AD 99-02-13

This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters, that requires the replacement of certain main rotor hub spindles (spindles) and flapping hinge pins (pins). This amendment is prompted by testing of aged frequency adapters, which shows that premature failure of the spindles and pins can occur due to increased loading from increased stiffness of the aged frequency adapters. The actions specified by this AD are intended to prevent the loss of a main rotor blade and subsequent loss of control of the helicopter.

Final rule

99-02-13 EUROCOPTER FRANCE: Amendment 39-11005. Docket No. 97-SW-41-AD.
Applicability: Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters with main rotor hub spindles (spindles), part number (P/N) 332A31-1390-00 through -07 or 332A31-1398-00 or flapping hinge pin (pin), P/N 332A31-1380-all dash numbers, 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 (g) 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 prevent failure of the spindles or pins that could result in loss of a main rotor blade and subsequent loss of control of the helicopter, accomplish the following:

(a) For the spindles and pins that have never been overhauled, remove the spindles and pins and replace them with airworthy spindles and pins in accordance with paragraphs 2.B.1)a) through 2.B.1)d) and 2.B.2) of the Accomplishment Instructions of Eurocopter France Service Bulletin No. 01.00.44, dated March 26, 1996 (SB), as follows:

(1) Within 6 calendar months for spindles and pins that have been in service for 12 or more calendar years.

(2) Within 18 calendar months for spindles and pins that have been in service for 8 or more calendar years but less than 12 calendar years.

(b) For the spindles and pins that have been overhauled at least once, remove the spindles and pins and replace them with airworthy spindles and pins in accordance with paragraphs 2.B.1)a) through 2.B.1)d) and 2.B.2) of the SB as follows:

(1) Within 3 calendar months for spindles and pins that have been in service for 6 or more calendar years since last overhaul.

(2) Within 15 calendar months for spindles and pins that have been in service for 4 or more calendar years but less than 6 calendar years since last overhaul.

(c) Remove spindle, Serial Number (S/N) FR 25012, and pins, S/N's M 243, FR 139, FR 230, M 127, or M 112, and replace them with airworthy spindles and pins in accordance with paragraphs 2.B.1)a) through 2.B.1)d) and 2.B.2) of the SB within 6 calendar months.

(d) Remove spindle, S/N FR 25866, and replace it with an airworthy spindle in accordance with paragraphs 2.B.1)a) through 2.B.1)d) and 2.B.2) of the SB within 18 calendar months.

(e) This AD revises the Airworthiness Limitations Section of the Maintenance Manual by establishing a new retirement life of 8 calendar years for the spindles, P/N 332A31-1390-00 through -07 and 332A31-1398-00, and pins, P/N 332A31-1380-all dash numbers, except as otherwise specifically limited by this AD.

(f) Installation of a main rotor hub with modification 332A07-43100 constitutes terminating action for the requirements of this AD.

(g) 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 FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(h) 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.

(i) The modification shall be done in accordance with paragraphs 2.B.1)a) through 2.B.1)d) and 2.B.2) of the Accomplishment Instructions of Eurocopter France Service Bulletin No. 01.00.44, dated March 26, 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 96-100-058-(B), dated May 22, 1996.

(j) This amendment becomes effective on March 4, 1999.

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 AS332C, L, and L1 helicopters was published in the Federal Register on October 27, 1998 (63 FR 57257). That action proposed to require replacing certain spindles and pins.

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 4 work hours per helicopter to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $21,600 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $87,360.

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 thisaction 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: