01-22085. Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time eddy current inspection for cracks of the fuselage butt joint which is forward of the emergency exits on the left- and right-hand sides of the airplane at the level of stringers 27/48. This proposal would also require repair of any cracks detected. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct cracks in the area of the emergency escape hatches, which, if undetected, could result in depressurization during flight, possibly leading to structural failure of the airplane.

DATES:

Effective October 11, 2001.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 11, 2001.

ADDRESSES:

The service information referenced in this AD may be obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

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 Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes was published in the Federal Register on June 27, 2001, (66 FR 34132). That action proposed to require a one-time eddy current inspection for cracks of the fuselage butt joint which is forward of the emergency exits on the left- and right-hand sides of the airplane at the level of stringers 27/48. That action also proposed to require repair of any cracks detected.

Comments

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.

Conclusions

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 23 Model F.28 Mark 1000, 2000, 3000, and 4000 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 eddy current 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 $2,760, 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. 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 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:

2001-18-02 Fokker Services B.V.: Amendment 39-12428. Docket 2001-NM-23-AD.

Applicability: All Model F.28 Mark 1000, 2000, 3000, and 4000 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 (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 detect and correct cracks in the area of the emergency escape hatches, which, if undetected, could result in depressurization during flight, possibly leading to structural failure of the airplane, accomplish the following:

Inspection

(a) Prior to the accumulation of 30,000 total flight cycles, or within 12 months after the effective date of this AD, whichever occurs later: Perform a one-time eddy current inspection to detect cracks of the fuselage butt joint forward of the emergency hatches on the left- and right-hand sides of the airplane at the level of stringers 27/48, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF28/53-148, dated August 15, 2000.

Repair

(b) If any crack is found during the inspection required by paragraph (a) of this AD: Prior to further flight, repair the crack per a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Rijksluchtvaartdienst (or its delegated agent).

Reporting

(c) Submit a report of inspection findings (both positive and negative) to Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; and to Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax [phone]. The report is to be submitted at the applicable time specified in paragraph (c)(1) or (c)(2) of this AD. The report must include the inspections results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. 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 is accomplished after the effective date of this AD: Submit a report of findings within 10 days after performing the inspection required by paragraph (a) of this AD.

(2) For airplanes on which the inspection was accomplished prior to the effective date of this AD: Submit a report of findings within 10 days after the effective date of this AD.

Alternative Methods of Compliance

(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. 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.

Special Flight Permits

(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.

Incorporation by Reference

(f) Except as specified by paragraph (b) of this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF28/53-148, dated August 15, 2000. 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 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 Dutch airworthiness directive 2000-151, dated November 30, 2000

Effective Date

(g) This amendment becomes effective on October 11, 2001.

Issued in Renton, Washington, on August 27, 2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.