82-19-03: Main Rotor Spindles

82-19-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4460. Applies to Model SA330J series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.03, 330A31.1122.06 to 330A31.1122.08. Compliance required as indicated. To detect possible cracks and to prevent fretting corrosion and possible cracking of the main rotor head outboard spindle lugs, accomplish the following: (a) Within the next 10 hours' spindle time in service after the effective date of this AD, unless already accomplished, remove the spindles from the helicopter and inspect each main rotor spindle lug bore for cracks using a magnetic particle inspection method. (b) Within 750 hours' spindle time in service after inspection per paragraph (a) of this AD, inspect each lug bore for cracks using a dye penetrant or equivalent inspection method. (c) Within 750 hours' spindle time in service after inspection per paragraph (b) of thisAD, remove the spindle from the helicopter and inspect each lug bore for cracks using a magnetic particle inspection method. (d) Within 1,500 hours' spindle time in service after the effective date of this AD or at next overhaul of the main rotor head, whichever comes first, install spindles that have bushings installed in accordance with Aerospatiale Modification Instructions, AMS 07.43.078, or FAA approved equivalent. The inspections, paragraphs (b) and (c) of this AD, are not required after these bushings are installed. (e) Replace spindles having a cracked bore prior to further flight. Install serviceable spindles. (f) Alternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Service Bulletin No. 01.35 pertains to visual inspections and protective finish of the spindle lug bore.) This amendment becomes effective September 27, 1982.