Airworthiness Directive

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

Amendment 39-3521; AD 69-22-02



Airworthiness Directives; Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-32-260, and PA-32-300 Airplanes
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AGENCY: Federal Aviation Administration, DOT





DATES: Effective July 30, 1979.






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69-22-02 PIPER: Amdt. 39-865 as amended by Amendment 39-1288 is further amended by Amendment 39-3521. Applies to the following models: PA-28-140, /-150, /-160, /-180, /-235, and PA-32-260/-300. The following are affected serial numbers: PA-28-140, 28-20001 through 28-7725290 inclusive; PA-28-150/-160/-180, 28-1 through 28-4377 inclusive; PA-28-235, 28- 10001 through 28-11039 inclusive; PA-32-260, 32-1 through 32-1110 inclusive; and PA-32-300, 32-40001 through 32-40565 inclusive.

Compliance required within 25 hours time in service from the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection.

To prevent possible failure of the control wheel, accomplish the following:

(a) Remove the Piper medallion from the face of each control wheel.

(b) Inspect each control wheel for cracks which may extend radially from the retaining pin. Cracks may be evident on the bottom of the control wheel hub where the pin enters the wheel as line cracks on the face or back of the hub as a crack in the hub cavity in line with the pin. The inspection is to be done using either of the following methods:

(1) Use a small pen light next to the surface and inspect under at least a three-power glass. Inspect in at least a 1/2" path from the top of the pin to the bottom on the front and back of the control wheel hub. Cracks, either needle shaped or extending across the entire surface will show as black lines in the light field. If a line is only a scratch, the bottom will always be visible. The wheel should be cleaned with ordinary detergent and water only. The use of chemical cleaners and/or solvents such as acetone must be avoided.

(2) An equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

(c) If cracks are found in the path along the hub as described in (b)(1), replace the control wheel before further time in service. This AD is applicable to new control wheels of the same part number installed in accordance with this paragraph.

(d) The control wheel medallion may be replaced with regular contact cement which has been allowed to dry thoroughly before assembly or with any commercial 2-part epoxy adhesive. Under no circumstances use acetate adhesive or other plastic cements or any form of Locktite as these materials may not be compatible with the plastic material in the wheel.

(e) The repetitive inspection requirements of this AD may be terminated by replacing the plastic control wheel(s) with metal ramshorn type control wheel Piper part number 78729-02V (.750" o.d. shaft) or 79276-00V (1.125" o.d. shaft) as applicable. Replacement of one control wheel (i.e., left or right) does not terminate the requirement for continuing repetitive inspections of the other control wheel, if that other control wheel is the molded plastic type.

(f) Piper Service Letter No. 527D, dated June 21, 1978, or later approved revisions, pertains to this same subject.

(g) Make appropriate logbook entry indicating compliance with the provisions of this AD.

Amendment 39-865 became effective November 4, 1969.

Amendment 39-1288 became effective September 15, 1971.

This amendment 39-3521 becomes effective July 30, 1979.