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Proposed Rule

Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This proposed AD would require a detailed inspection for wear of the attachment holes of the control levers of the braking system and applicable corrective actions. This proposed AD results from a report that, after landing, the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action. We are proposing this AD to prevent failure of one or more brake control levers, which could result in uncommanded braking and loss of control of the airplane during takeoff, landing, or taxiing.

DATES:

We must receive comments on this proposed AD by April 11, 2007.

ADDRESSES:

Use one of the following addresses to submit comments on this proposed AD.

  • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
  • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
  • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, Washington, DC 20590.
  • Fax: (202) 493-2251.
  • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, for service information identified in this proposed AD.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number “FAA-2007-27509; Directorate Identifier 2006-NM-201-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.

We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them.

Discussion

The Civil Aviation Authority—The Netherlands (CAA-NL), which is the airworthiness authority for the Netherlands, notified us that an unsafe Start Printed Page 10952condition may exist on all Fokker Model F.28 Mark 0070 and 0100 airplanes. The CAA-NL advises of a report that, after landing, the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action; concurrently, the temperature of the left-hand braking system was noted to be considerably higher than the right-hand braking system. Investigation revealed that the attachment holes of the control levers of the braking system were worn to the point of imminent failure. The airplane and affected levers had accumulated 15,583 total flight cycles and 21,460 total flight hours. This condition, if not corrected, could lead to failure of one or more brake levers, which could result in uncommanded braking and loss of control of the airplane during take-off, landing, or taxiing.

Relevant Service Information

Fokker Services B.V. has issued Fokker Service Bulletin SBF100-32-142, dated August 12, 2005. The service bulletin describes procedures for inspecting for wear of the attachment holes of the control levers of the braking system and applicable corrective actions. Corrective actions include replacing the control levers with new control levers at times determined by the level of wear found during the inspection. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The CAA-NL mandated the service information and issued Dutch airworthiness directive NL-2005-011, dated August 31, 2005, to ensure the continued airworthiness of these airplanes in the Netherlands.

FAA's Determination and Requirements of the Proposed AD

These airplane models are manufactured in the Netherlands and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA-NL has kept the FAA informed of the situation described above. We have examined the CAA-NL's findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes of this type design that are certificated for operation in the United States.

Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under “Differences Among the Proposed AD, the Dutch Airworthiness Directive, and the Service Information.”

Differences Among the Proposed AD, the Dutch Airworthiness Directive, and the Service Information

The Fokker service bulletin and the Dutch airworthiness directive describe a one-time inspection for wear of the attachment holes of the control levers. However, we have determined that confusion might occur regarding the inspection of any replacement control levers. Therefore, this proposed AD would require inspecting any replacement control lever for wear of the attachment holes, at an interval not to exceed 12,000 flight hours after the installation of any such lever, and applicable corrective actions thereafter, as described by the service information.

The service bulletin refers to a “detailed visual inspection” for wear of the attachment holes of the control levers. We have determined that the procedures in the service bulletin should be described as a “detailed inspection.” We have included a definition of this type of inspection in Note 1 of this proposed AD.

Where the service bulletin specifies immediate replacement of the control lever if the applicable remaining material (dimension X2) of the attachment hole is less than 2.0 millimeters (0.08 inches), this proposed AD would direct operators to replace the control lever if dimension X2 is less than or equal to 2.0 millimeters.

These differences have been coordinated with the CAA-NL.

Costs of Compliance

This proposed AD would affect about 9 airplanes of U.S. registry. The proposed inspection would take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $720, or $80 per airplane, per inspection cycle.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.

For the reasons discussed above, I certify that the proposed regulation:

1. Is not a “significant regulatory action” under Executive Order 12866;

2. Is not a “significant rule” under the 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.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]

2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD):

Fokker Services B.V.: Docket No. FAA-2007-27509; Directorate Identifier 2006-NM-201-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by April 11, 2007. Start Printed Page 10953

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category.

Unsafe Condition

(d) This AD results from a report that, after landing, the flight crew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action. We are issuing this AD to prevent failure of one or more brake control levers, which could result in uncommanded braking and loss of control of the airplane during takeoff, landing, or taxiing.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Inspection and Replacement

(f) Within 1,500 flight cycles or 12 months after the effective date of this AD, whichever occurs first: Perform a detailed inspection for excessive wear of the brake control levers and do the applicable corrective actions in accordance with and at the times specified in Section 3, “Accomplishment Instructions,” of Fokker Service Bulletin SBF100-32-142, dated August 12, 2005. Repeat the requirements of this paragraph thereafter for any replacement control lever at an interval not to exceed 12,000 flight hours after the installation of such a control lever. Operators should note that, where the service bulletin specifies immediate replacement of the control lever if the applicable remaining material (dimension X2) of the attachment hole is less than 2.0 millimeters (0.08 inches), this AD requires replacing the control lever if dimension X2 is less than or equal to 2.0 millimeters.

Note 1:

For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”

Alternative Methods of Compliance (AMOCs)

(g)(1) The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

Related Information

(h) Dutch airworthiness directive NL-2005-011, dated August 31, 2005, also addresses the subject of this AD.

Start Signature

Issued in Renton, Washington, on March 5, 2007.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Part End Supplemental Information

[FR Doc. E7-4379 Filed 3-9-07; 8:45 am]

BILLING CODE 4910-13-P