AD 95-03-04

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 series airplanes, that requires repetitive inspections to detect fatigue cracking in the pivot pins that attach both nose wheel steering actuators to the steering head assembly, and replacement of cracked pins. This amendment is prompted by a reported failure of a pivot pin due to fatigue cracking. The actions specified by this AD are intended to prevent failure of the pivot pin, which could result in the loss of nose wheel steering capability.

Final rule

95-03-04 BRITISH AEROSPACE REGIONAL AIRCRAFT LIMITED (Formerly British Aerospace Commercial Aircraft Limited, Vickers-Armstrongs Aircraft Limited): Amendment 39-9141. Docket 94-NM-109-AD.
Applicability: All Model Viscount 744, 745D, and 810 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 use the authority provided in paragraph (c) 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 airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent loss of nose wheel steering capability due to failure of the pivot pin, accomplish the following:

(a) Prior to the accumulation of 1,100 landings after the effective date of this AD, or within 14 months after the effective date of this AD, whichever occurs first, perform a magnetic particle inspection to detect cracks of the nose wheel steering actuators connecting (pivot) pins, in accordance with either Viscount Preliminary Technical Leaflet (PTL) 334, Issue 2, dated July 8, 1992 (for Model 744 and 745D series airplanes); or Viscount PTL 205, Issue 2, dated July 8, 1992 (for Model 810 series airplanes); as applicable. Repeat this inspection thereafter at intervals not to exceed 1,100 landings or 14 months, whichever occurs first.

(b) If any crack is found in a pivot pin during any inspection required by this AD, replace the pivot pin in accordance with either Preliminary Technical Leaflet (PTL) 334, Issue 2, dated July 8, 1992 (for Model 744 and 745D series airplanes), or Viscount PTL 205, Issue 2, dated July 8, 1992 (for Model 810 series airplanes). After replacement, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 1,100 landings or within 14 months, whichever occurs first.

(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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(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.

(e) The inspections and replacement shall be done in accordance with Viscount PTL 334, Issue 2, dated July 8, 1992; or Viscount PTL 205, Issue 2, dated July 8, 1992; as applicable. 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 British Aerospace Regional Aircraft Ltd., Engineering Support Manager, Military Business Unit, Chadderton Works, Greengate, Middleton, Manchester M24 1SA, England. 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.

(f) This amendment becomes effective on March 20, 1995.

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 all British Aerospace Model Viscount 744, 745D, and 810 series airplanes was published in the Federal Register on November 14, 1994 (59 FR 56435). That action proposed to require initial and repetitive magnetic particle inspections to detect cracking of the pivot pin that attaches the nose wheel steering actuators to the steering head assembly, and replacement of cracked pins.

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.

As a result of recent communications with the Air Transport Association (ATA) of America, the FAA has learned that, in general, some operators may misunderstand the legal effect of AD's on airplanes that are identified inthe applicability provision of the AD, but that have been altered or repaired in the area addressed by the AD. The FAA points out that all airplanes identified in the applicability provision of an AD are legally subject to the AD. If an airplane has been altered or repaired in the affected area in such a way as to affect compliance with the AD, the owner or operator is required to obtain FAA approval for an alternative method of compliance with the AD, in accordance with the paragraph of each AD that provides for such approvals. A note has been added to this final rule to clarify this requirement.

The FAA has determined that this addition will neither increase the economic burden on any operator nor increase the scope of the AD.

The FAA estimates that 29 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane, per inspection cycle, to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $5,220, or $180 per airplane, per inspection cycle.

The total 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 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 nota "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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and14 CFR 11.89.

39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: