E8-22065. Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes

AGENCY:

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

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Service experience has shown that heavy MLG (main landing gear) shimmy vibration can occur due to faulty/empty dampers or due to excessive free play in the T/L (torque link) apex joint. In several cases this shimmy vibration resulted in a MLG main fitting failure * * * finally resulting in a collapse of the MLG causing extensive damage to the wingtip, aileron and flaps. * * *

We are issuing this AD to require actions to correct the unsafe condition on these products.

DATES:

This AD becomes effective November 3, 2008.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 3, 2008.

ADDRESSES:

You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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 [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 2, 2008 (73 FR 37898). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Service experience has shown that heavy MLG (main landing gear) shimmy vibration can occur due to faulty/empty dampers or due to excessive free play in the T/L (torque link) apex joint. In several cases this shimmy vibration resulted in a MLG main fitting failure. In those cases where only the upper torque link attachment lug failed the damage to the aircraft was limited. In all other cases the MLG main fitting cracked, finally resulting in a collapse of the MLG causing extensive damage to the wingtip, aileron and flaps. To prevent the collapse of the MLG, Messier-Dowty has designed an upper torque link fuse pin with a static strength lower than the demonstrated strength of the MLG main fitting. In case of a heavy shimmy vibration the upper torque link fuse pin will fail before the main fitting. Therefore the installation of an upper torque link fuse pin will protect the LH and RH (left- and right-hand) MLG main fitting against extreme shimmy loads and thus against a MLG main fitting failure and a MLG collapse. Since an unsafe condition has been identified that may exist or develop on aircraft of the same type design this Airworthiness Directive requires the modification of the MLG by replacing the upper torque link pin with a new fuse pin.

You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.

Costs of Compliance

We estimate that this AD will affect about 2 products of U.S. registry. We also estimate that it will take about 15 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $0 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $2,400, or $1,200 per product.

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 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 this AD:

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.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone [phone]) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

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.

§ 39.13

[Amended]

2. The FAA amends § 39.13 by adding the following new AD:

2008-19-09 Fokker Services B.V.: Amendment 39-15676. Docket No. FAA-2008-0676; Directorate Identifier 2007-NM-280-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 3, 2008.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Fokker Model F.28 Mark 0070 and F.28 Mark 0100, serial numbers 11244 thru 11585, certificated in any category, equipped with Messier-Dowty main landing gears.

Subject

(d) Air Transport Association (ATA) of America Code 32: Landing Gear.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Service experience has shown that heavy MLG (main landing gear) shimmy vibration can occur due to faulty/empty dampers or due to excessive free play in the T/L (torque link) apex joint. In several cases this shimmy vibration resulted in a MLG main fitting failure. In those cases where only the upper torque link attachment lug failed the damage to the aircraft was limited. In all other cases the MLG main fitting cracked, finally resulting in a collapse of the MLG causing extensive damage to the wingtip, aileron and flaps. To prevent the collapse of the MLG, Messier-Dowty has designed an upper torque link fuse pin with a static strength lower than the demonstrated strength of the MLG main fitting. In case of a heavy shimmy vibration the upper torque link fuse pin will fail before the main fitting. Therefore the installation of an upper torque link fuse pin will protect the LH and RH (left- and right-hand) MLG main fitting against extreme shimmy loads and thus against a MLG main fitting failure and a MLG collapse. Since an unsafe condition has been identified that may exist or develop on aircraft of the same type design this Airworthiness Directive requires the modification of the MLG by replacing the upper torque link pin with a new fuse pin.

Actions and Compliance

(f) Unless already done: Within the applicable compliance time specified in paragraphs (f)(1) and (f)(2) of this AD, do the following actions.

(1) For Messier-Dowty MLG in a pre-mod Messier-Dowty Service Bulletin F100-32-050 configuration: Within 12 months after the effective date of this AD, replace the upper torque link pin with a new fuse pin in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-148, Revision 1, dated February 26, 2007.

(2) For Messier-Dowty MLG in a post-mod Messier-Dowty Service Bulletin F100-32-050 configuration: Within 30 months after the effective date of this AD, replace the upper torque link pin with a new fuse pin in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-148, Revision 1, dated February 26, 2007.

FAA AD Differences

Note:

This AD differs from the MCAI and/or service information as follows: The MCAI references the original version of the service bulletin or a later approved version. The original version of the service bulletin specifies to use an incorrect part number. This AD refers to Revision 1 of the service bulletin.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone [phone]; fax [phone]. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.

Related Information

(h) Refer to MCAI Dutch Airworthiness Directive NL-2007-001, dated February 26, 2007; and Fokker Service Bulletin SBF100-32-148, Revision 1, dated February 26, 2007; for related information.

Material Incorporated by Reference

(i) You must use Fokker Service Bulletin SBF100-32-148, Revision 1, dated February 26, 2007, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands.

(3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call [phone], or go to: http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.

Issued in Renton, Washington, on September 11, 2008.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.