AD 88-13-08 ACTIVE

88-13-08 PARTENAVIA COSTRUZIONE AERONAUTICHE S.p.A: Amendment 39-5953. Applies to models P 68, P 68B, P 68C, P 68C-TC, P 68 "Observer", and P 68-TC "Observer" (all serial numbers (S/N)) airplanes certificated in any category.

Compliance: Required initially within 6 calendar months after the effective date of this AD unless already accomplished within the last 24 calendar months preceding the effective date of this AD, and thereafter at intervals not to exceed 24 calendar months or 500 hours time-in- service, (TIS) whichever occurs first, unless already accomplished.

To prevent engine mount failure, whirl mode flutter, and structural failure of the wing, accomplish the following:

(a) For S/N 1 thru 368, at the time of the initial inspection specified in this AD, modify the engine skin panels for inspection access in accordance with the instructions in Section 1 of Partenavia Service Bulletin (S/B) No. 70, Rev. 1, dated May 13, 1987.

(b) For S/N 1 thru 368, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 1 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD.

(c) For S/N 369 and subsequent, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 3 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD.

(d) If cracks or surface corrosion are found as a result of the inspections specified in paragraphs (b) or (c) of this AD, prior to further flight, repair the affected structure as follows:

(1) If the surface corrosion or crack extends no deeper than 75/1000 (7.5 percent) of the original local thickness, so that no less than 92.5 percent of the original local thickness remains, repair using the procedures described in Section 1 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987.

(2) If any crack or surface corrosion extends deeper than 75/1000 (7.5 percent) of the original local thickness, so that less than 92.5 percent of the original local thickness remains including blistering, pitting, or flaking, prior to further flight, remove and replace the affected part with a serviceable part as described in Section 2 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987.

(e) Within one week following each inspection specified in paragraph (b) or (c) of this AD, submit a written report of the result of that inspection to include whether or not damage was found, part number(s) involved, extent, location, and description of any damage found, and a brief description of remedial measures. Submit the reports to the FAA, ACE-109, 601 East 12th Street, Kansas City, Missouri 64106.If an inspection was made previous to this AD, forward the requested data within one week of receipt of this AD. (Report approved by the Office of Management and Budget under OMB No. 2120-0056.)

(f) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium; Telephone (322) 513.3830 ext. 3710/2711.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Partenavia Costruzione Aeronautiche, S.p.A., Via Cava, Casoria-Naples, Italy; Telephone 81 759-0946 (Product Support); or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment, 39-5953, becomes effective onJuly 13, 1988.