- Effective
- July 31, 1998
- Published
- June 26, 1998 · 63 FR 34789–34790
- Models
- AS332C, AS332L, AS332L1
- Data sheet
- TCDSH4EU
- Registered aircraft
- 11 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-10630
- Docket
- 97-SW-39-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 May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 120 KB | ffb3b5c8…ec9964d | 98-17041.pdf on govinfo.gov |
| FAA DRS HTML | 37 KB | 52f9c2e1…30df47e | FAA DRS (API key needed) |
| Federal Register text | 8 KB | a8aeb92d…ce6cb51 | 98-17041.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, and L1 helicopters that requires initial and repetitive inspections of the tail rotor shaft flapping hinge retainers (retainers) for cracks. This amendment is prompted by a report of high vibrations occurring on a helicopter while in service due to a cracked retainer. The actions specified by this AD are intended to detect cracks on the retainers that could lead to high tail rotor vibrations, loss of tail rotor control, and subsequent loss of control of the helicopter.
The airworthiness directive
98-13-39 EUROCOPTER FRANCE: Amendment 39-10630. Docket No. 97-SW-39-AD. Applicability: AS 332C, L, and L1 helicopters, with tail rotor shaft flapping hinge retainer, part number 330A33.3165.00, 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 include an 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 on a tail rotor shaft flapping hinge retainer (retainer) that could lead to high tail rotor vibrations, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:
(a) Prior to further flight, and thereafter before the first flight of each day, perform a dye penetrant inspection of each retainer for cracks.
(b) If a crack is found on any retainer, replace it with an airworthy retainer.
NOTE 2: Eurocopter Service Bulletin No. 05.00.41, dated January 29, 1996, pertains to the subject of this AD.
(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 3: 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.
NOTE 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-074-057(B), dated March 27, 1996.
(e) This amendment becomes effective on July 31, 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 France Model AS 332C, L, and L1 helicopters was published in the Federal Register on April 1, 1998 (63 FR 15791). That action proposed to require initial and repetitive inspections of the retainers for cracks.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
The FAA estimates that 4 helicopters of U.S. registry will be affected by this AD, that it will take approximately 0.5 work hours per helicopter to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts, if replacement of the retainerson the tail rotor blades is necessary, would cost approximately $56,900 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $252,080, assuming that the retainers on the tail rotor blades are replaced on all 4 helicopters and each helicopter is dye penetrant inspected 200 times per year.
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 andProcedures (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, 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 · 11
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1982 | 1 |
|---|---|
| 1988 | 1 |
| 1990 | 1 |
| 1991 | 1 |
| 1992 | 1 |
| 1993 | 1 |
| 1994 | 1 |
| 2000 | 1 |
| 2003 | 2 |
| 2006 | 1 |