AD 99-02-12

This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time visual inspection to detect discrepancies of the components of the torque link apex joint and shimmy damper attachments of the main landing gear (MLG), and repair or replacement of any discrepant component with a new or serviceable component. 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 heavy vibration and possible damage to the components of the MLG, and consequent reduced controllability of the airplane during takeoff and landing.

Final rule

99-02-12 FOKKER SERVICES B.V.: Amendment 39-11004. Docket 98-NM-276-AD.

Applicability: Model F.28 Mark 0070 and 0100 series airplanes, as listed in Fokker Service Bulletin SBF100-32-113, dated May 28, 1998; 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 (d) 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 heavy vibration and possible damage to the components of the main landing gear (MLG), and consequent reduced controllability of the airplane during takeoff or landing, accomplish the following:

(a) Within 45 days after the effective date of this AD, perform a one-time visual inspection to detect discrepancies of the components of the torque link apex joint and shimmy damper attachments of the MLG, in accordance with Fokker Service Bulletin SBF100-32-113, dated May 28, 1998. If any discrepancy is detected, prior to further flight, repair or replace any discrepant component with a new or serviceable component, in accordance with the service bulletin.

NOTE 2: In paragraph 2.F.(10) of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-113, dated May 28, 1998, the parenthetical phrase that recommends the size of torque wrench to use, should read "... (0 to 75 lbf ft)," rather than "...(0 to 75 lbf in)".

(b) Submit a report of the inspection findings (positive or negative) to Fokker Services B.V., Technical Services, Attn.: Manager Airline Support, P.O. Box 75047, 1117 ZN Schiphol-Oost, the Netherlands; Fax No. 3120605200; at the time specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.

(1) For airplanes on which the inspection required by paragraph (a) of this AD is accomplished after the effective date of this AD: Submit a report within 10 days after accomplishing the inspection required by paragraph (a) of this AD.

(2) For airplanes on which the inspection required by paragraph (a) of this AD has been accomplished prior to the effective date of this AD: Submit a reportwithin 30 days after the effective date of this AD.

(c) As of the effective date of this AD, no person shall install on any airplane a Menasco MLG having part number (P/N) 41050-5, -6, -7, or -8; or P/N 41060-1 or -2; unless it has been inspected in accordance with paragraph (a) of this AD.

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

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

(f) Except as provided by paragraph (b) of this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF100-32-113, dated May 28, 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 Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the Netherlands. 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.

NOTE 4: The subject of this AD is addressed in Dutch airworthiness directive BLA 1998-058 (A), dated May 29, 1998.

(g) This amendment becomes effective on February 25, 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 certain Fokker Model F.28 Mark 0070 and 0100 series airplanes was published in the Federal Register on November 13, 1998 (63 FR 63423). That action proposed to require a one-time visual inspection to detect discrepancies of the components of the torque link apex joint and shimmy damper attachments of the main landing gear (MLG), and repair or replacement of any discrepant component with a new or serviceable component.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

Two commenters state that they are not affected by the proposed rule and, therefore, have no technical comments regarding the proposed rule.

Conclusion
After careful review of the available data, including the comments noted above, 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 131 Model F.28 Mark 0070 and 0100 series airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required inspection, 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 $15,720, or $120 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.

Regulatory Impact
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 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 the following new airworthiness directive: