PCB FOR WARNING HORN FAULT, RESEATED PIN E ON RIGHT GEAR DOWN LOCK CONNECTOR AND REPLACED RIGHT POWER LEVER GEAR WARNING HORN SWITCH. (M)

Part: RELAY — CONTAMINATED (HYD PUMP)

ON APPROACH TO LANDING, THE LANDING GEAR WOULD NOT NORMALLY EXTEND. THE FLIGHT CREW USED THE ALTERNATE HAND PUMP FOR EXTENSION AND PERFORMED AND UNEVENTFUL LANDING. MAINTENANCE CONFIRMED THAT THE LANDING GEAR HYDRAULIC MOTOR RELAY WOULD FREEZE AND NOT OPERATE THE HYDRAULIC POWER PACK. THE RELAY WAS REPLACED AND ALL SYSTEMS OPERATED NORMAL. POST REMOVAL INSPECTION OF THE OLD RELAY CONFIRMED THAT THE PLUNGER CAVITY WAS CONTAMINATED WITH WATER.

Part: CONNECTOR — SHORTED (NAV LIGHTS)

DURING SCHEDULED MAINTENANCE, FOUND THAT THE WING STROBE LIGHTS WERE INOPERATIVE WITH THE NAVIGATION LIGHT TURNED ON. TROUBLESHOOTING REVEALED INTERNAL SHORTING OF THE AFT PRESSURE BULKHEAD CONNECTOR. ALSO DISCOVERED THAT THE ELEVATOR ELECTRIC TRIM SERVO WIRES THAT RUN THROUGH THE SAME CONNECTOR, WERE SHORTED AND GETTING POWER FROM THE STROBE/NAV LIGHT CIRCUIT BREAKERS THEREBY MAKING THE TRIM SERVO ALWAYS POWERED AND UNABLE TO BE DEENERGIZED BY SECURING THE PROPER TRIM CIRCUIT BREAKER. SAFETY OF FLIGHT ISSUE. IN THE PREVIOUS 30 DAYS, THIS A/C HAD AT LEAST 4 DIFFERENT ELECTRIC ELEVATOR TRIM DISCREPANCIES THAT APPEARED TO BE INTERMITTENT AND MIGHT HAVE BEEN CAUSED BY THIS ELECTRICAL FAULT.

Part: CONNECTOR — SHORTED (STROBE)

DURING SCHEDULED MAINTENANCE, FOUND THAT THE WING STROBE LIGHTS WERE INOPERATIVE WITH THE NAVIGATION LIGHTS TURNED ON, TROUBLE SHOOTING REVEALED INTERNAL SHORTING OF THE AFT PRESSURE BULKHEAD CONNECTOR. DISCOVERED THAT THE ELEVATOR ELECTRIC TRIM SERVO WIRES THAT RUN THROUGH THE SAME CONNECTOR WERE SHORTED AND GETTING POWER FROM THE STROBE/NAV LIGHT CIRCUIT BREAKERS THERE BY MAKING THE TRIM SERVO ALWAYS POWERED AND UNABLE TO BE DEENERGIZED BY SECURING THE PROPER TRIM CIRCUIT BREAKER. SAFETY OF FLIGHT ISSUE. IN THE PREVIOUS 30 DAYS, THIS AC HAD AT LEAST 4 DIFFERENT ELECTRIC ELEVATOR TRIM DISCREPANCIES THAT APPEARED TO BE INTERMITTENT AND MIGHT HAVE BEEN CAUSED BY THIS ELECTRICAL FAULT.

Part: OIL COOLER — CRACKED (ENGINE)

MAINTENANCE FOUND OIL LEAKING FROM THE RIGHT ENGINE COWLING. INVESTIGATION REVEALED A CRACKED OIL COOLER. OIL COOLER WAS REPLACED. THE REMOVED OIL COOLER WAS INSPECTED AND A CRACK ALONG THE END PLATE WELD SEEM WAS LOCATED. THIS DEFECT IS COMMON WITH THIS PN. OIL COOLER.

Part: RELAY — BURNED (HYD PUMP)

ON APPROACH, THE LANDING GEAR WAS SELECTED DOWN AND THE GEAR EXTENDED NORMALLY, GIVING THREE GREEN SAFE INDICATIONS. MOMENTS AFTER GETTING THE GEAR DOWN AND SAFE INDICATION, THE LANDING GEAR PUMP CIRCUIT BREAKER POPPED. THE AIRCRAFT MADE AN UNEVENTFUL LANDING. MAINTENANCE DETERMINED THAT THE LANDING GEAR HYDRAULIC PUMP MOTOR RELAY WAS STUCK IN THE CLOSED POSITION AND REPLACED SAVE.

Part: WINDSHIELD — CRACKED (COCKPIT)

ON CLIMB OUT, RT WINDSHIELD CRACKED. AIRCRAFT IMMEDIATELY RETURNED TO THE AIRPORT AND MADE AN UNEVENTFUL LANDING. WINDSHIELD REPLACED.

Part: DOWNLOCK SWITCH — INOPERATIVE (NLG ACTUATOR)

PILOT REPORTED THAT ON APPROACH TO ANCHORAGE, WHEN THE LANDING GEAR WAS SELECTED DOWN. THE NOSE GEAR, GREEN DOWN AND LOCK LAMP FAILED TO ILLUMINATE (THE GEAR UNSAFE LIGHTS WERE NOT ILLUMINATED). THE GEAR WAS CYCLED AND AFTER A 30 SECOND DELAY, THE NOSE GEAR DOWN AND LOCK LAMP ILLUMINATED. AN UNEVENTFUL LANDING WAS MADE AND MAINTENANCE REPLACED THE NOSE GEAR ACTUATOR.

Part: LINE — CRACKED (P3 AIR)

FLIGHT CREW REPORTED THAT THE NR 2 ENGINE FLAMED OUT EN ROUTE. ATTEMPTED RESTART WAS UNSUCCESSFUL. THE ENGINE WAS SECURED AND ACCOMPLISHED UNEVENTFUL LANDING. MAINTENANCE LOCATED A CRACKED P3 ENGINE CONTROL AIR LINE AND REPLACED SAME. MAINTENANCE ALSO DETERMINED THAT AN ANGLE BRACKET (P/N MS9593485) AND LINE CLAMP HAD BEEN MISSING FROM THE ENGINE SINCE THE LAST ENGINE OVERHAUL. THIS LINE CLAMP WOULD REDUCE VIBRATION AND FATIGUE AT THE POINT OF FAILURE OF THE LINE. THE MISSING PARTS WERE REPLACED.

Part: RELAY — BURNED (MLG)

THE PILOT REPORTED THAT AFTER DEPARTURE FROM HPB, THE LANDING GEAR SELECTOR HANDLE WAS INOPERATIVE AND WOULD NOT RAISE THE LANDING GEAR. THE FLIGHT CONTINUED, WITH THE GEAR EXTENDED. AN UNEVENTFUL LANDING WAS MADE AND MAINTENANCE REPLACED THE LANDING GEAR POWER PACK CONTROL RELAY DUE TO BURNED CONTACTS.

Part: RELAY — BURNED (HYD SYSTEM)

ON ARRIVAL, THE LANDING GEAR MOTOR CIRCUIT BREAKER POPPED, THE LOW HYDRAULIC LEVEL ENUNCIATOR CAME ON AND THE GEAR HAD TO BE MANUALLY EXTENDED. AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE FOUND THE HYDRAULIC PUMP MOTOR VERY HOT AND THE CONTACTS IN THE MOTOR RELAY BURNED (WELDED), FLUID LEVEL WAS VERIFIED GOOD (FALSE LOW LEVEL WARNING). THE RELAY, PUMP MOTOR AND LOW LEVEL SENSOR WERE REPLACED. THIS FAILURE MAY BE RELATED TO CONTROL NR ACE1018011.

Part: LANDING GEAR — ICED

ON ARRIVAL, THE LANDING GEAR SELECTOR HAD TO BE CYCLED MULTIPLE TIMES TO ACHIEVE GEAR DOWN AND SAFE INDICATION. MAINTENANCE COULD NOT DUPLICATE THE FAULT AND INSPECTED THE SYSTEM, INCLUDING MULTIPLE SATISFACTORY CYCLES. THE POSSIBILITY THAT THE FAULT WAS ICING RELATED EXISTS.

Part: SWITCH — FAILED (ALTITUDE WARN)

CABIN ALTITUDE WAS NOTED AT 16,000 FT (DUE IMPACT - DAMAGE TO FUSELAGE) IN FLIGHT - CREW STATED USING SUPPLEMENTAL OXYGEN AT THIS POINT. CABIN ALTITUDE WARNING DID NOT FUNCTION, WARNING LIGHT SHOULD COME ON AT 12,250 FT. REPLACED DEFECTIVE SWITCH. WARNING SWITCH FOR CABIN PRESSURIZATION/ ALTITUDE, DID NOT FUNCTION DURING PRESSURIZATION LOSS.

Part: ENGINE — FAILED (RIGHT)

ON RETURN LEG OF ROUND TRIP, PILOT NOTICED AN ORANGE FLASH FRO THE RIGHT HAND ENGINE. ENGINE ITT STARTED RISING AND THE POWER STARTED RISING AND THE POWER STARTED SURGING. THE ENGINE WAS SECURED AND FEATHERED 45 MINUTES OUT. MADE UNEVENTFUL LANDING. NO DETERMINATION OF THE CAUSE OF FAILURE HAS MADE AT THIS TIME. THE OIL FILTER WAS CONTAMINATED WITH METALLIC PARTICLES AND THE COMPRESSOR SECTION WAS SEIZED UP. ENGINE HAS BEEN REMOVED AND REPLACED.

Part: WINDSHIELD — CRACKED (COCKPIT)

WINDSHIELD CRACKED A FL20. THE FLIGHT CREW CANCELED THE INTENDED FLIGHT AND RETURNED TO ANCHORAGE, WITHOUT FURTHER PROBLEMS.

Part: SWITCH — DISCONNECTED (EXTINGUISH SYS)

WHILE PERFORMING ENGINE FIRE EXTINGUISHER SYSTEM TEST IAW B1900C MM CAMP NR2 INSPECTION TEMP REVISION 26-1, FOUND NR 1 AND NR 2 ENGINE SQUIB POWER SWITCH DISCONNECTED FROM ANNUNCIATOR/ ACTUATOR ASSEMBLY. THIS A RECURRENT PROBLEM WITH THIS STYLE SWITCH ASSEMBLY. FAILURE OF THE SQUIB SWITCH ATTACHMENT DISABLES THE FIRE EXTINGUISHER SYSTEM AND COULD CAUSE LOSS OF LIFE IN THE EVENT OF A FIRE. THERE IS NO WAY FOR THE FLIGHT CREW TO GROUND TEST THIS SYSTEM FOR THIS TYPE OF FAILURE.

Part: CLAMP — UNSECURE (ENGINE BREATHER)

NR 1 ENGINE POWER FAILED TO REDUCE BELOW 2200 LBS. TORQUE FOR LANDING. THE ENGINE WAS SHUT DOWN IN FLIGHT JUST PRIOR TO LANDING. A NON EVENTFUL LANDING WAS ACCOMPLISHED AND THE ENGINE WAS RESTARTED FOR TAXI TO HANGAR. MAINTENANCE WAS UNABLE TO VERIFY THE CAUSE OF THE UNCONTROLLED POWER SETTING. A LOOSE, WORM TYPE, HOSE CLAMP WAS FOUND BELOW THE FUEL CONTROL AND IS BELIEVED TO HAVE LODGED IN THE FUEL CONTROL LINKAGE AND THEN CAME FREE AFTER LANDING.

Part: SWITCH — DISCONNECTED (FIRE EXT)

WHILE PERFORMING 'NEW' INSP REQUIREMENT, FND BOTH SQUIB POWER SWITCHES DISLOCATED FROM MAIN ENG FIRE EXTING ANNUNCIATOR/ACTUATOR ASSY. FOUND SQUIB SWITCH MODULE NOT PROPERLY RETAINED BY TABS ON ANNUNCIATOR BODY. THIS CONDITION HAS BEEN FND ON HALF OF INSPECTED ACFT. SUGGEST A CHANGE IN DESIGN OF ASSY FOR POSITIVE ATTACHMENT OF SQUIB POWER SWITCH. NOTE: CONDITION FOUND ON 2 ASSYS WOULD PREVENT FLIGHT CREW FROM BEING ABLE TO DISCHARGE AFFECTED ENG FIRE BOTTLES AT ANY TIME. THERE IS NO WAY FOR CREW TO PRE-FLIGHT SYS TO VERIFY THE FIRE BOTTLE SQUIBS COULD BE BLOWN IF NEEDED.

Part: SWITCH — DISCONNECTED (EXTINGUISH SYS)

WHILE PERFORMING A NEW INSPECTION REQUIREMENT, FOUND BOTH SQUIB POWER SWITCHES DISLOCATED FROM MAIN ENGINE FIRE EXTINGUISHER ANNUNCIATOR/ACTUATOR ASSEMBLY. FOUND SQUIB SWITCH MODULE NOT PROPERLY RETAINED BY TABS ON ANNUNCIATOR BODY. THIS CONDITION HAS BEEN FOUND ON HALF OF INSPECTED AIRCRAFT. SUGGEST CHANGE IN DESIGN OF THE ASSEMBLY FOR POSITIVE ATTACHMENT OF SQUIB POWER SWITCH. NOTE: THE CONDITION FOUND ON THE TWO ASSEMBLIES WOULD PREVENT THE FLIGHT CREW FROM BEING ABLE TO DISCHARGE THE AFFECTED ENGINE FIRE BOTTLES AT ANY TIME. ALSO, THERE IS NO WAY FOR THE CREW TO PREFLIGHT THIS SYSTEM TO VERIFY THAT THE FIRE BOTTLE SQUIBS COULD BE BLOWN IF NEEDED.

Part: ANNUNCIATOR — FAILED (GPS)

FAILURE OF NON-FIELD REPLACEABLE IFR GPS 'LEG' ANNUNCIATION. THIS COMPONENT IS THE INDICATOR/SWITCHING UNIT OF A CERTIFIED IFR GPS NAVIGATION SYSTEM.

Part: BULKHEAD — CRACKED (FLANGE)

DURING A ROUTINE ACE CAMP INSPECTION NR 6, HEAVY AFT FUSELAGE AND EMPENNAGE, FOUND MULTIPLE CRACKS IN CANTED BULKHEAD, STATION 588.10, IN EXCESS OF CRACK LIMITS PROVIDED IN BEECHCRAFT SERVICE BULLETIN 2564, REV 1 INCORPORATION OF SB 2564 KIT NR 129-4005-1S BEING PERFORMED AS A RESULT OF THE FINDINGS. (M)

Part: FUEL PUMP — FAILED (NR 2 ENGINE)

67.6 HOURS AFTER OVERHAUL, DRIVESHAFT BROKE. PUMP TURNS NORMAL, NO DAMAGE DETECTED INSIDE PUMP.

Part: LINE — RUPTURED (LT/RT MLG WW)

PILOT REPORTED CAPTAINS LEFT BRAKE VERY WEAK. BRAKE SYSTEM BLEED, OPS CHECKED GOOD. THE NEXT DAY, THE FLEXIBLE BRAKE LINES (UPPER) IN THE GEAR WELLS, LEFT AND RIGHT, WERE FOUND TO BE LEAKING THROUGH THE HOSE. REPLACED UPPER FLEX LINE. (M)

Part: RELAY — CONTAMINATED (LT NACELLE)

LANDING GEAR FAILED TO EXTEND WITH GEAR HANDLE SELECTION. LANDING GEAR EXTENDED USING HAND PUMP SYSTEM, GEAR INDICATIONS WERE NORMAL. FOUND LANDING GEAR PUMP RELAY CONTAMINATED WITH WATER AND SUSPECT UNIT FROZE IN-FLIGHT AND FAILED TO POWER ELECTRIC PUMP. SEALED NEW RELAY PLUNGER BODY WITH SILICONE RTV TO PREVENT MOISTURE CONTAMINATION AND INSTALLED IN AIRCRAFT. RETRACT TEST C/W, OK.

Part: SPAR CAP ASSY — CORRODED (COCKPIT)

FOUND CORROSION ON FORWARD SIDE OF MAIN WING SPAR LOWER CAP BOND ASSY. THE AFFECTED AREA IS UNDER THE CABIN FLOOR IN THE CABIN. CORROSION WAS FOUND ON THE FORWARD FACE OF THE SPAR AND WAS DISTRIBUTED IN SMALL AREAS ACROSS SPAR JUST ABOVE THE EDGE OF THE SEALANT THAT IS USED TO SEAL THE SPAR RIVET FLANGE. A SMALL AMOUNT OF PITTING WAS FOUND ON THE HORIZONTAL SURFACE JUST ABOVE AND AFT OF THE FORWARD FACE. DAMAGE WAS DETERMINED TO BE NEGLIGIBLE AFTER CORROSION REMOVAL.

Part: FUEL LINE — CHAFED (LT ENGINE)

ON NR 1 ENGINE - STARTER/GENERATOR COOLING DUCT HOSE CAME IN CONTACT WITH AN ENGINE FUEL LINE AND CHAFED A HOLE THROUGH THE TUBING WALL THICKNESS CAUSING FUEL TO LEAK INTO THE ACCESSORY SECTION OF THE ENGINE COMPARTMENT. P&WC SB 13250 ADDRESSES THIS PROBLEM AND HAD NOT BEEN C/W. BEECH HAS NO S/B THAT ADDRESSES THIS PROBLEM ON THE B1900C MODEL. BEECH COMMUNIQUE NR 34 STATES THE P&WC SB CORRECTS THIS PROBLEM.

Part: TERMINAL — SEPARATED (CONTROL CABLE)

AIRCRAFT DEPARTED ANC FOR FAI. CLLIMBING OUT OF 8,000 FEET, NR 2 PROPELLER AUTOFEATHERED. FLIGHT CREW SECURED NR 2 ENGINE AND RETURNED TO ANC. LANDING WAS NORMAL. MAINTENANCE FOUND PUSH/PULL TERMINAL AT FORWARD END OF PROPELLER REVERSING CONTROL HAD SEPARATED AT MANUFACTURED JOINT. REPLACED TERMINAL AND OPS CHECKED PROPELLER CONTROL. RELEASED AIRCRAFT TO SERVICE.

Part: RELAY — FAILED (LANDING GEAR)

ORD - GEAR DID NOT EXTEND. EXTENDED GEAR MANUALLY. REMOVED AND REPLACED LANDING GEAR RELAY. OPS CHECKS GOOD. (X)

Part: PROP GOVERNOR — MALFUNCTIONED (RT PROP)

BMG - DURING LANDING AT 110 KTS THE RIGHT PROP RPM DECREASES TO 900 AND THE LEFT STAYS AT 1400. RIGHT TORQUE INCREASES SLIGHTLY AND AIRCRAFT YAWS HEAVY TO THE LEFT. MAINTENANCE CLEANED LOW PITCH SOLENOIDS. LUBED PROP AND BETA CABLES. REMOVED ADN REPLACED RIGHT PRIMARY GOVERNOR. (M)

Part: MOTOR RELAY — FAILED (LANDING GEAR)

ESC - THE CREW REPORTED LANDIGN GEAR WOULD NOT EXTEND AND HAD TO MANUALLY EXTEND GEAR. AIRCRAFT MADE AN UNEVENTFUL LANDING. MAINTENANCE REMOVED AND REPLACED LANDING GEAR MOTOR RELAY. OPS CHECK WAS GOOD. (M)

Part: TRUSS — CRACKED (RIGHT)

ESC - DURING THE ROUTINE TRUSS INSPECTION REQUIRED BY AD95-02-18, A .75 INCH CRACK WAS FOUND NEAR THE LINSEED OIL PLUG OF THE INBOARD AREA 'A' OF THE RIGHT TRUSS. THE TRUSS WAS REPAIRED IAW BEECH KIT 129-9006, REPAIR NR 2.

Part: RECEIVER/TRANS — INTERMITTENT (NOSE)

DVL - THE CREW ELECTED AN AIR TURNBACK AFTER THE WEATHER RADAR PICTURE SHRUNK AND THE HORIZONTAL WAS INTERMITTENT. AN UNEVENTFUL LANDING WAS ACCOMPLISHED FOLLOWED BY THE REPLACEMENT OF THE RADAR R/T.

Part: AILERON — DENTED (LT WING)

ORD - WHILE PARKED WITHOUT PASSENGERS ON BOARD, THE LEFT WING TIP AND OUTBOARD TRAILING EDGE WERE DENTED BY A BAG CART TOW TRACTOR. MAINTENANCE REMOVED THE AILERON AND WING TIP AND INSPECTED THOSE AREAS FOR FURTHER DAMAGE. A SERVICEABLE AILERON AND WING TIP ASSEMBLY WERE INSTALLED. A TEST FLIGHT WAS SUCCESSFUL.

Part: ENGINE OIL — LOW (RT ENGINE)

DLH - INBOUND TO DLH, CREW EXPERIENCED THE RT ENGINE OIL PRESSURE FLUCTUATION BETWEEN 40-100 PSI ACCOMPANIED BY THE ILLUMINATION OF THE RT OIL PRESSURE ANNUNCIATOR. THE RT ENGINE WAS SECURED AFTER WHICH AN UNEVENTFUL LANDING WAS COMPLETED. MAINTENANCE INSPECTED FOR OIL LEAKS, SERVICED OIL LEVEL, AND MADE SEVERAL ENGINE RUNS, BUT COULD NOT DUPLICATE THE FLUCTUATION.

Part: RIVET — LOOSE (TOP SIDE WING)

SPW - DURING ROUTINE INSPECTION, MAINTENANCE FOUND 4 RIVETS IN RT FUEL TANK TOP SIDE BETWEEN THE NACELLE AND STALL FORCE LOOSE AND LEAKING FUEL. THE RIVETS WERE REPLACED, THE TANK SEALED, AND LEAK CHECK OKAY.

Part: TE SKIN — CRACKED (RUDDER)

SPW - DURING ROUTINE MAINTENANCE, RUDDER TRAILING EDGE FAIRING WAS FOUND CRACKED AND HAD SEVERAL WORKING RIVETS. THE CRACK WAS REPAIRED AND RIVETS WERE REPLACED IAW DER APPROVED FROM 8110-3. RUDDER BALANCE CHECKED AND RESINSTALLED.

Part: RIVETS — LOOSE (RT WING)

SPW - DURING ROUTINE INSPECTION, MAINTENANCE FOUND THE RIGHT WING SEEPING FUEL OUTBOARD OF THE NACELLE ALONG THE SPAR. SEVERAL RIVETS WERE REPLACED AND THE AREA WAS SEALED WITH MIL-S-8802F SEALANT.