PA-38Tomahawk

Parts most often named Cylinder (7) · Push Rod (3) · Rocker Boss (1) · Piston (1)

(AUS) NR 2 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM. ENGINE HAD BEEN SITTING IDLE FOR AT LEAST 18 MONTHS AND HAD JUST BEEN RETURNED TO OPERATION.

OIL LEAK AT NR 1 CYLINDER APPEARED TO BE COMING FROM PUSHROD TUBE SEALS. FURTHER INVESTIGATION AND PRESSURE CHECK DISCLOSED LEAK UNDER INTAKE PUSHROD AT HEAD/BARREL JOINT. A 2 INCH CRACK, 1.50 INCHES DOWN FROM TOP OF CYLINDER WALL WAS VISIBLE INSIDE THE CYLINDER. CYLINDER HAD BEEN CHROMED. CYLINDER SHOP STATED THIS IS COMMON PROBLEM ON CHROME CYLINDERS.

(AU) INSPECTION FOUND THERE WAS EXCESSIVE ROCKER SHAFT TO ROCKER SHAFT BOSS CLEARANCE ON THE INTAKE SIDE OF TWO SEPARATE CYLINDERS. THIS CLEARANCE WAS MEASURED AT 0.008 INCH.

Parts most often named Carburetor (2) · Float (1) · Jet Nozzle (1) · Needle Seat (1)

ENGINE QUIT DURING FLIGHT DUE TO CARBURETOR MALFUNCTION 4 MILES SOUTHEAST OF AIRPORT, MAKING AN EMERGENCY LANDING WITHOUT DAMAGE TO AIRCRAFT, PILOT OR PASSENGER. CARBURETOR WAS REMOVED FROM AIRCRAFT AND SENT FOR OVERHAUL. (WO NR 88013). AIRCRAFT HAD BEEN SETTING FOR A LONG PERIOD OF TIME, WITH FUEL TANKS HALF FULL, MAKING MOISTURE IN THE FUEL SYSTEM. RECOMMENDATION FOR OWNERS, DRAIN FUEL SYSTEM AND RUN THE ENGINE AT LEAST ONCE A WEEK FOR AIRCRAFT TIE DOWN OUTSIDE OF HANGAR. (SO15200509104) (K)

LOSS OF POWER AND SUBSEQUENT OFF-AIRPORT LANDING OCCURRED AFTER DARK. REMOVABLE ''''TANG'''' FROM A HELICOIL WAS FOUND IN THE FINGER SCREEN CAVITY STUCK IN THE HOLE OF THE SEAT (OF THE NEEDLE AND SEAT) STOPPING FUEL FLOW TO THE FLOAT BOWL. (X)

AIRCRAFT ENGINE LOST POWER FROM PARTIAL OBSTRUCTION OF MAIN JET WHICH FEEDS DISCHARGE NOZZLE. MATERIAL APPEARS TO HAVE BUILD-UP OF SEDIMENT SCALE. RECOMMEND INTERNAL BOWL INSPECTION OF CONDITION AT EACH 2,000-HOUR OPERATION.

Parts most often named Blade (4) · Propeller (1)

Parts most often named Bolt (2) · Attach Bolt (1) · Fitting (1)

(AUS) LT MAIN LANDING GEAR ATTACHMENT BOLT SHEARED. LT MAIN LANDING GEAR COLLAPSED. (OTHER CAUSE: MATERIAL - ENVIRONMENT ) (CASA NR 510002065)

(AUS) LEFT MAIN LANDING GEAR INBOARD ATTACHMENT FITTING SEVERELY CORRODED ALLOWING THE LEFT MLG INBOARD ATTACHMENT BOLT TO PULL OUT OF THE WING. RIGHT MLG FITTING CORRODED TO A LESSER DEGREE. PART TC: 8,079.

Parts most often named Bolt (3) · Saddle Bolt (1)

RT MLG DEPARTED AIRCRAFT DURING LANDING. FORWARD CLAMP BOLT FAILED CAUSING LANDING GEAR TO ROTATE FROM ITS PROPER LOCATION. BOLT WAS FOUND WITH A SHEAR TYPE FAILURE.

MLG ATTACH BOLTS WERE REMOVED FOR INSPECTION DUE TO AN INCIDENT THAT OCCURED ON 6/17/02 WITH A SAME MODEL AIRCRAFT. FOUND THE INBOARD GEAR ATTACH BOLTS FOR BOTH MAIN LANDING GEAR BENT IN THE SHANK AREA. ONE BOLT HAD ITS SHANK DISPLACED APPROX. .012 OF AN INCH. SECOND BOLT SHANK WAS DISPLACED APPPROX. .008.

Parts most often named Frame (4)

(AUS) FUSELAGE FRAME REINFORCEMENT CHANNEL DISTORTED AND CRACKED ON FLANGES. FUSELAGE FRAME DISTORTED WITH A SMALL CRACK WHERE ARIVET HAD PULLED OUT AT THE LOWER OUTBOARD ATTACHMENT TO THEFUSELAGE SKIN. FOUND DURING INSPECTION IAW AD/PA38/25.

(AUS) FUSELAGE FRAME LOCATED AT STN 99.9 CRACKED IN LOWER RH EDGE. THE FRAME HAD PREVIOUSLY BEEN REPAIRED BY INSTALLATION OF A DOUBLER AND CHANNEL AT BOTH LOWER CORNERS.

FS 99.29 FRAME ASSEMBLY (PN 77467-09) WAS FOUND BUCKLED IN THE VICINITY OF THE RT WING AFT ATTACH POINT. PIPER [S/N removed] KIT 765-177 REAR SPAR FRAME STIFFENER HAD NOT BEEN INSTALLED. DAMAGE APPEARS TO HAVE BEEN CAUSED BY POSSIBLE HARD LANDING.

Parts most often named Bracket (2) · Bearing (1) · Control (1)

FOUND EXCESSIVE PLAY IN ELEVATOR CONTROL SYSTEM. FOUND BOTH PULLEY BRACKETS BROKE WHERE BOLT GOES THROUGH FIVE PULLEYS. (TRIM, RUDDER, ELEVATOR, CABLES) AT FS 134. SUBMITTER SUGGESTED DYE CHECK FOR CRACKS IMMEDIATELY.

INVESTIGATION OF OFF AIRPORT LANDING FOUND EVIDENCE OF VACUUM FILTER LINES BEING CHAFED. IT WAS REPORTED ELEVATOR CONTROL FAILED TO RESPOND DURING TAKEOFF. SUBMITTER SUSPECTS CHAFE ON HOSE LINES IS INDICATIVE OF BINDING OR A CONTRIBUTING FACTOR TO LOSS OF ELEVATOR CONTROL. RECOMMENDS MORE ATTENTION TO CONTROL CLEARANCES DURING INSPECTION. HOSE LINE, PN 7791005.

Parts most often named Bracket (4)

Parts most often named Lifter (1) · Crankshaft (1) · Bolt (1)

AIRCRAFT DESTROYED AS A RESULT OF FORCED LANDING INDUCED BY A SEPARATION OF THE ENGINE CRANKSHAFT. SUBSEQUENT INVESTIGATION DISCLOSED A FATIGUE FAILURE ADJACENT TO THE CENTER MAIN BEARING JOURNAL. THIS ENGINE HAD EXPERIENCED 2 PREVIOUS PROPELLER STRIKES WHICH DID NOT REQUIRE CRANKSHAFT INSPECTION UNDER LYC AD 91-14-22. SUBMITTER SUGGESTED REVISING LYCOMING AD 91-14-22 TO REQUIRE CRANKSHAFT INSPECTION IAW LYC SL L163C, FOLLOWING ANY PROPELLER STRIKE RESULTING IN PROP REWORK OR REPLACEMENT.

DURING ANNUAL INSPECTION, NR 2 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION. WHEN CYLINDER WAS REMOVED, THE CUP PORTION OF THE EXHAUST SOLID LIFTER FELL TO THE FLOOR. THE CUP SECTION OF THE LIFTER HAD BROKEN COMPLETELY OFF. ALL LIFTERS HAD BEEN REPLACED DURING PREVIOUS ENGINE OVERHAUL.

Parts most often named Longeron (2)

LONGERON LOCATED IN THE FUSELAGE, BOTTOM LEFT, CRACKS AROUND THE NUTPLATES DUE TO STRESS FROM THE STEP. PREVENTION MAY BE A DOUBLER SLID UNDER THE CHANNEL RIVETED TO THE SKIN. THIS WILL PREVENT THE FLEX AROUND THE NUTPLATES WHERE CRACKS OCCUR.