Piper PA-22

To preclude the possibility of failure at the upper shock strut-drag tube area of the LPC 1012 series landing gear vees used in the STC-SA45RM taildragger modification, a second gusset has been added to the upper end of the streamline brace tube.

Procedures for replacing brake drum flanges on PA-22, PA-23, PA-24 and PA-25 wheel assemblies.

Tightening engine mounting bolts to obtain a torque of (40) inch pounds.

Instructions for inspecting the battery box lid for proper clearance between the lid and the battery terminals.

Immediate inspection of clearance between the aileron cable and the master switch wires (from the master switch to the ammeter).

Modifying the battery box lid to eliminate the possibility of "shorting" the battery terminal wing nuts.

Solution to water freezing in the oleo housing, which causes the nose wheel to become inoperative in regards to directional steering both on the ground and in the air.

Misalignment of the oil radiator lines on the Lycoming 0-290-D2 135 horsepower engines at the point where they pass through the rear engine baffle.

Correction to the fuel grade specification in flight manuals and fuel tank placards for the Lycoming O-290-D2 engines.

Inspection to determine if there is interference between the inboard end of the front spar web and the aileron pulley attachment bolt in the area of the front wing hinge fitting.

Modification and reinforcement of landing gear to prevent cracks in the leading edge of the streamlined tube where it joins the inboard end of the axle.

Instructions for correcting an incorrectly installed pointer on the fuel selector valve.

Possibility of the fuel valve detent pins in a few valves were improperly centered, thus preventing positive indication of valve position.

A recent design change to the fuel tank caps has created a possible hazard to the venting system and it is therefore requested that the caps be reworked in the following manner.

Failures of the diaphragm in the B711 Scott Master Cylinder used on the PA-22 Tri-Pacer within 300 or 400 hours of operation.

To preclude the possibility of in-flight fires, the following inspection and rework is necessary to eliminate combustible material and possible ignition sources from the area aft of the firewall underneath the forward cabin floor.

Installing an additional standard fuse (15A Bussman #AGC-15) in the wire between the cigar lighter and the ammeter at the next 100 hour inspection to protect against a short circuit condition.

Inspection of clearance between the pilot's seat and the master switch wires.

How to fix difficulties with the fabric where it attaches to the fuselage under the windshield top and/or directly over the rear edge of the windshield top attachment channel.

Mandatory replacement of 1/8 - 7 x 19 flexible stainless steel control cables to prevent cracked nicopress sleeves.