TBTampico · Tobago · Trinidad

Parts most often named Guide (11) · Lever (1) · Spring (1) · Rocker Arm (1)

THE PUSH ROD HOUSING TUBE RETAINING SPRINGS WERE BROKEN AT THE BEND JUST OB OF THE MOUNT HOLE. THE UNBROKEN SPRINGS HAD A TOOL LINE AT THE POINT OF THE BEND. THERE WERE 2 BROKEN SPRINGS, LOCATED ON NR 3 AND NR 4 CYLINDERS. ONE SPRING HAD ONE SIDE BROKEN OFF THE OTHER BOTH SIDES WERE BROKEN. BELIEVE THE TOOL MARKS ARE CAUSING THE PROBLEM. ALL 6 SPRINGS WERE REPLACED WITH NEW MFG PARTS AND SOME ALSO CONTAINED THE TOOL MARKS AT THE BEND. (K)

CUSTOMER COMPLAINED OF EXCESSIVE VIBRATION. ATTEMPTS TO BALANCE THE PROP WERE UNSUCCESSFUL. INSPECTION REVEALED THAT THE EXHAUST SUPPORT (LEVER ASSY) SUPPORT BUSHINGS WERE WORN ALLOWING THE METAL PORTION TO CONTACT THE MOUNT TRANSMITTING THE ENGINE VIBRATION TO THE AIRFRAME.

DURING CYLINDER OVERHAUL, FOUND LOWER PORTION OF THE EXHAUST GUIDE WAS MISSING APPROXIMATELY ONE-HALF OF ITS MATERIAL. THE UPPER PORTION OF THE GUIDE THAT PROJECTS IN THE ROCKER BOX AREA WAS FOUND BROKEN OFF LEVEL WITH THE CYLINDER HEAD.

Parts most often named Relay (3) · Seal (2) · Torque Link (2) · Pressure Switch (1)

LANDING GEAR FAILED TO EXTEND. CIRCUIT BREAKER FOUND OPEN. INVESTIGATION FOUND LANDING GEAR UP, RELAY POINTS WELDED CLOSED.

PILOTS REPORTED LANDING GEAR WOULD NOT RETRACT, CHECKED FUSES, ALL OK. BYPASSED PRESSURE SWITCH. GEAR RETRACTED, INSTALLED NEW PRESSURE SWITCH, PN TB206138001, SYSTEM CHECKED OK. NOTE: SEVERAL PRESSURE SWITCHES HAVE BEEN REPLACED. PART TT 128.1 HOURS, SWITCH WAS INSTALLED 3-16-00. (X)

NOSE GEAR DID NOT FULLY EXTEND AND LOCK DUE TO A NOSE GEAR END OF TRAVEL LIMIT SWITCH. THE SWITCH IS MOUNTED ON THE FORWARD LEG OF THE OVER-CENTER LINK AND DOWNLOCK. THE WIRE IS TY-WRAPPED TO THE LINK. THE SWITCH HAD 1736.08 HOURS TOTAL TIME. THE SWITCH SHOULD BE REPLACED ANY TIME THE OUTER COVER SHOWS SIGNS OF DETERIORATION OR CRACKING.

Parts most often named Support (6)

DURING ROUTINE 100-HOUR INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTION ACTION CONSISTS OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LOADS FROM THE CONTROL LOCK ASSEMBLY.

DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTIVE ACTION CONSISTS OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LOADS FROM THE CONTROL LOCK ASSEMBLY.

Parts most often named Support Baffle (2) · Baffle Assy (1) · Baffle (1)

BAFFLE OIL COOLER IS CRACKING AROUND OIL COOLER MOUNT POINT. SUBMITTER STATED BAFFLE NEEDS TO BE MADE FROM THICKER MATERIAL. THIS PROBLEM IS A COMMON OCCURRENCE. (SEE PREVIOUS M OR D REPORTS).

DURING SCHEDULED MAINTENANCE (100-HOUR INSPECTION), THE OIL COOLER SUPPORT BAFFLE WAS FOUND BROKEN AT 2 OF THE 4 MOUNT POINTS AND SEVERELY CRACKED ON THE OTHER 2 MOUNTS. THIS CONDITION COULD CAUSE OIL LOSS AND POSSIBLE ENGINE FAILURE. INSTALLED NEW OIL COOLER BAFFLE.

DURING A 100-HOUR INSPECTION, THE OIL COOLER WAS FOUND SUPPORTED BY ONLY TWO BOLTS. THE OIL COOLER MOUNTING BAFFLE WAS COMPLETELY BROKEN AT TWO OF THE MOUNT HOLES AND THE OTHER TWO WERE SEVERELY CRACKED. THIS COULD CAUSE OIL COOLER TANK LEAKAGE AND POSSIBLE ENGINE FAIILURE. NEW BAFFLE INSTALLED.

Parts most often named Lever (2) · Lever Arm (1)

INSP FOUND BOTH PITCH CONTROL LEVERS BENT OUTWARD FROM CENTER. PILOT EXPERIENCED INSUFFICIENT NOSE DOWN PITCH CONTROL JUST AFTER TAKEOFF. MOST LIKELY CAUSE DETERMINED TO BE A HIGH TAIL WIND GUST OR JET WASH HITTING BACK OF AIRCRAFT WHILE PARKED AND CHOCKED ON FBO RAMP. CONTROL YOKE GUST LOCKS WERE IN PLACE AT TIME PROBLEM DEVELOPED.

DURING 100-HOUR INSPECTION, FOUND TOP RIVET CONNECTING THE STABILATOR LEVER ARM TO THE CONTROL PYLON BROKEN. LOOKED UP THE PROPER PART NUMBER TO REPLACE THE RIVET, FOUND THE PARTS BOOK CALLED FOR TWO BOLTS, NOT RIVETS. ALSO, INSPECTED ACFT [tail no. removed], [S/N removed], MODEL TB-9, AND FOUND SAME IMPROPER HARDWARE. THERE ARE 26 SOCATA TB-9'S IN THE FLEET THAT ARE MAINTAINED.

Parts most often named Spar (3)

DURING AN ANNUAL INSPECTION OF THIS AIRCRAFT, A CONSIDERABLE AMOUNT OF CORROSION OF THE RIGHT WING SPAR WAS FOUND WITH SOME FORM OF DELAMINATION. THE PRIMARY CORROSION WAS FOUND ON THE RIGHT WING SPAR NEAR THE RIB ONTO WHICH THE LANDING GEAR IS ATTACHED.

Parts most often named Link (2) · Tank (1)

FOUND WELD AT TURBO BEND OF OIL DRAIN TANK CRACKED. UPON REMOVAL, TUBE CAME OUT OF TANK. LOOKING AT WELD, IT APPEARED TO BE A BAD WELD. SUBMITTER STATED THAT HAD THIS GONE UNDETECTED, IT COULD HAVE BEEN A DISASTER. (X)

Parts most often named Torque Link (2) · Cylinder (1)

MLG HYD CYL, PN TB2047007/[S/N removed] WAS REMOVED AND SENT FOR INTERNAL LEAK AND A VERY STIFF SPOT ABOUT CENTER OF TRAVEL. CYL WAS RETURNED, REPAIRED, WARRANTY AS IS. INSTALL CYL ON LT MLG. INTERNAL LEAK NO LONGER EXISTED. UPON TESTING EMERGENCY EXTENSION CYL WOULD NOT ALLOW LT MAIN TO EXTEND, STIFF SPOT CENTER OF TRAVEL, CAUSE: REPAIR STATION STAMPED TAG, DISTORTING CYLINDER? CYLINDER HAS TO BE REPLACED WITH [S/N removed] UNIT. (K)

(AUS) LH MAIN LANDING GEAR LOWER TORQUE LINK BROKEN AT INBOARD ATTACHMENT LUG - OUTBOARD LUG CONTAINS A HAIR LINE CRACK - RH MLG TORQUE LINK CONTAINS SOME PITTING IN THE ATTACHMENT LUG HOLES

Parts most often named Actuator (2) · Relay (1)

AIRCRAFT HAD AN INCIDENT IN WHICH THE GEAR WOULD NOT EXTEND NORMALLY. ATTEMPTED MULTIPLE EMERGENCY EXTENDS COULDN'T GET THE NOSE GEAR TO LOCK. RESULTED IN A NOSE GEAR COLLAPSE ON LANDING. UPON INSPECTION IN THE SHOP WAS FOUND THAT ONE NLG COMP ACTUATOR WAS BAD AND THUS NLG WOULD NOT LOCK IN FIGHT USING EMERGENCY PROCEDURE.

(CAN)PILOT WAS ATTEMPTING AN APPROACH WHEN THE CIRCUIT BREAKER FOR THE LANDING GEAR KEPT POPPING OUT AFTER BEING RESET SEVERAL TIMES MANUAL GEAR EXTENSION WAS PERFORMED BUT GEAR DOWN AND LOCKED LIGHTS WOU LD NOT ILLUMINATE. AFTER SEVERAL ATTEMPTS TO LOCK GEAR, PILOT REPORTED THREE IN THE GREEN AND MADE AN UNEVENTFUL LANDING. INSPECTION FOUND THE RELAY HAD SHORTED OUT AND WOULD NOT ALLOW THE ELECTRIC MOTOR TO RUN THE HYDRAULICS.

Parts most often named Seat Belt Assy (2)

WHILE PERFORMING MANDATORY SB 10-044, AMDT 1, DATED SEPT 1993 (DUE AT EACH ANNUAL INSPECTION), IT WAS NOTED THE LEFT AND RIGHT INERTIA REEL-TYPE FRONT SEAT BELTS HAVE SEVERE EXFOLIATION CORROSION ON THE EYE END THAT ATTACHES TO THE FORWARD OUTBOARD FUSELAGE STRUCTURE. THE SB CALLS FOR CHECKING FOR OXIDATION OR EXFOLIATON CORROSION SO THE MFG IS AWARE OF THE PROBLEM. EYE END IS OF AN ALUMINUM MATERIAL WHEREIN MOST U. S. MANUFACTURED SEAT BELTS HAVE STEEL EYE ENDS. SEAT BELT EYE ENDS TO BE REPLACED.