78-22-01 PIPER: Amendment 39-3323. Applies to Piper Model PA-38-112, Serial Numbers 38-78A0001 thru 38-78A-0400 certificated in all categories.
To prevent possible binding of the rudder or elevator in flight, accomplish the following:
(a) Applies to Model PA-38-112, Serial Numbers 38-78A0001 thru 38-78A0215 and 38-78A0217 thru 38-78A0226. Before further flight, unless already accomplished, and at intervals thereafter not to exceed 25 hours in service inspect for proper clearance between the rudder leading edge and fin trailing edge and repair in accordance with the "instructions" of Piper Service Bulletin Nos. 607 or 607A dated May 19, 1978, and June 2, 1978, or equivalent.
(b) Applies to Model PA-38-112, Serial Nos. 38-78A0001 thru 38-78A0215 and 38-78A0217 thru 38-78A0226. Within the next fifty hours in service after the effective date of this AD, unless already accomplished, install Piper Kit 763 872 Rudder Leading Edge Modification or equivalent. The inspections of (a) may be dispensed with upon incorporation of this modification.
(c) Applies to Model PA-38-112 Serial Nos. 38-78A0001 thru 38-78A0400. Within the next fifty hours in service after the effective date of this AD, unless already accomplished, inspect and repair the elevator leading edge in accordance with the procedure under "instructions" of Part II of Piper Service Bulletin No. 607A dated June 2, 1978, or equivalent.
(d) Equivalent inspections, repairs and modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(e) The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished.
(f) Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment is effective October 30, 1978.