PA-46Malibu · Meridian · M-Class

Parts most often named Mount (15) · Shield (1) · Heat Shield (1) · Fastener (1)

(CAN) ENGINE MOUNT CRACKED AT 2 PIECE ATTACH FOOTING. CRACK IDENTIFIED BY VISUAL INSPECTION AS PER SB1103C. THIS IS THE 31ST ENGINE MOUNT WITH SUCH FAILURE THROUGH THE SHOP. ENGINE MOUNT WILL BE REPAIRED AND RE-INFORCED USING TCCA RDC C-RA03-047. FAILURE TO INSPECT MOUNT AND RE-INFORCE MOUNT AS PER RDC C-RA03-047 MAY RESULT IN NOSE LANDING GEAR COLLAPSE.

(CAN) CUSTOMER MOUNT WAS SENT IN WITH CRACK IN LANDING GEAR ATTACHMENT. THIS IS THE 29TH ENGINE MOUNT WITH THIS DEFECT TO COME THROUGH OUR SHOP. REPLACEMENT ENGINE MOUNT WAS PROVIDED WITH STRENGTHENED ACTUATOR ATTACH FITTING INSTALLED AS PER RDC C-RA03-047. NOTE: PIPER SB 1103C DOES NOT REQUIRE REPETITIVE INSPECTION OF "ONE PIECE" STYLE ATTACHMENT POINT. THIS MOUNT HAD THIS NEWER STYLE ATTACHMENT POINT.

(CAN) ENGINE MOUNT DETECTED CRACKED BY AMO SENT IN FOR REPAIR. TWO PIECE FOOT STYLE MOUNT WITH CRACK IN TUBES ABOVE MLG ACTUATOR. ENGINE MOUNT WILL BE REPAIRED AND REINFORCED USING TCCA RDC C-RA03-047. THIS IS THE 33RD ENGINE MOUNT THROUGH THE SHOP WITH THIS DEFECT. PIPER SB 1103C DEALS WITH THIS ISSUE. ALL ENGINE MOUNTS REGARDLESS OF 1 OR 2 PIECE FEET SHOULD BE INSPECTED FOR CRACKS IMMEDIATELY ABOVE THE ACTUATOR ATTACHMENTS.

Parts most often named Engine (17)

(CAN) CUSTOMER REPORTS ON TAKE-OFF ENGINE ROLLED BACK ON POWER. CUSTOMER INSTANTLY REDUCED POWER AND ABORTED TAKEOFF AND DID NOT SEE WHAT INSTRUMENTATION WAS READING. NO DAMAGE, INJURIES OR INCIDENT REPORTED.

(CAN) DURING TAKE OFF, THE AIRCRAFT HAD AN OIL PRESSURE DROP FROM 48 PSI TO 28 PSI. THE PILOT DECLARED AN IFSD AND LANDED WITHOUT INCIDENT. UPON LANDING, THE OIL PRESSURE RETURNED TO NORMAL. THE TROUBLESHOOTING REVEALED METALLIC DEBRIS IN THE OIL FILTER.

(CAN) THE PLANE CRASHED SHORTLY AFTER TAKEOFF AS A RESULT OF A REPORTED TECHNICAL ISSUE. PRELIMINARY INFORMATION IS STATING ENGINE TROUBLE OCCURRED JUST AFTER TAKEOFF AND THE CRASH IS DESCRIBED AS A FORCED LANDING.

Parts most often named Magneto (4) · Cam (3) · Points (2) · Distributor Gear (1)

BREAKER CAM WORN BEYOND [S/N removed] LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START.

PILOT REPORTED FAILED RT MAGNETO. REMOVED MAGNETO FROM ENGINE AND DISASSEMBLED. FOUND ONE OF THE COIL ANCHOR WEDGES WAS DISPLACED AND HAD MIGRATED ONTO THE SECONDARY TOWER. THE TOWER WAS BURNED AND MELTED AND THERE WAS OBVIOUS SIGNS OF A DIRECT SHORT AT THE SECONDARY TERMINAL CONTACT TAB.

PILOT REPORTED LOSS OF POWER AND A ROUGH RUNNING ENGINE. AFTER COMPLETING MAGNETO CHECK, A DEAD LT MAGNETO WAS DISCOVERED. THE MAGNETO WAS DISASSEMBLED AND THE DISTRIBUTOR GEAR WAS DISASSEMBLED AND THE DISTRIBUTOR GEAR WAS FOUND TO HAVE 15 TEETH THAT WERE LIBERATED FROM IT WHICH RENDERED THE OUTPUT OF THE MAGNETO USELESS. SUBMITTER STATED DISTRIBUTOR GEARS SHOULD BE DISCARDED AT ROUTINE OVERHAUL DUE TO HEAT CRYSTALIZATION AND EMBRITTLEMENT.

Parts most often named Turbocharger (3) · Clamp (2) · Controller (1) · Lock Nut (1)

MANIFOLD PRESSURE OSCILLATED UNCONTROLLABLY FOR 30 SECONDS. REDUCING POWER MAY HAVE STOPPED OSCILLATION. OCCURRED DURING CLIMB AFTER INITIAL POWER REDUCTION. NO FURTHER PRECAUTIONARY PROCEDURES REQUIRED DURING FLIGHT, EXCEPT TO HAVE THE ENGINE INSPECTED AS SOON AS POSSIBLE. INSPECTION REVEALED A CRACK WHERE THE RIGHT TURBOCHARGER ATTACHES TO THE ENGINE OIL SUMP SO AIRCRAFT WAS REMOVED FROM [S/N removed] PENDING INVESTIGATION BY ENGINE MANUFACTURER.

THE LOCKNUT ON THE TURBO COMPRESSOR SHAFT CAME OFF. THE NUT CAUSED DAMAGE TO THE COMPRESSOR FAN BLADES. THE INTER-COOLER WAS REPLACED AS A PRECAUTIONARY MEASURE AFTER IT INGESTED FRAGMENTS FROM THE FAN BLADE AND NUT.

TURBOCHARGER WOULD NOT OBTAIN MANIFOLD PRESSURE AT CRITICAL ALTITUDE. TURBOCHARGER EXHIBITS NOTICEABLE RADIAL PLAY AND DRAGGING. THE COMPRESSOR OIL SEAL APPEARS TO BE DEFECTIVE. OIL IS BYPASSING THE SEAL BEING FORCED INTO ENGINE INDUCTION SYS. TURBINE WHEEL SHOWS CONSIDERABLE WEAR AND EROSION.

Parts most often named Skin (6) · Access Panel (1)

DURING ANNUAL INSPECTION NOTED WING ROOTS, BOTH LT AND RT WRINKLED. AREA OF DEFECT IS FORWARD OF MAIN CARRY THRU SPAR. A [S/N removed] OF 3 WAVES EXTENDING APPROXIMATELY 6-8 INCHES LONG. PROBABLE CAUSE: SEVERE TURBULENCE OR OVER CONTROL OF AIRCRAFT EXCEEDING (G) LIMITATIONS. WING REMOVED AND REPLACED. (K)

WING FUEL PANELS HAVE A FOAM FILLER BLOCK AND SEALANT TO PREVENT WATER FROM BEING TRAPPED AT PANELS. THE SEALANT HAD TORN FREE AND THE FOAM BLOCK WAS FLOATING LOOSE IN THE TANK FROM ONE PANEL AND WAS LOOSE FROM A SECOND PANEL BUT WAS NOT FREE IN THE TANK YET. THESE PIECES ARE ABOUT 5 INCHES LONG, 3 INCHES WIDE AND .5 INCH THICK. PANELS WERE REPAIRED AND REINSTALLED IAW MM.

(CAN) FOUND UPPER AND LOWER WING SURFACE SPAR RIVETS SMOKING. SUBMITTER STATES THAT A SIMILAR PROBLEM WAS ADDRESSED IN PIPER SB 796A.

Parts most often named Piston Pin (2) · Cylinder (2) · Bolt (1) · Retainer (1)

NR 2 CYLINDER SEPARATED FROM CRANKCASE AT THE MOUNTING BOLTS. ENGINE CONTINUED RUNNING AND SUBSEQUENT SHAKING BROKE EXHAUST MANIFOLD ON LT SIDE BETWEEN CYLINDERS AND TURBOCHARGER. NO HEAT DAMAGE TO SURROUNDING COMPONENTS NOTED PROBABLY BECAUSE AIRCRAFT WAS MOSTLY IN HIGH SPEED DESCENT AT LOW POWER UNTIL SHUTDOWN IN LANDING PATTERN.

(CAN) THE NR 2 CYLINDER ROCKER COVER HOLD-DOWN BOLTS BROKE, SENDING INTAKE BOLT UPPER BROKEN HALF THROUGH THE ROCKER COVER. THE CYLINDER WAS REMOVED AND SENT FOR REPAIR. NO OTHER DAMAGE WAS FOUND TO THE CYLINDER OR THE PISTON. ALL OTHER HOLD-DOWN BOLTS WERE CHECKED.

ON REMOVAL OF NR 6 CYLINDER DUE TO METAL FOUND IN OIL FILTER, FOUND PIECES IN ROCKER AREA. THIS WAS VERIFIED AS CONTAMINANTS THROUGH T.C.M. NO [S/N removed] INFO ISSUED TO DATE ON AN ONGOING PROBLEM OF THIS PART.

Parts most often named Landing Gear (2) · Scissor Link (1) · Cotter Pin (1) · Centering Mech (1)

OWNER NOTICED A VIBRATION SHORTLY AFTER LANDING. FOUND NLG CENTER TORQUE LINK HARDWARE MISSING AND NLG MISALIGNED. COMPLETED INSPECTION OF NLG ASSY AND FOUND BOLT, NUT, WASHER, AND COTTER KEY MISSING FROM CENTER TORQUE LINK AND NLG TIRE WAS LIGHTLY FLAT SPOTTED.

UPON TOUCHDOWN AIRCRAFT VEERED LT ABRUPTLY AND DEPARTED RUNWAY SURFACE. GEAR EXTENSION AND INDICATION WERE NORMAL. INVESTIGATION REVEALED THAT UPON TOUCHDOWN THE NOSE LANDING GEAR HAD FAILED TO CENTER CORRECTLY DURING EXTENSION.

(CAN)A FULL PENETRATION CRACK, 5 CM IN LENGTH, WAS FOUND ON THE NOSE TRUNNION AS INDICATED. REPLACEMENT PART WAS P/N 83606-07 AND TRUNNION KIT P/N 766-211.

Parts most often named Sequence Valve (2) · Valve (1) · Circuit Board (1) · Spring (1)

AFTER LANDING AT HOME BASE, NOTICED HYDRAULIC FLUID ON GROUND UNDER NOSE WHEEL AREA. DISCOVERED NLG SEQUENCE VALVE LEAKING. PART REPLACED BY MAINTENANCE.

PILOT REPORTED HYDRAULIC LIGHT ON AFTER TAKE OFF. RETURNED AND FOUND NLG SEQUENCE VALVE LEAKING. REMOVED AND REPLACED VALVE.

NOSE GEAR EMERGENCY EXTENSION SPRING UNABLE TO EXTEND NOSE GEAR AND LOCK IN-FLIGHT. AFTER LANDING AND ROLL-OUT ON MAINS HOLDING NOSE OFF, NOSE GEAR LOCKED AT 30 KNOTS AIRSPEED. NEW PART WAS 2 INCHES LONGER THAN OLD PART. SUBMITTER RECOMMENDED TIME-LIFE CYCLE REPLACEMENT SCHEDULE.

Parts most often named Tailpipe (2) · Exhaust Gate (1) · Flange (1) · Collector Ring (1)

THIS IS THE COLLECTOR THAT MOUNTS TO THE TOP OF THE LT TURBO. FOUND HOLES ON BOTH SIDES OF WELDS ON THE AFT END NEAR THE SMALL BALANCE TUBE. (K)

DURING MAINTENANCE, CHECKING EXHAUST FOR POSSIBLE LEAKS, FOUND RIGHT HAND EXHAUST TEE ABOVE RIGHT TURBOCHARGER CRACKED HALF WAY AROUND, THE CRACK IS NOT VISIBLE FROM OUTSIDE AND WAS FOUND BY PRESSURIZING EXHAUST AND SOAP AND WATER.

PILOT EXPERIENCED LOW MP AT 22K. SLOWLY BLED DOWN AT CRUISE. PILOT SAID AT NORMAL 25 INCHES, IT BLED DOWN TO 22 INCHES WITH FUEL THROTTLE. UPON CHECK MECHANIC NOTED EX STAINS ON R/CYL BANK AND DISCOVERED FLANGE COMPLETELY SEPARATED AT TURBO FLANGE AREA EXHAUST MANIFOLD. NEW PART ORDERED AND REPLACED.

Parts most often named Intake Duct (1) · Door (1) · Screen (1) · Air Filter (1)

AIRCRAFT WAS UNDERGOING AN ANNUAL INSPECTION. DURING THE FUNCTIONAL CHECK OF THE ALTERNATE AIR SYSTEM THE TECH DISCOVERED LOOSE AND WORN ALTERNATE AIR COMPONENTS AT AIR BOX ASSY. NEW PARTS WERE INSTALLED AND SYSTEM RIGGED IAW MM. SYSTEM FUNCTIONED NORMAL. MANUFACTURER WAS NOTIFIED AND SUPPLIED PHOTOS.

(CAN) ENGINE AIR INTAKE DUCTS / INERTIA SEPERATORS WERE FOUND TO BE CRACKED PRETTY MUCH ALL OVER. PLEASE NOTE THAT THE PAIR OF AIR INTAKE DUCTS IS CRACKED. THEY ARE MADE OF FIBERGLASS. NEW INTAKES WERE ORDERED AND THE ENGINE AND ENGINE MOUNT HAVE BEEN REMOVED TO ALLOW REPLACEMENT.

DURING FLIGHT AT ALTITUDE, AIRCRAFT LOST MANIFOLD PRESSURE RESULTING IN LOSS OF CABIN PRESSURE. ON GROUND, FOUND LEFT FORWARD INDUCTION TUBE CLAMP OFF. AIRCRAFT WAS A RAM CONVERSION. RE-INSTALLED CLAMP. GROUND CHK OK. SUSPECT LOOSE CLAMP.