 Header InformationDEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Amendment 39-386; AD 67-12-06 Airworthiness Directives; Piper Models PA-28 and PA-32 Series Airplanes PDF Copy (If Available): Regulatory Information67-12-06 PIPER: Amdt. 39-386 Part 39 Federal Register April 4, 1967. Applies to Models PA-28 and PA-32 Series Airplanes as follows:
Compliance required as follows: Group I - Prior to but not later than July 31, 1967. Group II - Prior to but not later than July 31, 1968. Group III - Prior to but not later than July 31, 1969. At the option of the local FAA General Aviation District office inspector, these compliance times may be extended, for a period not to exceed 30 days, to coincide with the annual inspection for the aircraft involved. Due to the possibility of internal corrosion resulting from inadequate corrosion protection of certain open end steel tube assemblies, accomplish the inspections described below on the following parts:
(a) Conduct a close visual inspection of the interior of the open end tubes specified above for a protective coating and evidence of corrosion, in accordance with Inspection Procedure, Piper Service Bulletin No. 240, dated December 13, 1966, or later FAA-approved revision, or by a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. Inspect both right and left aileron balance weight assemblies in accordance with Inspection of Aileron Balance Weight assembly provision of this Service Bulletin. (b) If there is evidence of a protective coating on the interior of the tube, and there is no evidence of corrosion, further inspection is not required. (c) If there is no evidence of a protective coating on the interior of the tube and evidence of corrosion, or if there is a protective coating, and evidence of corrosion, accomplish the following: (1) Remove all corrosion from the interior of the tube in accordance with the instructions in Piper Service Bulletin No. 240, dated December 13, 1966, or later FAA-approved revision, or by a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (2) Replace all corroded parts with a new part of the same part number if the corrosion cannot be removed as provided for in (c) (1). If doubt exists as to whether or not the corrosion involved can be removed without replacing the part, the matter must be referred to the local FAA General Aviation District office for assistance in making a determination. (3) If the extent of corrosion does not require replacement of the part in accordance with (c)(2), and the corrosion has been removed in accordance with (c)(1), apply a zinc chromate primer, Spec. MIL-P-8585, or an FAA-approved equivalent, to the inside of the tube to prevent further corrosion. (d) Further inspection is not required after accomplishing (c)(1), (c)(2), or (c)(3). |
