Airworthiness Directives: 328 Support Services GmbH Dornier Model 328-100 and -300 Airplanes

Federal Register: May 8, 2009 (Volume 74, Number 88)

Rules and Regulations

Page 21544-21547

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

DOCID:fr08my09-2

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 14 CFR Part 39

Docket No. FAA-2009-0419; Directorate Identifier 2009-NM-050-AD;

Amendment 39-15898; AD 2009-10-03

RIN 2120-AA64

Airworthiness Directives; 328 Support Services GmbH Dornier Model 328-100 and -300 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of

Transportation (DOT).

ACTION: Final rule; request for comments.

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:

During a recent Aileron Dual Load Path and Linkage Inspection, which is a certification maintenance requirement (CMR) task, the installed control rods were found to be corroded. The affected rod assemblies

Page 21545

were removed for investigation and it was found that the Tab Side

Fitting was cracked.

Subsequently, similar cracks were found on another aeroplane in a supporting lever of the Control Rod attachment fitting of the Trim

Tab. Those cracks were found during the applicable CMR inspection.

This condition, if not corrected, could lead to structural failure of the dual load path attachment arrangement of the affected trim and spring tabs, possibly resulting in a flutter problem that could lead to loss of control of the aeroplane.

* * * * *

This AD requires actions that are intended to address the unsafe condition described in the MCAI.

DATES: This AD becomes effective May 26, 2009.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 26, 2009.

We must receive comments on this AD by June 8, 2009.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Portal: Go to http:// www.regulations.gov. Follow the instructions for submitting comments.

Fax: (202) 493-2251.

Mail: U.S. Department of Transportation, Docket

Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New

Jersey Avenue, SE., Washington, DC 20590.

Hand Delivery: U.S. Department of Transportation, Docket

Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New

Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the

ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Groves, Aerospace Engineer,

International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1503; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

The European Aviation Safety Agency (EASA), which is the Technical

Agent for the Member States of the European Community, has issued EASA

Airworthiness Directive 2009-0044, dated February 27, 2009 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

During a recent Aileron Dual Load Path and Linkage Inspection, which is a certification maintenance requirement (CMR) task, the installed control rods were found to be corroded. The affected rod assemblies were removed for investigation and it was found that the

Tab Side Fitting was cracked.

Subsequently, similar cracks were found on another aeroplane in a supporting lever of the Control Rod attachment fitting of the Trim

Tab. Those cracks were found during the applicable CMR inspection.

This condition, if not corrected, could lead to structural failure of the dual load path attachment arrangement of the affected trim and spring tabs, possibly resulting in a flutter problem that could lead to loss of control of the aeroplane.

For the reasons described above, this [EASA] AD requires a one- time inspection of all flight controls trim and spring tab assemblies and their surrounding area, the replacement of any parts that are found to be cracked and the reporting of all findings to the TC [type certificate] holder. This AD is considered to be an interim action and the current [CMR] inspection interval for the affected parts may be reduced.

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

Relevant Service Information 328 Support Services has issued Service Bulletins SB-328-27-483 and

SB-328J-27-233, both including Compliance Report, both dated December 30, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between the 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 FAA policies. Any such differences are highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because structural failure of the control rod attachment fittings could lead to control surface flutter, and consequent loss of control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0419; Directorate

Identifier 2009-NM-050-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.

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,

Page 21546

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.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment 0

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

PART 39--AIRWORTHINESS DIRECTIVES 0 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] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2009-10-03 328 Support Services GmbH (Formerly, AvCraft Aerospace

GmbH, formerly Fairchild Dornier GmbH, formerly Dornier Luftfahrt

GmbH): Amendment 39-15898. Docket No. FAA-2009-0419; Directorate

Identifier 2009-NM-050-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective May 26, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to 328 Support Services GmbH Dornier Model 328-100 and -300 airplanes, certificated in any category, all serial numbers.

Subject

(d) Air Transport Association (ATA) of America Code 27: Flight controls.

Reason

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

During a recent Aileron Dual Load Path and Linkage Inspection, which is a certification maintenance requirement (CMR) task, the installed control rods were found to be corroded. The affected rod assemblies were removed for investigation and it was found that the

Tab Side Fitting was cracked.

Subsequently, similar cracks were found on another aeroplane in a supporting lever of the Control Rod attachment fitting of the Trim

Tab. Those cracks were found during the applicable CMR inspection.

This condition, if not corrected, could lead to structural failure of the dual load path attachment arrangement of the affected trim and spring tabs, possibly resulting in a flutter problem that could lead to loss of control of the aeroplane.

For the reasons described above, this [European Aviation Safety

Agency (EASA)] AD requires a one-time inspection of all flight controls trim- and spring tab assemblies and their surrounding area, the replacement of any parts that are found to be cracked and the reporting of all findings to the TC [type certificate] holder. This

AD is considered to be an interim action and the current [CMR] inspection interval for the affected parts may be reduced.

Actions and Compliance

(f) Unless already done, do the following actions.

(1) Within 3 months after the effective date of this AD: Do a detailed visual inspection of all flight controls trim and spring tab assemblies and their surrounding area, in accordance with the

Accomplishment Instructions of 328 Support Services Service Bulletin

SB-328-27-483 or 328 Support Services Service Bulletin SB-328J-27- 233, both dated December 30, 2008, as applicable.

(2) If any crack is detected during any inspection required by this AD: Before further flight, replace the cracked fitting with a new fitting in accordance with the Accomplishment Instructions of 328 Support Services Service Bulletin SB-328-27-483 or 328 Support

Services Service Bulletin SB-328J-27-233, both dated December 30, 2008, as applicable.

(3) At the applicable time specified in paragraph (f)(3)(i) or

(f)(3)(ii) of this AD: Using the Compliance Report attached to 328

Support Services SB-328-27-483 or 328 Support Services Service

Bulletin SB-328J-27-233, both dated December 30, 2008, as applicable, send 328 Support Services GmbH a report of findings

(both positive and negative) found during the inspection required by paragraph (f)(1) of this AD. The report must include the inspection results, a description of any cracks found, the airplane serial number, and the number of landings and flight hours on the airplane.

Send the report to: Attention: Dept. P1, 328 Support Services,

Customer Services, P.O. Box 1252, D-82231 Wessling, Federal Republic of Germany; telephone +49 8153 88111 6666; fax 49 8153 88111 6565; e-mail gsc.op@328support.de.

(i) For any inspection done on or after the effective date of this AD: Within 30 days after the inspection.

(ii) For any inspection done before the effective date of this

AD: Within 30 days after the effective date of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

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

Groves, Aerospace Engineer, International Branch, ANM-116, Transport

Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1503; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.

(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 EASA Airworthiness Directive 2009-0044, dated

February 27, 2009; and 328 Support Services Service Bulletins SB- 328-27-483 and SB-328J-27-233, both dated December 30, 2008; for related information.

Page 21547

Material Incorporated by Reference

(i) You must use 328 Support Services Service Bulletin SB-328- 27-483, dated December 30, 2008, including Compliance Report; or 328

Support Services Service Bulletin SB-328J-27-233, dated December 30, 2008, including Compliance Report; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (Only the odd-numbered pages of these documents contain the issue date of the documents.)

(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 328

Support Services GmbH, Global Support Center, P.O. Box 1252, D-82231

Wessling, Federal Republic of Germany; telephone +49 8153 88111 6666; fax +49 8153 88111 6565; e-mail gsc.op@328support.de; Internet http://www.328support.de.

(3) You may review copies of the service information at the FAA,

Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,

Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records

Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.

Issued in Renton, Washington, on April 29, 2009.

Stephen P. Boyd,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

FR Doc. E9-10655 Filed 5-7-09; 8:45 am

BILLING CODE 4910-13-P