N101UE

Part: LINE — CHAFED (FUEL SYSTEM) · airframe 31,277 hrs · 38,711 cycles

AFTER A NORMAL TAKEOFF, THE PILOT WAS UNABLE TO MAINTAIN CLIMB POWER AND TORQUE ON THE LT ENGINE. AS POWER CONTINUED TO DECREASE, THE PILOT SHUT DOWN THE LT ENGINE AND RETURNED TO DEPARTURE FOR AN UNEVENTFUL LANDING. INSPECTION REVEALED THAT THE PRIMARY FUEL LINE FROM THE FUEL CONTROL UNIT WAS LEAKING BECAUSE THE STARTER GENERATOR COOLING DUCT HAD CHAFED A HOLE IN THE LINE.

Part: WIRE — LOOSE (COCKPIT) · airframe 29,366 hrs · 36,174 cycles

PILOT REPORTED - OVERHEAD PANEL OVERHEATING WITH A STRONG ELECTRICAL BURNING ODOR IN-FLIGHT. WINDSHIELD WIPERS CYCLED ONCE UNCOMMANDED. MAINTENANCE TROUBLESHOOTING - MAINTENANCE LOWERED OVERHEAD CONTROL PANEL TO TROUBLESHOOT, FOUND BALLAST RESISTOR HAD A LOOSE WIRE. RESECURED WIRE IAW BEECH MAINTENANCE MANUAL 30-40-00. OPERATIONAL CHECKS WERE GOOD. NO OTHER DEFECTS NOTED AND NO SIGNS OF OVERHEATING NOTED.

Part: SKIN — CORRODED · airframe 29,325 hrs · 36,111 cycles

FUSELAGE STATION 438 HAS AREA OF EXFLOLIATION CORROSION ON LOWER FUSELAGE SKIN. CUT OUT EXFLOLIATED AREA AND FABRICATED FILLER (1.8750" X 2.6250") USING MATERIAL SPEC. 2024T3 .025. FABRICATED DOUBLER (5.1875" X 6.0625") USING MATERIAL SPEC. 2024T3 .032. CLEANED, TREATED, PRIMED, PAINTED AND SEALED. REPAIR INSTALLED IAW SRM 51-70-06 AND 53-30-01. REPAIR NR2- FUSELAGE STATION 468 HAS AREA OF EXFLOLIATION CORROSION ON LOWER FUSELAGE SKIN. CUT OUT EXFLOLIATED AREA AND FABRICATED FILLER (4" X 1.3750") USING MATERIAL SPEC. 2024T3 .025. FABRICATED DOUBLER USING MATERIAL SPEC. 2024T3 .032. CLEANED, TREATED, PRIMED, PAINTED AND SEALED. REPAIR INSTALLED IAW SRM 51-70-05 AND 51-20-00. NO ADDITIONAL DEFECTS NOTED OR FOUND.

Part: SKIN — CORRODED (BS 453) · airframe 29,002 hrs · 35,602 cycles

STATION 453 HAS EXFOLIATION CORROSION FUSELAGE BELLY SKIN. CUT OUT SKIN CORROSION (2.5" X 3.25") AND FABRICATED FILLER FROM .040 2024T3-FABRICATED DOUBLER (5.75" X 6.75") FROM .050 2024T3. CLEANED, TREATED, PRIMED AND SEALED- INSTALLED IAW SRM 51-70-00, 53-30-02 AND 51-70-06. NO OTHER DEFECTS NOTED. STA 482 HAS EXFOLIATION CORROSION FUSELAGE BELLY SKIN. CUT OUT CORROSION (4" X 6") AND FABRICATED FILLER .040 2024T3 - FABRICATED DOUBLER (6.75" X 8.75") FROM .050 2024T3. CLEANED, TREATED, PRIMED AND SEALED - INSTALLED IAW SRM 51-70-00, 53-30-02 AND 51-70-06. NO OTHER DEFECTS NOTED.

Part: RESISTOR — HOT (WINDSHIELD WIPER) · airframe 28,654 hrs · 35,060 cycles

ENROUTE, PILOT OF FLIGHT 145 REPORTED THAT HE OBSERVED AN ACRID/BURNING ODOR IN THE COCKPIT. ATTEMPTED TO ISOLATE THE SOURCE VIA TURNING OFF ALL NON ESSENTIAL SYS THEN REACTIVATING THEM ONE BY ONE. HE WAS UNABLE TO ISOLATE THE SOURCE. ACFT LANDED WITHOUT INCIDENT AND MX WAS ADVISED. MX TROUBLESHOOT AND FOUND WINDSHIELD RESISTOR HOT, WINDSHIELD WIPER STUCK TO WINDSHIELD DUE TO BEING DRY AND WINDSHIELD SWITCH IN THE SLOW POSITION. UNSTUCK WINDSHIELD WIPERS THEN PERFORMED WINDSHIELD WIPER OPS CHECK WITH WET WINDSHIELD -OPS CHECK GOOD. ALL WORK DONE IAW MM 30-40-00.

Part: ATTACH FITTING — CRACKED (ZONE 500) · airframe 28,345 hrs · 34,588 cycles

FOUND BOTH THE LT AND RT AILERON BALANCE WEIGHT CLIPS CRACKED IN HALF. REMOVED AND REPLACED BALANCE WEIGHT CLIPS IAW KIT NR 129-4036-001.

Part: RIB — CRACKED (VERTICAL STAB) · airframe 27,531 hrs · 34,091 cycles

DURING SCHEDULED MX - SIM TASK 55-30-00 (1200 FLT HR/ 24 MO) REF. B1900 STRUCTURAL INSPECTION MANUAL, MX PERFORMED A VISUAL INSPECTION OF THE VERTICAL STABILIZER STRUCTURAL COMPONENTS AND FOUND RIB, AT CANTED STAB. STA. 69.184, CRACKED ON THE RT SIDE FLANGE AT THE 39.5 PERCENT CHORD REF. LINE AREA. MX INSTALLED REPAIR DOUBLERS ON THE UPPER AND LOWER PORTIONS OF THE DAMAGED AREA IAW THE MFG SRM AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: ENGINE — READS HIGH (LEFT) · airframe 27,518 hrs · 34,081 cycles

DURING CRUISE, THE CREW REPORTED THAT THE LT ENGINE INDICATED ABNORMALLY HIGH ITT. THE CREW ELECTED TO RETURN DEPARTURE AND LANDED WITH OUT INCIDENT. MX PERFORMED A LT ENGINE ITT THERMOCOUPLE LOOP RESISTANCE CHECK AND ADJUSTED. MX ALSO PERFORMED AND ITT CALIBRATION CHECK AND WAS FOUND TO BE SATISFACTORY. PERFORMED ENGINE TORQUE INDICATION CALIBRATION CHECK AND WAS FOUND TO BE SATISFACTORY. PERFORMED ENGINE TRIM THERMOCOUPLE TEST AND WAS FOUND TO BE WITHIN LIMITS. MX PERFORMED LT AND RT ENGINE RIGGING AND ADJUSTMENTS AND PERFORMED AN ENGINE ROCOVERY WASH AND GROUND PERFORMANCE RUN UP AND FOUND THE ENGINE PARAMETERS TO BE WITH IN LIMITS AT THIS TIME. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: ROTOR SHAFT — SHEARED (ZONE 600) · airframe 27,150 hrs · 33,608 cycles

UPON REACHING ALTITUDE THE RT ENGINE LOST OIL AND FUEL PRESSURE AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. THE NR 2 ENGINE WAS REMOVED AND SENT FOR TEARDOWN TO DETERMINE CAUSE OF THE FAILURE. ON TEARDOWN THE COMPRESSOR ROTOR SHAFT (STUB SHAFT) WAS FOUND TO HAVE FAILED. ANY ADDITIONAL INFORMATION WILL BE SUBMITTED AS IT BECOMES AVAILABLE.

Part: TRANSMITTER · airframe 25,724 hrs · 31,965 cycles

HIGH OIL PRESS RT ENG, R&R LH OIL PRESS TRANSMITTER OPS CKE LEAK CKE GOOD

Part: GYRO — PRECESSES (COCKPIT)

NR 2 DIRECTIONAL GYRO PRECESSING CONSTANTLY. REMOVED AND REPLACED NR 2 DIRECTINAL GYRO. (M)

Part: CONNECTOR — DIRTY (COCKPIT)

ORD - AIR TURN BACK, AFTER CAPTAINS ALTIMETER, ALTITUDE PRESELECT, TCAS AND TRANSPONDER FAILED. MAINTENANCE CLEANED SEVERAL CANNON PLUGS. (M)

Part: BULB — FAILED (CABIN)

SPW - EMERGENCY LIGHTS MISSING ONE BULB ON RIGHT SIDE, BURNED OUT. MAINTENANCE REPLACED BULB. (M)

Part: DOWNLOCK SWITCH — OUT OF ADJUST (LT MLG)

SPI - GEAR WOULD NOT RETRACT. MAINTENANCE ADJUSTED LT MAIN LANDING GEAR DOWNLOCK SWITCH. (M)

Part: SWITCHES — DIRTY (LANDING GEAR)

SPI - GEAR HANDLE REMAINS RED WITH GEAR UP. MAINTENANCE CLEANED UPLOCK AND DOWNLOCK SWITCHES. (M)

Part: GEAR HANDLE — INTERMITTENT (COCKPIT)

DVL - RED LIGHTS REMAIN ILLUMINATED WHEN GEAR IS UP. MAINTENANCE REMOVED AND REPLACED LANDING GEAR HANDLE AND PC RELAY BOARD. TEST FLIGHT NORMAL. (X)

Part: UPLOCK SWITCH — FAILED (LT MLG)

DVL - AFTER GEAR RETRACTION, GEAR UNSAFE LIGHTS REMAINED ILLUMINATED. MAINTENANCE ADJUSTED PEDESTAL SWITCH TO OBTAIN LOWER N1 SETTING FOR GEAR UNSAFE LIGHT. TEST FLIGHT NORMAL. LEFT UPLOCK SWITCH WAS LATER REPLACED. (X)

Part: WIPERS — MALFUNCTIONED (WINDSHIELD)

ORD - WINDSHIELD WIPERS DO NOT WORK WITH SWITCH IN SLOW MODE, NO OPERATION AND STRONG SMELL OF ELECTRICAL ODOR. OVERHEAD PANEL EXTREMELY HOT. MAINTENANCE INSPECTED ELECTRICAL SYSTEM AND OPERATIONS OF WIPERS OK IN ALL MODES. NO OVERHEAT OF PANELS. (M)

Part: TRUSS — CRACKED (LT ENGINE)

SPW - MAINTENANCE FOUND LEFT TRUSS CRACKED AT AREA 'A' OF INBOARD SIDE. REMOVED AND REPLACED TRUSS. (M)

Part: ACTUATOR — BINDING (NLG STEERING)

ORD - ON TOUCHDOWN THE RUDDER PEDALS JAMMED. AIRCRAFT PULLED HARD RIGHT AND FELT A SNAP BEFORE NORMAL STEERING WAS AVAILABLE. MAINTENANCE REMOVED AND REPLACED NOSE STEERING ACTUATOR. (M)

Part: FIRE LOOP — FAILED (RT ENGINE)

DEN - FALSE FIRE INDICATION FOR RIGHT ENGINE. MAINTENANCE REMOVED AND REPLACED FORWARD FIRE LOOP ON RIGHT ENGINE. SYSTEM OPERATES NORMALLY. (M)

Part: FIRE LIGHT — ILLUMINATED (RT ENGINE)

MUN - RIGHT ENGINE 'FIRE PULL' LIGHT ILLUMINATED DURING SINGLE ENGINE TURN. MAINTENANCE INSPECTED FIRE ZONE AND FOUND NO DAMAGE, COULD NOT DUPLICATE PROBLEM. (M)

Part: INTRANSIT LIGHT — ILLUMINATED (LANDING GEAR)

MSP - CREW REPORTED, THE GEAR 'INTRANSIT' LIGHT ILLUMINATED WITH GEAR DOWN. MX INSPECTED SYSTEM AND PERFORMED NUMEROUS GEAR SWINGS BUT COULD NOT DUPLICATE DISCREPANCY ON THE GROUND OR ON TEST FLIGHT. (M)

Part: COWL LATCH — WORN (LT ENG)

LAN - DURING CLIMB-OUT, CREW OBSERVED LEFT TOP COWL WAS DETACHED FROM INBOARD LATCHES (OUTBOARD LATCHES REMAINED LATCHED). CREW ELECTED AN AIR TURN BACK AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REPLACED INBOARD, AFT COWL LATCH AND RESECURED COWL. (M)

Part: SWITCHES — FROZEN (LANDING GEAR)

DVL - AFTER DEPARTURE, THE CREW ELECTED AN AIR TURN BACK DUE TO INABILITY TO RETRACT LANDING GEAR. MAINTENANCE PLACED THE AIRPLANE IN A HEATED HANGAR, THAWED OUT THE SWITCHES, AND ACCOMPLISHED SATISFACTORY GEAR SWINGS.

Part: CONTROL HANDLE — OPEN (LANDING GEAR)

JMS - ON DEPARTURE FROM JMS, THE CREW DETERMINED THE LANDING GEAR WOULD NOT RETRACT. THEY ELECTED AN AIR TURN BACK AND ACCOMPLISHED AN UNEVENTFUL LANDING. MAINTENANCE REPLACED THE LANDING GEAR CONTROL HANDLE. THE GEAR SWING AND OPS CHECK WERE SATISFACTORY.

Part: TRUSS — CRACKED (LT ENGINE)

SPW - DURING ROUTINE INSPECTION, MAINTENANCE FOUND THE OUTER LEFT ENGINE TRUSS CRACKED AT UPPER WELD ON COWL ATTACH BRACKET ON TUBE, APPROXIMATELY .5 INCH LONG ON OUTER AND .125 INCH LONG ON INNER. BOTH CRACKS WERE REPAIRED IAW BEECH KIT NR 129-9006.