AD 79-08-02 ACTIVE

79-08-02 PIPER: Amendment 39-3446. Applies to Model PA-38-112, Serial Nos. as shown below, certificated in all categories.

To avoid possible hazards in flight associated with a crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts, accomplish the following:

(a) Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312.

Compliance required within the next ten hours in service unless previously accomplished.

1. Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edges of the stabilizer pulley bracket mounting fitting P/N 77615-07 at the bend radius for cracks using a dye penetrant inspection method.

2. Report positive findings including crack length from paragraph (a) Inspection to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-RO174.)

3. If a cracked fitting is found, replace with an undamaged part of the same part number before further flight except a ferry flight under FAR 21.197 to a place of repair may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(b) Serial Nos. 38-78A0001 through 38-79A0254.
Compliance required within the next 100 hours in service unless previously accomplished.

1. Disconnect rudder cables from rudder, remove lower rudder hinge bolt and displace rudder to gain access to rear spar attachment bolts.

2. Remove lower vertical fin fairing, upper vertical fin fairing, upper vertical fin inspection panel and lower aft vertical fin inspection panel.

3. Using a calibrated torque wrench, check the torque of each of eighteen (18) stabilizer to fin and fin to fuselage attach bolts and tighten as required to 90-110 in-lbs. Torque value given takes into account friction drag torque. (Piper Service Bulletin No. 637 refers to the subject.)

This amendment is effective April 12, 1979.