AD 2000-16-06

This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters. This AD requires replacing arm clamp screws (screws) in the yaw, roll, pitch, and collective syncro resolvers, and installing a guard bracket on the yaw, roll, pitch, and collective syncro resolvers. This AD is prompted by an operator's report that a yaw control channel jammed during freedom-of-control checks following maintenance. The actions specified by this AD are intended to prevent a jammed flight control and subsequent loss of control of the helicopter.

Final rule

2000-16-06 BELL HELICOPTER TEXTRON CANADA: Amendment 39-11860. Docket No. 99-SW-84-AD.
Applicability: Model 430 helicopters, serial numbers 49001 through 49018, 49020 through 49043, and 49045 through 49051, 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 (c) 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 within 150 hours time-in-service after the effective date of this AD, unless accomplished previously.

To prevent a jammed flight control and subsequent loss of control of the helicopter, accomplish the following:

(a) Remove the arm clamp screws (screws) in the yaw, roll, pitch, and collective syncro resolvers and replace them with airworthy screws in accordance with the Accomplishment Instructions in Alert Service Bulletin 430-99-1, dated May 7, 1999 (ASB).

(b) Install a guard bracket on the yaw, roll, pitch, and collective syncro resolvers in accordance with the Accomplishment Instructions in the ASB.

(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, 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.

(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 modifications shall be done in accordance with the Accomplishment Instructions in Alert Service Bulletin 430-99-11, dated May 7, 1999. 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 Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax (514) 433-0272. 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.

(f) This amendment becomes effective on September 20, 2000.

NOTE 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-99-26, dated September 28, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD for BHTC Model 430 helicopters was published in the Federal Register on May 3, 2000 (65 FR 25694). That action proposed to require replacing screws in the yaw, roll, pitch, and collective syncro resolvers, and installing a guard bracket on the yaw, roll, pitch, and collective syncro resolvers.

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 33 helicopters of U.S. registry will be affected by this AD, that it will take approximately 6 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 $548. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $29,964.

The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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: