Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes, 40948-40951 [E8-15711]

Download as PDF 40948 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations provide information regarding FSIS policies, procedures, regulations, Federal Register notices, FSIS public meetings, and other types of information that could affect or would be of interest to constituents and stakeholders. The Update is communicated via Listserv, a free electronic mail subscription service for industry, trade groups, consumer interest groups, health professionals, and other individuals who have asked to be included. The Update is also available on the FSIS Web page. Through the Listserv and Web page, FSIS is able to provide information to a much broader and more diverse audience. In addition, FSIS offers an email subscription service that provides automatic and customized access to selected food safety news and information. This service is available at http://www.fsis.usda.gov/ news_and_events/email_subscription/. Options range from recalls to export information to regulations, directives and notices. Customers can add or delete subscriptions themselves, and have the option to password protect their accounts. List of Subjects in 9 CFR Part 390 Public information. For the reasons discussed in the preamble, FSIS is amending 9 CFR Chapter III, Subchapter D, as follows: I PART 390—FREEDOM OF INFORMATION AND PUBLIC INFORMATION 1. The authority citation for part 390 is revised to read as follows: I Authority: 5 U.S.C. 301, 552; 21 U.S.C. 451–471, 601–695; 7 CFR 1.3, 2.7. 2. A new § 390.10 is added to read as follows: I § 390.10 Availability of Lists of Retail Consignees during Meat or Poultry Product Recalls. rwilkins on PROD1PC63 with RULES The Administrator of the Food Safety and Inspection Service will make publicly available the names and locations of retail consignees of recalled meat or poultry products that the Agency compiles in connection with a recall where there is a reasonable probability that the use of the product could cause serious adverse health consequences or death. Done in Washington, DC, July 11, 2008. Alfred V. Almanza, Administrator. [FR Doc. E8–16221 Filed 7–16–08; 8:45 am] BILLING CODE 3410–DM–P VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0639; Directorate Identifier 2007–NM–003–AD; Amendment 39–15564; AD 2008–13–01] RIN 2120–AA64 Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: 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 scheduled X-ray inspections of Fokker 50 (F27 Mark 050) engine mounting frames, welding defects were discovered. In two forward frames and one aft frame, defects were found in a total of 4 weld locations. Investigation showed that during manufacture of the frames, when the tubes were welded to the end fittings, unintentional sideways movement of the electric arc resulted in some welds running beside the borderline for a part of the tube circumference. Where a weld runs beside the borderline, there is no connection between tube and end fitting for that part of the circumference, directly affecting the structural integrity of the engine mounting frame connections. The defective welding process appears to have happened at some of the welds in an unknown number of engine mounting frames. This condition, if not corrected, could lead to failure of the engine mounting frame in cases where multiple welds are severely affected, potentially resulting in in-flight loss of an engine. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective August 1, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 1, 2008. We must receive comments on this AD by August 18, 2008. 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. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 • 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 Rodriguez, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The Civil Aviation Authority—The Netherlands (CAA-NL), which is the aviation authority for the Netherlands, has issued Dutch Airworthiness Directive NL–2005–015, dated November 30, 2005 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During scheduled X-ray inspections of Fokker 50 (F27 Mark 050) engine mounting frames, welding defects were discovered. In two forward frames and one aft frame, defects were found in a total of 4 weld locations. Investigation showed that during manufacture of the frames, when the tubes were welded to the end fittings, unintentional sideways movement of the electric arc resulted in some welds running beside the borderline for a part of the tube circumference. Where a weld runs beside the borderline, there is no connection between tube and end fitting for that part of the circumference, directly affecting the structural integrity of the engine mounting frame connections. The defective welding process appears to have happened at some of the welds in an unknown number of engine mounting frames. This condition, if not corrected, could lead to failure of the engine mounting frame in cases where multiple welds are severely affected, potentially resulting in in-flight loss of an engine. Since E:\FR\FM\17JYR1.SGM 17JYR1 40949 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations an unsafe condition had been identified that may exist on aircraft of the same type design, Airworthiness Directive NL–2005–007 was issued to require * * * a one-time inspection for improper welds. The present AD further specifies the criteria and compliance times for the follow-up NDT (non-destructive test) inspection and repair or replacement of engine mounting frames, as necessary. Corrective action includes contacting Fokker for repair instructions and repair. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Fokker Services B.V. has issued the service information identified in the following table. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. SERVICE INFORMATION Fokker Service Bulletin Date Component Service Bulletin F8200–035–71–10 ..................................................................................................................... Component Service Bulletin F8200–035–71–11 ..................................................................................................................... Service Bulletin SBF50–71–048 .............................................................................................................................................. Service Bulletin SBF50–71–049 .............................................................................................................................................. 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. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future. Differences Between the AD and the MCAI or Service Information rwilkins on PROD1PC63 with RULES 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 Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary. VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 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–2007–0639; Directorate Identifier 2007–NM–003– 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, 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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 May 30, 2005. October 25, 2005. May 30, 2005. October 25, 2005. 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I E:\FR\FM\17JYR1.SGM 17JYR1 40950 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations 2008–13–01 Fokker Services B.V.: Amendment 39–15564. Docket No. FAA–2008–0639; Directorate Identifier 2007–NM–003–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 1, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Fokker Model F27 Mark 050 airplanes, certificated in any category, all serial numbers. Subject (d) Air Transport Association (ATA) of America Code 71: Powerplant. rwilkins on PROD1PC63 with RULES Reason (e) The mandatory continued airworthiness information (MCAI) states: During scheduled X-ray inspections of Fokker 50 (F27 Mark 050) engine mounting frames, welding defects were discovered. In two forward frames and one aft frame, defects were found in a total of 4 weld locations. Investigation showed that during manufacture of the frames, when the tubes were welded to the end fittings, unintentional sideways movement of the electric arc resulted in some welds running beside the borderline for a part of the tube circumference. Where a weld runs beside the borderline, there is no connection between tube and end fitting for that part of the circumference, directly affecting the structural integrity of the engine mounting frame connections. The defective welding process appears to have happened at some of the welds in an unknown number of engine mounting frames. This condition, if not corrected, could lead to failure of the engine mounting frame in cases where multiple welds are severely affected, potentially resulting in in-flight loss of an engine. Since an unsafe condition had been identified that may exist on aircraft of the same type design, Airworthiness Directive NL–2005–007 was issued to require * * * a one-time inspection for improper welds. The [MCAI supersedes Airworthiness Directive NL–2005–007 and] further specifies the criteria and compliance times for the follow-up NDT (non-destructive test) inspection and repair or replacement of engine mounting frames, as necessary. Corrective action includes contacting Fokker for repair instructions and repair. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 2 months after the effective date of this AD, inspect the engine mounting frames to identify those that have any sideways deviations in the welds, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–048, dated May 30, 2005. When deviations are found that are less than or equal to 2.0 mm, no further action is required on that frame and the aircraft may be returned to service. (2) When, during the inspection required by paragraph (f)(1) of this AD, deviations are VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 found that are greater than 2.0 mm but less than or equal to 2.5 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 12 months after the effective date of this AD, NDT (non-destructive test) inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (3) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 2.5 mm but less than or equal to 3.0 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 9 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (4) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 3.0 mm but less than or equal to 3.5 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 6 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (5) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 3.5 mm but less than or equal to 5.0 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 3 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (6) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 2.0 mm but less than or equal to 5.0 mm on tubes 7, 8, and 12 of the rear frame: Within 3 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (7) Within 7 days after doing any NDTinspection required by this AD, or within 30 days after the effective date of this AD, whichever occurs later, report all findings to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. (8) Within 30 days after reporting in accordance with paragraph (f)(7) of this AD, or within 30 days after the effective date of this AD, whichever occurs later, repair any frame deviation in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or by the European Aviation Safety Agency (EASA) (or its designated agent). (9) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found exceeding 5 mm, before further flight, PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 report the inspection findings to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, and repair any such deviation in accordance with a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA, or by EASA (or its designated agent). (10) Except as provided by paragraphs (f)(10)(i), (f)(10)(ii), (f)(10)(iii), (f)(10)(iv), and (f)(10)(v) of this AD, as of the effective date of this AD, no person may install an engine mounting frame having part number F8200– 035–427/–441/–451/–463 (forward frames); F8200–035–425/–443 (A-frames); or F8200– 035–403/–439/–449/–461 (rear frames), as a replacement part, unless it has been inspected and found to have deviations less than or equal to 2.0 mm, in accordance with the requirements of Fokker Component Service Bulletin F8200–035–71–10, dated May 30, 2005. (i) Any frame inspected in accordance with Fokker Component Service Bulletin F8200– 035–71–10, and found to have any deviation greater than 2.0 mm but less than or equal to 2.5 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 12 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (ii) Any frame inspected in accordance with Fokker Component Service Bulletin F8200–035–71–10, and found to have any deviation greater than 2.5 mm but less than or equal to 3.0 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 9 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (iii) Any frame inspected in accordance with Fokker Component Service Bulletin F8200–035–71–10, and found to have any deviation greater than 3.0 mm but less than or equal to 3.5 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 6 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (iv) Any frame inspected in accordance with Fokker Component Service Bulletin F8200–035–71–10, and found to have any deviation greater than 3.5 mm but less than or equal to 5.0 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 3 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. (v) Any tube 7, 8, or 12 of the rear frame, inspected in accordance with Fokker E:\FR\FM\17JYR1.SGM 17JYR1 40951 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations Component Service Bulletin F8200–035–71– 10, and found to have any deviation greater than 2.0 mm but less than or equal to 5.0 mm, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 3 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50–71–049, dated October 25, 2005. FAA AD Differences Note: 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, 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 (425) 227–1137; fax (425) 227–1149. 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 Mandatory Continuing Airworthiness Information (MCAI) Dutch Airworthiness Directive NL–2005–015, dated November 30, 2005, and the service bulletins identified in Table 1 of this AD for related information. TABLE 1.—SERVICE INFORMATION Fokker Service Bulletin Date Component Service Bulletin F8200–035–71–10 ..................................................................................................................... Component Service Bulletin F8200–035–71–11 ..................................................................................................................... Service Bulletin SBF50–71–048 .............................................................................................................................................. Service Bulletin SBF50–71–049 .............................................................................................................................................. Material Incorporated by Reference (i) You must use the service information specified in Table 2 of this AD to do the actions required by this AD, as applicable, 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 May 30, 2005. October 25, 2005. May 30, 2005. October 25, 2005. Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Date Fokker Component Service Bulletin F8200–035–71–10 ......................................................................................................... Fokker Service Bulletin SBF50–71–048 .................................................................................................................................. Fokker Service Bulletin SBF50–71–049 .................................................................................................................................. Issued in Renton, Washington, on June 26, 2008. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–15711 Filed 7–16–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0543 Directorate Identifier 2007–CE–092–AD; Amendment 39–15607; AD 2008–14–12] RIN 2120–AA64 Airworthiness Directives; Pacific Aerospace Limited Model FU–24 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rwilkins on PROD1PC63 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 May 30, 2005. May 30, 2005. October 25, 2005. airworthiness information (MCAI) issued 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: To prevent the possible in-flight failure of the vertical fin, leading to loss of control of the aircraft * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 21, 2008. On August 21, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at Document Management Facility, U.S. E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 73, Number 138 (Thursday, July 17, 2008)]
[Rules and Regulations]
[Pages 40948-40951]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15711]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0639; Directorate Identifier 2007-NM-003-AD; 
Amendment 39-15564; AD 2008-13-01]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 050 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 scheduled X-ray inspections of Fokker 50 (F27 Mark 050) 
engine mounting frames, welding defects were discovered. In two 
forward frames and one aft frame, defects were found in a total of 4 
weld locations. Investigation showed that during manufacture of the 
frames, when the tubes were welded to the end fittings, 
unintentional sideways movement of the electric arc resulted in some 
welds running beside the borderline for a part of the tube 
circumference. Where a weld runs beside the borderline, there is no 
connection between tube and end fitting for that part of the 
circumference, directly affecting the structural integrity of the 
engine mounting frame connections. The defective welding process 
appears to have happened at some of the welds in an unknown number 
of engine mounting frames. This condition, if not corrected, could 
lead to failure of the engine mounting frame in cases where multiple 
welds are severely affected, potentially resulting in in-flight loss 
of an engine. * * *

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

DATES: This AD becomes effective August 1, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 1, 
2008.
    We must receive comments on this AD by August 18, 2008.

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

SUPPLEMENTARY INFORMATION:

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is 
the aviation authority for the Netherlands, has issued Dutch 
Airworthiness Directive NL-2005-015, dated November 30, 2005 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During scheduled X-ray inspections of Fokker 50 (F27 Mark 050) 
engine mounting frames, welding defects were discovered. In two 
forward frames and one aft frame, defects were found in a total of 4 
weld locations. Investigation showed that during manufacture of the 
frames, when the tubes were welded to the end fittings, 
unintentional sideways movement of the electric arc resulted in some 
welds running beside the borderline for a part of the tube 
circumference. Where a weld runs beside the borderline, there is no 
connection between tube and end fitting for that part of the 
circumference, directly affecting the structural integrity of the 
engine mounting frame connections. The defective welding process 
appears to have happened at some of the welds in an unknown number 
of engine mounting frames. This condition, if not corrected, could 
lead to failure of the engine mounting frame in cases where multiple 
welds are severely affected, potentially resulting in in-flight loss 
of an engine. Since

[[Page 40949]]

an unsafe condition had been identified that may exist on aircraft 
of the same type design, Airworthiness Directive NL-2005-007 was 
issued to require * * * a one-time inspection for improper welds. 
The present AD further specifies the criteria and compliance times 
for the follow-up NDT (non-destructive test) inspection and repair 
or replacement of engine mounting frames, as necessary.

Corrective action includes contacting Fokker for repair instructions 
and repair. You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    Fokker Services B.V. has issued the service information identified 
in the following table. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

                           Service Information
------------------------------------------------------------------------
       Fokker Service Bulletin                       Date
------------------------------------------------------------------------
Component Service Bulletin F8200-035- May 30, 2005.
 71-10.
Component Service Bulletin F8200-035- October 25, 2005.
 71-11.
Service Bulletin SBF50-71-048.......  May 30, 2005.
Service Bulletin SBF50-71-049.......  October 25, 2005.
------------------------------------------------------------------------

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.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these products are 
placed on the U.S. Register in the future.

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

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

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-2007-0639; Directorate 
Identifier 2007-NM-003-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, 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:


[[Page 40950]]


2008-13-01 Fokker Services B.V.: Amendment 39-15564. Docket No. FAA-
2008-0639; Directorate Identifier 2007-NM-003-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Model F27 Mark 050 airplanes, 
certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 71: 
Powerplant.

Reason

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

    During scheduled X-ray inspections of Fokker 50 (F27 Mark 050) 
engine mounting frames, welding defects were discovered. In two 
forward frames and one aft frame, defects were found in a total of 4 
weld locations. Investigation showed that during manufacture of the 
frames, when the tubes were welded to the end fittings, 
unintentional sideways movement of the electric arc resulted in some 
welds running beside the borderline for a part of the tube 
circumference. Where a weld runs beside the borderline, there is no 
connection between tube and end fitting for that part of the 
circumference, directly affecting the structural integrity of the 
engine mounting frame connections. The defective welding process 
appears to have happened at some of the welds in an unknown number 
of engine mounting frames. This condition, if not corrected, could 
lead to failure of the engine mounting frame in cases where multiple 
welds are severely affected, potentially resulting in in-flight loss 
of an engine. Since an unsafe condition had been identified that may 
exist on aircraft of the same type design, Airworthiness Directive 
NL-2005-007 was issued to require * * * a one-time inspection for 
improper welds. The [MCAI supersedes Airworthiness Directive NL-
2005-007 and] further specifies the criteria and compliance times 
for the follow-up NDT (non-destructive test) inspection and repair 
or replacement of engine mounting frames, as necessary.

Corrective action includes contacting Fokker for repair instructions 
and repair.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 2 months after the effective date of this AD, inspect 
the engine mounting frames to identify those that have any sideways 
deviations in the welds, in accordance with Part 3 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF50-71-048, 
dated May 30, 2005. When deviations are found that are less than or 
equal to 2.0 mm, no further action is required on that frame and the 
aircraft may be returned to service.
    (2) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found that are greater than 2.0 mm but less 
than or equal to 2.5 mm on any of the welds of the engine mounting 
frame, except those of tubes 7, 8, and 12 of the rear frame: Within 
12 months after the effective date of this AD, NDT (non-destructive 
test) inspect the affected frame tubes in accordance with Part 3 of 
the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-
049, dated October 25, 2005.
    (3) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found that are greater than 2.5 mm but less 
than or equal to 3.0 mm on any of the welds of the engine mounting 
frame, except those of tubes 7, 8, and 12 of the rear frame: Within 
9 months after the effective date of this AD, NDT-inspect the 
affected frame tubes in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (4) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found that are greater than 3.0 mm but less 
than or equal to 3.5 mm on any of the welds of the engine mounting 
frame, except those of tubes 7, 8, and 12 of the rear frame: Within 
6 months after the effective date of this AD, NDT-inspect the 
affected frame tubes in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (5) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found that are greater than 3.5 mm but less 
than or equal to 5.0 mm on any of the welds of the engine mounting 
frame, except those of tubes 7, 8, and 12 of the rear frame: Within 
3 months after the effective date of this AD, NDT-inspect the 
affected frame tubes in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (6) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found that are greater than 2.0 mm but less 
than or equal to 5.0 mm on tubes 7, 8, and 12 of the rear frame: 
Within 3 months after the effective date of this AD, NDT-inspect the 
affected frame tubes in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (7) Within 7 days after doing any NDT-inspection required by 
this AD, or within 30 days after the effective date of this AD, 
whichever occurs later, report all findings to Fokker Services B.V., 
Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the 
Netherlands.
    (8) Within 30 days after reporting in accordance with paragraph 
(f)(7) of this AD, or within 30 days after the effective date of 
this AD, whichever occurs later, repair any frame deviation in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or by the 
European Aviation Safety Agency (EASA) (or its designated agent).
    (9) When, during the inspection required by paragraph (f)(1) of 
this AD, deviations are found exceeding 5 mm, before further flight, 
report the inspection findings to Fokker Services B.V., Technical 
Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, 
and repair any such deviation in accordance with a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or by EASA (or its designated agent).
    (10) Except as provided by paragraphs (f)(10)(i), (f)(10)(ii), 
(f)(10)(iii), (f)(10)(iv), and (f)(10)(v) of this AD, as of the 
effective date of this AD, no person may install an engine mounting 
frame having part number F8200-035-427/-441/-451/-463 (forward 
frames); F8200-035-425/-443 (A-frames); or F8200-035-403/-439/-449/-
461 (rear frames), as a replacement part, unless it has been 
inspected and found to have deviations less than or equal to 2.0 mm, 
in accordance with the requirements of Fokker Component Service 
Bulletin F8200-035-71-10, dated May 30, 2005.
    (i) Any frame inspected in accordance with Fokker Component 
Service Bulletin F8200-035-71-10, and found to have any deviation 
greater than 2.0 mm but less than or equal to 2.5 mm on any tube, 
except tubes 7, 8, and 12 of the rear frame, is acceptable for 
installation. However, if a frame is installed in accordance with 
this paragraph, it must be NDT-inspected within 12 months after the 
installation, in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (ii) Any frame inspected in accordance with Fokker Component 
Service Bulletin F8200-035-71-10, and found to have any deviation 
greater than 2.5 mm but less than or equal to 3.0 mm on any tube, 
except tubes 7, 8, and 12 of the rear frame, is acceptable for 
installation. However, if a frame is installed in accordance with 
this paragraph, it must be NDT-inspected within 9 months after the 
installation, in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (iii) Any frame inspected in accordance with Fokker Component 
Service Bulletin F8200-035-71-10, and found to have any deviation 
greater than 3.0 mm but less than or equal to 3.5 mm on any tube, 
except tubes 7, 8, and 12 of the rear frame, is acceptable for 
installation. However, if a frame is installed in accordance with 
this paragraph, it must be NDT-inspected within 6 months after the 
installation, in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (iv) Any frame inspected in accordance with Fokker Component 
Service Bulletin F8200-035-71-10, and found to have any deviation 
greater than 3.5 mm but less than or equal to 5.0 mm on any tube, 
except tubes 7, 8, and 12 of the rear frame, is acceptable for 
installation. However, if a frame is installed in accordance with 
this paragraph, it must be NDT-inspected within 3 months after the 
installation, in accordance with Part 3 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-71-049, dated October 
25, 2005.
    (v) Any tube 7, 8, or 12 of the rear frame, inspected in 
accordance with Fokker

[[Page 40951]]

Component Service Bulletin F8200-035-71-10, and found to have any 
deviation greater than 2.0 mm but less than or equal to 5.0 mm, is 
acceptable for installation. However, if a frame is installed in 
accordance with this paragraph, it must be NDT-inspected within 3 
months after the installation, in accordance with Part 3 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, 
dated October 25, 2005.

FAA AD Differences

    Note: 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, 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 
(425) 227-1137; fax (425) 227-1149. 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 Mandatory Continuing Airworthiness Information 
(MCAI) Dutch Airworthiness Directive NL-2005-015, dated November 30, 
2005, and the service bulletins identified in Table 1 of this AD for 
related information.

                      Table 1.--Service Information
------------------------------------------------------------------------
       Fokker Service Bulletin                       Date
------------------------------------------------------------------------
Component Service Bulletin F8200-035- May 30, 2005.
 71-10.
Component Service Bulletin F8200-035- October 25, 2005.
 71-11.
Service Bulletin SBF50-71-048.......  May 30, 2005.
Service Bulletin SBF50-71-049.......  October 25, 2005.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information specified in Table 2 of 
this AD to do the actions required by this AD, as applicable, 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 (202) 741-6030, 
or go to: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.

              Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
          Service Bulletin                           Date
------------------------------------------------------------------------
Fokker Component Service Bulletin     May 30, 2005.
 F8200-035-71-10.
Fokker Service Bulletin SBF50-71-048  May 30, 2005.
Fokker Service Bulletin SBF50-71-049  October 25, 2005.
------------------------------------------------------------------------


    Issued in Renton, Washington, on June 26, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-15711 Filed 7-16-08; 8:45 am]
BILLING CODE 4910-13-P