AD 98-22-01

This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, 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 cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing and possible injury to the flightcrew and passengers.

Final rule.

98-22-01 FOKKER SERVICES B.V.: Amendment 39-10847. Docket No. 98-NM-101-AD.

Applicability: Model F.28 Mark 0100 series airplanes, equipped with Messier-Dowty Nose Landing Gear (NLG) having part number (P/N) 201071001 or P/N 201071002, on which the NLG main fitting has not been overhauled in accordance with Component Maintenance Manual 32-20-51; certificated in any category.

NOTE 1: This AD applies to each airplane 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 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 (e) 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 cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing and possible injury to the flightcrew and passengers, accomplish the following:

(a) Perform a one-time visual inspection to detect cracking of the NLG main fitting, in accordance with Fokker Service Bulletin SBF100-32-112, dated November 14, 1997, at the applicable time specified in either paragraph (a)(1) or (a)(2) of this AD. If any cracking is found, prior to further flight, accomplish the requirements of paragraph (b) of this AD.

(1) For airplanes that have accumulated fewer than 15,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 8,000 total flight cycles, or within 90 days after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated 15,000 or more total flight cycles as of the effective date of this AD: Inspect within 30 days after the effective date of this AD.

(b) Perform a one-time eddy current and/or dye penetrant inspection to detect cracking of the NLG main fitting, in accordance with Messier-Dowty Service Bulletin F100-32-92, dated November 14, 1997, at the applicable time specified in either paragraph (b)(1) or (b)(2) of this AD. Accomplishment of the inspection required by paragraph (b) of this AD, if accomplished prior to the inspection required by paragraph (a) of this AD, terminates the inspection requirement of paragraph (a) of this AD.

(1) For airplanes that have accumulated fewer than 15,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 8,000 total flight cycles, or within 180 days after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated 15,000 or more total flight cycles as of the effective date of this AD: Inspect within 60 days after the effective date of this AD.

(c) If any crack is detected during the inspection required by paragraph (b) of this AD, prior to further flight, rework the NLG main fitting in accordance with Messier-Dowty Service Bulletin F100-32-92, dated November 14, 1997.

(d) Within 7 days after accomplishing the inspection required by either paragraph (a) or (b) of this AD, or within 7 days after the effective date of this AD, whichever occurs later, submit a report of the inspection results (both positive and negative findings) to Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the Netherlands. 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 havebeen assigned OMB Control Number 2120-0056.

(e) 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.

(f) 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.

(g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF100-32-112, dated November 14, 1997, and Messier-Dowty Service Bulletin F100-32-92, dated November 14, 1997. 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 BLA 1997-116 (A), dated November 28, 1997.

(h) This amendment becomes effective on December 7, 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 certain Fokker Model F.28 Mark 0100 series airplanes was published in the Federal Register on May 28, 1998 (63 FR 29157). That action proposed to require a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, if necessary.

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

Two commenters support the intent of the proposal but request that the reporting requirement of the proposed AD be revised to recognize inspections accomplished prior to the effective date of this AD. The commenters indicate that paragraph (d) of the proposed rule specifies that results of the inspections performed in accordance with paragraph (a) or (b) of the AD are to be submitted to the manufacturer within 7 days after accomplishment of the inspections. Both commenters point out that operators that have accomplished the inspections previously, but that did not submit a report of the results to the manufacturer within 7 days after accomplishment of the inspections, would be immediately out of compliance with the AD and would have to accomplish the inspections again in order to comply.

The FAA concurs with the request. Therefore, the FAA has revised paragraph (d) of the final rule to incorporate a grace period for the reporting requirement. Paragraph (d) of the final rule specifies that a report of the inspection results must be submitted to the manufacturer, "Within 7 days after accomplishing the inspection required by either paragraph (a) or (b) of this AD, or within 7 days after the effective date of this AD, whichever occurs later."
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 127 airplanes of U.S. registry will be affected by this AD.
It will take approximately 2 work hours per airplane to accomplish the visual inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the visual inspection required by this AD on U.S. operators is estimated to be $15,240, or $120 per airplane.

It will take approximately 2 work hours per airplane to accomplish the eddy current and/or dye penetrant inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the eddy current and/or dye penetrant inspection required by this AD on U.S. operators is estimated to be $15,240, or $120 per airplane.

The cost impact figures discussed above are 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: