Airworthiness Directives; Fokker Services B.V. Airplanes, 81018-81021 [2016-27529]

Download as PDF sradovich on DSK3GMQ082PROD with PROPOSALS 81018 Federal Register / Vol. 81, No. 222 / Thursday, November 17, 2016 / Proposed Rules This assurance is given in consideration of and for the purpose of obtaining any and all Federal assistance extended to the State by USDA under the authority of the Food and Nutrition Act of 2008, as amended. Federal financial assistance includes grants, and loans of Federal funds; reimbursable expenditures, grants, or donations of Federal property and interest in property; the detail of Federal personnel; the sale, lease of, or permission to use Federal property or interest in such property; the furnishing of services without consideration, or at a nominal consideration, or at a consideration that is reduced for the purpose of assisting the recipient or in recognition of the public interest to be served by such sale, lease, or furnishing of services to the recipient; or any improvements made with Federal financial assistance extended to the State by USDA. This assistance also includes any Federal agreement, arrangement, or other contract that has as one of its purposes the provision of cash assistance for the purchase of food, cash assistance for purchase or rental of food service equipment or any other financial assistance extended in reliance on the representations and agreements made in this assurance. By accepting this assurance, the State agency agrees to compile data, maintain records, and submit records and reports as required, to permit effective enforcement of nondiscrimination laws and permit authorized USDA personnel during hours of program operation to review and copy such records, books, and accounts, access such facilities and interview such personnel as needed to ascertain compliance with the nondiscrimination laws. If there are any violations of this assurance, USDA, FNS, shall have the right to seek judicial enforcement of this assurance. This assurance is binding on the State agency, its successors, transferees and assignees as long as it receives assistance or retains possession of any assistance from USDA. The person or persons whose signatures appear below are authorized to sign this assurance on behalf of the State agency. 3. (For States with Indian Reservations only). Implement the Program in a manner that is responsive to the special needs of American Indians on reservations and consult in good faith with tribal organizations about that portion of the State’s Plan of Operation pertaining to the implementation of the Program for members of the tribe on reservations. 4. FNS agrees to: 1. Pay administrative costs in accordance with the Food and Nutrition Act of 2008, implementing VerDate Sep<11>2014 17:46 Nov 16, 2016 Jkt 241001 regulations, and an approved Cost Allocation Plan. 2. Carry out any other responsibilities delegated by the Secretary in the Food and Nutrition Act of 2008, as amended. Date llllllllllllllll Signature llllllllllllll (Governor or Authorized Designee) Date llllllllllllllll Signature llllllllllllll (Regional Administrator, FNS) Dated: November 7, 2016. Audrey Rowe, Administrator, Food and Nutrition Service. [FR Doc. 2016–27604 Filed 11–16–16; 8:45 am] CODE 3410–30–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9389; Directorate Identifier 2014–NM–153–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new Airworthiness Directive (AD) for all Fokker Services B.V. Model F28 Mark 0100 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain wing fuel tank access panels are subject to widespread fatigue damage (WFD). This proposed AD would require replacement of affected access panels and modification of the coamings of the associated access holes. We are proposing this AD to prevent the unsafe condition on these products. DATES: We must receive comments on this proposed AD by January 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 SUMMARY: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone: +31 (0)88– 6280–350; fax: +31 (0)88–6280–111; email: technicalservices@fokker.com; Internet: http://www.myfokkerfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9389; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed 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, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1137; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–9389; Directorate Identifier 2014–NM–153–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 proposed AD. Discussion Fatigue damage can occur locally, in small areas or structural design details, E:\FR\FM\17NOP1.SGM 17NOP1 sradovich on DSK3GMQ082PROD with PROPOSALS Federal Register / Vol. 81, No. 222 / Thursday, November 17, 2016 / Proposed Rules or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information VerDate Sep<11>2014 17:46 Nov 16, 2016 Jkt 241001 development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0125, dated June 21, 2016, which supersedes EASA AD 2014–0158, dated July 7, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Fokker Services B.V. Model F28 Mark 0100 series airplanes. The MCAI states: Based on findings on test articles, fatigueinduced cracks may develop in the coamings of certain wing fuel tank access panels Part Number (P/N) D12395–403 and P/N D12450– 403, installed on Fokker F28 Mark 0100 aeroplanes. To ensure the continued structural integrity with respect to fatigue, repetitive inspections were included in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness. Fokker Services also developed precautionary measures to reduce stress loads in the affected areas by replacement of the affected access panels with new panels, P/N D19701–401 and P/N D19701–403, having thinner skin, and a modification by introducing internal patches to the coamings of the affected access holes. These precautionary measures were introduced with Service Bulletins (SB) SBF100–57–027 and SBF100–57–028. As part of the Widespread Fatigue Damage reevaluation, it was concluded that repetitive inspections through the ALS do not provide a sufficient level of protection against the fatigue-induced cracks. This condition, if not corrected, would affect the structural integrity of the lower wing skins of both outer wings in the areas surrounding the affected fuel tank access panels. For the reasons described above, this [EASA] AD requires replacement of the affected access panels and modification of the coamings of these access holes. Post-modification inspection requirements depend on the actual number of flight cycles accumulated at the moment of modification. Related detailed information is provided in SBF100–57–027 and SBF100–57–028, as well as in Fokker Services ALS Report SE–623 Issue 12. Fokker Services All Operators Message AOF100.178#05 provides additional information concerning the subject addressed by this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 81019 and locating Docket No. FAA–2016– 9389. Related Service Information Under 1 CFR Part 51 Fokker Services B.V. has issued the following service information: • Fokker Service Bulletin SBF 100– 57–027, Revision 2, dated December 11, 2013. This service information provides instructions to replace certain fuel tank access panels. • Fokker Service Bulletin SBF 100– 57–028, Revision 2, dated December, 11, 2013. This service information provides instructions to modify the coamings of certain fuel tank access holes. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed 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 proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information In the ‘‘Required Action(s) and Compliance Times’’ section of the MCAI, paragraphs (3) and (4) specify to incorporate or comply with certain maintenance tasks (repetitive inspections). These actions are not included in this proposed AD. Since EASA AD 2014–0158, dated July 7, 2014, was issued, EASA issued AD 2016–0125, dated June 21, 2016, which includes a requirement to incorporate those maintenance tasks. We are considering further rulemaking to require the actions specified in EASA AD 2016–0125, dated June 21, 2016. Costs of Compliance We estimate that this proposed AD affects 15 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\17NOP1.SGM 17NOP1 81020 Federal Register / Vol. 81, No. 222 / Thursday, November 17, 2016 / Proposed Rules ESTIMATED COSTS Action Labor cost Replacement and Modification ....................... 510 work-hours × $85 per hour = $43,350 per airplane. 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 sradovich on DSK3GMQ082PROD with PROPOSALS We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, VerDate Sep<11>2014 17:46 Nov 16, 2016 Jkt 241001 Parts cost the FAA proposes to amend 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 airworthiness directive (AD): ■ Fokker Services B.V.: Docket No. FAA– 2016–9389; Directorate Identifier 2014– NM–153–AD. (a) Comments Due Date We must receive comments by January 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Fokker Services B.V. Model F28 Mark 0100 series airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain wing fuel tank access panels are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking in the wing structure, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification and Replacement Within 63,000 flight cycles since first flight of the airplane, or within 90 days after the effective date of this AD, whichever occurs later, accomplish the actions specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable. (1) For airplanes identified in Fokker Service Bulletin SBF100–57–028, Revision 2, dated December 11, 2013: Modify the coamings of the fuel tank access holes at the access panel locations identified in, and in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–57–028, Revision 2, dated December 11, 2013. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 $45,500 Cost per product $88,350 Cost on U.S. operators $1,325,250 (2) For airplanes identified in Fokker Service Bulletin SBF100–57–027, Revision 2, dated December 11, 2013: Replace access panels having part number D12395–403 and D12450–403 with new panels having part number D19701–401 and D19701–403, at the access panel locations identified in, and in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–57–027, Revision 2, dated December 11, 2013. (h) Parts Installation Prohibition (1) For airplanes that, on the effective date of this AD, have an access panel with part number D12395–403 or D12450–403 installed at any of the affected locations: After accomplishing the actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, no person may install, on any airplane, access panels having part number D12395–403 or D12450–403 at any access panel location as identified in Fokker Service Bulletin SBF100–57–027, Revision 2, dated December 11, 2013. (2) For airplanes that, on the effective date of this AD, do not have an access panel with part number D12395–403 or D12450–403 installed at any of the affected locations: As of the effective date of this AD, no person may install, on any airplane, access panels having part number D12395–403 or D12450– 403 at any access panel location as identified in Fokker Service Bulletin SBF100–57–027, Revision 2, dated December 11, 2013. (i) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) Fokker Service Bulletin SBF100–57– 028, dated May 2, 1994. (ii) Fokker Service Bulletin SBF100–57– 028, Revision 1, dated November 1, 1994. (2) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) Fokker Service Bulletin SBF100–57– 027, dated September 13, 1993. (ii) Fokker Service Bulletin SBF100–57– 027, Revision 1, dated May 2, 1994. (j) Other FAA AD Provisions 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. E:\FR\FM\17NOP1.SGM 17NOP1 Federal Register / Vol. 81, No. 222 / Thursday, November 17, 2016 / Proposed Rules In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1137; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA); or Fokker Services B.V.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014–0158, dated July 7, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9389. (2) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone: +31 (0)88–6280–350; fax: +31 (0)88–6280–111; email: technicalservices@ fokker.com; Internet: http:// www.myfokkerfleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 7, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–27529 Filed 11–16–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration sradovich on DSK3GMQ082PROD with PROPOSALS 14 CFR Part 39 [Docket No. FAA–2016–9384; Directorate Identifier 2016–NM–154–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 17:46 Nov 16, 2016 Jkt 241001 Notice of proposed rulemaking (NPRM). ACTION: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–300ER series airplanes. This proposed AD was prompted by a report that certain galley tripod mount assemblies were not connected to the tie rods in the overhead support structure. This proposed AD would require an inspection of certain galleys for the presence of the hardware that connects the tripod mount assembly to the tie rods in the overhead support structure, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by January 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9384. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9384; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 81021 street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Brown, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6476; fax: 425– 917–6590; email: eric.m.brown@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–9384; Directorate Identifier 2016– NM–154–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. Discussion We have received a report that the T53 and T52 tie rods to the tripod mount assembly in the A2 and A3 galleys were found unattached during a routine production inspection of certain airplanes before delivery. The cause was determined to be a change to the galley installation sequence. This changed installation sequence did not include a robust method to make sure that the tie rods were attached to the galley before delivery. Since this unsafe condition was found, Boeing has implemented a new improved process to ensure that the hardware that attaches the T53 and T52 tie rods to the tripod mount assembly in the A2 and A3 galleys is attached. A galley tripod mount assembly that is unconnected to the tie rods in the overhead support structure can cause a galley to come loose under a high dynamic load causing a risk of serious injury to passengers and the blocking of evacuation routes. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 777–25A0677, dated April 25, E:\FR\FM\17NOP1.SGM 17NOP1

Agencies

[Federal Register Volume 81, Number 222 (Thursday, November 17, 2016)]
[Proposed Rules]
[Pages 81018-81021]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27529]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9389; Directorate Identifier 2014-NM-153-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new Airworthiness Directive (AD) for all 
Fokker Services B.V. Model F28 Mark 0100 series airplanes. This 
proposed AD was prompted by an evaluation by the design approval holder 
(DAH) indicating that certain wing fuel tank access panels are subject 
to widespread fatigue damage (WFD). This proposed AD would require 
replacement of affected access panels and modification of the coamings 
of the associated access holes. We are proposing this AD to prevent the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 3, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Fokker 
Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL 
Hoofddorp, the Netherlands; telephone: +31 (0)88-6280-350; fax: +31 
(0)88-6280-111; email: technicalservices@fokker.com; Internet: http://www.myfokkerfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9389; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed 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, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1137; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9389; 
Directorate Identifier 2014-NM-153-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 proposed AD.

Discussion

    Fatigue damage can occur locally, in small areas or structural 
design details,

[[Page 81019]]

or globally, in widespread areas. Multiple-site damage is widespread 
damage that occurs in a large structural element such as a single rivet 
line of a lap splice joining two large skin panels. Widespread damage 
can also occur in multiple elements such as adjacent frames or 
stringers. Multiple-site damage and multiple-element damage cracks are 
typically too small initially to be reliably detected with normal 
inspection methods. Without intervention, these cracks will grow, and 
eventually compromise the structural integrity of the airplane. This 
condition is known as widespread fatigue damage. It is associated with 
general degradation of large areas of structure with similar structural 
details and stress levels. As an airplane ages, WFD will likely occur, 
and will certainly occur if the airplane is operated long enough 
without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0125, dated June 21, 2016, which supersedes EASA AD 2014-0158, 
dated July 7, 2014 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Fokker Services B.V. Model F28 Mark 0100 series 
airplanes. The MCAI states:

    Based on findings on test articles, fatigue-induced cracks may 
develop in the coamings of certain wing fuel tank access panels Part 
Number (P/N) D12395-403 and P/N D12450-403, installed on Fokker F28 
Mark 0100 aeroplanes.
    To ensure the continued structural integrity with respect to 
fatigue, repetitive inspections were included in the Airworthiness 
Limitations Section (ALS) of the Instructions for Continued 
Airworthiness. Fokker Services also developed precautionary measures 
to reduce stress loads in the affected areas by replacement of the 
affected access panels with new panels, P/N D19701-401 and P/N 
D19701-403, having thinner skin, and a modification by introducing 
internal patches to the coamings of the affected access holes.
    These precautionary measures were introduced with Service 
Bulletins (SB) SBF100-57-027 and SBF100-57-028. As part of the 
Widespread Fatigue Damage re-evaluation, it was concluded that 
repetitive inspections through the ALS do not provide a sufficient 
level of protection against the fatigue-induced cracks.
    This condition, if not corrected, would affect the structural 
integrity of the lower wing skins of both outer wings in the areas 
surrounding the affected fuel tank access panels.
    For the reasons described above, this [EASA] AD requires 
replacement of the affected access panels and modification of the 
coamings of these access holes.
    Post-modification inspection requirements depend on the actual 
number of flight cycles accumulated at the moment of modification. 
Related detailed information is provided in SBF100-57-027 and 
SBF100-57-028, as well as in Fokker Services ALS Report SE-623 Issue 
12.
    Fokker Services All Operators Message AOF100.178#05 provides 
additional information concerning the subject addressed by this 
[EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9389.

Related Service Information Under 1 CFR Part 51

    Fokker Services B.V. has issued the following service information:
     Fokker Service Bulletin SBF 100-57-027, Revision 2, dated 
December 11, 2013. This service information provides instructions to 
replace certain fuel tank access panels.
     Fokker Service Bulletin SBF 100-57-028, Revision 2, dated 
December, 11, 2013. This service information provides instructions to 
modify the coamings of certain fuel tank access holes.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed 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 proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    In the ``Required Action(s) and Compliance Times'' section of the 
MCAI, paragraphs (3) and (4) specify to incorporate or comply with 
certain maintenance tasks (repetitive inspections). These actions are 
not included in this proposed AD. Since EASA AD 2014-0158, dated July 
7, 2014, was issued, EASA issued AD 2016-0125, dated June 21, 2016, 
which includes a requirement to incorporate those maintenance tasks. We 
are considering further rulemaking to require the actions specified in 
EASA AD 2016-0125, dated June 21, 2016.

Costs of Compliance

    We estimate that this proposed AD affects 15 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 81020]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement and Modification..........  510 work-hours x $85 per         $45,500         $88,350      $1,325,250
                                         hour = $43,350 per
                                         airplane.
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 airworthiness 
directive (AD):

Fokker Services B.V.: Docket No. FAA-2016-9389; Directorate 
Identifier 2014-NM-153-AD.

(a) Comments Due Date

    We must receive comments by January 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Fokker Services B.V. Model F28 Mark 0100 
series airplanes, certificated in any category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that certain wing fuel tank access panels 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to prevent fatigue cracking in the wing structure, which could 
result in reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification and Replacement

    Within 63,000 flight cycles since first flight of the airplane, 
or within 90 days after the effective date of this AD, whichever 
occurs later, accomplish the actions specified in paragraphs (g)(1) 
and (g)(2) of this AD, as applicable.
    (1) For airplanes identified in Fokker Service Bulletin SBF100-
57-028, Revision 2, dated December 11, 2013: Modify the coamings of 
the fuel tank access holes at the access panel locations identified 
in, and in accordance with the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013.
    (2) For airplanes identified in Fokker Service Bulletin SBF100-
57-027, Revision 2, dated December 11, 2013: Replace access panels 
having part number D12395-403 and D12450-403 with new panels having 
part number D19701-401 and D19701-403, at the access panel locations 
identified in, and in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-57-027, Revision 2, 
dated December 11, 2013.

(h) Parts Installation Prohibition

    (1) For airplanes that, on the effective date of this AD, have 
an access panel with part number D12395-403 or D12450-403 installed 
at any of the affected locations: After accomplishing the actions 
required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, 
no person may install, on any airplane, access panels having part 
number D12395-403 or D12450-403 at any access panel location as 
identified in Fokker Service Bulletin SBF100-57-027, Revision 2, 
dated December 11, 2013.
    (2) For airplanes that, on the effective date of this AD, do not 
have an access panel with part number D12395-403 or D12450-403 
installed at any of the affected locations: As of the effective date 
of this AD, no person may install, on any airplane, access panels 
having part number D12395-403 or D12450-403 at any access panel 
location as identified in Fokker Service Bulletin SBF100-57-027, 
Revision 2, dated December 11, 2013.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using the service information 
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD.
    (i) Fokker Service Bulletin SBF100-57-028, dated May 2, 1994.
    (ii) Fokker Service Bulletin SBF100-57-028, Revision 1, dated 
November 1, 1994.
    (2) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using the service information 
specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
    (i) Fokker Service Bulletin SBF100-57-027, dated September 13, 
1993.
    (ii) Fokker Service Bulletin SBF100-57-027, Revision 1, dated 
May 2, 1994.

(j) Other FAA AD Provisions

    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.

[[Page 81021]]

In accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, 
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone: 425-227-1137; fax: 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or European 
Aviation Safety Agency (EASA); or Fokker Services B.V.'s EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0158, dated July 7, 2014, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-9389.
    (2) For service information identified in this AD, contact 
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 
EL Hoofddorp, the Netherlands; telephone: +31 (0)88-6280-350; fax: 
+31 (0)88-6280-111; email: technicalservices@fokker.com; Internet: 
http://www.myfokkerfleet.com. You may view this service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on November 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-27529 Filed 11-16-16; 8:45 am]
 BILLING CODE 4910-13-P