Airworthiness Directives; Airbus Airplanes, 24207-24210 [2015-09811]

Download as PDF Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations (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. Federal Aviation Administration #!docketDetail;D=FAA-2014-0589 or in person at the Docket 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. For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@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–2014–0589. 14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Issued in Renton, Washington, on March 25, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. [Docket No. FAA–2014–0589; Directorate Identifier 2014–NM–069–AD; Amendment 39–18148; AD 2015–09–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes SUPPLEMENTARY INFORMATION: Discussion Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318–111 and –112 airplanes and Model A319, A320, and A321 series airplanes. This AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. This AD requires repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. This AD also provides optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. DATES: This AD becomes effective June 4, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 4, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ rmajette on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318– 111 and –112 airplanes and Model A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on September 3, 2014 (79 FR 52267). The NPRM was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. The NPRM proposed to require repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. The NPRM also proposed to provide optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0064, dated March 14, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 24207 Several operators of A320 family aeroplanes have reported finding cracks on the forward corner fittings of engine pylon aft secondary structures, on the lateral face (lateral panel side). In some cases, these cracks had propagated onto the forward face (Rib 11 side). Investigation results have highlighted that these cracks are initiated by stress corrosion. This condition, if not detected and corrected, could lead to loss (i.e. detachment from the aeroplane) of the lower fairing attachment at Rib 10, and/or loss of the aft fixed fairing with the movable fairing, possibly resulting in * * * [damage to the airplane]. For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DI) of the right hand (RH) Part Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner fittings of engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin (SB) A320–54–1019) to detect cracks or deformation in the splicing area with corner fitting between Ribs 11–12 and, depending on findings, replacement of the corner fittings. This [EASA] AD also recognizes that replacement of the corner fittings with improved parts (as per Airbus SB A320–54– 1019) constitutes a terminating action for the repetitive DI required by this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-05890003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 52267, September 3, 2014) and the FAA’s response to each comment. Requests to Reference Revised Service Bulletins United Airlines and US Airways requested that we revise the NPRM (79 FR 52267, September 3, 2014) to reference Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014, in lieu of Airbus Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008. United Airlines also requested that we revise the NPRM to reference Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014, in lieu of Airbus Service Bulletin A320– 54–1022, Revision 02, dated July 12, 2013. We agree with the commenters’ requests to reference revised service bulletins. Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014, improves the test procedures, and Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014, specifies that certain actions in the Accomplishment Instructions are E:\FR\FM\30APR1.SGM 30APR1 24208 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations required for compliance (RC). Both service bulletins state that no additional work is required for airplanes modified by any previous issue. We have revised paragraphs (g) and (h) of this AD to reference Airbus Service Bulletin A320– 54–1022, Revision 03, dated April 15, 2014, and paragraphs (h)(2) and (i) of this AD to reference Airbus Service Bulletin A320–54–1019, Revision 02, dated April 15, 2014, as the appropriate sources of service information for accomplishing the required actions. We have redesignated paragraph (l) of the NPRM (79 FR 52267, September 3, 2014) as paragraph (l)(1) of this AD and revised it to give credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–54–1022, Revision 02, dated July 12, 2013. We have added new paragraph (l)(2) to this AD to give credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008. Airbus Service Bulletin A320–54– 1022, Revision 03, dated April 15, 2014, steps that are identified as RC must be done to comply with the AD. However, steps that are not identified as RC are recommended. We have added an explanation of RC steps in the preamble of this AD. We have also added new paragraph (m)(3) to this AD to specify compliance with RC steps. rmajette on DSK2VPTVN1PROD with RULES Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 52267, September 3, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 52267, September 3, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as RC (required for compliance) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. Procedures and tests that are identified as RC in any service information must be done to comply with the AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014. This service information describes procedures for inspections of forward corner fittings of the engine pylon aft secondary structures, and corrective actions. We also reviewed Airbus Service Bulletin A320–54–1019, Revision 02, dated April 15, 2014. This service information describes procedures for replacement of the corner fittings on the engine pylons. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0589. Or see ADDRESSES for other ways to access this service information. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. We also estimate that it would take about 30 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $2,170,050, or $2,550 per product. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 In addition, we estimate the optional terminating modification would take about 60 work-hours and require parts costing about $932 per product, for a cost of $6,032 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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. E:\FR\FM\30APR1.SGM 30APR1 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0589; 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 street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. 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 adding the following new airworthiness directive (AD): ■ 2015–09–03 Airbus: Amendment 39–18148. Docket No. FAA–2014–0589; Directorate Identifier 2014–NM–069–AD. (a) Effective Date This AD becomes effective June 4, 2015. (b) Affected ADs None. rmajette on DSK2VPTVN1PROD with RULES (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 33844 or Modification 33847, as applicable, has been embodied in production. (1) Airbus Model A318–111 and –112 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Reason This AD was prompted by reports of cracks on the forward corner fittings of engine pylon VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 aft secondary structures. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking of forward corner fittings having part number (P/N) D54530014201 (right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon aft secondary structures, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014, except as provided by paragraph (j) of this AD. Repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 22,500 flight hours, whichever occurs first. Accomplishment of the actions specified in paragraph (i) of this AD terminates the actions required by this paragraph. (1) Within 15,000 flight cycles or 22,500 flight hours, whichever occurs first since first flight of the airplane. (2) Within 5,000 flight cycles or 7,500 flight hours after the effective date of this AD, without exceeding 40,750 flight cycles or 60,750 flight hours, whichever occurs first since first flight of the airplane. (3) Within 750 flight cycles or 750 flight hours, whichever occurs first after the effective date of this AD. (h) Related Investigative and Corrective Actions If any crack is found on the corner fittings of a pylon during any inspection required by paragraph (g) of this AD: Before further flight, do a detailed inspection for cracking of the lower and medium spars, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014. (1) If any damage is found: Before further flight, repair 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). (2) If no damage is found: Within 5,000 flight cycles or 7,500 flight hours, whichever occurs first after the detailed inspection specified in the introductory text to paragraph (h) of this AD, modify the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014. (i) Optional Terminating Action Modification of an airplane by installation of corner fittings having P/N D0041092120000 (RH) and P/N D0041092120100 (LH) on both pylons, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014, constitutes terminating action for the PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 24209 repetitive inspections required by paragraph (g) of this AD. (j) Parts Installation Limitation Airplanes on which Airbus Modification 38067 (installation of new corner fittings) has been embodied in production, and airplanes already modified in service as described in Airbus Service Bulletin A320–54–1019, are not affected by the requirements of paragraph (g) of this AD, provided that no corner fittings having P/N D54530014201 (RH) or P/ N D54530014200 (LH) have been installed since first flight of the airplane, or since modification, as applicable. (k) Parts Installation Prohibition (1) As of the effective date of this AD, for airplanes on which Airbus Modification 38067 has been embodied in production on both pylons, and for airplanes previously modified in service as described in Airbus Service Bulletin A320–54–1019: Do not install any corner fittings having P/N D54530014201 (RH) or P/N D54530014200 (LH). (2) After modification as required by paragraph (h) of this AD, or after optional modification as specified in paragraph (i) of this AD, as applicable: Do not install any corner fittings having P/N D54530014201 (RH) or P/N D54530014200 (LH). (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using a service bulletin identified in paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD; this service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A320–54–1022, dated July 7, 2009. (ii) Airbus Service Bulletin A320–54–1022, Revision 01, dated September 29, 2011. (iii) Airbus Service Bulletin A320–54– 1022, Revision 02, dated July 12, 2013. (2) This paragraph provides credit for actions required by paragraphs (h)(2) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008, which is not incorporated by reference in this AD. (m) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using E:\FR\FM\30APR1.SGM 30APR1 24210 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 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. The AMOC approval letter must specifically reference this AD. (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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance: Except as required by paragraph (i) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. rmajette on DSK2VPTVN1PROD with RULES (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information EASA Airworthiness Directive 2014–0064, dated March 14, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0589-0003. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) 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 Service Bulletin A320–54–1019, Revision 02, dated April 15, 2014. (ii) Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ 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 VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on April 17, 2015. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–09811 Filed 4–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE INTERIOR National Park Service 36 CFR Part 7 [NPS–BRCA–17884; PA.PD191235A.00.3] RIN 1024–AE23 Special Regulations, Areas of the National Park System, Bryce Canyon National Park, Bicycling National Park Service, Interior. Final rule. AGENCY: ACTION: The National Park Service is planning to construct a paved, multi-use visitor path in Bryce Canyon National Park. The path will be approximately 6.2 miles long and be open to several uses, including running, walking, and bicycling. National Park Service regulations require promulgation of a special regulation to designate new routes for bicycle use off park roads and outside developed areas. DATES: This rule is effective June 1, 2015. SUMMARY: FOR FURTHER INFORMATION CONTACT: Daniel J. Cloud, Chief of Facility Management, Bryce Canyon National Park, P.O. Box 640201, Bryce Canyon, UT 84764–0201. Phone: (435) 834–4720. Email: daniel_cloud@nps.gov. SUPPLEMENTARY INFORMATION: Background Bryce Canyon National Park (BRCA or park) is in south-central Utah. The park encompasses approximately 35,835 acres and ranges between 6,600 and 9,100 feet in elevation. BRCA was originally established as a national monument by presidential proclamation in 1923. The park was renamed Utah National Park in 1924, and the name was changed to Bryce Canyon National Park in 1928. The park’s most noted feature is the eroded landscape below the east rim of the Paunsaugunt Plateau. The erosional force of frost-wedging and the dissolving power of rainwater have worn away the colorful and weak limestone rock into bizarre shapes, PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 including slot canyons, windows, fins, and spires called ‘‘hoodoos.’’ Because the park transcends 2,500 feet of elevation, the park exists in three distinct climatic zones characterized by spruce/fir forest, ponderosa pine forest, and pinyon pine/juniper woodlands. The diversity of forest and meadow habitats provides a high degree of plant and animal diversity. BRCA is also one of the best places to experience a truly dark night sky. The park’s purpose statement, which provides the foundation for park management, administration, and use decisions, states that ‘‘Bryce Canyon National Park protects and conserves resources integral to a landscape of unusual scenic beauty exemplified by highly colored and fantastically eroded geological features, including rock fins and spires, for the benefit and enjoyment of the people.’’ (May 2014 Foundation Document). The park’s Foundation Document identifies ‘‘increased use of alternative transportation (e.g., biking, hiking) within and surrounding the park’’ as an opportunity to protect clean air—one of the fundamental resources of the park. The proposal to construct a multi-use path in the park will support the park’s purpose statement by providing a new opportunity for safe enjoyment and protection of the fundamental resources in the park. Purpose of the Multi-Use Path The primary purpose of the multi-use path is to relieve safety problems for visitors of all ages who choose to use non-motorized transportation to experience the park and adjacent United States Forest Service (USFS) areas near Bryce Canyon City. Increases in visitation of the park (30% increase between 2008 and 2012) are leading to transportation system capacity problems and traffic congestion. Cyclists and pedestrians need a way to travel to and within the park that is safer, provides a better visitor experience, and promotes non-motorized travel between nearby communities and the park as well as between key destinations in the park. The path will enhance the park’s transportation system by connecting the park’s gateway communities with high visitor use areas along the canyon rim in the Bryce Amphitheater and with other key features of the park. The proposed path will also connect to the existing transportation system, including visitor shuttle buses, hiking trails and walking paths, parking lots, and roads. This will link major visitor attractions and facilities with both nonmotorized and motorized transportation modes. Visitor safety will be improved E:\FR\FM\30APR1.SGM 30APR1

Agencies

[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)]
[Rules and Regulations]
[Pages 24207-24210]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09811]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0589; Directorate Identifier 2014-NM-069-AD; 
Amendment 39-18148; AD 2015-09-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318-111 and -112 airplanes and Model A319, A320, and A321 
series airplanes. This AD was prompted by reports of cracks on the 
forward corner fittings of engine pylon aft secondary structures. This 
AD requires repetitive inspections of certain forward corner fittings 
of the pylon aft secondary structures, and corrective actions if 
necessary. This AD also provides optional terminating action for the 
repetitive inspections. We are issuing this AD to detect and correct 
detachment of the lower fairing attachment and/or loss of the aft fixed 
fairing with the movable fairing from the airplane in flight, which 
could result in damage to the airplane.

DATES: This AD becomes effective June 4, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 4, 2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0589 or in person at the 
Docket 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.
    For service information identified in this AD, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email account.airworth-eas@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-2014-
0589.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A318-
111 and -112 airplanes and Model A319, A320, and A321 series airplanes. 
The NPRM published in the Federal Register on September 3, 2014 (79 FR 
52267). The NPRM was prompted by reports of cracks on the forward 
corner fittings of engine pylon aft secondary structures. The NPRM 
proposed to require repetitive inspections of certain forward corner 
fittings of the pylon aft secondary structures, and corrective actions 
if necessary. The NPRM also proposed to provide optional terminating 
action for the repetitive inspections. We are issuing this AD to detect 
and correct detachment of the lower fairing attachment and/or loss of 
the aft fixed fairing with the movable fairing from the airplane in 
flight, which could result in damage to the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0064, dated March 14, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition. The MCAI states:

    Several operators of A320 family aeroplanes have reported 
finding cracks on the forward corner fittings of engine pylon aft 
secondary structures, on the lateral face (lateral panel side). In 
some cases, these cracks had propagated onto the forward face (Rib 
11 side). Investigation results have highlighted that these cracks 
are initiated by stress corrosion.
    This condition, if not detected and corrected, could lead to 
loss (i.e. detachment from the aeroplane) of the lower fairing 
attachment at Rib 10, and/or loss of the aft fixed fairing with the 
movable fairing, possibly resulting in * * * [damage to the 
airplane].
    For the reasons described above, this [EASA] AD requires 
repetitive detailed inspections (DI) of the right hand (RH) Part 
Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner 
fittings of engine pylon aft secondary structures (pre-mod 38067 or 
pre-Airbus Service Bulletin (SB) A320-54-1019) to detect cracks or 
deformation in the splicing area with corner fitting between Ribs 
11-12 and, depending on findings, replacement of the corner 
fittings.
    This [EASA] AD also recognizes that replacement of the corner 
fittings with improved parts (as per Airbus SB A320-54-1019) 
constitutes a terminating action for the repetitive DI required by 
this [EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0589-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 52267, September 3, 2014) and the FAA's response to each comment.

Requests to Reference Revised Service Bulletins

    United Airlines and US Airways requested that we revise the NPRM 
(79 FR 52267, September 3, 2014) to reference Airbus Service Bulletin 
A320-54-1019, Revision 02, dated April 15, 2014, in lieu of Airbus 
Service Bulletin A320-54-1019, Revision 01, dated April 10, 2008. 
United Airlines also requested that we revise the NPRM to reference 
Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 
2014, in lieu of Airbus Service Bulletin A320-54-1022, Revision 02, 
dated July 12, 2013.
    We agree with the commenters' requests to reference revised service 
bulletins. Airbus Service Bulletin A320-54-1019, Revision 02, dated 
April 15, 2014, improves the test procedures, and Airbus Service 
Bulletin A320-54-1022, Revision 03, dated April 15, 2014, specifies 
that certain actions in the Accomplishment Instructions are

[[Page 24208]]

required for compliance (RC). Both service bulletins state that no 
additional work is required for airplanes modified by any previous 
issue. We have revised paragraphs (g) and (h) of this AD to reference 
Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 
2014, and paragraphs (h)(2) and (i) of this AD to reference Airbus 
Service Bulletin A320-54-1019, Revision 02, dated April 15, 2014, as 
the appropriate sources of service information for accomplishing the 
required actions.
    We have redesignated paragraph (l) of the NPRM (79 FR 52267, 
September 3, 2014) as paragraph (l)(1) of this AD and revised it to 
give credit for actions required by paragraphs (g) and (h) of this AD, 
if those actions were performed before the effective date of this AD 
using Airbus Service Bulletin A320-54-1022, Revision 02, dated July 12, 
2013. We have added new paragraph (l)(2) to this AD to give credit for 
actions required by paragraph (i) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-54-1019, Revision 01, dated April 10, 2008.
    Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 
2014, steps that are identified as RC must be done to comply with the 
AD. However, steps that are not identified as RC are recommended. We 
have added an explanation of RC steps in the preamble of this AD. We 
have also added new paragraph (m)(3) to this AD to specify compliance 
with RC steps.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 52267, September 3, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 52267, September 3, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    Procedures and tests that are identified as RC in any service 
information must be done to comply with the AD. However, procedures and 
tests that are not identified as RC are recommended. Those procedures 
and tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an alternative method 
of compliance (AMOC), provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC will require approval of an AMOC.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A320-54-1022, Revision 03, 
dated April 15, 2014. This service information describes procedures for 
inspections of forward corner fittings of the engine pylon aft 
secondary structures, and corrective actions.
    We also reviewed Airbus Service Bulletin A320-54-1019, Revision 02, 
dated April 15, 2014. This service information describes procedures for 
replacement of the corner fittings on the engine pylons.
    This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0589. Or see ADDRESSES for other ways to access this service 
information.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    We also estimate that it would take about 30 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $2,170,050, or $2,550 per product.
    In addition, we estimate the optional terminating modification 
would take about 60 work-hours and require parts costing about $932 per 
product, for a cost of $6,032 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.
    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.

[[Page 24209]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0589; 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 street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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 adding the following new airworthiness 
directive (AD):

2015-09-03 Airbus: Amendment 39-18148. Docket No. FAA-2014-0589; 
Directorate Identifier 2014-NM-069-AD.

(a) Effective Date

    This AD becomes effective June 4, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except for airplanes on which Airbus Modification 33844 or 
Modification 33847, as applicable, has been embodied in production.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by reports of cracks on the forward corner 
fittings of engine pylon aft secondary structures. We are issuing 
this AD to detect and correct detachment of the lower fairing 
attachment and/or loss of the aft fixed fairing with the movable 
fairing from the airplane in flight, which could result in damage to 
the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the latest of the times specified in paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking 
of forward corner fittings having part number (P/N) D54530014201 
(right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon 
aft secondary structures, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-54-1022, Revision 03, 
dated April 15, 2014, except as provided by paragraph (j) of this 
AD. Repeat the inspection thereafter at intervals not to exceed 
15,000 flight cycles or 22,500 flight hours, whichever occurs first. 
Accomplishment of the actions specified in paragraph (i) of this AD 
terminates the actions required by this paragraph.
    (1) Within 15,000 flight cycles or 22,500 flight hours, 
whichever occurs first since first flight of the airplane.
    (2) Within 5,000 flight cycles or 7,500 flight hours after the 
effective date of this AD, without exceeding 40,750 flight cycles or 
60,750 flight hours, whichever occurs first since first flight of 
the airplane.
    (3) Within 750 flight cycles or 750 flight hours, whichever 
occurs first after the effective date of this AD.

(h) Related Investigative and Corrective Actions

    If any crack is found on the corner fittings of a pylon during 
any inspection required by paragraph (g) of this AD: Before further 
flight, do a detailed inspection for cracking of the lower and 
medium spars, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-54-1022, Revision 03, dated April 15, 
2014.
    (1) If any damage is found: Before further flight, repair 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).
    (2) If no damage is found: Within 5,000 flight cycles or 7,500 
flight hours, whichever occurs first after the detailed inspection 
specified in the introductory text to paragraph (h) of this AD, 
modify the airplane, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-54-1019, Revision 02, 
dated April 15, 2014.

(i) Optional Terminating Action

    Modification of an airplane by installation of corner fittings 
having P/N D0041092120000 (RH) and P/N D0041092120100 (LH) on both 
pylons, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-54-1019, Revision 02, dated April 15, 2014, 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD.

(j) Parts Installation Limitation

    Airplanes on which Airbus Modification 38067 (installation of 
new corner fittings) has been embodied in production, and airplanes 
already modified in service as described in Airbus Service Bulletin 
A320-54-1019, are not affected by the requirements of paragraph (g) 
of this AD, provided that no corner fittings having P/N D54530014201 
(RH) or P/N D54530014200 (LH) have been installed since first flight 
of the airplane, or since modification, as applicable.

(k) Parts Installation Prohibition

    (1) As of the effective date of this AD, for airplanes on which 
Airbus Modification 38067 has been embodied in production on both 
pylons, and for airplanes previously modified in service as 
described in Airbus Service Bulletin A320-54-1019: Do not install 
any corner fittings having P/N D54530014201 (RH) or P/N D54530014200 
(LH).
    (2) After modification as required by paragraph (h) of this AD, 
or after optional modification as specified in paragraph (i) of this 
AD, as applicable: Do not install any corner fittings having P/N 
D54530014201 (RH) or P/N D54530014200 (LH).

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using a service bulletin 
identified in paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of 
this AD; this service information is not incorporated by reference 
in this AD.
    (i) Airbus Service Bulletin A320-54-1022, dated July 7, 2009.
    (ii) Airbus Service Bulletin A320-54-1022, Revision 01, dated 
September 29, 2011.
    (iii) Airbus Service Bulletin A320-54-1022, Revision 02, dated 
July 12, 2013.
    (2) This paragraph provides credit for actions required by 
paragraphs (h)(2) and (i) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-54-1019, Revision 01, dated April 10, 2008, which is 
not incorporated by reference in this AD.

(m) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using

[[Page 24210]]

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. The 
AMOC approval letter must specifically reference this AD.
    (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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Required for Compliance: Except as required by paragraph (i) 
of this AD: If any service information contains procedures or tests 
that are identified as RC, those procedures and tests must be done 
to comply with this AD; any procedures or tests that are not 
identified as RC are recommended. Those procedures and tests that 
are not identified as RC may be deviated from using accepted methods 
in accordance with the operator's maintenance or inspection program 
without obtaining approval of an AMOC, provided the procedures and 
tests identified as RC can be done and the airplane can be put back 
in a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC require approval of an AMOC.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2014-0064, dated March 14, 2014, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0589-0003.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) 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 Service Bulletin A320-54-1019, Revision 02, dated 
April 15, 2014.
    (ii) Airbus Service Bulletin A320-54-1022, Revision 03, dated 
April 15, 2014.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@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 April 17, 2015.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-09811 Filed 4-29-15; 8:45 am]
 BILLING CODE 4910-13-P