| AD Number | 80-22-13 | Status | Active |
| Effective Date | October 31, 1980 | Issue Date | October 17, 1980 |
| Docket Number | Unknown | Amendment | 39-3960 |
| 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 |
80-22-13 PIPER: Amendment 39-3960. Applies to model PA-38-112 airplanes, Serial Nos. 38-78A0001 thru 38-80A0099, 38-80A0113, 38-80A0120 and 38-80A0123 thru 38-80A0165, certificated in all categories.
To avoid possible hazards in flight associated with a crack in the rudder upper hinge P/N 77610-02, accomplish the following:
a. Within the next five hours in service unless previously accomplished and thereafter at intervals not to exceed 50 hours in service from the last inspection, remove the rudder upper hinge pin and carefully displace the rudder from the fin aft to expose the surfaces of the rudder upper hinge P/N 77610-02. The rudder upper hinge consists of two brackets, P/N 77610-02. Inspect all the hinge surfaces in the area of the hinge pin hole to the forward edge of the hinge for cracks using a dye check inspection method or an equivalent. Upper hinge bolt is to be installed with a torque of 50 to 70 in. lb.; do not exceed the maximum value.
b. If a cracked fitting is found, before further flight, replace with a part of the same part number or an equivalent, which have been inspected in accordance with (a).
c. Within the next 100 hours in service replace brackets, P/N 77610-02, with two steel rudder upper hinge brackets, Piper P/N 77610-03 or equivalent in accordance with the instruction section of Piper Service Bulletin No. 686 dated May 23, 1980, or equivalent. Upon compliance with this paragraph, the inspections required in paragraph (a) may be discontinued.
d. The steel upper rudder hinge P/N 77610-03 or equivalent must be replaced within 5000 hours time in service.
e. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance times specified in this AD.
f. Equivalent parts, instructions and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA,Eastern Region.
g. Report findings of cracked parts to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within five days of the inspection: include the time on the part, and aircraft serial No. (Reporting approved by the Office of Management and Budget under OMB No. O4-R0174.)
This supersedes AD Number 80-11-02 issued by letter dated May 16, 1980.
This amendment is effective October 31, 1980.