02-1963. Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires repetitive operational tests for discrepancies of the heating system of pitot tube #1, and replacement of the pitot tube, if necessary. This AD also requires eventual modification of the alternating current sensing circuit for pitot tube #1, which terminates the repetitive operational test requirement. This action is necessary to prevent failure of the heating system of pitot tube #1 due to a short circuit, which may go undetected and lead to the pilot receiving erroneous airspeed indications, resulting in reduced control of the airplane. This action is intended to address the identified unsafe condition.

DATES:

Effective March 6, 2002.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 6, 2002.

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 certain Fokker Model F.28 Mark 0070 and 0100 series airplanes was published in the Federal Register on November 5, 2001 (66 FR 55896). That action proposed to require repetitive operational tests for discrepancies of the heating system of pitot tube #1, and replacement of the pitot tube, if necessary. That action also proposed to require eventual modification of the alternating current sensing circuit for pitot tube #1, which would terminate the repetitive operational test requirement.

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.

Conclusion

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 129 airplanes of U.S. registry will be affected by this AD.

It will take approximately 1 work hour per airplane to accomplish the required operational test, at the average labor rate of $60 per work hour. Based on these figures, the cost impact of the operational test required by this AD on U.S. operators is estimated to be $7,740, or $60 per airplane, per test cycle.

It will take approximately 34 work hours per airplane to accomplish the required modification, at the average labor rate of $60 per work hour. Required parts will cost approximately $350 per airplane. Based on these figures, the cost impact of the modification required by this AD on U.S. operators is estimated to be $308,310, or $2,390 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. 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:

2002-01-19 Fokker Services B.V.: Amendment 39-12613. Docket 2001-NM-128-AD.

Applicability: Model F.28 Mark 0070 and 0100 series airplanes, serial numbers 11244 through 11585 inclusive, on which Fokker Service Bulletin SBF100-30-019 or SBF100-30-020 has been accomplished, 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 failure of the heating system of pitot tube #1 due to a short circuit, which may go undetected and lead to the pilot receiving erroneous airspeed indications, resulting in reduced control of the airplane, accomplish the following:

Operational Test

(a) Within 3 months after the effective date of this AD, do an operational test for discrepancies (i.e., correct functioning) of the heating system of pitot tube #1, according to Fokker Service Bulletin SBF100-30-025, Revision 1, dated March 14, 2001. Repeat the operational test every 12 months, until paragraph (d) of this AD has been done.

Replacement of Pitot Tube

(b) If any discrepancy is found during the operational test required by paragraph (a) of this AD: Before further flight, replace pitot tube #1 with a new pitot tube, according to Fokker Service Bulletin SBF100-30-025, Revision 1, dated March 14, 2001.

Reporting Requirement

(c) At the applicable time specified in paragraph (c)(1) or (c)(2) of this AD: Use page 38 of Fokker Service Bulletin SBF100-30-025, Revision 1, dated March 14, 2001, to submit a report of findings from each operational test (both positive and negative) to Fokker Services B.V., Attn: Manager Airline Support, P.O. Box 231, 2150 AE Nieuw-Vennep, 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 have been assigned OMB Control Number 2120-0056.

(1) For airplanes on which the operational test is accomplished after the effective date of this AD: Submit the report within 5 days after performing the test required by paragraph (a) of this AD.

(2) For airplanes on which the operational test is accomplished before the effective date of this AD: Submit the report within 5 days after the effective date of this AD.

Modification

(d) Within 36 months after the effective date of this AD, modify the alternating current (AC) sensing circuit for pitot tube #1 (including removing the supply current wire from the AC current sensor for the pitot tube, removing the wire that grounds the heating system of pitot tube #1, installing the supply current wire to the inverter, installing the return current wire from pitot tube #1 to the AC current sensor, and grounding the AC current sensor), according to Fokker Service Bulletin SBF100-30-025, Revision 1, dated March 14, 2001. Such modification terminates the repetitive operational tests required by paragraph (a) of this AD.

Alternative Methods of Compliance

(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, Transport Airplane Directorate, FAA. 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

(f) Special flight permits may be issued in accordance with §§ 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

(g) The actions shall be done in accordance with Fokker Service Bulletin SBF100-30-025, Revision 1, dated March 14, 2001. 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.

Effective Date

(h) This amendment becomes effective on March 6, 2002.

Issued in Renton, Washington, on January 17, 2002.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.