PA-24Comanche

Parts most often named Bearing (5) · Propeller Assy (5) · Clamp (5) · Prop Assy (4)

PISTON SEIZED IN HIGH PITCH POSITION TO PISTON ROD TUBE (HAD TO BE REMOVED AND PRESSED OUT OF PISTON PROP) WOULD NOT CYCLE ON AIRCRAFT. PISTON TUBE AND PISTON SENT TO MFG TECH REP. SUSPECT THAT PROP GOV WORN PARTS ALLOWED METAL INTO PROP AND SEIZED PISTON TUBE. MARKED AND GROOVED PARTS.

Parts most often named Bungee Arm (5) · Transmission (3) · Tube (3) · Motor (2)

UPON TOUCH DOWN ON KMFE RUNWAY, RIGHT MAIN GEAR SLOWLY STARTED TO COLLAPSE. PILOT REACHED A FULL STOP SAFELY, ON FURTHER INVESTIGATION THE RIGHT SIDE MAIN GEAR CONTROL CABLE WAS FOUND BENT KEEPING THE GEAR FROM COMPLETELY EXTENDING TO THE DOWN AND LOCK POSITION.

THE LT MAIN LANDING GEAR PUSH PULL CONDUIT SEPARATED AT THE BALL END WHERE IT IS ATTACHED TO THE SUPPORT STRUCTURE IN THE WHEEL WELL. BELIEVE THIS FAILURE OCCURRED AT THE PREVIOUS LANDING GEAR RETRACTION. (K)

RT MLG EXTEND/RETRACT CONDUIT PUSH-PULL TUBING SEPARATED AT THE SWEDGE CONNECTION JUST OB OF THE LANDING GEAR CONTROL SUPPORT BRACKET. THERE WERE NO INDICATIONS OF IMPROPER INSTALLATION. (K)

Parts most often named Bolt (2) · Swivel Stud (2) · Cable Assy (1) · Stud (1)

(CAN) RT MAIN RETACTION PUSH PULL CONDUIT AT LANDING GEAR END WAS WORN BETWEEN INNER AND OUTER SLEEVES. SEPARATION OF THE SLEEVES DID NOT ALLOW THE GEAR TO EXTEND FULLY DOWN AND CAUSED ACFT TO VEER ONE WAY UPON LANDING.

APPROXIMATELY 2149 Z PILOT ADVISED HE BELIEVED THE AIRCRAFT LT MAIN GEAR COLLAPSED. THE SAFETY DEVICE (ROLL PIN) WAS NOT INSTALLED. THIS ALLOWED THE NUT TO ROTATE ALLOWING THE STUD TO BACK OUT OF THE CASTING. THIS CAUSED THE LT MAIN LANDING GEAR TO COLLAPSE. AD97-01-01R1 TO PREVENT MAIN LANDING GEAR (MLG) COLLAPSE CAUSED BY MAIN GEAR SIDE BRACE STUD CRACKED. ANNUAL INSPECTION C/W FEB 1, 2005.

ON C/W AD 95-20-07, BOTH MLG SIDE BRACE STUDS WERE FOUND CRACKED BY MPI. ONE STUD WAS NEW TYPE 487-596 WITH ZERK GREASE FITTING. CRACKS NOT VISIBLE WITHOUT MPI. CRACKS AT SHANK RADIUS.

Parts most often named Blade (6) · Bearing (2) · Clamp (2) · Piston (1)

DURING INSPECTION FOR COMPLIANCE WITH AD 97-18-02 PARAGRAPH (B)(2) AND (3). EDDY CURRENT INDICATIONS WERE FOUND IN THE RETENTION RADIUS OF BOTH BLADES.

PROPELLER SUBMITTED FOR INSPECTION IAW AD 97-18-02R1. BLADE [S/N removed] FOUND CRACKED APPROX 3 INCH LONG IN V GROOVE OF BLADE SHANK. BLADE [S/N removed] FOUND CRACKED USING EDDY CURRENT APPROX .5 INCH LONG IN V GROOVE. BOTH CRACKS ARE IN SUBJECT AREA OF AD. TIME SINCE LAST AD 97-18-02 INSPECTION 89.0 HRS ACCOMPLISHED SEPTEMBER 11, 2005.

(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION AND COMPLIANCE WITH AD 97-18-02. INSPECTION FOUND ONE BLADE; ONE CLAMP AND TWO BLADE BEARINGS WERE ALL UNSERVICEABLE.

Parts most often named Bolt (10)

DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE. TT 3705.

DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY,BOLTS, TOTAL AIRFRAME APPROXIMATELY 5515.0. NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. FILED WITH FAA. (SW15200210929)

Parts most often named Carburetor (4) · Screw (1) · Seal (1) · Servo (1)

THE ACCELERATOR PUMP IN THE CARBURETOR FAILED. INSPECTION SHOWED THAT THE PUMP HEAD GLAND HAD SHRUNK, SO THAT IT DID NOT PROVIDE A SEAL BETWEEN THE CARBURETOR BODY AND THE PUMP ITSELF. THE RESULT WAS THAT ADVANCING THE THROTTLE DID NOT CAUSE FUEL TO BE SQUIRTED FROM THE PUMP EXIT ORIFICE. REPLACEMENT OF THE PUMP RESOLVED THE PROBLEM.

(CAN) SCREWS HOLDING FLOAT BOWL TO CARBURETOR HOUSING. ALL SCREWS LOCKED BUT ALL LOOSE IN HOUSING CAUSING CHAFING BETWEEN BOWL, GASKET HOUSING WITH A 1/16 INCHES GAP AND ALL AROUND. DISCOVERED ON ANNUAL INSPECTION.

ENGINE ROUGHNESS DUE TO EXCESS RIGH MIXTURE. FOUND RECENT OVERHAULED SERVO TO BE AT FAULT DUE TO SEAL LEAKING FUEL INTO AIR CHAMBER. SERVO TSO [S/N removed] 30 HOURS. SEAL, [S/N removed].

Parts most often named Spar (5) · Rib (2)

FOUND 1 IN CRACK IN SPAR BEHIND TOP RUDDER HINGE, AT THE EDGE OF THE HINGE, RUNNING VERTICALLY. RUDDER HAD BEEN REMOVED, AND HINGES REMOVED TO LOOK FOR THIS CONDITION. SPAR HAS SUBSEQUENTLY BEEN REPLACED.

DURING AN ANNUAL INSPECTION, MORE THAN NORMAL SURFACE CORROSION WAS FOUND ON THE RUDDER TAIL POST. UPON DISASSEMBLY OF THE RUDDER, DISSIMILAR METAL CORROSION WAS PRESENT WHERE THE STEEL STIFFENER ATTACHES TO THE LOWER RIB (PN 2072904). (WP07200505592) (K)

DURING [S/N removed] OF AIRCRAFT THE RUDDER WAS REMOVED. NOTHING WAS FOUND ABNORMAL. REMOVAL OF THE UPPER RUDDER HINGE (PN 2018300. CRACKS WERE FOUND AT THE HINGE ATTACH POINT OF THE RUDDER SPAR (2072910). (WP07200505589) (K)

Parts most often named Housing (2) · Distributor (1) · P-Lead (1) · Points (1)

ROUGH MAGNETO ON RUN UP, FOUND MAGNETO TIMING ON RT MAGNETO OFF. INSPECTED CONTACT POINTS AND FOUND FOLLOWER THAT RIDES ON CAM IN MAGNETO TO HAVE LOOSE RIVETS. REPLACED POINTS. REINSTALLED MAG AND RUNUP CHECKS WERE OK.

(AUS) MAGNETO DISTRIBUTOR BLOCK CENTRAL BUSH LOOSE ALLOWING THE DISTRIBUTOR GEAR TO PARTIALLY DISENGAGE AND SHEAR THE TEETH.

DURING ANNUAL INSPECTION , MAGNETS WERE FOUND TO BE OUT OF TIME TO THE ENGINE. EXAM OF CAM / CONTACT POINT AREA, DISCLOSED OIL AND LG AMTS OF DUST AND ALUMINUM SHAVINGS. DISASSEMBLY OF MAGNETS DISCLOSED BEARING, OUTER RACE / CUP / LOOSE IN THE HOUSING. WEAR HAD REACHED POINT OF PERMITTING MOVEMENT THE ROTARY MAGNET SUFFICIENT CAUSE OIL SEEPAGE PAST OIL SEAL.

Parts most often named Torque Tube (3) · Stabilator Horn (1) · Structure (1) · Bearing (1)

REMOVED BOTH STABILATORS TO REPLACE BEARINGS. FOUND TORQUE TUBE CORRODED. THIS SECTION CANNOT BE SEEN WITHOUT REMOVING STABILATORS. IT IS AN UNPAINTED STEEL TUBE. REMOVED CORROSION, ALODINED, PRIMED AND PAINTED.

DURING ANNUAL INSPECTION, FOUND IT WAS NECESSARY TO REMOVE THE STABILATOR TORQUE TUBE ASSY TO CORRECT ANOTHER DISCREPANCY. THE RT AND LT STABILATORS WERE FOUND DIFFICULT TO REMOVE FROM THE TORQUE TUBE. THE INBD FITTING (PN 21420-02) WAS UNBOLTED FROM THE STABILATORS AND LEFT ON THE TUBE WHILE THE STABILATORS WERE REMOVED. DISCOVERED THE TORQUE TUBE HAD A LOT OF CORROSION BUILT UP ON IT.

NOTED LOOSENESS OF STABILATOR DURING ANNUAL. AD 94-13-10 ADDRESSES THIS PROBLEM. WHILE DIAGNOSING LOOSENESS, FOUND THE STABILATOR TORQUE TUBE BEARINGS WORN. THE TORQUE TUBE BEARING SUPPORT FITTINGS WERE FOUND OK PER THE AD. FOUND CORROSION BETWEEN BEARING AND OUTER RACE, WHICH CAUSED ADVERSE WEAR. REPLACED BEARINGS WHICH ELIMINATED LOOSENESS.

Parts most often named Stud (5) · Side Brace (1)

LANDING GEAR STUD IS TO BE INSPECTED EVERY 1,000 HOURS PER AD 97-01-01. CRACKED STUD IN QUESTION HAD ONLY 453 HOURS SINCE LAST MAGNAFLUX INSPECTION. (X)

(CAN) INSPECTION OF STUDS AS PER AWD 95-20-07 REVEALED FINE LINEAR CRACK INDICATIONS AT THE RADIUS UNDER THE BOLT HEAD. THE BOLTS WERE REJECTED.