| AD Number | 86-15-10 R1 | Status | Superseded |
| Effective Date | March 22, 1990 | Issue Date | Not specified |
| Docket Number | 86-ASW-22 | Amendment | 39-6514 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France Eurocopter France |
| Model(s) | AS-350B AS-350B1 AS-350B2 AS-350B3 AS-350BA AS-350C AS-350D AS-350D1 AS355E AS355F AS355F1 AS355F2 AS355N |
| Superseded By | 86-15-10 R2 |
86-15-10 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5517 as revised by Amendment 39-6514. Docket No. 86-ASW-22.
Applicability: Aerospatiale Model AS 350 and AS 355 series helicopters, certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To prevent the failure of the main rotor head star arms and the main gearbox suspension bars, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD:
(1) For Model AS 350 series helicopters, inspect the main rotor head components, the main gearbox suspension bars (struts), and the landing gear ground resonance prevention components (aft spring blades and hydraulic shock absorbers) in accordance with Service Bulletin (SB) 01.17a, paragraph CC.3.
(2) For Model AS 355 series helicopters, inspect the main rotor head components, the main gearbox suspension bars (struts), and the landing gear ground resonance prevention components (aft spring blades and hydraulic shock absorbers) in accordance with SB 01.14a, paragraph CC.3.
(b) Rework or replace damaged components in accordance with SB 01.17a or 01.14a (as applicable).
(c) Repeat the inspections and rework of paragraphs (a) and (b) in intervals not to exceed 400 hours' time in service.
(d) In the event the helicopter is subjected to a hard landing or to high surface winds, when parked without effective tiedown straps installed, repeat the inspections of paragraph (a) for the main rotor head star arms and the main gearbox suspension bars before further flight.
(e) In the event of a landing which exhibits abnormal self-sustained dynamic vibrations (ground resonance type vibrations) repeat all the inspections of paragraph (a).
(f) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, Fort Worth, Texas 76193-0100, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.
(g) In accordance with 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 shall be done in accordance with Aerospatiale SB 01.17a or 01.14a (as applicable).
The incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1). Copies may be obtained from Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. These documents may 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 or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C.
This AD revises AD 86-15-10, Amendment 39-5517 (52 FR 13233; April 22, 1987), which became effective on April 22, 1987, as to all persons except those persons to whom it was made immediately effective by priority letter AD 86-15-10, issued July 30, 1986, which contained this amendment.
This amendment (39-6514, AD 86-15-10 R1) becomes effective on March 22, 1990.