Airworthiness Directives; Fokker Services B.V. Airplanes, 1532-1535 [2018-00339]

Download as PDF 1532 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations (ii) Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 1, dated May 25, 1995. (iii) Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, dated June 30, 1994. (4) Airplanes on which the outboard chord has not been replaced in accordance with the method specified in paragraph (h)(4)(i), (h)(4)(ii), or (h)(4)(iii) of this AD. (i) Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006. (ii) Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 1, dated May 25, 1995. (iii) Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, dated June 30, 1994. sradovich on DSK3GMQ082PROD with RULES (i) Edge Margin Measurement, Related Investigative Actions, and Repair For Model 737–100, –200, and –200C series airplanes having line numbers 1 through 999 inclusive, identified as Groups 1 through 3 in Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006, on which the preventive modification has been installed in accordance with Boeing Alert Service Bulletin 737–53A1166, dated June 30, 1994; or Boeing Alert Service Bulletin 737–53A1166, Revision 1, dated May 25, 1995: Within 60,000 flight cycles after accomplishing the preventive modification, determine if the modification is classified as interim or permanent by using the edge margin measurement classification specified in part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006. In lieu of measuring on the airplane, a review of engineering documentation may be used to classify the modification if the engineering documentation was completed at the time of the modification and has the edge margins recorded. (1) If the modification is classified as permanent, no further action is required by paragraph (i) of this AD. (2) If the modification is classified as interim: Within 60,000 flight cycles after accomplishment of the interim modification of the outboard chord of the frame at BS 727 at S–18A, but no earlier than 50,000 flight cycles after accomplishment of the modification, do a one-time follow-on openhole eddy current inspection to detect cracks in the modified chord, in accordance with part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006. If any crack is found, before further flight, repair in accordance with part 3 or part 4, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006; except, if the repairs cannot be installed using the identified procedures, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 (j) Follow-On Inspection for Interim Modification and Repair For airplanes having line numbers 1 through 3132 inclusive, on which an interim modification of the BS 727 outboard chord as defined in part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006, has been accomplished: Within 60,000 flight cycles after accomplishment of the interim modification of the outboard chord of the frame at BS 727 at S–18A, but no earlier than 50,000 flight cycles after accomplishment of the modification, do a one-time follow-on open-hole eddy current inspection to detect cracks in the modified chord, in accordance with part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006. If any crack is found during the inspection required by this paragraph, before further flight, repair in accordance with part 3 or part 4, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006; except, where the repairs cannot be installed using the procedures identified in this service bulletin, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) Exception to the Service Information Access and restoration procedures specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1166, Revision 2, dated May 25, 2006, are not required by this AD. Operators may do those actions following their approved maintenance procedures. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 manager of the certification office, send it to the attention of the person identified in paragraph (m) of this AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (m) Related Information For more information about this AD, contact George Garrido, Aerospace Engineer, PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5232; fax: 562–627–5210; email: george.garrido@faa.gov. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 26, 2012 (77 FR 69747, November 21, 2012). (i) Boeing Alert Service Bulletin 737– 53A1166, Revision 2, dated May 25, 2006. (ii) Reserved. (4) For service information identified in this AD, 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. (5) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–00256 Filed 1–11–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1242; Product Identifier 2013–NM–043–AD; Amendment 39–19150; AD 2018–01–09] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 95–25–02, which applied to certain Fokker Services B.V. Model F28 Mark 0100 SUMMARY: E:\FR\FM\12JAR1.SGM 12JAR1 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations airplanes. AD 95–25–02 required inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. This new AD was prompted by a report that the hinges of the small cargo door are made of a material that is sensitive to stress corrosion and fatigue cracking, and by the determination that the existing inspection program does not provide sufficient protection against fatigue-induced cracks. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products. This AD becomes effective January 29, 2018. We must receive comments on this AD by February 26, 2018. 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 https://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 W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: sradovich on DSK3GMQ082PROD with RULES Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1242; 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 telephone: 425–227–1137; fax: 425– 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued AD 95–25–02, Amendment 39–9446 (60 FR 63615, December 12, 1995) (‘‘AD 95–25–02’’), which applied to certain Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 95–25–02 was prompted by a report that the hinges of the small cargo door are made of a material that is sensitive to stress corrosion cracking. AD 95–25–02 required inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. We issued AD 95–25–02 to prevent failure of the hinges of the small cargo door due to stress corrosion cracking, which could result in opening and/or separation of the door while the airplane is in flight, and resultant rapid decompression and/or structural damage to the airplane. Since we issued AD 95–25–02, we have determined that the existing inspection program does not provide sufficient protection against fatigueinduced cracks. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013–0028, dated February 8, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The MCAI states: Over the years, stress corrosion- and fatigue-induced cracks were found on the hinges of the downward opening small cargo doors installed on Fokker F28 Mark 0100 aeroplanes. To address the potential unsafe condition with respect to stress corrosion, CAA–NL issued AD (BLA) 93–036/2 [which corresponded to FAA AD 95–25–02] to require repetitive inspections and, if cracks are found, replacement of the hinges with hinges of a new design. These new hinges were installed before delivery on aeroplanes with s/n 11409 and higher. To ensure the continued structural integrity with respect to fatigue, a repetitive inspection was included in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness. As part of the Widespread Fatigue Damage re-evaluation, it was concluded that the repetitive fatigue inspection in the ALS does not provide a sufficient level of protection against the fatigue-induced cracks. For the reasons described above, this [EASA] AD retains the requirements of CAA– NL AD 93–036/2, which is superseded, and requires replacement of Part Number (P/N) PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 1533 A28410–405 and P/N A28410–407 hinges with modified P/N D28410–409 hinges. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2017–1242. 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. 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. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason(s) stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–1242; Product Identifier 2013–NM–043–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 based on those comments. We will post all comments we receive, without change, to https:// 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. Costs of Compliance Currently, there are no affected U.S.registered airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition, and doing the actions specified in those instructions. Based on the actions specified in the MCAI AD, E:\FR\FM\12JAR1.SGM 12JAR1 1534 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations we are providing the following cost estimates for an affected airplane that is placed on the U.S. Register in the future: ESTIMATED COSTS Action Labor cost Parts cost Inspections (retained actions from AD 95–25– 02). Replacement (new action) ............................... 2 work-hours × $85 per hour = $170 per inspection cycle. Up to 186 work-hours × $85 per hour = $15,810. $0 ............................... We estimate the following costs to do any necessary on-condition replacements that would be required based on the results of the required actions: Up to $7,700 .............. Cost per product $170 per inspection cycle. Up to $23,510. ON-CONDITION COSTS Labor cost Parts cost Replacement (retained actions from AD 95– 25–02). Up to 186 work-hours × $85 per hour = $15,810. Up to $7,700 .............. Authority for This Rulemaking sradovich on DSK3GMQ082PROD with RULES Action the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that 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); 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. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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 VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 95–25–02, Amendment 39–9446 (60 FR 63617, December 12, 1995), and adding the following new AD: ■ 2018–01–09 Fokker Services B.V.: Amendment 39–19150; Docket No. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Cost per product Up to $23,510. FAA–2017–1242; Product Identifier 2013–NM–043–AD. (a) Effective Date This AD becomes effective January 29, 2018. (b) Affected ADs This AD replaces AD 95–25–02, Amendment 39–9446 (60 FR 63615, December 12, 1995) (‘‘AD 95–25–02’’). (c) Applicability This AD applies to Fokker Services B.V. Model F28 Mark 0100 series airplanes, certificated in any category, serial numbers 11244 through 11267 inclusive, 11284, 11285, 11287, 11288, 11290, 11292, 11294, 11296, 11298, 11299, 11301, 11302, 11304, 11305, 11307, 11309, 11311, 11315, 11317, 11319, 11320, 11322, 11336, 11339, 11341 through 11344 inclusive, 11347, 11348, 11350, 11351, 11362 through 11364 inclusive, 11371, 11374, 11375, 11381 through 11384 inclusive, 11386, 11389, 11390, 11394, and 11401. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report that the hinges of the small cargo door are made of a material that is sensitive to stress corrosion cracking, and by the determination that the existing inspection program does not provide sufficient protection against fatigue-induced cracks. We are issuing this AD to prevent failure of the hinges of the small cargo door due to stress corrosion cracking, which could result in opening and/or separation of the door while the airplane is in flight, and resultant rapid decompression and/or structural damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\12JAR1.SGM 12JAR1 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations (g) Required Action(s) DEPARTMENT OF TRANSPORTATION Within 30 days after the effective date of this AD, request instructions from the Manager, International Section, Transport Standards Branch, FAA, to address the unsafe condition specified in paragraph (e) of this AD; and accomplish the action(s) at the times specified in, and in accordance with, those instructions. Guidance can be found in Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) AD 2013–0028, dated February 8, 2013. The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 Section, send it to the attention of the person identified in paragraph (i)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (i) Related Information (1) Refer to MCAI EASA AD 2013–0028, dated February 8, 2013, for related information. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2017–1242. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425– 227–1137; fax: 425–227–1149. (j) Material Incorporated by Reference None. Issued in Renton, Washington, on January 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. sradovich on DSK3GMQ082PROD with RULES BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2017–1243; Product Identifier 2012–NM–150–AD; Amendment 39–19151; AD 2018–01–10] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: (h) Alternative Methods of Compliance (AMOCs) [FR Doc. 2018–00339 Filed 1–11–18; 8:45 am] Federal Aviation Administration We are superseding Airworthiness Directive (AD) 2011–14– 10, which applied to certain Airbus Model A330–342 airplanes. AD 2011– 14–10 required repetitive ultrasonic inspections for cracks of a certain fuselage frame at the fastener hole area just above a certain stringer, and repair, if necessary. This new AD was prompted by a new fatigue and damage tolerance evaluation, which showed that certain inspection thresholds and intervals need to be shorter. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD becomes effective January 29, 2018. We must receive comments on this AD by February 26, 2018. 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 https://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 W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 1535 1243; 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425– 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued AD 2011–14–10, Amendment 39–16745 (76 FR 41657, July 15, 2011) (‘‘AD 2011–14–10’’), which applied to certain Airbus Model A330–342 airplanes. AD 2011–14–10 was prompted by a determination that airworthiness limitation item (ALI) task 533105–10–02 was not performed on certain airplanes. AD 2011–14–10 required repetitive ultrasonic inspections for cracks of fuselage frame 39.1 at the fastener hole area just above stringer 28, and repair, if necessary. We issued AD 2011–14–10 to detect and correct fatigue cracking of the internal structure of the fuselage, which could adversely affect the structural integrity of the airplane. Since we issued AD 2011–14–10, we have determined, based on a new fatigue and damage tolerance evaluation that took into account airplane usage, that the compliance time threshold and intervals need to be shorter. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2012–0140, dated July 27, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–342 airplanes. The MCAI states: Airworthiness Limitation Item (ALI) task 533105–01–02 is applicable to aeroplanes on which Airbus modification 40391 has not been embodied in production. The requirements associated to this task are applicable to aeroplanes on which Modification Proposal (MP) S10374 has not been embodied. Following a query from an operator, investigations revealed that some aeroplane [manufacturer serial numbers] MSN, for which Airbus modification 40391 was indicated as fully embodied inside the Aircraft Inspection Report (AIR), did not E:\FR\FM\12JAR1.SGM 12JAR1

Agencies

[Federal Register Volume 83, Number 9 (Friday, January 12, 2018)]
[Rules and Regulations]
[Pages 1532-1535]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00339]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1242; Product Identifier 2013-NM-043-AD; Amendment 
39-19150; AD 2018-01-09]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 95-25-02, 
which applied to certain Fokker Services B.V. Model F28 Mark 0100

[[Page 1533]]

airplanes. AD 95-25-02 required inspection(s) to detect cracks of the 
fuselage-mounted half of hinge assemblies of the small cargo door, and 
replacement of any cracked hinge assembly with a new hinge assembly. 
This new AD was prompted by a report that the hinges of the small cargo 
door are made of a material that is sensitive to stress corrosion and 
fatigue cracking, and by the determination that the existing inspection 
program does not provide sufficient protection against fatigue-induced 
cracks. This AD requires contacting the FAA to obtain instructions for 
addressing the unsafe condition on these products, and doing the 
actions specified in those instructions. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD becomes effective January 29, 2018.
    We must receive comments on this AD by February 26, 2018.

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 https://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 W12-140, 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1242; 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 Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1137; fax: 425-
227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued AD 95-25-02, Amendment 39-9446 (60 FR 63615, December 12, 
1995) (``AD 95-25-02''), which applied to certain Fokker Services B.V. 
Model F28 Mark 0100 airplanes. AD 95-25-02 was prompted by a report 
that the hinges of the small cargo door are made of a material that is 
sensitive to stress corrosion cracking. AD 95-25-02 required 
inspection(s) to detect cracks of the fuselage-mounted half of hinge 
assemblies of the small cargo door, and replacement of any cracked 
hinge assembly with a new hinge assembly. We issued AD 95-25-02 to 
prevent failure of the hinges of the small cargo door due to stress 
corrosion cracking, which could result in opening and/or separation of 
the door while the airplane is in flight, and resultant rapid 
decompression and/or structural damage to the airplane.
    Since we issued AD 95-25-02, we have determined that the existing 
inspection program does not provide sufficient protection against 
fatigue-induced cracks.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0028, dated February 8, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Fokker Services B.V. Model F28 
Mark 0100 airplanes. The MCAI states:

    Over the years, stress corrosion- and fatigue-induced cracks 
were found on the hinges of the downward opening small cargo doors 
installed on Fokker F28 Mark 0100 aeroplanes.
    To address the potential unsafe condition with respect to stress 
corrosion, CAA-NL issued AD (BLA) 93-036/2 [which corresponded to 
FAA AD 95-25-02] to require repetitive inspections and, if cracks 
are found, replacement of the hinges with hinges of a new design. 
These new hinges were installed before delivery on aeroplanes with 
s/n 11409 and higher.
    To ensure the continued structural integrity with respect to 
fatigue, a repetitive inspection was included in the Airworthiness 
Limitations Section (ALS) of the Instructions for Continued 
Airworthiness.
    As part of the Widespread Fatigue Damage re-evaluation, it was 
concluded that the repetitive fatigue inspection in the ALS does not 
provide a sufficient level of protection against the fatigue-induced 
cracks.
    For the reasons described above, this [EASA] AD retains the 
requirements of CAA-NL AD 93-036/2, which is superseded, and 
requires replacement of Part Number (P/N) A28410-405 and P/N A28410-
407 hinges with modified P/N D28410-409 hinges.

    You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1242.

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. 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.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, we 
find good cause that notice and opportunity for prior public comment 
are unnecessary. In addition, for the reason(s) stated above, we find 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-1242; Product 
Identifier 2013-NM-043-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 based on 
those comments.
    We will post all comments we receive, without change, to https://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.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. This AD 
requires contacting the FAA to obtain instructions for addressing the 
unsafe condition, and doing the actions specified in those 
instructions. Based on the actions specified in the MCAI AD,

[[Page 1534]]

we are providing the following cost estimates for an affected airplane 
that is placed on the U.S. Register in the future:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from   2 work-hours x $85 per hour  $0....................  $170 per inspection
 AD 95-25-02).                        = $170 per inspection                                cycle.
                                      cycle.
Replacement (new action)...........  Up to 186 work-hours x $85   Up to $7,700..........  Up to $23,510.
                                      per hour = $15,810.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
replacements that would be required based on the results of the 
required actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement (retained actions from   Up to 186 work-hours x $85   Up to $7,700..........  Up to $23,510.
 AD 95-25-02).                        per hour = $15,810.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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 that 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);
    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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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 removing airworthiness directive (AD) 
95-25-02, Amendment 39-9446 (60 FR 63617, December 12, 1995), and 
adding the following new AD:

2018-01-09 Fokker Services B.V.: Amendment 39-19150; Docket No. FAA-
2017-1242; Product Identifier 2013-NM-043-AD.

(a) Effective Date

    This AD becomes effective January 29, 2018.

(b) Affected ADs

    This AD replaces AD 95-25-02, Amendment 39-9446 (60 FR 63615, 
December 12, 1995) (``AD 95-25-02'').

(c) Applicability

    This AD applies to Fokker Services B.V. Model F28 Mark 0100 
series airplanes, certificated in any category, serial numbers 11244 
through 11267 inclusive, 11284, 11285, 11287, 11288, 11290, 11292, 
11294, 11296, 11298, 11299, 11301, 11302, 11304, 11305, 11307, 
11309, 11311, 11315, 11317, 11319, 11320, 11322, 11336, 11339, 11341 
through 11344 inclusive, 11347, 11348, 11350, 11351, 11362 through 
11364 inclusive, 11371, 11374, 11375, 11381 through 11384 inclusive, 
11386, 11389, 11390, 11394, and 11401.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report that the hinges of the small 
cargo door are made of a material that is sensitive to stress 
corrosion cracking, and by the determination that the existing 
inspection program does not provide sufficient protection against 
fatigue-induced cracks. We are issuing this AD to prevent failure of 
the hinges of the small cargo door due to stress corrosion cracking, 
which could result in opening and/or separation of the door while 
the airplane is in flight, and resultant rapid decompression and/or 
structural damage to the airplane.

(f) Compliance

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

[[Page 1535]]

(g) Required Action(s)

    Within 30 days after the effective date of this AD, request 
instructions from the Manager, International Section, Transport 
Standards Branch, FAA, to address the unsafe condition specified in 
paragraph (e) of this AD; and accomplish the action(s) at the times 
specified in, and in accordance with, those instructions. Guidance 
can be found in Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) AD 2013-0028, dated 
February 8, 2013.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, International Section, Transport Standards Branch, 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. 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 Section, send it to the 
attention of the person identified in paragraph (i)(2) of this AD. 
Information may be emailed to: [email protected]. 
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.

(i) Related Information

    (1) Refer to MCAI EASA AD 2013-0028, dated February 8, 2013, for 
related information. You may examine the MCAI on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-1242.
    (2) For more information about this AD, contact Tom Rodriguez, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 
425-227-1137; fax: 425-227-1149.

(j) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on January 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-00339 Filed 1-11-18; 8:45 am]
BILLING CODE 4910-13-P
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