AD 2000-17-03

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently 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 requires new inspections (one-time detailed visual inspection and repetitive eddy current or dye penetrant inspections) to detect cracking of the NLG main fitting subassembly, and corrective actions, if necessary. This amendment also revises the applicability of the existing AD. This amendment is prompted by the 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.

2000-17-03 FOKKER SERVICES B.V.: Amendment 39-11876. Docket 2000-NM-02-AD. Supersedes AD 98-22-01, Amendment 39-10847.

Applicability: Model F.28 Mark 0100 series airplanes, certificated in any category; equipped with Messier-Dowty nose landing gear (NLG) having part number (P/N) 201071001 or 201071002, on which a main fitting subassembly (MFSA) having P/N 201071200, 201071228, 201071248, or 201071249 is installed.

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 (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repairon 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:

One-time Detailed Visual Inspection
(a) Prior to the accumulation of 7,500 total flight cycles or within 50 flight cycles after the effective date of this AD, whichever occurs later: Perform a one-time detailed visual inspection of the NLG main fitting subassembly to detect cracking, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999.

(1) If no cracking is detected, no further action is required by this paragraph.

(2) If any cracking is detected, prior to further flight, accomplish the actions required by paragraph (b) of this AD.

NOTE 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirrors, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."

NOTE 3: Actions accomplished prior to the effective date of this AD, in accordance with Fokker Service Bulletin SBF100-32-112, dated November 14, 1997, which was cited in AD 98-22-01, amendment 39-10847, are not considered acceptable for compliance with any requirements of this AD.

Repetitive Eddy Current and/or Dye Penetrant Inspections
(b) Except as required by paragraph (a)(2) of this AD: Prior to the accumulation of 7,875 total flight cycles or within 375 flight cycles after the effective date of this AD, whichever occurs later, perform an eddy current or dye penetrant inspection of the NLG main fitting subassembly to detect cracking, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999. Such inspection within the compliance time required by paragraph (a) of this AD terminates the requirements of paragraph (a) of this AD. Repeat the inspection thereafter, using an eddy current or dye penetrant technique, at intervals not to exceed 750 flight cycles.

(c) If any cracking is detected during any inspection required by paragraph (b) of this AD: Prior to further flight, rework the main fitting of the NLG, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999. If, after rework, any cracking remains that exceeds the limits specified in the service bulletin, prior to further flight, accomplish the actions specified by either paragraph (c)(1) or (c)(2) of this AD.

(1) Replace the NLG in accordance with the service bulletin; and within 7,875 flight cycles after such replacement, perform the inspection as specified in paragraph (b) of this AD, and repeat the inspection thereafter at intervals not to exceed 750 flight cycles. Or

(2) Repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Rijksluchtvaartdienst (RLD) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

NOTE 4: The Fokker service bulletin references Messier-Dowty Service Bulletin F100-32-92, Revision 1, dated October 8, 1999, as an additional source of service information for accomplishing the inspections and rework of the NLG main fitting subassembly.

Reporting Requirements
(d) Submit a report of the detailed visual inspection findings (positive and negative) required by paragraph (a) and a report of the initial eddy current or dye penetrant inspection findings (positive and negative) required by paragraph (b) to Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; at the applicable time specified in paragraph (d)(1) or (d)(2). Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMP) 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 detailed visual inspection specified by paragraph (a) of this AD and the initial repetitive eddy current or dye penetrant inspection specified by paragraph (b) of this AD are accomplished after the effective date of this AD: Submit each report within 7 days after performing the applicable inspection.

(2) For airplanes on which the detailed visual inspection specified by paragraph (a) of this AD and the initial repetitive eddy current or dye penetrant inspection specified in paragraph (b) of this AD have been accomplished prior to the effective date of this AD: Submit the reports within 7 days after the effective date of this AD.

Spares
(e) As of the effective date of this AD, no person shall install a NLG having P/N 201071001 or 201071002 unless the installed MFSA has been inspected, by means of an eddy current or dye penetrant inspection, in accordance with paragraph (b) of this AD.

Alternative Methods of Compliance
(f) 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. 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 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits
(g) 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
(h) Except as provided by paragraph (c)(2) of this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF100-32-118, dated October 8, 1999. 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., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. Copies may be inspected atthe 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 6: The subject of this AD is addressed in Dutch airworthiness directive BLA 1997-116/2 (A), dated October 29, 1999.

Effective Date

(i) This amendment becomes effective on October 3, 2000.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 98-22-01, amendment 39-10847 (63 FR 58625, November 2, 1998), which is applicable to certain Fokker Model F.28 Mark 0100 series airplanes, was published in the Federal Register on March 15, 2000 (65 FR 13923). The action proposed to require new inspections (one-time detailed visual inspection and repetitive eddy current or dye penetrant inspections) to detect cracking of the nose landing gear (NLG) main fitting subassembly, and corrective actions, if necessary. The action also proposed to revise the applicability of the existing AD.

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

One commenter states that it has completed the inspections and has a repetitive inspection program already in place to comply with the requirementsof this AD.

Type Certificate Holder
One commenter requests that the Explanation of Relevant Service Information section of the AD be revised to refer to the current type certificate holder (Fokker Services B.V.), rather than the now defunct airplane manufacturer, as the issuer of the relevant service information. The FAA acknowledges the accuracy of this information; however, since this section is not repeated in the final rule, no change is made to the AD.

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
There are approximately 87 airplanes of U.S. registry that will be affected by this AD.

The one-time detailed visual inspection required by this AD action will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the one-time inspection required by this AD on U.S. operators is estimated to be $5,220, or $60 per airplane.

The repetitive eddy current or dye penetrant inspections required by this AD action will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the repetitive inspection required by this AD on U.S. operators is estimated to be $5,220, or $60 per airplane, per inspection cycle.

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD, 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 maybe 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 removing amendment 39-10847 (63 FR 58625, November 2, 1998), and by adding a new airworthiness directive (AD), amendment 39-11876, to read as follows: