85-15-01 R2 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (AEROSPATIALE): Amendment 39-5093 as amended by Amendment 39-5679 is further amended by amendment 39-6021. Applies to Aerospatiale Model SA 365 series helicopters, certificated in any category, when equipped with main rotor masts with Part Numbers 365A31- 1060-23 or -25, or 365A31-1179-03, -20, or -21.
Compliance with this amendment to the AD is required as indicated after the effective date of this amendment, unless already accomplished.
To prevent possible failure of the main rotor mast, accomplish the following:
(a) For helicopters which have 250 hours or more time in service on the main rotor mast on the effective date of this AD, inspect in accordance with paragraph (d) within 50 hours time in service.
(b) For those helicopters which have less than 250 hours time in service on the main rotor mast on the effective date of this AD, inspect in accordance with paragraph (d) before reaching 300 hourstime in service.
(c) For those helicopters exhibiting a severe tracking defect, inspect in accordance with paragraph (d) before further flight.
(d) Remove the main rotor hub from the main rotor mast and inspect the mast in accordance with Service Bulletin No. 05.08 (for Model SA 365C series helicopters) and Service Bulletin No. 05.04 (for Model SA 365N helicopters) or FAA-approved equivalent, as appropriate.
(e) Replace any cracked mast with a serviceable part.
(f) Reinstall the main rotor hub in accordance with Service Bulletin No. 05.08, Service Bulletin 05.04, or FAA-approved equivalent, after completion of the inspection and rework of paragraphs (d) and (e).
(g) Conduct the following repetitive inspections:
(i) Repeat the inspections of paragraph (d) at intervals not to exceed 300 hours time in service from the last inspection.
(ii) Visually inspect the upper mast flange-to-shaft radius within the next 50 hours time in service from the effective date of this amendment and thereafter at intervals not to exceed 50 hours time in service from the last inspection. Inspect for finish deterioration, corrosion, or cracks. Use a 10-power glass in areas of suspected surface cracks. Conduct magnetic particle or dye penetrant inspections of all areas where finish deterioration is found. Remove polyurethane shock-proofing coating of the upper main rotor shaft, if installed, to allow more effective inspections of this area (Service Bulletin SA 365 No. 01-17 provides information concerning the shock-proofing coating and its removal).
(h) (Removed)
(i) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, FAA, P.O. Box 1689, Fort Worth, Texas 76101, or by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium, APO NY 09667.
(j) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished.
This amendment, 39-6021, becomes effective October 19, 1988.
This amendment, 39-6021, further amends Amendment 39-5093 (50 FR 29649; July 22, 1985), AD 85-15-01, as amended by Amendment 39-5679 (52 FR 27787; July 24, 1987) AD 85- 15-01 R1.