- Effective
- June 11, 1998
- Published
- May 7, 1998 · 63 FR 25158–25160
- Superseded by
- AD2000-11-17
- Models
- AS-365N2, SA-365N1, SA-366G1
- Data sheet
- TCDSH10EU
- Registered aircraft
- 7 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-10515
- Docket
- 97-SW-49-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. Only the govinfo PDF is the legal edition. DRS record last changed August 7, 2025.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 124 KB | e5c40497…837f60c | 98-12114.pdf on govinfo.gov |
| FAA DRS HTML | 44 KB | 625cec17…e6272b3 | FAA DRS (API key needed) |
| Federal Register text | 10 KB | 283e2353…e628e5d | 98-12114.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Eurocopter) Model SA-365N1, AS-365N2, and SA-366G1 helicopters, that requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified by this AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.
The airworthiness directive
98-10-04 EUROCOPTER FRANCE: Amendment 39-10515. Docket No. 97-SW-49-AD. Applicability: SA-365N1, AS-365N2, and SA-366G1 model helicopters, with tail rotor blade (blade), Part Number 365A12-010-all dash numbers, 365A12-0020-00, 365A33-2131-all dash numbers, or 365A12-0020-20, installed, certificated in any category.
NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should includean assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To detect cracks that could lead to delamination of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar), loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 250 hours TIS, inspect each Kevlar tie-bar for a crack or delamination in accordance with paragraph B, Operational Procedure, of Eurocopter France Service Bulletin 05.00.34, Revision 3, dated November 14, 1996.
(b) If any delamination or cracking is found during any of the inspections required by paragraph (a) of this AD, remove the blade and replace it with an airworthy blade before further flight.
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished.
(e) The inspections and replacement, if necessary, shall be done in accordance with Eurocopter France Service Bulletin 05.00.34, Revision 3, dated November 14, 1996. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
NOTE 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 92-185-033(B)R4 dated December 4, 1996.
(f) This amendment becomes effective on June 11, 1998.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Eurocopter Model SA-365N1, AS-365N2, and SA-366G1 helicopters was published in the Federal Register on March 13, 1998 (63 FR 12419). That action proposed to require initial and repetitive inspections of the tail rotor blade Kevlar tie-bar for cracks or delaminations.
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comment received.
The sole commenter states that the proposed AD is more restrictive than either Eurocopter France Service Bulletin 05.00.34R3, dated November 14, 1996, or Direction Generale De L'Aviation Civile (DGAC) AD 92-185-033(B)R4, dated December 4, 1996, which allow operation of a helicopter having cracks that are within a certain tolerance. The commenter states that not all cracks warrant replacement of the part, and that the proposed AD should give the same parameters for the cracks as given in the Eurocopter France service bulletin and the DGAC AD. The FAA does not concur. Any crack or delamination of the Kevlar tie-bar could initiate a failure and lead to loss of control of the helicopter. The FAA considers any crack in a flight critical part to be unsafe, and the part must be replaced prior to further flight.
After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
The FAA estimates that 47 helicopters of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per helicopter to accomplish the actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $3,000 per blade. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $152,280 to replace one blade and perform one inspection on each helicopter.
The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."
List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701.
39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 7
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1989 | 1 |
|---|---|
| 1995 | 1 |
| 1999 | 1 |
| 2008 | 1 |
3 with no year recorded