8Silvaire

Parts most often named Spar (8) · Spar Capstrip (1)

DURING ANNUAL INSPECTION OF THE CARRY THROUGH SPARS, INTER GRANULAR CORROSION WAS FOUND IN THE BOTTOM WEB OF THE AFT SPAR, NONE FOUND IN THE FORWARD SPAR. PROBABLE CAUSE WAS IN MANUFACTURING. RECOMMEND CONTINUED INSPECTION OF OLD SPARS.

INTERGRANULAR CORROSION, FOUND IN THE FOLLOWING WING COMPONENTS DURING A REPAIR/REBUILD PROCESS. LT AND RT MAIN SPAR BEAMS, REAR, LEFT MAIN SPAR BEAM, FRONT.

DURING C/W AD 96-24-17R (AMEND NR 39-10229 EFF 1-27-97), INTERGRANULAR CORROSION WAS FOUND ON THE LOWER WEB OF THE RT REAR SPAR AFT FACE APPROXIMATELY 17 INCHES FROM THE WING ATTACH POINT. THE CORROSION HAD CAUSED A BULGE IN THE MATERIAL AND WAS APPROXIMATELY 50 PERCENT THROUGH THE THICKNESS OF THE SPAR. THE CORROSION WAS APPROXIMATELY 3 INCHES LONG AND 1.25 INCHES TALL. NO OTHER CORROSION FOUND. NO FOREIGN MATERIAL FOUND AGAINST THE SPAR.

Parts most often named Gear Leg (3) · Axle (1) · Fork End (1)

DURING TAXI (AFTER LANDING) THE RT WHEEL ASSY BROKE OFF WHILE APPROACHING TAXI TURNOFF. INVESTIGATION REVEALED SEVERE CORROSION ON INSIDE OF LANDING GEAR TUBE AT POINT WHERE AXLE AND DOWNTUBES ARE WELDED.

CORROSION INTERNALLY. FRACTURE ABOVE WELD BELOW BRAKE PULLEY. TOTAL GEAR FAILURE ON RIGHT GEAR ON LANDING. SEE LUSCOMBE NEW LETTER NR 113.

LOWER GEAR LEG CRACKED AT BOLT HOLE AT ATTACHMENT TO UPPER ARM ASSEMBLY. CRACK CAUSED GEAR LEG TO FAIL ON LANDING. CRACK WAS NOT DETECTED BECAUSE OF SKI ATTACHMENT BRACKET COVERING GEAR LEG AT THIS AREA. SUBMITTER SUGGESTS FOR MECHANIC TO INSPECT BOLT HOLE AREAS FOR CRACKING.

Parts most often named Bulkhead (4)

DURING AN ANNUAL INSPECTION, FOUND AFT FUSELAGE BULKHEAD CRACKED AT TOP OF CUTOUT FOR ELEVATOR HORN. 50 PERCENT. THIS IS WHERE THE VERTICAL AND HORIZONTAL STABILIZERS ATTACH. THIS AREA IS HIDDEN BEHIND THE WEB OF THE VERTICAL STAB AFT SPAR AND WAS FOUND WHEN COMPONENTS WERE REMOVED TO REPAIR FWD SPAR (FOUND CRACKED) OF THE HORIZONTAL STAB. THE VERTICAL STAB IS NOT OF THE ROUNDED TIP TYPE, HAS AN ALUMINUM FWD ATTACHMENT AND STEEL AFT ATTACHMENT. (K)

BULKHEAD WAS FOUND CRACKED DURING THE REPLACEMENT OF THE VERTICAL ATTACH FITTING PER AD. PROBABLE CAUSE WAS AN EARLIER GROUND LOOP THIS AIRCRAFT SUFFERED IN 1959. THE CRACK WAS IN BETWEEN TWO BOLT HOLES AND WAS UNNOTICEABLE UNLESS THE VERTICAL FIN WAS REMOVED.

DURING ANNUAL INSPECTION, CRACKS WERE FOUND ON BULKHEAD AT FS 2.5 WHERE JACK STRUT ATTACHES. JACK STRUT FITTINGS WERE ALSO FOUND CORRODED AND WORN. SUSPECT ROUGH OPERATION ON SKIS CAUSED CRACKS.

Parts most often named Tank (2) · Fuel System (1)

TANK WORN FROM INTERIOR UPHOLSTERY PANEL VIBRATING AGAINST WELD. COULD BE CATASTROPHIC, DUMPING 14 GALS FUEL INTO CABIN AND AFT FUSELAGE. SUBMITTER STATED HAVE FOUND THIS IN NUMEROUS LUSCOMBES WITH FUS TANKS. RECOMMEND INSPECTING FOR DAMAGE TO EDGE WELD. IF STILL AIRWORTHY PUT FELT SPACERS ON PANEL TO KEEP PANEL AWAY FROM TANK. OTHERWISE, PURGE TANK AND RE-WELD OR REPLACE WITH AIRWORTHY TANK.

LOST ENGINE POWER DURING TAKEOFF AT 200 FEET AGL. AIRCRAFT DESTROYED. FOUND WATER IN GASCOLATOR. BOTH FUEL FILL CAPS LEAKING. FUEL FILL CAPS DID NOT PROVIDE A TIGHT SEAL. SUSPECT WATER DAMMED AROUND FILTER NECKS DURING HEAVY RAIN AND ENTERED FUEL TANKS.

Parts most often named Valve (1) · Cylinder (1) · Plug Piston Pin (1)

AIRCRAFT IN-FLIGHT, LOST POWER, MADE FORCED LANDING ON ROAD. DAMAGE TO WINGS AND FUSELAGE, NO INJURIES, TEAR DOWN OF ENGINE REVEALED BROKEN NR 2 CYLINDER INTAKE VALVE. ENGINE TSOH: 120 HOURS.

(CAN) PISTON PIN PLUG IN NR2 CYLINDER CAME LOOSE AND CAUSED WEAR ON THE CYLINDER WALL. METAL WAS FOUND IN THE OIL FILTER. ALL CYLINDERS WERE REMOVED FOR INSPECTION.

Parts most often named Brake Assy (2)

LEFT BRAKE LOCKED UP DURING LANDING ROLLOUT. LT BRAKE DISC CLIPS WERE BROKEN, SHEARED OFF AND APPEARED TO JAM THE BRAKE ASSY.

WHILE PULLING OFF THE RUNWAY AND TURNING OFF TO THE TAXIWAY, THE BRAKES WERE GENTLY APPLIED, THE LT BRAKE GRABBED AND THE ACFT NOSED OVER. DISASSEMBLY OF THE BRAKES REVEALED THE LT BRAKE FLOATING DISC WAS FOUND WEDGED AGAIN THE ANVIL PUCK BY ONE OF ITS CLIPS.

Parts most often named Piston Pin (1) · Casting (1)

DURING ANNUAL INSPECTION, OIL WAS FOUND LEAKING NEAR BOTTOM OF ROCKER COVERS. THE LEAK WAS TRACKED TO THE CASTING LINE BETWEEN THE VALVE GUIDES IN THE FIN AREA. LOCATION OF THE PROBLEM IS THE SAME ON ALL 4 CYLINDERS. LEAK SEEMED TO BE CAUSED BY POROSITY IN CASTING LINE. (X)

Parts most often named Stabilizer (1) · Horiz Stabilizer (1)

AIRCRAFT GROUND LOOPED AND DAMAGED HORIZONTAL TIP. 1991 STORED INSIDE. REMOVED TIP AND SKINS FOR REPAIR NOTING EXCESSIVE INTERNAL CORROSION (AIRCRAFT PARKED OVER GRASS). NO INSPECTION HOLES TO ALLOW FOR INSPECTION. APPARENTLY, NO INSPECTIONS CONDUCTED AT ANNUAL INSPECTION. NOTED SIMILAR LACK OF ACCESS TO WINGS FOR INSPECTIONS.

Parts most often named Wing Assy (1)

AIRCRAFT OPENED FOR ANNUAL AND FOUND SEVERAL RAT NESTS AND URINE DAMAGE IN BOTH WINGS (NORMALLY SEALED). LARGE RAT NEST AND URINE DAMAGE IN RT WING TRAILING EDGE. WASP/MUD DAUBER NEST IN RT LEADING EDGE ATTACHED TO SPAR CABLES. BIRD NEST IN LT WING. LUSCOMBE WING HAS NO ACCESS FOR ROUTINE INSPECTIONS. FOUND NESTS WHILE INSTALLING DLAHF INSPECTION ACCESS KIT.

Parts most often named Hinge Fitting (1)

A NEW FAA PMA RIGHT AILERON IS PURCHASED FROM UNIVAIR AIRCRAFT FOR INSTALLATION ON AIRCRAFT. THE AILERON WOULD NOT FIT ON THE AIRCRAFT AS RECEIVED DUE TO MISALIGNMENT OF THE CENTER HINGE FITTING. NO OTHER AILERON WAS AVAILABLE FROM THIS MANUFACTURER. THE MANUFACTURER SHIPPED AN UNDRILLED CENTER HINGE FITTING P/N U18279 WHICH WAS INSTALLED ON THE NEW AILERON. SUBSEQUENT OPERATION WAS NORMAL.