AD 99-21-13 ACTIVE

This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires inspecting and replacing certain bolts that secure the hoist arm lower fitting. This amendment is prompted by a report of a failure of the bolts that secure the hoist arm lower fitting during a factory load test. The actions specified by this AD are intended to prevent failure of the bolts that secure the hoist arm lower fitting, separation of components from the helicopter, impact with the main or tail rotor, and subsequent loss of control of the helicopter.

Final rule

99-21-13 EUROCOPTER FRANCE: Amendment 39-11358. Docket No. 99-SW-13-AD. Issued September 29, 1999
Applicability: Model AS332C, L, and L1 helicopters, that are not modified in accordance with modification AMS 0722955, certificated in any category.

NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required prior to the next use of the hoist, unless accomplished previously.

To prevent failure of the bolts that secure the hoist arm lower fitting, separation of components from the helicopter, impact with the main or tail rotors, and subsequent loss of control of the helicopter, accomplish the following:

(a) Remove the four bolts that secure the hoist arm lower fitting.

(b ) Inspect each bolt as follows:

(1) Measure each bolt shank from beneath the bolt head to the shank end;

(2) Determine the part number (P/N) of the bolt; and

(3) Determine what engraved marking is present on the bolt head.

(c) Each bolt, P/N 22201BE080020L, inspected in accordance with paragraph (b), measuring 20 mm in length and having "BE" engraved on the bolt head may be reinstalled if otherwise airworthy.

(d) Any bolt inspected in accordance with paragraph (b), not measuring 20 mm in length and having "BC" or letters other than "BE" engraved on the bolt head must be replaced. Replace with an airworthy bolt, P/N 22201BE080020L, that measures 20 mm in length and has "BE" engraved on the bolt head.

(e) 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, Regulations Group, 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, Regulations Group.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group.

(f) 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 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD No. 98-487-072(A), dated December 2, 1998.

(g) This amendment becomes effective on November 10, 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 France Model AS332C, L, and L1 helicopters was published in the Federal Register on July 7, 1999 (64 FR 36623). That action proposed to require inspecting and replacing certain bolts that secure the hoist arm lower fitting.

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 except for two nonsubstantive changes that have been made to paragraph (e) and Note 2 of the AD. In paragraph (e), the NPRM incorrectly states that alternative methods of compliance (AMOC) or adjustments of the compliance time may be approved by the "Manager, Rotorcraft Certification Office, Rotorcraft Directorate." This is incorrect and has been changed to state that the Manager, Regulations Group, Rotorcraft Directorate, is responsible for approving any AMOC or adjustment of the compliance time. Note 2 of the NPRM states that information concerning the existence of approved AMOC may be obtained from the "Rotorcraft Certification Office;" this is also incorrect and has been changed to state that information may be obtained from the "Regulations Group." The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

The FAA estimates that 4 helicopters of U.S. registry will be affected by this AD, that it will take approximately 1.5 work hours per helicopter to inspect and replace the bolts, and that the average labor rate is $60 per work hour. Required parts will cost approximately $50 for 4 bolts. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $560.

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 itmay be obtained from the Rules Docket at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. 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:

Shep Blackman, Aerospace Engineer, FAA, Rotorcraft Directorate, Regulations Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 222-5961.