| AD Number | 78-23-04 | Status | Active |
| Effective Date | November 10, 1978 | Issue Date | October 27, 1978 |
| Docket Number | Unknown | Amendment | 39-3340 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | --- - _EMPTY_ |
| Citation | This information is not available. | ||
| Manufacturer(s) | Piper Aircraft Inc. |
| Model(s) | PA-38-112 |
78-23-04 PIPER: Amendment 39-3340. Applies to Piper Model PA-38-112 Serial Nos. 38-78A0001, 38-78A0005 thru 38-78A0016, 38-78A0018 thru 38-78A0039, 38-78A0042 thru 38-78A0130, 38-78A0132 thru 38-78A0212, 38-78A0214 thru 38-78A0233, 38-78A0235 thru 38-78A0270, 38-78A0272 thru 38-78A0324, 38-78A0326 thru 38-78A0329, 38-78A0331, 38-78A0333 thru 38-78A0356, 38-78A0358 thru 38-78A0372, 38-78A0374, 38-78A0375, 38-78A0377 thru 38-78A0385, 38-78A0387 thru 38-78A0399, 38-78A0401 thru 38-78A0410, 38-78A0413, 38-78A0415, 38-78A0416, 38-78A0418 thru 38-78A0421, 38-78A0424 thru 38-78A0426, 38-78A0428, 38-78A0429, 38-78A0431, 38-78A0432, 38-78A0434, 38-78A0435, 38-78A0437 thru 38-78A0439, 38-78A0441 thru 38-78A0443, 38-78A0445, 38-78A0446, 38-78A0449 thru 38-78A0455, 38-78A0457 thru 38-78A0466, 38-78A0468, 38-78A0469, 38-78A0471, 38-78A0472, 38-78A0474, 38-78A0475, 38-78A0477, 38-78A0478, 38-78A0480, 38-78A0481, 38-78A0483, 38-78A0484, 38-78A0486, 38-78A0489, 38-78A0490, 38-78A0492 thru 38-78A0494, 38-78A0496 thru 38-78A0498, 38-78A0500 thru 38-78A0502, 38-78A0504 thru 38-78A0506, 38-78A0509, 38-78A0510, 38-78A0512 thru 38-78A0526, 38-78A0528 thru 38-78A0532, 38-78A0534, 38-78A0535, 38-78A0537, 38-78A0538, 38-78A0540, 38-78A0541, 38-78A0544, 38-78A0546 thru 38-78A0548, 38-78A0550, 38-78A0552, 38-78A0555, 38-78A0556, 38-78A0558, 38-78A0559, 38-78A0561, 38-78A0565, 38-78A0567, 38-78A0568, 38-78A0570, 38-78A0573, 38-78A0574, 38-78A0576, 38-78A0578, 38-78A0581, 38-78A0584, 38-78A0585, 38-78A0587, 38-78A0588, 38-78A0606 and 38-78A0622.
To prevent weakening of the wing rear spar to fuselage attach fitting connection due to missing rivets, accomplish the following:
(a) Within the next 10 hours in service after the effective date of this AD, unless already accomplished, perform the steps 1 thru 4 as indicated under the Instructions section in Piper Service Bulletin No. 618, dated September 5, 1978, or equivalent.
(b) Equivalent inspections, repairs, and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(c) The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished.
(d) Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment is effective November 10, 1978.