75-22-04 HUGHES HELICOPTERS: Amendment 39-2289. Applies to Hughes Model 369, 369A, 369H, 369HM, 369HS, and 369HE helicopters certificated in all categories, including military YOH-6A and OH-6A equipped with fiberglass tail rotor blades P/N 369A1710, 369A1710-9, 369A1710-11, 369-6120, 369A1607, and 369CSK22.
Compliance required as indicated.
To detect possible corrosion, cracks, or other defects, inspect by visual, X-ray, or other specified means, the affected tail rotor blades and replace or rework in accordance with the instructions specified in Hughes Service Information Notice (SIN) No. HN-88, dated August 28, 1975, or later FAA-approved revisions, as follows:
(a) For blades with 500 or more hours time in service on the effective date of this AD, perform the visual and X-ray inspection, corrosion removal, casting procedure, metal treatment procedure, corrosion protection procedure, and fiberglass inspection - repair/spar exterior inspection procedure, set forth atParts I through VIII of the Hughes SIN, referenced above, within the next 100 hours additional time in service or within six calendar months from the effective date of the AD, whichever occurs first, unless already accomplished.
(b) For blades with less than 500 hours time in service on the effective date of this AD, perform the visual and X-ray inspections, corrosion removal, casting procedures, metal treatment procedure, corrosion protection procedure, and fiberglass inspection - repair/spar exterior inspection procedure, set forth at Parts I through VIII of the Hughes SIN, referenced above, prior to accumulating 600 hours total time in service or within six calendar months from the effective date of this AD, whichever occurs first, unless already accomplished.
(c) After the effective date of this AD, perform the inspections and procedures described at Parts I through VIII of the Hughes SIN, referenced above, prior to the installation of spare blades or rotors on the aircraft.
(d) After the effective date of this AD, for all blades, perform the visual and X-ray inspections described at Part X of the Hughes SIN, referenced above, at intervals not to exceed 12 calendar months from the last inspection.
(e) After the effective date of this AD, repair or rework eligible blades as specified in the Hughes SIN, referenced above, as necessary, prior to further flight. Reinstall blades in accordance with Part IX of the Hughes SIN. Blades that exceed limits specified in the Hughes SIN and are therefore not repairable, must be marked in a conspicuous manner or destroyed so as to prevent inadvertent return to service.
(f) Paragraphs (a), (b), and (c), above, do not have to be accomplished on blades marked with a green dot or white dot per the preface, Hughes SIN. After the effective date of this AD, perform the visual and X-ray inspections for corrosion described at Part X of the Hughes SIN, referenced above, within twelve months after putting theblades into service, and at intervals not to exceed twelve months thereafter.
(g) Equivalent inspections and rework may be approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(h) Special flight permits may be issued for operating aircraft to a base for performance of the inspections and repairs or rework required by paragraphs (a) and (b), above, of this AD, per FAR's 21.197 and 21.199.
This amendment becomes effective October 23, 1975.