AD 67-12-06

67-12-06 PIPER: Amdt. 39-386 Part 39 Federal Register April 4, 1967. Applies to Models PA-28 and PA-32 Series Airplanes as follows:

GROUP I - PA-28-140, Serial Nos. 28-20000 through 28-20622; PA-28-150-160-180, Serial Nos. 28-2 through 28-35; 28-37 through 28-497; 28-499 through 28-543; 28-545 through 28-1307; 28-1309 through 28-2136; PA-28-235, Serial Nos. 28-10000 through 28-10590. GROUP II - PA-28-140, Serial Nos. 28-20623 through 28-21383; PA-28-150-160-180, Serial Nos. 28-2137 through 28-3021; PA-28-235, Serial Nos. 28-10591 through 10719; PA-32-260, Serial Nos. 32-1 through 32-307. GROUP III - PA-28-140, Serial Nos. 28-21384 through 28-21764; 28-21767 through 28-21786; 28-21788 through 28-21807; 28-21809 through 28-21835; 28-21837 through 28-21856; 28-21858 through 28-21877; 28-21879 through 28-22003; 28-22005 through 28-22010; 28-22012 through 28-22026; 28-22028 through 28-22032; 28-22035 through 28-22040; 28-22043 through 28-22050; 28-22052 through 28-22056; 28-22058, 28-22059, 28-22061 through 28-22064; 28-22066, 28-22071, 28-22074, 28-22080, 28-22082, 28-22088.

PA-28-150-160-180, Serial Nos. 28-3022 through 28-3499; 28-3501 through 28-3503; 28-3505 through 28-3508; 28-3510; 28-3512 through 28-3528; 28-3530 through 28-3537; 28-3541, 28-3543, 28-3545 through 28-3549; 28-3552; 28-3555 through 28-3557; 28-3562.

PA-28-235, Serial Nos. 28-10720, 28-10721, 28-10732.

PA-32-260, Serial Nos. 32-308 through 32-540; 32-542 through 32-558; 32-560 through 32-570, 32-572 through 32-677; 32-679 through 32-683; 32-685, 32-689, 32-690; 32-692 through 32-698; 32-700 through 32-702; 32-704 through 32-711; 32-714, 32-716, 32-717, 32-719 through 32-722; 32-725, 32-727, 32-730, 32-733; 32-740 through 32-742; 32-744 through 32-746; 32-749.

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 thanJuly 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:

PART NO. NOMENCLATURE MODELS AFFECTED 62369-0 Aileron Balance Weight PA-28-140-150-160-180-235 62369-1 Aileron Balance Weight PA-32-260 63546 Rudder Horn Assembly PA-28-140-150-160-180-235 PA-32-260 63578 Balance Weight Assembly-Stabilator PA-28-140-150-160-180 65310 Balance Weight Assembly-Stabilator PA-28-235 68432 Balance Weight Assembly-Stabilator PA-32-260

(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).