Erickson Transport, Inc.

CLIMBING THROUGH 4,500MSL, PILOT FELT NOTICEABLE YAW TO THE LEFT. PILOT NOTICED EGT HAD DROPPED TO 231 DEGREES. LOOKED OUTSIDE TO SEE IF THERE WAS ANY INDICATION OF FIRE, WHEN HE LOOKED BACK IN THE GAUGE, THE EGT HAD SPIKED TO 870. ANNOUNCED THE MALFUNCTION AND PERFORMED THE EP (E-HANDLE AFFECTED SIDE TO FEATHER, GO TO THE CHECKLIST). TURNED BACK TOWARDS BASE. PERFORMED SE APPROACH & LANDING AND REVIEWED THE SE GO AROUND CHECKLIST. LANDED WITH APPROACH FLAPS AND WITH NO FURTHER INCIDENT. AFTER TROUBLE SHOOTING, MAINTENANCE REPORTED THE PROBLEM WAS A BAD EGT COMPENSATOR. THIS PART IS NOT A TIME CONTROLLED ITEM. AT THE TIME OF SENDING THE REPORT, THE TOTAL TIME HAD NOT BEEN DETERMINED.

RETURNED TO BASE AFTER LOW OIL PRESSURE ANNUNCIATOR CAME ON DURING TAXI. FOUND ENGINE IDLING AT 54-59% N1. UPON OPENING ENGINE COWLS FOUND ENGINE BAY WET WITH FUEL. FOUND FUEL LINE BETWEEN FCU AND FUEL PRESSURE TRANSDUCER, P/N 3040637, CHAFFED THROUGH TO WHERE A PIN HOLE EXISTED, AND LET THE FUEL PRESSURE DROP TO WHERE MINIMUM GROUND IDLE COULD NOT BE SUSTAINED. REMOVED AND REPLACED FUEL LINE IN ACCORDANCE WITH APPLICABLE INSTRUCTIONS, LEAK CHECKED AND RETURNED TO SERVICE.

FLAP SELECTOR HANDLE BECAME VERY LOOSE DURING TAXI. RETURNED TO BLOCKS UPON DISCOVERY. NO INCIDENT REPORTED. FOUND ONE OF THE BOLTS HOLDING FLAP HANDLE CRACKED & PARTIALLY SHEARED.

CORROSION CRACKING FOUND ON BELLY SKIN BETWEEN BS 273.25 AND 288, BL 0 AND 12 INCHES LEFT AND RIGHT OF SAID BUTT LINE. NO VISUAL CORROSION IS DETECTABLE FROM EITHER INSIDE OR OUTSIDE THE AIRCRAFT. ONLY THE BULGING IN THE SKIN STRUCTURE IS VISIBLE.

FLAP CONTROL HANDLE BROKE OFF WHEN PILOT SELECTED FLAPS UP ON CLIMB PHASE. PILOTS RETURNED TO BASE WITHOUT FURTHER INCIDENT.

PROP GOVERNOR STUCK IN FLIGHT. ACFT RETURNED TO BASE. GOVERNOR FOUND TO BE STICKY.

DURING PERIODIC SCHEDULED INSPECTION FOUND CRACK IN FWD ATTACHMENT BRACKET FOR THE RT HORIZONTAL STABILIZER INBD LE.

BEFORE START UP THE NR 1 COM CONTROL HEAD SHORTED OUT & STARTED TO SMOKE. POWER WAS SHUTDOWN & WE BEGAN TO TROUBLESHOOT. AFTER LOOKING AT THE WIRING DIAGRAM & CHECKING THE POWER CIRCUIT AT THE NR 1 COM CONTROL CONNECTOR, FOUND THERE WAS NO SHORT TO GND. INSTALLED AN OVERHAULED COM CONTROL HEAD & POWERED IT UP & OPERATIONS CHECKED IT WITH NO ISSUES. CONCLUDED THAT THE COM CONTROL HEAD MUST HAVE HAD AN INTERNAL SHORT. THE AVIONICS SYS WAS POWERED UP FOR APPROX 20 MINUTES BEFORE TAKEOFF WITH NO ISSUES. THE WORK WAS SIGNED OFF & THE ACFT WAS RELEASED. AFTER ABOUT 30 MINUTES OF FLIGHT TIME THE NR 1 COM CONTROL STARTED TO SMOKE AGAIN. SHUT OFF THE AVIONICS SWITCH & WERE WITHOUT COMMUNICATION & NAVIGATION SYS. RETURNED WITHOUT COM OR NAV SYS. TROUBLESHOOTING AGAIN & WHEN THE BATTERY SWITCH WAS TURNED ON, THE BATTERY RELAY DID NOT CLOSE. MX WENT TO THE BATTERY BOX & FOUND THE BURNED DIODES & WIRES. AFTER REMOVING THE DIODES, FOUND THAT BOTH WERE MISSING AN INSULATION RING. PN DF3D.

CREW PUT THE LG UP WITH NO ISSUES. WHEN THEY PUT THE GEAR HANDLE DOWN, THE GEAR DID NOT GO DOWN. THEY NOTICED THAT THE LG CONTROL CB WAS POPPED & ATTEMPTED TO PUSH IT IN. WHEN THEY DID THIS THE GEAR UNLOCKED & STARTED TO DROP & THE GEAR CONTROL BREAKER POPPED AGAIN. THEY THEN RETURNED & PROCEEDED TO PUMP THE GEAR DOWN & LOCKED. AFTER TROUBLESHOOTING, FOUND THE LG POWER PACK MOTOR RELAY K3 TO BE STUCK SHUT CAUSING THE MOTOR TO RUN CONTINUOUSLY & HEAT UP CAUSING THE BREAKER TO POP. THE K3 RELAY WAS REPLACED & OPERATIONS CHECKS WERE GOOD.

DURING 25 HOUR SERVICE CHECK FOUND RT OTBD AILERON & WING ATTACHMENT BRACKET CRACKED. TEMPORARY REPAIR ACCOMPLISHED IAW DERT 8110-3 TO ALLOW ACFT TO RELOCATE TO PERMANENT MAINTENANCE BASE WHERE FINAL REPAIR CAN TAKE PLACE. FORM 337 FILED & SENT TO FAA FOR TEMPORARY REPAIR.

DURING POST FLIGHT CHECK, PILOT DISCOVERED A PIECE OF BROKEN FAIRING ON LT INBD FLAP OB PYLON. FIBERGLASS FAIRING PN 212-13223.1 CHAFED A HOLE THROUGH LT INBD FLAP LE PLATE OVER TIME. REPAIRS ARE CURRENTLY IN PROCESS, SUPPLEMENTAL INFORMATION WILL BE SUBMITTED AFTER REPAIR IS COMPLETED.

DURING ROUTINE 25 HOUR INSPECTION, MAINTENANCE FOUND LT OTBD AILERON HINGE TO BE CRACKED. REMOVED & REPLACED HINGE BRACKET WITH SERVICEABLE BRACKET. MOC FLIGHT PERFORMED SATISFACTORY.

BIRD STRIKE ON NR 2 ENG. WAITING FOR OFFICIAL REPORT FROM FLT CREW & MAINTENANCE. ENG CHANGE CURRENTLY IN PROCESS. SUPPLEMENTAL INFORMATION WILL BE PROVIDED UPON RECEIPT OF OFFICIAL REPORT & MAINTENANCE LOGS FOR ENG CHANGE MOC FLIGHT.

ON LANDING , DURING 180 DEGREE TURNAROUND TO BACK TAXI OFF RUNWAY, RT MAIN TIRE BLEW OUT. MAINTENANCE CREW REPAIRED BLOWN TIRE & ACFT TAXIED BACK TO BASE.

DURING INSPECTION FOUND CORROSION IN AFT CARGO DOOR. REMOVED CORROSION DAMAGED PANELS. FABRICATED & INSTALLED TWO REPAIR PANELS. ALL REPAIRS PERFORMED IAW SRM.

DURING 1200 HR FALSE SPAR RECURRING INSPECTION, & AD INSPECTION AD 98-12-28. FOUND CRACKS IN THE PROFILE OF FALSE SPAR LOCATED IN THE RT WING. REMOVED RT WING AUXILIARY SPAR PROFILE ANGLE. INSTALLED REINFORCED RT WING AUXILIARY SPAR PROFILE ANGLE. ALL REMOVAL AND REPLACEMENT OF PARTS WAS ACCOMPLISHED IAW CASA C-212 SERVICE BULLETIN SB-212-57-30.

DURING 1200 HR FALSE SPAR RECURRING AD INSPECTION, IAW AD 98-12-28. FOUND CRACKS IN THE PROFILE OF FALSE SPAR LOCATED IN THE LT WING. REMOVED LT WING AUXILIARY SPAR PROFILE ANGLE, WS 5700. INSTALLED REINFORCED LT WING AUXILIARY SPAR PROFILE ANGLE. ALL REMOVAL AND REPLACEMENT OF PARTS ACCOMPLISHED IAW EADS CASA C-212 SERVICE BULLETIN SB-212-57-30 REV.1.

DURING POST FLIGHT INSPECTION MAINTENANCE CREW FOUND LT MLG OTBD WHEEL HALF TO BE CRACKED IN FOUR PLACES, CRACK LENGTH NOT EXCEEDING .25 INCHES. ACFT WAS GROUNDED IMMEDIATELY & A NEW WHEEL & TIRE ASSEMBLY WERE INSTALLED.

DURING 400HR SCHEDULED INSPECTION MECHANIC FOUND NR 2 ENG FIRE SHIELD AUGMENTER FLANGE COUPLING ATTACHED TO FIREWALL CRACKED APPROXIMATELY 80% AROUND CIRCUMFERENCE. REMOVED & RE-INSTALLED ENG & PROPELLER TO FACILITATE REMOVAL & REPLACEMENT OF COUPLING WITH NEW. MOC FLIGHT SATISFACTORY AFTER MAINTENANCE COMPLETED. RE-INSPECTED AFTER MOC FLIGHT, NO DEFECTS NOTED.

DURING POST FLIGHT INSPECTION, FOUND ENG ISOLATOR MOUNT PAD TO BE DEFORMED AFTER 13.6 HOURS IN USE. THIS UNIT WAS REPLACED PREVIOUSLY ON 01/06/2013 DUE TO DE-BONDING FROM FUEL & OIL CONTAMINATION.

FOUND DENT IN UPPER SKIN OF FUSELAGE DURING INSPECTION, BETWEEN FRAMES 17 & 18. REPAIRED WITH PATCH IAW SRM.

DURING ROUTINE INSPECTION A CRACK WAS FOUND ON THE RT WING FLAP. THE ACFT WAS REMOVED FROM SERVICE & REPAIRED.

DURING INSPECTION A CRACK WAS FOUND ON THE LT WING FLAP. THE ACFT WAS REMOVED FROM SERVICE & REPAIRED.

DURING INSPECTION A CRACK WAS FOUND ON THE RT WING FLAP. THE ACFT WAS REMOVED FROM SERVICE & REPAIRED.

DURING INSPECTION A CRACK WAS FOUND ON THE LT WING FLAP. THE ACFT WAS REMOVED FROM SERVICE & REPAIRED.

DURING POST FLIGHT INSPECTION, PILOT DISCOVERED THE LT MLG WHEEL AXLE BEARING COVER DEPARTED ACFT DURING TRANSIT ON PREVIOUS FLIGHT. THERE WAS NO INDICATION OF MALFUNCTION DURING FLIGHT. COVER WAS REPLACED WITH NEW FROM KIT.

CRACKS ON & IN THE VICINITY OF THE AFT UPPER DOOR WERE FOUND. ON 22-NOV-13 5 CRACKS WERE REPAIRED IAW THE SRM. THE ACFT WAS FLOWN UNTIL 27-NOV-13 WHEN THE DOM BECAME AWARE OF THE CRACKS, UPON READING THE E-MAIL & THEN PULLED THE ACFT OUT OF SERVICE. THIS E-MAIL WAS RESPONDED TO ON 2-DEC-13.

CRACKS ON & IN THE VICINITY OF THE AFT UPPER DOOR WERE FOUND. ON 22-NOV-13 5 CRACKS WERE REPAIRED IAW THE SRM. THE ACFT WAS FLOWN UNTIL 27-NOV-13 WHEN THE DOM BECAME AWARE OF THE CRACKS, UPON READING THE E-MAIL & THEN PULLED THE ACFT OUT OF SERVICE. THIS E-MAIL WAS RESPONDED TO ON 2-DEC-13.

AFTER THE NORMAL REFUELING, REMOVED HATCH AND FUELED FROM THE TOP OF AIRPLANE, WENT TOPSIDE TO INSPECT THE FUEL CAPS. ON RETURNING TO THE CABIN, REINSTALLED THE HATCH. ROTATED THE HANDLE TO THE "LOCKED" POSITION, THERE WAS A POP AND THE HANDLE CAME OFF IN HAND. NOTICED THE ROLL PIN THAT RETAINS THE HANDLE TO THE SHAFT OF THE LOCKING MECHANISM WAS LYING ON THE FLOOR BELOW. REINSTALLED HANDLE TO SHAFT AND REINSERTED THE ROLL PIN TO RETAIN THE HANDLE. HATCH APPEARED SECURE. CRANKED AND TAXIED FOR TAKEOFF. TAKEOFF NORMAL. DIVERTED ATTENTION TO OVERHEAD PANEL TO MOVE SWITCHES AND NOTICED HATCH GONE. LANDED AND INSPECTED HATCH AND COULD NOT FIND ANY DAMAGE TO HATCH.

AFTER NORMAL REFUELING OPERATION, REMOVE HATCH AND FUELED FROM TOP OF AIRPLANE, WENT TOPSIDE TO INSPECT THE FUEL CAPS. ON RETURNING TO CABIN, REINSTALLED HATCH. ROTATED THE HANDLE TO "LOCKED" POSITION AND HANDLE CAME OFF. NOTICED ROLL PIN FOR HANDLE TO SHAFT WAS LYING ON THE FLOOR BELOW. REINSTALLED HANDLE. HATCH APPEARED SECURE. TAXIED FOR TAKEOFF. TAKEOFF NORMAL AND NOTICED HATCH GONE. FOUND ON GROUND. LANDED AND INSPECTED HATCH AND COULD NOT FIND ANY DAMAGE. INSPECTED TOP OF AIRPLANE AND COULD NOT DEFINITIVELY ATTRIBUTE ANY MARKINGS, TO THE LOSS OF THE HATCH.

ALL PRE-FLIGHT AND RUN-UP SYSTEM CHECKS HAD BEEN NORMAL, AND ALL SYSTEMS HAD BEEN OPERATING NORMALLY FOR ALL PREVIOUS LEGS OF THE FLIGHT. ON APPROACH REDUCED THE POWER TO APPROX 600 LBS OF TORQUE PER SIDE TO SLOW DOWN TO FOLLOW PRECEDING TRAFFIC. THE AUTOFEATHER WAS ARMED AND THE DESCENT CHECKLIST CONFIRMING THIS HAD ALREADY BEEN COMPLETED. WHEN THE POWER REACHED 600 LBS, THE NR 2 ENGINE STARTED TO CYCLE IN AND OUT OF AUTOFEATHER AS IT WOULD DO WHEN TESTING THE AUTOFEATHER ON THE GROUND. BUMPED THE POWER UP TO ABOUT 1000 LBS OF TORQUE PER SIDE, TURNED THE AUTOFEATHER OFF AND LEFT IT OFF FOR THE REMAINDER OF THE FLIGHT. LANDING WAS UNEVENTFUL.

RIGHT AUTOFEATHER ACTIVATED ON APPROACH WITH NORMAL POWER SETTINGS.

FIFTEEN MINUTES INTO THE FLIGHT, THE NR 1 ENGINE EXPERIENCED A MOMENTARY POWER LOSS OF ABOUT TEN PERCENT TORQUE. ALL THE GAUGES INDICATED THE SAME AND THE ACFT YAWED IN THAT DIRECTION. THIS LASTED ONLY A SECOND OR TWO, BUT A FEW MINUTES LATER THE SAME THING HAPPENED. AT THIS POINT THE ACFT RETURNED TO BASE. ON THIS FLIGHT IT HAPPENED A TOTAL OF THREE TIMES.

ON TAKEOFF ROLL, THE UPPER ESCAPE HATCH FELL OFF THE AIRCRAFT.