AD 99-02-09

This amendment adopts a new airworthiness directive (AD), applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This amendment requires removing the main rotor pitch link assemblies, measuring the radial play of the upper and lower spherical bearings (bearings), and replacing any unairworthy bearings. This amendment is prompted by four reports of increased vibration of the helicopters caused by wear in the bearings of the main rotor pitch change link assembly. The actions specified by this AD are intended to detect unairworthy bearings on the pitch change link assembly and to prevent increased vibration and subsequent reduced controllability of the helicopter.

Final Rule

99-02-09 AGUSTA S.p.A.: Amendment 39-11000. Docket No. 97-SW-55-AD.

Applicability: Model A109C and A109K2 helicopters, 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 (d) 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 main rotor pitch change link spherical bearing axial play due to wear, which could result in an increase in the vibration level and reduced controllability of the helicopter, accomplish the following:

(a) Within the next 10 hours time-in-service (TIS) and thereafter at intervals not to exceed 100 hours TIS, remove the pitch change link assembly, part number (P/N) 109-0110-71.

(b) Measure the radial play at both the upper and lower spherical bearings. If the radial play of a bearing exceeds 0.2 millimeters, or .008 inches, replace the affected bearing with an airworthy bearing prior to further flight.

NOTE 2: Agusta Bollettino Technico Telegrafico No. 109-9, dated March 23, 1995, pertains to the subject of this AD.

(c) Reinstall the pitch change link assembly.

(d) 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, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff. 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.

(e) 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 Registro Aeronautico Italiano (Italy) AD's 95-082 and 95-083, both dated March 28, 1995.

(f) This amendment becomes effective on February 19, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that is applicable to Agusta S.p.A. Model A109C and A109K2 helicopters was published in the Federal Register June 5, 1998 (63 FR 30660). That action proposed removing the main rotor pitch link assemblies, measuring the radial play of the bearings, and replacing any unairworthy bearings.

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 3 helicopters of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per helicopter to accomplish the actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $1122 for the upper bearing and $995 for the lower bearing per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $6891.

The regulations 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 amendment will not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this regulation (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under the 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 may be obtained by requesting a copy from the Office of the Regional Counsel, Southwest Region Attention: Rules Docket No. 97-SW-55-AD, 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 (AD) to read as follows: