DHC-2Beaver

Parts most often named Cylinder Head (22) · Cylinder (21) · Stud (5) · Piston (3)

DURING CRUISE FLIGHT, ENGINE LOST PARTIAL POWER. PILOT TURNED AROUND TO RETURNED, COULD NOT MAINTAIN ALTITUDE, AND LANDED. DURING TAXIING THE ENGINE DIED. PILOT NEVER TRIED TO RESTART ENGINE AND THE AIRCRAFT WAS TOWED. NO VISIBLE DAMAGE TO THE AIRCRAFT. INVESTIGATION FOUND THE NR 8 CYLINDER EXHAUST VALVE PUSHROD BROKEN AT ROCKER ARM END. THE PUSHROD WAS REPLACED AND THE ENGINE IS RUNNING GOOD.

(CAN) DURING AN INSPECTION FOR METAL CONTAMINATION FOUND AT A SCHEDULED INSPECTION, THE NR 8 CYLINDER EXHAUST VALVE GUIDE WAS FOUND TO HAVE COME LOOSE AND WAS BEING STRUCK BY THE EXHAUST VALVE. THE CYLINDER PN 399353, [S/N removed] WAS REMOVED WITH 1104.0 TSO, AND REPLACED WITH A [S/N removed] CYLINDER, PN SAME, [S/N removed] WITH TSO 292.6 TREM 1207.4. ALL WORK WAS PERFORMED MM. GROUND RUN AND LEAK CARRIED OUT, NO DEFECTS.

(CAN) DURING INSPECTION FOUND FOUR FAILED STUDS ON NR 3 CYLINDER ASSEMBLY. ALSO CRACK WAS SEEN ON FRONT CRANK CASE ADJACENT TO THE CYLINDER.

Parts most often named Fitting (8) · Torque Tube (3) · Plate (2) · Bar (2)

FORWARD LT LOWER TIE-ROD (FLYING WIRE) WIRE-PULL ATTACHMENT FAILED. THE AFT RT UPPER TIE-ROD (FLYING WIRE) WIRE-PULL ATTACHMENT FAILED. THE AIRCRAFT'S RIGIDITY TO ITS FLOATS BECAME EFFECTED, THE AIRCRAFT PIVOTED (ROLLED) TO THE LEFT. THE AIRCRAFT'S LT WING CONTACTED THE WATER RESULTING IN IT BECOMING SUBMERGED UPSIDE DOWN IN THE WATER.

(CAN) DURING A SCHEDULED 100 HR INSPECTION, THE RT FORWARD FLOAT FITTING, PN 58S926R WAS FOUND CRACKED ON THE BOTTOM SIDE OF THE FORWARD HOLE. THE FLOAT FITTING WAS REPLACED WITH A [S/N removed] FITTING, PN 58S926R TO RECTIFY THE DEFECT.

(CAN) ON ROUTINE INSPECTION OF FLOAT ASSY FOUND SMALL CRACK ON THE LT SIDE OF THE FORWARD SPREADER BAR. UPON REMOVAL OF THE FORWARD SPREADER BAR FOUND THAT THE RT FORWARD SPREADER BAR ATTACH FITTING WAS CRACKED. THE FLOATS WERE REMOVED FROM [S/N removed] AND THE OTHER ACFT THAT HAD THE ALUMINIUM ATTACH FITTING WAS INSPECTED WITH NO DEFECTS FOUND. THERE WAS NO VISIBLE INDICATION, FRETTING SMOKING OR LOOSENESS OF ATTACH BOLT ON THE OUTSIDE OF THE SPREADER BAR.

Parts most often named Connecting Rod (3) · Main Bearing (2) · Engine (2) · Case (2)

(CAN) DURING CRUISE, THE ENGINE HAD HIGH VIBRATIONS FOR COUPLE OF SECONDS AND THEN THE ENGINE STOPS SUDDENLY. THE PILOT DID AN EMERGENCY LANDING. THE AME`S FOUND THE CYLINDER NR 5 BEEN PUNCTURED BY CONNECTING ROD. ENGINE OVERHAUL SHOP ACKNOWLEDGED THE PROBABLE CAUSE IS THE FAILURE OF THE MASTER CONNECTING ROD. ENGINE OIL SAMPLE WAS SENT FOR FURTHER INVESTIGATION.

DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP. INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD BEARING. ENGINE REMOVED FOR OVERHAUL.

(CAN) DURING RUNUP AFTER INSPECTION, INVESTIGATION OF A MINOR OIL LEAK REVEALED THAT THE ENGINE CRANKCASE WAS CRACKED NEAR AN ENGINE THROUGHBOLT AT THE BASE OF NR 2 CYLINDER, BETWEEN CYLS NR 2 AND NR 3. THE ENGINE WAS REPLACED. (TC NR 20071109004)

Parts most often named Control Cable (6) · Torque Tube (3) · Mount (2) · Spring (1)

(CAN) AFTER WATER LANDING PILOT EXPERIENCED LOSS OF WATER RUDDER STEERING CONTROL. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE TORQUE TUBE WHICH CONTROLS THE WATER RUDDER/TAIL WHEEL STEERING HAD SUFFERED A TORSIONAL SHEAR ACROSS THE TUBES DIAMETER AT ITS MIDWAY POINT. THE FAILURE WAS A DIRECT RESULT OF INTERNAL CORROSION ON THE TUBE.

(CAN) ON THE TAKEOFF RUN THE PILOT HOLDING FULL RT RUDDER NOTED A LOUD SNAP AND THE RT RUDDER PEDAL MOVED FORWARD TO THE FIRE WALL. THE TAKEOFF WAS ABORTED AND THE ACFT RETURNED TO THE DOCK. ON INVESTIGATION, IT WAS REVEALED THAT THE RT RUDDER BRACKET HAD FAILED AT THE LOWER WELDED ATTACH AREA. IT APPEARS THAT THE WELD DID NOT FULLY PENETRATE THE TUBULAR SUB STRUCTURE AND POPPED OFF THE BRACKET ASSY. THE OPERATORS FLEET WERE INSPECTED FOR SIMILIAR DAMAGE BUT NONE WERE FOUND TO BE FAULTY.

(CAN) ON REMOVAL OF RUDDER FOR BEARING REPLACEMENT CORROSION WAS PRESENT ON THE OB ATTACH POINTS OF THE RUDDER BELLCRANK NR C2TR445 (PICTURE ATTACHED) CORROSION WAS NOT EVIDENT BEFORE THE REMOVAL OF THE RUDDER AS THE DAMAGED AREA WAS COVERED BY THE RUDDER CONNECTING RODS NR C2UT233. THE AIRCRAFT NOTED ABOVE HAS BEEN OPERATED EXTENSIVELY FROM SALT WATER. (TC NR 20070209005)

Parts most often named Magneto (3) · Gear (2) · Spring (1) · Distributor Gear (1)

(CAN) DURING THE SECOND GROUND RUN ON AN O/H ENGINE, THE ENGINEER SELECTED RT MAGNETO, THE ENGINE RPM DECAYED, AND WAS FOLLOWED BY A LOUD BACKFIRE. THE ENGINEER SELECTED BOTH MAGNETOS AND THEN SHUT ENGINE DOWN. AFTER AN INSPECTION, THE RT INTERNAL DRIVE GEAR HAD FOUND TO HAVE FAILED. TIME ON THE MAG WAS 0.0 TSO. THE RT MAGNETO, PN SB9RU-3, [S/N removed] WAS REPLACED WITH AN O/H MAGNETO, PN SB9RU-3, [S/N removed] IAW MM. GROUND RUN PROCEDURES CARRIED OUT AND THE ACFT WAS RETURNED TO [S/N removed].

LT MAGNETO SEAL - PART OF BLOWER ASSY APPEARS TO HAVE SHRUNK ALLOWING SEAL TO LEAK IN 4 BOLT HSG PLATE PN 164315. PERHAPS THE ENGINE OIL IS NOT COMPATIBLE WITH THE SEAL MATERIALS. SB 1266 EXPLAINS THIS ASSEMBLY.

(CAN) DURING CRUISE OPERATIONS, THE ENGINE WAS NOTED AS RUNNING ROUGH. THE AIRCRAFT RETURNED TO THE MAINTENANCE FACILITY FOR INVESTIGATION. INSPECTION REVEALED A UNSERVICABLE DISTRIBUTOR GEAR. MAGNETO REMOVED FROM [S/N removed].

Parts most often named Frame (9) · Strut (1) · Tube (1) · Tube Frame (1)

(CAN) DURING MODIFICATION TO THE FWD FUSELAGE FRAME "BIRDCAGE" IAW STC SA97-88, A LOT OF CORROSION HAS BEEN VISUALLY DISCOVERED ON THE LOWER TUBES. IT HAS BEEN DETERMINED THAT IT WOULD BE CHEAPER AND FASTER TO CHANGE THE BIRDCAGE RATHER THAN REPAIR IT. THIS BIRDCAGE HAS BEEN SENT AS A CORE EXCHANGE AND THEN SENT FOR FURTHER EXPERTISE.

(CAN) DURING AN UNSCHEDULED FWD TUBULAR FRAME, BIRDCAGE REPLACEMENT, THE RUDDER STOPS ON THE RECEIVED REPAIRED TUBULAR STRUCTURE WERE FOUND TO HAVE BEEN WELDED .5" FWD OF THE DWG LOCATION. IT WAS ALSO NOTED THAT THE FUEL SELECTOR CABLE GUARD WAS FOUND WELDED ON THE WRONG SIDE. BOTH ITEMS WERE REPAIRED IAW THE APPLICABLE DWG C2FS, 3147A, SB 2/49, AND PSM 1-2-3 TO RECTIFY THE DEFECTS.

(CAN) INSPECTION REQUIRED BY CF98-38 WAS CARRIED OUT. THE BULKHEAD AND THE CHANNEL ASSEMBLY WERE FOUND CRACKED. P/N C2FS533 FORMER AND P/N C2FS4045A WERE REPLACED.

Parts most often named Spar (6) · Rib (4) · Doubler (1)

DURING ROUTINE MX WITH THE ELEVATOR OFF, A CRACK WAS NOTED ON THE BUTT RIB DOUBLER PN C2-TE-9ND. CF80-25 REQUIRES A INSP OF THE AREA EVERY 400 HOURS, THE CRACK WAS NOTICED WITH 278.2 HOURS SINCE THE LAST INSP.

(CAN) THIS ELEVATOR LEADING EDGE RIB WAS FOUND CRACKED WHILE CARRYING OUT ANNUAL INSPECTION. IT WAS DETERMINED THAT THE CRACK WAS THE RESULT OF TOO SHARP OF A BEND RADIUS IN THE AREA WHERE THE PART GETS RIVETED TO THE ELEVATOR LEADING EDGE SKIN. THIS DEFECT WAS COMMUNICATED AND THE TOOLING HAS BEEN REPAIRED ALLOWING FOR A MOVE UNIFORM RADIUS ON THE PART IN QUESTION. (TC NR 20070426009)

(CAN) LT AND RT ELEVATOR FRONT SPAR UPPER ATTACH HOLES FOR CENTER HINGE POSITION HAS A SMALL CRACKS AROUND THE UPPER AN3 BOLT HOLE.

Parts most often named Control Cable (3) · Rod (2) · Torque Tube (2) · Push-Pull Rod (2)

PUSH/PULL TUBE WAS REMOVED FROM THE ACFT DURING AN ANNUAL INSPECTION AND WAS FOUND TO HAVE SEVERE PITTING AND HOLES THRU THE TUBE. FOUND THE ALUMINUM WAS SEVERLY CORRODED AT THE AREA WHERE IT MATES WITH THE STEEL TUBE. CORROSION WAS SO SEVERE IT CRACKED THE FITTING. ONLY WAY TO DISCOVER THE CRACK WAS TO DISASSEMBLE PART WHICH IS USUALLY ONLY DONE AT A REPAIR SHOP.

(CAN) DURING FUEL BAY MX, THE ELEVATOR PUSH PULL ROD ASSY PN C2CF619A8 WAS NOTED TO HAVE BLISTERING IN THE PAINT COVERING. ON FURTHER INVESTIGATION THE BLISTERS WERE REMOVED TO REVEAL CORROSION, WATER AND A HOLES IN THE TUBE ASSY. THE UNIT HAS BEEN REMOVED FROM [S/N removed] PENDING NDT INSP AND REPAIR/OVERHAUL. (TC 20100217001)

DURING THE REPLACEMENT OF THE BEARING IN THE ELEVATOR BELL CRANK ASSY, THE LINKS AND SPACERS WERE THE ELEVATOR CABLE ATTACHES WERE FOUND WORN, SPACERS WERE WORN RIGHT THROUGH (PN C2CF349ND). THE AN3 BOLT THAT ATTACHES LINK IN PLACE WAS WORN 1/3 THROUGH. SPACERS AND BOLTS WERE REPLACED.

Parts most often named Selector (2) · Cable (1) · Shaft (1) · Handle (1)

(CAN) REMOVED CABLE DRUM FROM FUEL SELECTOR, LUBRICATED SELECTOR WITH YIELD AND REINSTALLED CABLE DRUM. (TC NR 20070711007)

(CAN) STRONG FUEL ODOR IN COCKPIT. INVESTIGATED AND FOUND FUEL SHUTOFF VALVE WAS LEAKING. OVERHAULED PN PV3320-10 INSTALLED AND SYSTEM CHECKED FOR LEAKS. AIRCRAFT [S/N removed]. (TC NR 20071024006)

(CAN) FUEL SELECTOR CABLE VERY BADLY CORRODED, CABLE FAILED WHEN REMOVED. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 20071214003)

Parts most often named G Switch (4) · Elt (2) · Battery (2) · Antenna (1)

DURING A ROUTINE ELT INSPECTION IAW 14 CFR 91.207, THE ELT G SWITCH WAS FOUND TO BE NON-FUNCTIONAL. THIS IS A RECURRING PROBLEM WITH THESE BEACONS.

DURING A ROUTINE ELT INSPECTION IAW 14 CFR 91.207, THE G SWITCH WAS FOUND TO BE INOPERATIVE. THIS IS A RECURRING PROBLEM WITH THESE BEACONS.

(CAN) BATTERY REPLACED AFTER YEAR 1, (SUPPOSED TO BE A 5 YEAR LITHIUM BATTERY) G SWITCH FAILURE 3 TIMES IN 4 YEARS. UNIT HAS BEEN REPLACED WITH ACK 406MHZ ELT. (TC# 20140916006)