AD 98-21-33

This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time inspection of the torque links of the main landing gear (MLG) assemblies to determine if the lockwire is present on the apex bolt; and corrective action, if necessary. 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 failure of the MLG due to loose connections between the upper and lower torque links of the MLG.

Final rule

98-21-33 FOKKER: Amendment 39-10841. Docket 97-NM-278-AD.

Applicability: All Model F.28 Mark 0070 and 0100 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 failureof the main landing gear (MLG) due to loose connections between the upper and lower torque links of the MLG, accomplish the following:

(a) Inspect the torque links of the left and right MLG assemblies to determine if the lockwire is installed on the apex bolt, in accordance with Fokker F100 All Operator Message (AOM) AOF100.013, Reference TS96.68988, dated December 19, 1996, at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. If any discrepancy is found, prior to further flight, retorque the apex bolt and install lockwire in accordance with the AOM.

(1) For airplanes equipped with Menasco Aerospace, Ltd., MLG assemblies: Inspect within 5 days after the effective date of this AD.

(2) For airplanes equipped with Messier-Dowty, Ltd., MLG assemblies: Inspect within 30 days after the effective date of this AD.

(b) As of the effective date of this AD, no person shall install on any airplane an MLG torque link joint apex pin and nut installation, unless it has been inspected and corrective action has been accomplished, in accordance with Fokker F100 AOM AOF100.013, Reference TS96.68988, dated December 19, 1996.

(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 International Branch, ANM-116.

(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 actions shall be done in accordance with Fokker F100 All Operator Message (AOM) AOF100.013, Reference TS96.68988, dated December 19, 1996. 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 3: The subject of this AD is addressed in Dutch airworthiness directive 1996-147 (A), dated December 23, 1996.

(f) This amendment becomes effective on November 20, 1998.

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 Fokker Model F.28 Mark 0070 and 0100 series airplanes was published in the Federal Register on January 29, 1998 (63 FR 4406). That action proposed to require a one-time inspection of the torque links of the main landing gear (MLG) assemblies to determine if the lockwire is present on the apex bolt; and corrective action, if necessary.

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

Support for the Proposal
One commenter supports the proposed rule. Request to Revise Area of Inspection

One commenter requests that paragraph (b) of the proposal be clarified to more accurately define the area to be inspected. The commenter states that the proposal, which specified that theMLG "torque links" are to be inspected before installation, could cause confusion because the inspection actually pertains to the "torque link joint apex pin and nut installation."

The FAA concurs. Paragraph (b) of the final rule has been revised to clarify that the "torque link joint apex pin and nut installation" is to be inspected before installation.

Comment Regarding Availability of Service Information
The same commenter suggests that paragraph (b) of the proposal should be revised because Fokker All Operator Message (AOM) AOF100.013, Reference TS96.68988, dated December 19, 1996 (which is cited in the proposal as the appropriate source of service information), refers to revision pages and a figure that have not yet been distributed.

Although the commenter does not identify a specific request in regard to the AD, the FAA infers that the commenter is concerned about the lack of availability of procedure 32-11-10-400-814-A (Figure 32-11-10-990-034-A00) or procedure32-11-10-400-814-B (Figure 32-11-10-990-034-B00), which are referenced in the AOM as additional sources of service information. The FAA has determined that this information is available from the manufacturer, and suggests that a further request for the referenced pages may be necessary. No change to the final rule in this regard is necessary.

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

Cost Impact
The FAA estimates that 131 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour 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 $7,860, or $60 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: