Airworthiness Directives; Short Brothers Model SD3-60 SHERPA Series Airplanes

Summary:

This amendment supersedes an existing airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that currently requires a one-time visual inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary. This amendment requires accomplishment of the inspection and replacement in accordance with revised procedures. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane.

Table of Contents

Addresses:

The service information referenced in this AD may be obtained from Short Brothers, Airworthiness Engineering Quality, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

For further information contact:

Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

Supplementary information:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 99-03-06, amendment 39-11020 (64 FR 5588, February 4, 1999), which is applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, was published in the Federal Register on June 30, 2000 (65 FR 40549). The action proposed to require a one-time inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact

The FAA estimates that approximately 28 airplanes of U.S. registry will be affected by this AD, that it will take approximately 15 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $25,200, or $900 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

Regulatory Impact

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 2. Section 39.13 is amended by removing amendment 39-11020 (64 FR 5588, February 4, 1999), and by adding a new airworthiness directive (AD),amendment 39-11951, to read as follows:

2000-22-05Short Brothers, PLC: Amendment 39-11951. Docket 2000-NM-202-AD. Supersedes AD 99-03-06, Amendment 39-11020.

Applicability: All Model SD3-60 SHERPA series airplanes, certificated in any category.

Note 1:

This AD applies to each airplane 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 airplanes 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 as indicated, unless accomplished previously.

To prevent breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane, accomplish the following:

Inspection and Corrective Actions

(a) At the next scheduled heavy maintenance inspection, but no later than 1,200 flight hours after the effective date of this AD: Perform a one-time inspection to determine the part number (P/N) of the power control cable assemblies and pulleys of the engine controls, in accordance with Part A of the Accomplishment Instructions of Shorts Service Bulletin SD3-60 SHERPA-76-1, Revision 2, dated March 21, 2000.

(1) If any power control cable assembly having P/N SD3-47-1091 or SD3-47-1094 is found, prior to further flight, replace the power control cable assembly with a new power control cable assembly in accordance with Part B of the Accomplishment Instructions of the service bulletin.

(2) If any pulley having P/N C181605 is found, prior to further flight, replace the pulley with a new pulley in accordance with Part C of the Accomplishment Instructions of the service bulletin.

Spares

(b) As of the effective date of this AD, no person shall install on the engine controls of any airplane a cable assembly having P/N SD3-47-1091 or SD3-47-1094, or any pulley having P/N C181605.

Alternative Methods of Compliance

(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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

Note 2:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, International Branch, ANM-116.

Special Flight Permits

(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 airplane to a location where the requirements of this AD can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance with Shorts Service Bulletin SD3-60 SHERPA-76-1, Revision 2, dated March 21, 2000, which contains the following list of effective pages:

Page No.Revision level shown on pageDate shown on page
1, 3, 4, 7, 13, 27 2 Mar. 21, 2000.
2, 8, 10-12, 14-16, 23, 29 1 Oct. 14, 1998.
5, 6, 9, 17-22, 24-26, 28 Original July 1998.

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 Short Brothers, Airworthiness Engineering Quality, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

(f) This amendment becomes effective on December 4, 2000.

Issued in Renton, Washington, on October 23, 2000. Donald L. Riggin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

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