ATAir Tractor 301 – 802

Parts most often named Engine (36) · Gas Generator (2) · Gearbox (1)

AIRCRAFT 802-4037 HAD AN ENGINE CHIP DETECTOR LIGHT ILLUMINATE IN-FLIGHT. ABOUT 2 MINUTES LATER, A DROP IN OIL PRESSURE WAS OBSERVED BY THE CREW, ACCOMPANIED BY THE SMELL OF BURNING OIL. AIRCREW SHUT THE ENGINE DOWN & PROCEEDED WITH AN EMERGENCY, ENGINE-OUT LANDING

(CAN) THE CUSTOMER CONTACTED THE FSR TO REPORT ENGINE IFSD, LOUD BANG FOLLOWED BY POWER LOSS. THE PILOT PERFORMED AN EMERGENCY LANDING ON A BEACH. POST-EVENT INSPECTION REVEALED THE COMPRESSOR FREE TO ROTATE, UNABLE TO TURN PROPELLER BY HAND, EXHAUST DUCT DISTORTED, AND ALL PT2 BLADES AND SOME PT1 BLADES FRACTURED. FSR TO MEET CUSTOMER, AUTHORITIES ARE NOT INVOLVED.

(CAN) WHILE TRAINING ON A DUAL SEAT AT802 FIREBOSS, INSTRUCTOR SIMULATED ENGINE OUT BY REDUCING THE PL TO IDLE SPEED, TRAINEE PILOT RE-APPLIED POWER, AND FLAMES WERE NOTICED FROM EXHAUST STACKS. ENGINE WAS NOT ACCELERATING AND EPL DEPLOYED. ENGINE NOT ACCELERATING AND DUE TO LOW ALTITUDE, PILOT SHUTDOWN ENGINE AND LANDED HARD ON THE WATER WITHOUT INCIDENT. THERE WERE NO INJURIES.

Parts most often named Float (4) · Wheel (4) · Rivet (3) · Frame (3)

(CAN) RH FLOAT BAY NR 4 A CRACK FOUND IN FORWARD MID I/B VERTICAL FRAME FLANGE. FOUND DURING WINTER MAINTENANCE, ANNUAL INSPECTION.

(CAN) RT FLOAT BAY NR 3, A CRACK IN FORWARD MID INBOUND VERTICAL FRAME FLANGE. FOUND DURING WINTER MAINTENANCE, ANNUAL INSPECTION.

(CAN) BAND CLAMP HOLDING PULLEY FOR WATER RUDDER STEERING CABLES FOUND BROKEN RT SIDE. MOUNT ROTATED AND ENGAGED FLAP UP SW CAUSING FLAPS TO NOT OPERATE. CLAMP INSTALLED. FLIGHT CONTROLS/FLAPS CYCLED. NO FURTHER DEFECTS.

Parts most often named Control Cable (5) · Pedal (1) · Torque Tube (1) · Bushing (1)

(CAN) PILOT REPORTED ACFT ROLLING SLIGHTLY RIGHT. RUDDER/AILERON INTERCONNECT FOUND CROSSED OVER. THIS CONDITION WAS REPLICATED ON GROUND WHEN HARD RT OR LT RUDDER AND AILERON APPLIED. BRACKET ADJUSTED TO ENSURE CABLE RUN STRAIGHT ON FUSELAGE FRAME TO PREVENT FURTHER ENTANGLEMENT. FUNCTION CHECKED SEVERAL TIMES. UNABLE TO RECREATE CONDITION ONCE ADJUSTED.

RT RUDDER PEDAL MOUNT ASSY HAS EXCESSIVE WEAR, PLAY BETWEEN THE BUSHING AND RUDDER MOUNT ASSY AT TOP WHERE BUSHING IS INSERTED FOR THE THROUGH BOLT.

RIGHT RUDDER PETAL MOUNT ASSY HAS EXCESSIVE WEAR FROM SIDE TO SIDE. BOLT WAS RUSTED IN PLACE AND VERY HARD TO REMOVE. FOUND BOLT SEVERLY GROOVED AROUND SHANK. BOLT APPEARS TO BE ORIGINAL AND NEVER LUBRICATED SINCE FACTORY. THE BOLT WORN AWAY, THE ATTACHMENT BRACKETS ALLOWING THE EXCESS SIDE TO SIDE PLAY.

Parts most often named Gas Generator (4) · Blade (3) · Turbine Blades (2) · Blades (2)

(CAN) DURING HOT SECTION INSPECTION, 1 COMPRESSOR TURBINE BLADE, FOUND CRACKED AT T/E, APPROXIMATELY MID CORD, LT UNDETECTED, COULD HAVE LED TO BLADE SEPARATION AND CATASTROPHIC ENGINE FAILURE. HAVE REQUESTED REPAIR AGENCY TO SEND 2 BLADES FOR METALLURGICAL ANALYSIS FOR ASSESSMENT OF ANY POSSIBLE OVER TEMPS, NO OVER TEMP OCCURRENCES HAVE BEEN REPORTED.

REPORTED THAT AFTER LANDING, PROPELLER SLOWED DOWN QUICKER THAN NORMAL. DURING SHUTDOWN THE PROPELLER DID NOT FEATHER AND CAME TO LOW SPEED STOP. INSPECTION OF THE ENGINES REVEALED GGT ROTOR BLADE SEPARATION. SUBJECT ENGINE WAS REMOVED FROM [S/N removed] AND SENT FOR REPAIR.

(CAN) DURING T/O ROLL, THE ENGINE LOST POWER. THE T/O WAS ABORTED. POST EVENT ENGINE EXAMINATION FOUND FRACTURED 2ND STAGE POWER TURBINE BLADES. THE ENGINE WAS REMOVED AND FORWARDED, WHERE IT WAS LAST REPAIRED LESS THAN 1000 HRS AGO, FOR INVESTIGATION AND REPAIR. THE ACFT WAS RETURNED TO [S/N removed] AFTER ENGINE REPLACEMENT. THE ENGINE DISASSEMBLY AND EXAMINATION REVEALED FRACTURED 2ND STAGE PT BLADES IN FATIGUE WITHIN THE FIXING. THE AFFECTED PARTS HAVE BEEN REQUESTED TO BE SENT FOR FURTHER INVESTIGATION.

Parts most often named Access Door (6) · Door Latch (6) · Striker (1)

PILOTS R/H FWRD DOOR LATCH DOES NOT CONTACT STRIKER PLATE. SHIMMED R/H FWD COPILOTS DOOR LATCH STRIKER PLATE. CONTACT ACCEPTABLE. NO DEFECTS NOTED.

DOOR SEALS/RIGGING IS A LITTLE OFF FROM NORMAL. COCKPIT IS 5 DB LOUDER THAN TAILS 003 & 005. MEASURED IN FRONT COCKPIT , 30 0#, LEVEL FLIGHT, 105DB IN THIS TAIL, 100DB IN THE REST (INCLUDES BLOCK 0 TAILS TOO) COMMENTS: AWAITING FURTHER DOWNTIME. DOES NOT AFFECT AIRWORTHINESS. WUC:11AD0 SHIMMED FWD COCKPIT DOORS TO INCREASE ENGAGEMENT WITH LOCK AND ADDED AERODYNAMIC SEALANT TO FWD LH DOOR CORNER TO SEAL AIR INTRUSION PATH. REF: AC 43.13-1B SECTION 4 1-36 TOOL & FOD CHECK C/W

FORWARD COCKPIT R/H DOOR LOWER LATCH DOES NOT MAKE CONTACT WITH STRIKE PLATE. COMMENTS: WUC:11AE0 FWD COCKPIT R/H DOOR LOWER LATCH STRIKER PLATE SHIMMED FOR POSITIVE CONTACT. OPS CHECK GOOD REF A/C 43.13 1B SECTION 4 1-36

Parts most often named Cylinder (9) · Bearing (1) · Exhaust Valve (1) · Rocker Boss (1)

(CAN) WHILE CARRYING OUT VALVE CLEARANCE INSPECTION, THE EXHAUST VALVE ROCKER ARM ON THE NR 7 CYLINDER WAS FOUND WITH EXCESSIVE PLAY BOTH RADIALLY AND AXIALLY. UPON REMOVAL BEARING BALLS FELL OUT OF THE BEARING CAGE.

AFTER TAKEOFF NR 2 CYLINDER EXHAUST VALVE STUCK IN OPEN POSITION LETTING PISTON CONTACT VALVE, BREAKING EXHAUST ROCKER HOUSING FROM CYLINDER. ACFT LOST POWER FORCING LANDING. ACFT CAUGHT FIRE.

THE NR 3 CYLINDER HEAD CRACKED AT THE ROCKER BOSS, ENGINE LOST POWER, AIRCRAFT EMERGENCY LANDED IN A FIELD. 2ND OCCURANCE.

Parts most often named Clamp (2) · Bearing (2) · Pilot Tube (2) · Piston Unit (1)

(AUS) PROPELLER BLADE THRUST ROLLER BEARING PNO 70096 BROKEN INTO FIVE PIECES - THE OTHER BEARING WAS CRACKED, CORRODED AND HAD PIECESMISSING FROM THE ROLLER - INVESTIGATION FOUND MOISTURE HAD CAUSEDTHE BEARING TO RUST WHICH LED TO THE EVENTUAL BEARING FAILURE -AIRCRAFT HAS A LOW UTILISATION RATE AND HAD BEEN ORIGINALLY FITTED TO AN OTTER SEAPLANE IN CANADA BEFORE BEING PURCHASED BYTHE PRESENT OWNER

Parts most often named Eyebolt (3) · Attach Fitting (2) · Mount Bracket (1) · Longeron (1)

(CAN) CRACK NOTED AT HORIZONTAL STABILIZER PEDESTAL ATTACH POINT, APPROXIMATELY BS 268, TOP RT FWD CRACK APPROXIMATELY 1" IN LENGTH.

(CAN) WHEN WE WERE DOING SL-NR 285, NOTICED A CRACK ON THE FWD WELD ON THE LT BRACKET THAT THE STABILIZER REAR SPAR MOUNT BRACKET BOLTS TO. (TC NR 20100218010)

(CAN) DURING ANNUAL INSPECTION IT WAS NOTED THAT ON THE LT AND RT HORIZONTAL STABILIZERS, THE HOLES THAT WERE DRILLED FOR THE GAP COVER SCREW HOLES WERE DRILLED THROUGH 2 RIVETS ON THE LT AND RT STABILIZERS ON THE LOWER SURFACES ONLY. THE RIVETS ATTACH THE SKIN TO THE END RIB. REPAIRS WILL BE ACCOMPLISHED PRIOR TO THE AIRCRAFT BEING RETURNED TO [S/N removed].

Parts most often named Actuator (4) · Adapter (2) · Coupling (1) · Gear (1)

WHEN FRONT COCKPIT PILOT ACTUATED THE FLAP SWITCH, BOTH SIDES DROPPED TO FULL DOWN IMMEDIATELY AND THE FLAP SWITCH WAS UNABLE TO MOVE THE FLAPS ON EITHER SIDE. MAINTENANCE FOUND THAT THE FLAP ACTUATOR HAD SEPARATED FROM THE FLAP MOTOR/GEARBOX. REMOVED AND REPLACED FLAP ACTUATOR.

WHILE COMPLYING WITH AIR TRACTOR SL 375, A FLAP MOTOR MOUNTING ADAPTER WAS FOUND WITH A BROKEN MOUNTING STUD. IF THE SECOND STUD HAD BROKE THE FLAP MOTOR WOULD FALL DOWN ON THE AILERON PUSH PULL TUBE. ON THREE OF OUR AIRCRAFT IT HAS BEEN THE LOWER OF THE TWO MOUNTING STUDS.

(CAN) RUBBER FLAP ACTUATOR COUPLING FOUND EXCESSIVELY TWISTED DURING FLAP ACTUATOR INSPECTION. RUBBER COUPLING REPLACED AND ACFT RETURNED TO [S/N removed].

Parts most often named Angle (2) · Gusset (2) · Bolt (1) · Nut (1)

(CAN) CRACK NOTED AREA "C" OF SC 71 APPROXIMATELY .5" IN LENGTH. APPROXIMATELY BS 105, LT SIDE CLUSTER AREA. SPECIFIC CRACK LOCATION AT WELD OF DOUBLER AND GUSSET TAT: 1944.5.

(CAN) CRACK NOTED AREA "C" OF SL 71, APPROX .5" IN LENGTH. APPROXIMATELY BS 105. RT SIDE CLUSTER AREA. SPECIFIC CRACK LOCATION AT WELD OF DOUBLER AND GUSSET.

(CAN) RETARDANT WAS DISCOVERED LEAKING FROM AROUND THE TANK DOORS. UPON INVESTIGATION, IT WAS NOTED THAT THE BOLT SECURING THE ANGLE INSIDE THE RT DISPERSAL GATE ASSY WAS BROKEN. THE BOLT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO [S/N removed]. (TC NR 20070830001)