85-14-06 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5089 as amended by Amendment 39-5121. Applies to all Aerospatiale Model AS 350 and AS 355 series helicopters certificated in all categories.
Compliance is required as indicated, unless already accomplished.
To prevent possible failure of the fuselage to tailboom interface frame, accomplish the following:
(a) For helicopters which have 1,100 hours or more time in service on the effective date of this AD, inspect in accordance with paragraph (d) within the next 100 hours time in service.
(b) For helicopters which have 900 hours or more but less than 1,100 hours time in service on the effective date of this AD, inspect in accordance with paragraph (d) before reaching 1,200 hours time in service.
(c) For helicopters which have less than 900 hours time in service on the effective date of this AD, inspect in accordance with paragraph (d) within the next 300 hours time in service.
(d) Inspect the bolts for torque and, if necessary, the frame for cracks at the fuselage-to-tailboom interface in accordance with:
(1) Service Bulletin No. 05.16 for Model AS 350 series helicopters.
(2) Service Bulletin No. 05.14 for Model AS 355 series helicopters.
(e) In addition for AS 355 series helicopters, conduct the following initial visual inspection within the next 100 hours time in service for helicopters which have 1,100 hours or more time in service on the effective date of this AD or before reaching 1,200 hours time in service for those helicopters having less than 1,100 hours total time in service on the effective date of this AD:
(1) Remove the tailboom from the fuselage in accordance with the Model AS 355 maintenance manual, or FAA-approved equivalent, as appropriate. Prior to tailboom removal, inspect the bolts for torque readings in accordance with paragraph (d).
(i) Visually inspect the aft fuselage frame at the fuselage tailboom interface for cracks. Conduct the visual inspection on all accessible frame areas with special emphasis in frame flange radii and at bolt holes.
(ii) Conduct dye penetrant inspections of areas of suspected cracks that cannot be verified by a visual inspection.
(2) If all the bolt torque readings from the inspection of SB No. 05.14 are 26.5-inch-pounds or greater, the following RH upper quadrant (looking forward) frame inspection may be conducted in lieu of the full frame inspection of paragraph (1):
(i) Remove the bolts common to the tailboom, fuselage frame, and RH fuselage frame radius block.
(ii) Remove the RH radius block after grinding off the three rivet heads which retain the radius block. The radius block is shown as Item 21 of detail C of page 10 of Aerospatiale Repair Manual 53.10.22, Volume 1.
(iii) Visually inspect the forward side of the RH aft fuselage frame for cracks. Conduct the visual inspection on all accessible frame areas with special emphasis in frame flange radii and at bolt holes.
(iv) Conduct dye penetrant inspections of areas of suspected cracks that cannot be verified by a visual inspection.
(v) Apply zinc chromate primer to the aft surface of the radius block; replace it using the original bolts, but do not re-rivet to the frame.
(3) Report cracks and bolt torque values measured before tailboom or radius block removal to the Manager, Aircraft Certification Division, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101 within 10 days of the inspection. Use a copy of View F of Service Bulletin No. 05.14 or No. 05.16 to show the locations of cracks or loose fasteners (those below 26.5 inch-pounds of measured torque). If all fasteners are found to have a torque of 26.5 inch-pounds or greater, a statement of such is sufficient without a marked-up View F. Provide aircraft serial numbers, total time, and time since tailboom removal, if any. (Reporting is approved by the Office of Managementand Budget under OMB No. 2120-1156.)
NOTE: The initial visual inspection of paragraph (e) and reporting of results are required for all Model AS 355 helicopters even if the bolt torque values measured during the inspections of paragraph (d) are 26.5 inch-pounds or greater.
(f) Replace any cracked frames or repair in accordance with Service Bulletin No. 05-14 or No. 05-16.
(g) Reinstall the tailboom in accordance with the appropriate Model AS 350 or AS 355 maintenance manual, or FAA-approved equivalent, if removed during the inspections and rework of paragraphs (d), (e), and (f).
(h) Repeat the inspections required in paragraph (d) at intervals not to exceed 1,200 hours time in service from the last inspection.
(i) An alternate method of compliance with this AD and adjustment of repetitive compliance times may be approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106 or by the Manager,Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Adjustments in compliance time may be approved upon recommendations of the FAA aviation safety inspector.
(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.
The manufacturer's specifications and procedures identified and described in this directive are incorporated by reference and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. These documents may also be examined in the Rules Docket at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration Room 156, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106.
Amendment 39-5089 became effective July 26, 1985.
This amendment 39-5121 becomes effective September 12, 1985.