AD 70-26-04

70-26-04 PIPER: Amdt. 39-1134 as amended by Amendment 39-1196 is further amended by Amendment 39-1232. Applies to PA-28-140, Serial Numbers 28-20000 through 28- 26946 and 28-7125000 through 28-7125334.

PA-28-150-160-180 and PA-28S-180, Serial Numbers 28-1 through 28-5859 and 28- 7105001 through 28-7105126.

PA-28-235, Serial Numbers 28-10001 through 28-11378 and 28-7110001 through 28- 7110011.

PA-28R-180, Serial Numbers 28R-30001 through 28R-31270 and 28R-7130001 through 28R-7130005.

PA-28R-200, Serial Numbers 28R-30482, 28R-35001 through 28R-35820, and 28R- 7135001 through 28R-7135104.

PA-32-260, Serial Numbers 32-04, 32-1 through 32-1297, and 32-7100001 through 32- 7100016.

PA-32-300 and PA-32S-300, Serial Numbers 32-15, 32-21, 32-40000 through 32-40974, and 32-7140001 through 32-7140050.

Compliance required as indicated, unless already accomplished:

I. Aircraft with less than 500 hours total time in service:

Inspect in accordancewith instructions below at 500 hours total time or within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service.

II. Aircraft with 500 hours through 1000 hours total time in service:

Inspect in accordance with instructions below within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service.

III. Aircraft with more than 1000 hours time in service:

Inspect in accordance with instructions below within the next 25 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service.

To detect cracks in the stabilator balance weight tube in the area of the attachment bolt holes accomplish the following:

1. Remove tail cone assembly and bulkhead close out plate if so equipped.

2. In the tail cone section, remove safeties from stabilator cable turnbuckles and release cable tension. 3. Disconnect stabilator cables at the balance weight tube assembly.

NOTE: Care should be taken as not to misplace the bushing fitted in the tube/cable attachment lugs.

4. Remove the stabilator balance weight tube assembly attachment bolts.

5. Pull stabilator balance weight tube assembly forward and remove from stabilator. (It is not necessary to remove balance weight from tube.)

6. Remove paint from balance weight tube in areas of the stabilator attachment bolt holes.

NOTE: Use any commercial paint remover or caustic soda to remove paint; wash part in gasoline to remove any wax.

7. Inspect tube for cracks in this area using dye penetrant. If a crack or cracks are detected replace the balance weight tube assembly with new part. If cracks are not detected, the part may be reinstalled on the airplane after the tube has been cleaned, primed with zinc chromate primer, and painted.

NOTE: When a new balance weight tube assembly, Part Number 63578-00V, 65310-00V, or 68432-00V is installed, an initial inspection after 500 hours time in service on the assembly and repetitive inspections at 200 hour intervals will still be required.

8. Inspect stabilator mounting points for possible stabilator side movement. Should side movement be evident, install combination of AN960-416L (Piper code no. 407 585) and AN960-416 (Piper code no. 407 565) washers, as many as necessary to center the stabilator assembly and eliminate any side movement.

9. Visually inspect stabilator fittings (part no. 63567-03) for evidence of cracks and/or loose rivets.

a. Should the fitting(s) be cracked, replace with new stabilator fitting(s), part no. 63567-03.

b. Remove loose rivets and replace with new rivets.

Piper Service Bulletin No. 327 dated 9 December 1970 pertains to this same subject.

The installation of a new stabilator balance weight support tube, Part Number 69623-04V, 69623-02V, or 69624-02V, in accordance with Piper Service Letter No. 576 will eliminate the necessity for the initial and repetitive inspections required in Paragraphs I, II and III.

NOTE: The above referenced new tubes may be identified by the presence of green paint on the cable attachment lugs.

Amendment 39-1134 became effective December 28, 1970.

Amendment 39-1196 became effective April 30, 1971.

This Amendment 39-1232 becomes effective June 24, 1971.