Discussion
On December 28, 1999, we issued AD 99-27-13, amendment 39-11494 (65 FR 695, January 6, 2000), for all Fokker Model F27 Mark 050 series airplanes. That AD requires using a torque wrench to repetitively tighten the screws for the attachment of the leading edges of the elevators, rudder, and ailerons. That AD resulted from an issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We issued that AD to prevent loose attachment screws on the leading edges of the elevators, rudder, and ailerons due to vibration, which could result in interference with adjacent structure and consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 99-27-13, the Civil Aviation Authority--The Netherlands (CAA-NL), which is the airworthiness authority for the Netherlands, notified us that an additional further unsafe condition may exist on all Fokker Model F27Mark 050 airplanes. The CAA-NL advises that an operator reported in-flight vibration, which was caused by one loose elevator leading edge section. The airplane was found to have been inspected only seven months before the incident, which was within the original 12-month inspection interval of the existing AD. Further investigation by the manufacturer showed that the self-locking properties of the attachment screws gradually decrease when tightened repeatedly as required by the procedures in the existing AD. This condition, if not corrected, could result in binding of the flight controls caused by loose attachment screws, which could cause reduced controllability of the airplane.
Relevant Service Information
Fokker Services B.V. has issued bulletins in the following table.
Fokker Services Bulletin
Describes procedures for
SBF50 55 007, Revision 2, dated June 17, 2002.
Tightening the attachment screws of the elevators leading edges.
SBF50 55 008, Revision 3, dated June 17, 2002.
Modifying the elevator attachments by installing additional locking devices for the elevators leading edges.
SBF50 55 009, Revision 2, dated June 17, 2002.
Tightening the attachment screws for the rudder s leading edge.
SBF50 55 010, Revision 2, dated June 17, 2002.
Modifying the rudder attachments by installing additional locking devices for the rudder s leading edge.
SBF50 57 020, Revision 2, dated June 17, 2002.
Tightening the attachment screws for the ailerons leading edges.
SBF50 57 021, Revision 2, dated June 17, 2002.
Modifying the aileron attachments by installing additional locking devices for the ailerons leading edges.
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 2000-131/2, dated July 31, 2002, to ensure the continued airworthiness of these airplanes in the Netherlands.
Fokker Service Bulletin SBF50-55-010, Revision 2, refers to Fokker Service Bulletin SBF50-55-011, dated October 29, 2001, as an additional source of service information for modifying the rudder attachments.
Fokker Service Bulletin SBF50-57-021, Revision 2, refers to Fokker Service Bulletin SBF50-57-025, dated October 29, 2001, as an additional source of service information for modifying the aileron attachments.
FAA's Determination and Requirements of this AD
This airplane model is manufactured in the Netherlands and is 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 issuean AD for products of this type design that are certificated for operation in the United States.
Therefore, we are issuing this AD to prevent binding of the flight controls caused by loose attachment screws, which could result in reduced controllability of the airplane. This AD requires accomplishing the actions specified in the service information described previously.
This AD supersedes AD 99-27-13. This AD continues to require the same actions as the existing AD, but at reduced repetitive intervals. This AD also requires a new modification for the elevators, rudder, and aileron attachments, which terminates the repetitive inspection requirements of this AD. This AD requires accomplishing the actions specified in the service bulletins described previously.
Change To Existing AD
This AD will retain all requirements of AD 99-27-13. Since AD 99- 27-13 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this AD, as listed in the following table:
Revised Paragraph Identifiers
Requirement in AD 99 27 13
Corresponding requirement in this proposed AD
paragraph (a)
paragraph (f).
paragraph (b)
paragraph (g).
paragraph (c)
paragraph (h).
Explanation of Change to Applicability
We have revised the applicability of the proposed AD to identify model designations as published in the most recent type certificate data sheet for the affected models.
Costs of Compliance
None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future.
The following table provides the estimated costs to comply with this AD for any affected airplane that might be imported and placed on the U.S. Register in the future.
Estimated Costs
Action
Work hours
Average labor rate per hour
Parts cost
Cost per airplane
Tightening (required by AD 99 27 13)
12
$65
None
$780, per inspection cycle
Modification (new action)
37
65
$1,025 to 3,372
$3,430 to 5,777
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Sendyour comments to an address listed in the ADDRESSES section. Include "Docket No. FAA-2005- 23214; Directorate Identifier 2001-NM-338-AD" at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it.
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 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 DocketYou 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.
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 safeflight 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 AD will not have federalism implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 39-11494 (65 FR 695, January 6, 2000) and by adding the following new airworthiness directive (AD):