Airworthiness Directives; Airbus Airplanes, 15985-15988 [2017-06098]

Download as PDF Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) M7 Aerospace LLC SA226 Series Service Bulletin 226–76–012, dated March 17, 2015. (ii) M7 Aerospace LLC SA227 Series Service Bulletin 227–76–007, dated March 17, 2015. (iii) M7Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7– 76–004, dated March 17, 2015. (iv) M7 Aerospace SA226 Series Maintenance Manual Temporary Revision 71–02, dated March 15, 2016. (v) M7 Aerospace SA227 Series Maintenance Manual Temporary Revision 71–03, dated March 15, 2016. (vi) M7 Aerospace SA227 Series Commuter Category Maintenance Manual Temporary Revision 71–02, dated March 15, 2016. (vii) Honeywell International Inc. Service Bulletin TPE331–72–2190, dated December 21, 2011. (3) For service information identified in this AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766; Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com; or Honeywell International Inc. 111 S. 34th Street, Phoenix, Arizona 85034–2802; phone: (855) 808–6500; email: AeroTechSupport@honeywell.com; Internet: https://aerospace.honeywell.com/ en/services/maintenance-and-monitoring. (4) You may view this service information at FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. (5) 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri on March 17, 2017. William Schinstock, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–05857 Filed 3–30–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration nlaroche on DSK30NT082PROD with RULES 14 CFR Part 39 [Docket No. FAA–2017–0245; Directorate Identifier 2017–NM–023–AD; Amendment 39–18841; AD 2017–07–05] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 14:25 Mar 30, 2017 Jkt 241001 Final rule; request for comments. ACTION: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–243, –243F, –341, –342, and –343 airplanes. This AD requires an inspection to determine if affected hydraulic pressure tube assemblies are installed, and replacement with serviceable hydraulic pressure tube assemblies if necessary. This AD also requires repetitive replacements of serviceable hydraulic pressure tube assemblies. This AD was prompted by a determination that cracks can develop on the ripple damper of the hydraulic pressure tube assembly and reports of failure of the ripple damper of the hydraulic pressure tube assembly. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective April 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 17, 2017. We must receive comments on this AD by May 15, 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: 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. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.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–2017– 0245. SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 15985 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–2017– 0245; 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 Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0041, dated February 24, 2017; corrected February 28, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330– 243, –243F, –341, –342, and –343 airplanes. The MCAI states: Following introduction in-service of Airbus modification (mod) 205242, a new hydraulic pressure tube assembly Part Number (P/N) AE711121–18 was installed, one on each engine, with an integral ripple damper. It was determined that, at a relatively low number of cycles, cracks can develop on the ripple damper weld of this new hydraulic pressure tube, which could lead to hydraulic leakage and consequent loss of the green hydraulic system. Recently, there has been a high rate of failure of the affected dampers that, if continued, may exceed the overall safety objective of the certified design. This condition, if not corrected, could, in combination with other system failures, result in reduced control of the aeroplane. Prompted by these findings, Airbus issued Alert Operators Transmission (AOT) A71L012–16 Revision 01, to provide instructions to replace the hydraulic pressure tube assembly P/N AE711121–18 with an improved assembly, P/N AE711121–18 Rev A, equipped with a double-welded ripple damper. For the reasons described above, this [EASA] AD requires [inspection for and] replacement of each affected hydraulic pressure tube assembly with a [serviceable] tube assembly having the double welded ripple damper installed. This [EASA] AD also requires implementation of a life limit E:\FR\FM\31MRR1.SGM 31MRR1 15986 Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations on the new part [i.e., repetitive replacements of serviceable hydraulic pressure tube assemblies]. This [EASA] AD is considered as interim measure and further AD action may follow. This [EASA] AD is republished to correct the TCDS number and add a previous manufacturer name. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0245. Related Service Information Under 1 CFR Part 51 Airbus has issued Alert Operators Transmission (AOT) A71L012–16, Revision 01, dated February 24, 2017. The service information describes procedures for replacing hydraulic pressure tube assembly, part number (P/ N) AE711121–18, and hydraulic pressure tube assembly, P/N AE711121– 18 Rev A. 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. nlaroche on DSK30NT082PROD with RULES 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 these same type design. Difference Between This AD and the MCAI The MCAI mandates replacement of the hydraulic pressure tube assembly, using Airbus AOT A71L012–16, Revision 01, dated February 24, 2017. However, Airbus AOT A71L012–16, Revision 01, dated February 24, 2017, also specifies to first inspect or do a records review to determine the part number of the hydraulic pressure tube assembly. Therefore, paragraph (i) of this AD requires the inspection or records review. The MCAI includes a compliance time of ‘‘within 5 months’’ for the replacement of the affected part. We have determined that a compliance time of ‘‘within 4 months’’ is necessary to adequately address the identified unsafe condition. We have included the 4month compliance time in paragraphs (j), (l), and (m) of this AD. VerDate Sep<11>2014 14:25 Mar 30, 2017 Jkt 241001 We have coordinated these differences with EASA. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracks can develop on the ripple damper of the hydraulic pressure tube assembly, which could lead to hydraulic leakage and consequent loss of the green hydraulic system and because of reports of failure of the ripple damper of the hydraulic pressure tube assembly. This condition could, in combination with other system failures, result in reduced control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0245; Directorate Identifier 2017–NM–023– 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 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. Costs of Compliance We estimate that this AD affects 53 airplanes of U.S. registry. We also estimate that it will take about 5 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $20,000 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,082,525, or $20,425 per product. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 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: E:\FR\FM\31MRR1.SGM 31MRR1 Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations 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): ■ 2017–07–05 Airbus: Amendment 39–18841; Docket No. FAA–2017–0245; Directorate Identifier 2017–NM–023–AD. (a) Effective Date This AD becomes effective April 17, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 243, –243F, –341, –342, and –343 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a determination that cracks can develop on the ripple damper of the hydraulic pressure tube assembly, which could lead to hydraulic leakage and consequent loss of the green hydraulic system. This AD was also prompted by reports of failure of the ripple damper of the hydraulic pressure tube assembly. We are issuing this AD to prevent cracking and failure of the ripple damper of the hydraulic pressure tube assembly, which could, in combination with other system failures, result in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Part For the purpose of this AD, a hydraulic pressure tube assembly, part number (P/N) AE711121–18, as introduced by Airbus mod 205242, is hereafter referred to as an ‘‘affected part’’ in this AD. (h) Definition of Serviceable Part For the purpose of this AD, a ‘‘serviceable part’’ is a hydraulic pressure tube assembly (which has a double-welded ripple damper 15987 installed), P/N AE711121–18 Rev A, that has accumulated fewer than 800 total flight cycles since first installation on an airplane. The hydraulic pressure tube assembly, P/N AE711121–18 Rev A, is introduced by Airbus mod 206979 on the production line. (i) Identification of Affected Parts Within 15 days after the effective date of this AD, inspect to determine the part number of the hydraulic pressure tube assembly that is installed on each engine. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the hydraulic pressure tube assembly can be conclusively determined from that review. (j) Replacement of Affected Parts Within the compliance time specified in table 1 to paragraph (j) of this AD, as applicable, or within 4 months after the effective date of this AD, whichever occurs first, replace each affected part (see paragraph (g) of this AD) with a serviceable part (see paragraph (h) of this AD), in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A71L012–16, Revision 01, dated February 24, 2017. TABLE 1 TO PARAGRAPH (j) OF THIS AD—REPLACEMENT COMPLIANCE TIMES Flight cycles accumulated * Compliance time Fewer than 775 total flight cycles ................................................. Before exceeding 800 total flight cycles on the affected hydraulic pressure tube assembly since first installation on an airplane. Within 25 flight cycles after the effective date of this AD. Within 25 flight cycles after the effective date of this AD. 775 total flight cycles or more ...................................................... An unknown number of flight cycles accumulated ....................... * Unless specified otherwise, the flight cycles in the ‘‘flight cycles accumulated’’ column of table 1 to paragraph (j) of this AD are those accumulated by an affected hydraulic pressure tube assembly, on the effective date of this AD, since first installation on an airplane. (n) Credit for Previous Actions (k) Repetitive Replacement of Serviceable Parts—Life Limit Before a serviceable part (see paragraph (h) of this AD) exceeds 800 total flight cycles since first installation on an airplane, replace it with a serviceable part, in accordance with the instructions of Airbus AOT A71L012–16, Revision 01, dated February 24, 2017. nlaroche on DSK30NT082PROD with RULES (l) Engine Installation Limitation As of the effective date of this AD, except as required by paragraph (m) of this AD, it is allowed to install on any airplane a replacement engine having an affected part (see paragraph (g) of this AD) installed, provided that, before that affected part exceeds 800 total flight cycles since first installation on an airplane, or within 4 months after the effective date of this AD, whichever occurs first, the part is replaced with a serviceable part (see paragraph (h) of this AD), in accordance with the instructions of Airbus AOT A71L012–16, Revision 01, dated February 24, 2017. (m) Parts and Engine Installation Prohibition As of 4 months after the effective date of this AD: Do not install on any airplane an affected part (see paragraph (g) of this AD), or an engine having an affected part installed. VerDate Sep<11>2014 14:25 Mar 30, 2017 Jkt 241001 This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71L012– 16, dated December 22, 2016. (o) 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. 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0041, dated February 24, 2017; corrected February 28, 2017, 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– 2017–0245. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. E:\FR\FM\31MRR1.SGM 31MRR1 15988 Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) 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 this AD specifies otherwise. (i) Airbus Alert Operators Transmission (AOT) A71L012–16, Revision 01, dated February 24, 2017. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (4) 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. (5) 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 17, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–06098 Filed 3–30–17; 8:45 am] Examining the AD Docket BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0603; Directorate Identifier 2013–CE–026–AD; Amendment 39–18827; AD 2017–06–03] RIN 2120–AA64 Airworthiness Directives; Meggitt (Troy), Inc. Combustion Heaters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 81–09–09 for certain Meggitt (Troy), Inc. (previously known as Stewart Warner South Wind Corporation and as Stewart Warner South Wind Division) Model Series (to include all the variants) 921, 930, 937, 940, 944, 945, 977, 978, 979, nlaroche on DSK30NT082PROD with RULES SUMMARY: VerDate Sep<11>2014 14:25 Mar 30, 2017 Jkt 241001 8240, 8253, 8259, and 8472 combustion heaters. AD 81–09–09 required repetitive inspections of the combustion heater; repetitive installation inspections of the combustion heater; and, for combustion heaters having 1,000 hours or more time-in-service (TIS), overhaul of the combustion heater. This new AD requires detailed repetitive inspections, repetitive pressure decay tests, and disable/ removal of the combustion heater if necessary. This AD was prompted by an airplane accident and reports that the heater was malfunctioning. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective May 5, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 5, 2017. ADDRESSES: For service information identified in this final rule, contact Meggitt Control Systems, 3 Industrial Drive, Troy, Indiana 47588; telephone: (812) 547–7071; fax: (812) 547–2488; email: infotroy@meggitt.com; Internet: www.stewart-warner.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0603. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0603; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Chung-Der Young, Aerospace Engineer, FAA, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; telephone (847) 294–7309; fax (847) 294–7834 email: chung-der.young@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 81–09–09, Amendment 39- 4102 (46 FR 24936, May 4, 1981) (‘‘AD 81–09–09’’). The SNPRM published in the Federal Register on November 3, 2016 (81 FR 76532). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on August 20, 2014 (79 FR 49249). The NPRM proposed to retain most actions from AD 81–09–09, add a calendar time to the repetitive inspections, add more detailed actions to the inspections, and add a pressure decay test (PDT). The NPRM was prompted by an airplane accident and reports we received of the heater malfunctioning. The SNPRM proposed to retain the actions proposed in the NPRM, add combustion heater models series to the applicability, and modify the compliance times. We also completed and included in the SNPRM an initial regulatory flexibility analysis. We are issuing this AD to correct the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA’s response to each comment. Request The European Aviation Safety Agency (EASA) requested we change the wording in paragraph (k) of this AD, Removal or Disable of the Combustion Heater. If an operator installs or reenables an applicable combustion heater, the SNPRM requires the operator to do either the inspections required by the AD, disable the heater, or remove the heater. However, the actions of remove or disable would not apply to an operator installing or re-enabling a heater. EASA requested we only require the inspections for a heater that has been re-enabled and only require the inspections or disable options for a heater that has been installed. We partially agree with this comment. We agree that the wording of the SNPRM may be confusing—re-enable the heater and then disable or remove it. However, we do not agree with completely omitting the disable or removal options. If an operator installs or re-enables an applicable heater, that heater must be inspected as required by the AD, and, if it fails the inspections, the heater must be disabled or removed. We changed the language in paragraph (k) of this AD, Removal or E:\FR\FM\31MRR1.SGM 31MRR1

Agencies

[Federal Register Volume 82, Number 61 (Friday, March 31, 2017)]
[Rules and Regulations]
[Pages 15985-15988]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06098]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0245; Directorate Identifier 2017-NM-023-AD; 
Amendment 39-18841; AD 2017-07-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD 
requires an inspection to determine if affected hydraulic pressure tube 
assemblies are installed, and replacement with serviceable hydraulic 
pressure tube assemblies if necessary. This AD also requires repetitive 
replacements of serviceable hydraulic pressure tube assemblies. This AD 
was prompted by a determination that cracks can develop on the ripple 
damper of the hydraulic pressure tube assembly and reports of failure 
of the ripple damper of the hydraulic pressure tube assembly. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD becomes effective April 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 17, 
2017.
    We must receive comments on this AD by May 15, 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: 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.
    For service information identified in this final rule, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.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-2017-
0245.

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-2017-
0245; 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0041, dated February 24, 2017; corrected 
February 28, 2017 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus Model A330-243, -243F, -341, -342, and -343 
airplanes. The MCAI states:

    Following introduction in-service of Airbus modification (mod) 
205242, a new hydraulic pressure tube assembly Part Number (P/N) 
AE711121-18 was installed, one on each engine, with an integral 
ripple damper. It was determined that, at a relatively low number of 
cycles, cracks can develop on the ripple damper weld of this new 
hydraulic pressure tube, which could lead to hydraulic leakage and 
consequent loss of the green hydraulic system. Recently, there has 
been a high rate of failure of the affected dampers that, if 
continued, may exceed the overall safety objective of the certified 
design.
    This condition, if not corrected, could, in combination with 
other system failures, result in reduced control of the aeroplane.
    Prompted by these findings, Airbus issued Alert Operators 
Transmission (AOT) A71L012-16 Revision 01, to provide instructions 
to replace the hydraulic pressure tube assembly P/N AE711121-18 with 
an improved assembly, P/N AE711121-18 Rev A, equipped with a double-
welded ripple damper.
    For the reasons described above, this [EASA] AD requires 
[inspection for and] replacement of each affected hydraulic pressure 
tube assembly with a [serviceable] tube assembly having the double 
welded ripple damper installed. This [EASA] AD also requires 
implementation of a life limit

[[Page 15986]]

on the new part [i.e., repetitive replacements of serviceable 
hydraulic pressure tube assemblies]. This [EASA] AD is considered as 
interim measure and further AD action may follow.
    This [EASA] AD is republished to correct the TCDS number and add 
a previous manufacturer name.

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A71L012-16, 
Revision 01, dated February 24, 2017. The service information describes 
procedures for replacing hydraulic pressure tube assembly, part number 
(P/N) AE711121-18, and hydraulic pressure tube assembly, P/N AE711121-
18 Rev A. 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 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 these 
same type design.

Difference Between This AD and the MCAI

    The MCAI mandates replacement of the hydraulic pressure tube 
assembly, using Airbus AOT A71L012-16, Revision 01, dated February 24, 
2017. However, Airbus AOT A71L012-16, Revision 01, dated February 24, 
2017, also specifies to first inspect or do a records review to 
determine the part number of the hydraulic pressure tube assembly. 
Therefore, paragraph (i) of this AD requires the inspection or records 
review.
    The MCAI includes a compliance time of ``within 5 months'' for the 
replacement of the affected part. We have determined that a compliance 
time of ``within 4 months'' is necessary to adequately address the 
identified unsafe condition. We have included the 4-month compliance 
time in paragraphs (j), (l), and (m) of this AD.
    We have coordinated these differences with EASA.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
cracks can develop on the ripple damper of the hydraulic pressure tube 
assembly, which could lead to hydraulic leakage and consequent loss of 
the green hydraulic system and because of reports of failure of the 
ripple damper of the hydraulic pressure tube assembly. This condition 
could, in combination with other system failures, result in reduced 
control of the airplane. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-0245; Directorate 
Identifier 2017-NM-023-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 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.

Costs of Compliance

    We estimate that this AD affects 53 airplanes of U.S. registry.
    We also estimate that it will take about 5 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $20,000 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $1,082,525, or $20,425 per product.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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:

[[Page 15987]]

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):

2017-07-05 Airbus: Amendment 39-18841; Docket No. FAA-2017-0245; 
Directorate Identifier 2017-NM-023-AD.

(a) Effective Date

    This AD becomes effective April 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that cracks can develop 
on the ripple damper of the hydraulic pressure tube assembly, which 
could lead to hydraulic leakage and consequent loss of the green 
hydraulic system. This AD was also prompted by reports of failure of 
the ripple damper of the hydraulic pressure tube assembly. We are 
issuing this AD to prevent cracking and failure of the ripple damper 
of the hydraulic pressure tube assembly, which could, in combination 
with other system failures, result in reduced control of the 
airplane.

(f) Compliance

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

(g) Definition of Affected Part

    For the purpose of this AD, a hydraulic pressure tube assembly, 
part number (P/N) AE711121-18, as introduced by Airbus mod 205242, 
is hereafter referred to as an ``affected part'' in this AD.

(h) Definition of Serviceable Part

    For the purpose of this AD, a ``serviceable part'' is a 
hydraulic pressure tube assembly (which has a double-welded ripple 
damper installed), P/N AE711121-18 Rev A, that has accumulated fewer 
than 800 total flight cycles since first installation on an 
airplane. The hydraulic pressure tube assembly, P/N AE711121-18 Rev 
A, is introduced by Airbus mod 206979 on the production line.

(i) Identification of Affected Parts

    Within 15 days after the effective date of this AD, inspect to 
determine the part number of the hydraulic pressure tube assembly 
that is installed on each engine. A review of airplane maintenance 
records is acceptable in lieu of this inspection if the part number 
of the hydraulic pressure tube assembly can be conclusively 
determined from that review.

(j) Replacement of Affected Parts

    Within the compliance time specified in table 1 to paragraph (j) 
of this AD, as applicable, or within 4 months after the effective 
date of this AD, whichever occurs first, replace each affected part 
(see paragraph (g) of this AD) with a serviceable part (see 
paragraph (h) of this AD), in accordance with the instructions of 
Airbus Alert Operators Transmission (AOT) A71L012-16, Revision 01, 
dated February 24, 2017.

    Table 1 to Paragraph (j) of This AD--Replacement Compliance Times
------------------------------------------------------------------------
     Flight cycles accumulated *                Compliance time
------------------------------------------------------------------------
Fewer than 775 total flight cycles...  Before exceeding 800 total flight
                                        cycles on the affected hydraulic
                                        pressure tube assembly since
                                        first installation on an
                                        airplane.
775 total flight cycles or more......  Within 25 flight cycles after the
                                        effective date of this AD.
An unknown number of flight cycles     Within 25 flight cycles after the
 accumulated.                           effective date of this AD.
------------------------------------------------------------------------
* Unless specified otherwise, the flight cycles in the ``flight cycles
  accumulated'' column of table 1 to paragraph (j) of this AD are those
  accumulated by an affected hydraulic pressure tube assembly, on the
  effective date of this AD, since first installation on an airplane.

(k) Repetitive Replacement of Serviceable Parts--Life Limit

    Before a serviceable part (see paragraph (h) of this AD) exceeds 
800 total flight cycles since first installation on an airplane, 
replace it with a serviceable part, in accordance with the 
instructions of Airbus AOT A71L012-16, Revision 01, dated February 
24, 2017.

(l) Engine Installation Limitation

    As of the effective date of this AD, except as required by 
paragraph (m) of this AD, it is allowed to install on any airplane a 
replacement engine having an affected part (see paragraph (g) of 
this AD) installed, provided that, before that affected part exceeds 
800 total flight cycles since first installation on an airplane, or 
within 4 months after the effective date of this AD, whichever 
occurs first, the part is replaced with a serviceable part (see 
paragraph (h) of this AD), in accordance with the instructions of 
Airbus AOT A71L012-16, Revision 01, dated February 24, 2017.

(m) Parts and Engine Installation Prohibition

    As of 4 months after the effective date of this AD: Do not 
install on any airplane an affected part (see paragraph (g) of this 
AD), or an engine having an affected part installed.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(j) of this AD, if those actions were performed before the effective 
date of this AD using Airbus AOT A71L012-16, dated December 22, 
2016.

(o) 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. 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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 the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0041, dated February 24, 
2017; corrected February 28, 2017, 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-
2017-0245.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.

[[Page 15988]]

    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission (AOT) A71L012-16, 
Revision 01, dated February 24, 2017.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) 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.
    (5) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-06098 Filed 3-30-17; 8:45 am]
BILLING CODE 4910-13-P