87-10-12 PARTENAVIA COSTRUZIONE AERONAUTICHE, S.p.A.: Amendment 39-5614. Applies to Models P 68, P 68B, P 68C (Serial Numbers (S/N) 1 through 250), and P 68C-TC (S/N's 300-1TC through 300-22TC) airplanes certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To prevent possible loss of control and structural failure, accomplish the following:
(a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, and each 100 hours TIS thereafter, visually and tactilely (by touch) inspect the composite leading edge wing ribs for cracking, and the composite wing leading edge for debonding from the ribs of both wings using the procedure and locally fabricated tool described in the "INSTRUCTIONS" section of Partenavia Service Bulletin (S/B) No. 67, Revision 1, dated November 5, 1986. (The tool is used to exert force on the ribs to check for lack of stiffness by tactile inspection.) If a crack or debonding is found,prior to further flight, remove the wing leading edge and repair the cracks or debonds as described by the repair "INSTRUCTIONS" in Partenavia Service Information (SI) No. 21, dated August 30, 1985.
(b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.
(c) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30, extension 2710/2711.
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, Naples, Italy; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.
This amendment 39-5614 becomes effective on June 1, 1987.