COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-38 (Tomahawk) Series Aeroplanes
AD/PA-38/11
Amdt 1
Stabiliser Pulley Bracket Mounting Fitting and Empennage Attachments - Inspection
3/82
Applicability: All model PA-38-112 with S/Nos. 38-78A0001 to 38-79A0312.
Requirement: To avoid possible hazards in flight associated with a cracked stabiliser pulley bracket mounting fitting or loose vertical fin to fuselage and horizontal stabiliser to vertical fin spar attach fitting bolts, accomplish the following:
- Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edge of the stabiliser pulley bracket mounting fitting P/N 77615-07 in the area of the bend for cracks using a dye penetrant inspection method or a suitable visual aid.
2. Remove rudder, lower vertical fin fairing, upper vertical fin fairing and upper and lower vertical fin inspection panels. Using an accurately calibrated torque wrench check the torque of each of the eighteen affected bolts and tighten as required to 90-110 inch-pounds. (Note - torque value takes into account friction drag torque). Affected bolt locations:
(a) upper forward vertical fin spar attach fitting - six (6) AN-4 bolts;
(b) upper aft vertical fin spar attach fitting - six (6) AN-4 bolts;
(c) lower forward vertical fin spar fitting - two (2) AN-4 bolts;
(d) lower aft vertical fin spar attachment - four (4) AN-4 bolts.
After checking torque, mark each bolt head and nut for future inspection for any rotation.
Compliance: Para. 1 - At intervals not exceeding 100 hours time in service. Para. 2 - At intervals not exceeding 500 hours time in service.
Background: Service experience indicates that extension of the period between inspections of the empennage attach bolts is warranted. Alternative inspection method for stabiliser pulley bracket mounting fitting has been included.