80 FR 24207 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 83 (April 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 83 (April 30, 2015)
| Page Range | 24207-24210 | |
| FR Document | 2015-09811 |
[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)] [Rules and Regulations] [Pages 24207-24210] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-09811] ----------------------------------------------------------------------- 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. ----------------------------------------------------------------------- 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 [email protected]; 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: [email protected]. 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 [email protected]; 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
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(4) You may view this service information #!docketDetail;D=FAA-2014-0589 or in Several operators of A320 family
at the FAA, Transport Airplane Directorate, person at the Docket Management aeroplanes have reported finding cracks on
1601 Lind Avenue SW., Renton, WA. For Facility, U.S. Department of the forward corner fittings of engine pylon aft
information on the availability of this secondary structures, on the lateral face
Transportation, Docket Operations, M– (lateral panel side). In some cases, these
material at the FAA, call 425–227–1221.
(5) You may view this service information
30, West Building Ground Floor, Room cracks had propagated onto the forward face
that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE., (Rib 11 side). Investigation results have
National Archives and Records Washington, DC. highlighted that these cracks are initiated by
Administration (NARA). For information on For service information identified in stress corrosion.
the availability of this material at NARA, call this AD, contact Airbus, Airworthiness This condition, if not detected and
202–741–6030, or go to: http:// corrected, could lead to loss (i.e. detachment
Office—EIAS, 1 Rond Point Maurice
www.archives.gov/federal-register/cfr/ibr- from the aeroplane) of the lower fairing
Bellonte, 31707 Blagnac Cedex, France; attachment at Rib 10, and/or loss of the aft
locations.html.
telephone +33 5 61 93 36 96; fax +33 5 fixed fairing with the movable fairing,
Issued in Renton, Washington, on March 61 93 44 51; email account.airworth- possibly resulting in * * * [damage to the
25, 2015. eas@airbus.com; Internet http:// airplane].
Michael Kaszycki, www.airbus.com. You may view this For the reasons described above, this
Acting Manager, Transport Airplane referenced service information at the [EASA] AD requires repetitive detailed
Directorate, Aircraft Certification Service. FAA, Transport Airplane Directorate, inspections (DI) of the right hand (RH) Part
Number (P/N) D54530014201 and left hand
[FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] 1601 Lind Avenue SW., Renton, WA.
(LH) P/N D54530014200 corner fittings of
BILLING CODE 4910–13–P For information on the availability of engine pylon aft secondary structures (pre-
this material at the FAA, call 425–227– mod 38067 or pre-Airbus Service Bulletin
1221. It is also available on the Internet (SB) A320–54–1019) to detect cracks or
DEPARTMENT OF TRANSPORTATION at http://www.regulations.gov by deformation in the splicing area with corner
searching for and locating Docket No. fitting between Ribs 11–12 and, depending
Federal Aviation Administration FAA–2014–0589. on findings, replacement of the corner
fittings.
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: This [EASA] AD also recognizes that
Sanjay Ralhan, Aerospace Engineer, replacement of the corner fittings with
[Docket No. FAA–2014–0589; Directorate International Branch, ANM–116, improved parts (as per Airbus SB A320–54–
Identifier 2014–NM–069–AD; Amendment Transport Airplane Directorate, FAA, 1019) constitutes a terminating action for the
39–18148; AD 2015–09–03] repetitive DI required by this [EASA] AD.
1601 Lind Avenue SW., Renton, WA
RIN 2120–AA64 98057–3356; telephone 425–227–1405; You may examine the MCAI in the
fax 425–227–1149. AD docket on the Internet at http://
Airworthiness Directives; Airbus www.regulations.gov/
Airplanes SUPPLEMENTARY INFORMATION:
#!documentDetail;D=FAA-2014-0589-
Discussion 0003.
AGENCY: Federal Aviation
Administration (FAA), Department of We issued a notice of proposed Comments
Transportation (DOT). rulemaking (NPRM) to amend 14 CFR We gave the public the opportunity to
ACTION: Final rule. part 39 by adding an AD that would participate in developing this AD. The
apply to certain Airbus Model A318– following presents the comments
SUMMARY: We are adopting a new 111 and –112 airplanes and Model
airworthiness directive (AD) for certain received on the NPRM (79 FR 52267,
A319, A320, and A321 series airplanes. September 3, 2014) and the FAA’s
Airbus Model A318–111 and –112 The NPRM published in the Federal
airplanes and Model A319, A320, and response to each comment.
Register on September 3, 2014 (79 FR
A321 series airplanes. This AD was 52267). The NPRM was prompted by Requests to Reference Revised Service
prompted by reports of cracks on the reports of cracks on the forward corner Bulletins
forward corner fittings of engine pylon fittings of engine pylon aft secondary United Airlines and US Airways
aft secondary structures. This AD structures. The NPRM proposed to requested that we revise the NPRM (79
requires repetitive inspections of certain require repetitive inspections of certain FR 52267, September 3, 2014) to
forward corner fittings of the pylon aft forward corner fittings of the pylon aft reference Airbus Service Bulletin A320–
secondary structures, and corrective secondary structures, and corrective 54–1019, Revision 02, dated April 15,
actions if necessary. This AD also actions if necessary. The NPRM also 2014, in lieu of Airbus Service Bulletin
provides optional terminating action for proposed to provide optional A320–54–1019, Revision 01, dated April
the repetitive inspections. We are terminating action for the repetitive 10, 2008. United Airlines also requested
issuing this AD to detect and correct inspections. We are issuing this AD to that we revise the NPRM to reference
detachment of the lower fairing detect and correct detachment of the Airbus Service Bulletin A320–54–1022,
attachment and/or loss of the aft fixed lower fairing attachment and/or loss of Revision 03, dated April 15, 2014, in
fairing with the movable fairing from the aft fixed fairing with the movable lieu of Airbus Service Bulletin A320–
the airplane in flight, which could result fairing from the airplane in flight, which 54–1022, Revision 02, dated July 12,
in damage to the airplane. could result in damage to the airplane. 2013.
DATES: This AD becomes effective June The European Aviation Safety Agency We agree with the commenters’
4, 2015. (EASA), which is the Technical Agent requests to reference revised service
The Director of the Federal Register for the Member States of the European bulletins. Airbus Service Bulletin A320–
rmajette on DSK2VPTVN1PROD with RULES
approved the incorporation by reference Union, has issued EASA Airworthiness 54–1019, Revision 02, dated April 15,
of certain publications listed in this AD Directive 2014–0064, dated March 14, 2014, improves the test procedures, and
as of June 4, 2015. 2014 (referred to after this as the Airbus Service Bulletin A320–54–1022,
ADDRESSES: You may examine the AD Mandatory Continuing Airworthiness Revision 03, dated April 15, 2014,
docket on the Internet at http:// Information, or ‘‘the MCAI’’), to correct specifies that certain actions in the
www.regulations.gov/ an unsafe condition. The MCAI states: Accomplishment Instructions are
VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM 30APR1](https://thefederalregister.org/doc/80_FR_24290/page/1.svg)
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Examining the AD Docket aft secondary structures. We are issuing this repetitive inspections required by paragraph
AD to detect and correct detachment of the (g) of this AD.
You may examine the AD docket on lower fairing attachment and/or loss of the aft
the Internet at http:// (j) Parts Installation Limitation
fixed fairing with the movable fairing from
www.regulations.gov/ the airplane in flight, which could result in Airplanes on which Airbus Modification
#!docketDetail;D=FAA-2014-0589; or in damage to the airplane. 38067 (installation of new corner fittings) has
person at the Docket Management been embodied in production, and airplanes
(f) Compliance already modified in service as described in
Facility between 9 a.m. and 5 p.m.,
Comply with this AD within the Airbus Service Bulletin A320–54–1019, are
Monday through Friday, except Federal
compliance times specified, unless already not affected by the requirements of paragraph
holidays. The AD docket contains this done. (g) of this AD, provided that no corner
AD, the regulatory evaluation, any fittings having P/N D54530014201 (RH) or P/
comments received, and other (g) Repetitive Inspections N D54530014200 (LH) have been installed
information. The street address for the At the latest of the times specified in since first flight of the airplane, or since
Docket Operations office (telephone paragraphs (g)(1), (g)(2), and (g)(3) of this AD: modification, as applicable.
800–647–5527) is in the ADDRESSES Do a detailed inspection for cracking of
forward corner fittings having part number (k) Parts Installation Prohibition
section.
(P/N) D54530014201 (right-hand (RH)) and (1) As of the effective date of this AD, for
List of Subjects in 14 CFR Part 39 P/N D54530014200 (left-hand (LH)) of the airplanes on which Airbus Modification
pylon aft secondary structures, in accordance 38067 has been embodied in production on
Air transportation, Aircraft, Aviation with the Accomplishment Instructions of both pylons, and for airplanes previously
safety, Incorporation by reference, Airbus Service Bulletin A320–54–1022, modified in service as described in Airbus
Safety. Revision 03, dated April 15, 2014, except as Service Bulletin A320–54–1019: Do not
provided by paragraph (j) of this AD. Repeat install any corner fittings having P/N
Adoption of the Amendment the inspection thereafter at intervals not to D54530014201 (RH) or P/N D54530014200
Accordingly, under the authority exceed 15,000 flight cycles or 22,500 flight (LH).
delegated to me by the Administrator, hours, whichever occurs first. (2) After modification as required by
the FAA amends 14 CFR part 39 as Accomplishment of the actions specified in paragraph (h) of this AD, or after optional
follows: paragraph (i) of this AD terminates the modification as specified in paragraph (i) of
actions required by this paragraph. this AD, as applicable: Do not install any
PART 39—AIRWORTHINESS (1) Within 15,000 flight cycles or 22,500 corner fittings having P/N D54530014201
flight hours, whichever occurs first since first (RH) or P/N D54530014200 (LH).
DIRECTIVES flight of the airplane.
(l) Credit for Previous Actions
(2) Within 5,000 flight cycles or 7,500
■ 1. The authority citation for part 39 (1) This paragraph provides credit for
flight hours after the effective date of this AD,
continues to read as follows: without exceeding 40,750 flight cycles or actions required by paragraphs (g) and (h) of
Authority: 49 U.S.C. 106(g), 40113, 44701. 60,750 flight hours, whichever occurs first this AD, if those actions were performed
since first flight of the airplane. before the effective date of this AD using a
§ 39.13 [Amended] (3) Within 750 flight cycles or 750 flight service bulletin identified in paragraph
hours, whichever occurs first after the (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD; this
■ 2. The FAA amends § 39.13 by adding
effective date of this AD. service information is not incorporated by
the following new airworthiness reference in this AD.
directive (AD): (h) Related Investigative and Corrective (i) Airbus Service Bulletin A320–54–1022,
Actions dated July 7, 2009.
2015–09–03 Airbus: Amendment 39–18148.
Docket No. FAA–2014–0589; Directorate If any crack is found on the corner fittings (ii) Airbus Service Bulletin A320–54–1022,
Identifier 2014–NM–069–AD. of a pylon during any inspection required by Revision 01, dated September 29, 2011.
paragraph (g) of this AD: Before further flight, (iii) Airbus Service Bulletin A320–54–
(a) Effective Date do a detailed inspection for cracking of the 1022, Revision 02, dated July 12, 2013.
This AD becomes effective June 4, 2015. lower and medium spars, in accordance with (2) This paragraph provides credit for
the Accomplishment Instructions of Airbus actions required by paragraphs (h)(2) and (i)
(b) Affected ADs Service Bulletin A320–54–1022, Revision 03, of this AD, if those actions were performed
None. dated April 15, 2014. before the effective date of this AD using
(1) If any damage is found: Before further Airbus Service Bulletin A320–54–1019,
(c) Applicability flight, repair using a method approved by the Revision 01, dated April 10, 2008, which is
This AD applies to the Airbus airplanes Manager, International Branch, ANM–116, not incorporated by reference in this AD.
identified in paragraphs (c)(1) through (c)(4) Transport Airplane Directorate, FAA; or the
of this AD, certificated in any category, (m) Other FAA AD Provisions
European Aviation Safety Agency (EASA); or
except for airplanes on which Airbus Airbus’s EASA Design Organization The following provisions also apply to this
Modification 33844 or Modification 33847, as Approval (DOA). AD:
applicable, has been embodied in (2) If no damage is found: Within 5,000 (1) Alternative Methods of Compliance
production. flight cycles or 7,500 flight hours, whichever (AMOCs): The Manager, International
(1) Airbus Model A318–111 and –112 occurs first after the detailed inspection Branch, ANM–116, Transport Airplane
airplanes. specified in the introductory text to Directorate, FAA, has the authority to
(2) Airbus Model A319–111, –112, –113, paragraph (h) of this AD, modify the airplane, approve AMOCs for this AD, if requested
–114, –115, –131, –132, and –133 airplanes. in accordance with the Accomplishment using the procedures found in 14 CFR 39.19.
(3) Airbus Model A320–211, –212, –214, Instructions of Airbus Service Bulletin A320– In accordance with 14 CFR 39.19, send your
–231, –232, and –233 airplanes. 54–1019, Revision 02, dated April 15, 2014. request to your principal inspector or local
(4) Airbus Model A321–111, –112, –131, Flight Standards District Office, as
(i) Optional Terminating Action appropriate. If sending information directly
–211, –212, –213, –231, and –232 airplanes.
Modification of an airplane by installation to the International Branch, send it to ATTN:
rmajette on DSK2VPTVN1PROD with RULES
(d) Subject of corner fittings having P/N Sanjay Ralhan, Aerospace Engineer,
Air Transport Association (ATA) of D0041092120000 (RH) and P/N International Branch, ANM–116, Transport
America Code 54, Nacelles/pylons. D0041092120100 (LH) on both pylons, in Airplane Directorate, FAA, 1601 Lind
accordance with the Accomplishment Avenue SW., Renton, WA 98057–3356;
(e) Reason Instructions of Airbus Service Bulletin A320– telephone 425–227–1405; fax 425–227–1149.
This AD was prompted by reports of cracks 54–1019, Revision 02, dated April 15, 2014, Information may be emailed to: 9-ANM-116-
on the forward corner fittings of engine pylon constitutes terminating action for the AMOC-REQUESTS@faa.gov. Before using
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![24210 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations
any approved AMOC, notify your appropriate 202–741–6030, or go to: http:// including slot canyons, windows, fins,
principal inspector, or lacking a principal www.archives.gov/federal-register/cfr/ibr- and spires called ‘‘hoodoos.’’ Because
inspector, the manager of the local flight locations.html. the park transcends 2,500 feet of
standards district office/certificate holding elevation, the park exists in three
Issued in Renton, Washington, on April 17,
district office. The AMOC approval letter
must specifically reference this AD.
2015. distinct climatic zones characterized by
(2) Contacting the Manufacturer: For any Victor Wicklund, spruce/fir forest, ponderosa pine forest,
requirement in this AD to obtain corrective Acting Manager, Transport Airplane and pinyon pine/juniper woodlands.
actions from a manufacturer, the action must Directorate, Aircraft Certification Service. The diversity of forest and meadow
be accomplished using a method approved [FR Doc. 2015–09811 Filed 4–29–15; 8:45 am] habitats provides a high degree of plant
by the Manager, International Branch, ANM– BILLING CODE 4910–13–P and animal diversity. BRCA is also one
116, Transport Airplane Directorate, FAA; or of the best places to experience a truly
the EASA; or Airbus’s EASA DOA. If dark night sky.
approved by the DOA, the approval must The park’s purpose statement, which
include the DOA-authorized signature. DEPARTMENT OF THE INTERIOR provides the foundation for park
(3) Required for Compliance: Except as management, administration, and use
required by paragraph (i) of this AD: If any National Park Service
service information contains procedures or
decisions, states that ‘‘Bryce Canyon
tests that are identified as RC, those 36 CFR Part 7 National Park protects and conserves
procedures and tests must be done to comply resources integral to a landscape of
with this AD; any procedures or tests that are [NPS–BRCA–17884; PA.PD191235A.00.3] unusual scenic beauty exemplified by
not identified as RC are recommended. Those RIN 1024–AE23
highly colored and fantastically eroded
procedures and tests that are not identified geological features, including rock fins
as RC may be deviated from using accepted Special Regulations, Areas of the and spires, for the benefit and
methods in accordance with the operator’s enjoyment of the people.’’ (May 2014
maintenance or inspection program without
National Park System, Bryce Canyon
National Park, Bicycling Foundation Document). The park’s
obtaining approval of an AMOC, provided Foundation Document identifies
the procedures and tests identified as RC can AGENCY: National Park Service, Interior.
be done and the airplane can be put back in
‘‘increased use of alternative
a serviceable condition. Any substitutions or ACTION: Final rule. transportation (e.g., biking, hiking)
changes to procedures or tests identified as within and surrounding the park’’ as an
RC require approval of an AMOC. SUMMARY: The National Park Service is opportunity to protect clean air—one of
planning to construct a paved, multi-use the fundamental resources of the park.
(n) Related Information visitor path in Bryce Canyon National The proposal to construct a multi-use
(1) Refer to Mandatory Continuing Park. The path will be approximately path in the park will support the park’s
Airworthiness Information EASA 6.2 miles long and be open to several purpose statement by providing a new
Airworthiness Directive 2014–0064, dated uses, including running, walking, and opportunity for safe enjoyment and
March 14, 2014, for related information. This bicycling. National Park Service
MCAI may be found in the AD docket on the
protection of the fundamental resources
Internet at http://www.regulations.gov/
regulations require promulgation of a in the park.
#!documentDetail;D=FAA-2014-0589-0003. special regulation to designate new
routes for bicycle use off park roads and Purpose of the Multi-Use Path
(2) Service information identified in this
AD that is not incorporated by reference is outside developed areas. The primary purpose of the multi-use
available at the addresses specified in DATES: This rule is effective June 1, path is to relieve safety problems for
paragraphs (o)(3) and (o)(4) of this AD. 2015. visitors of all ages who choose to use
non-motorized transportation to
(o) Material Incorporated by Reference FOR FURTHER INFORMATION CONTACT: experience the park and adjacent United
(1) The Director of the Federal Register Daniel J. Cloud, Chief of Facility States Forest Service (USFS) areas near
approved the incorporation by reference Management, Bryce Canyon National Bryce Canyon City. Increases in
(IBR) of the service information listed in this Park, P.O. Box 640201, Bryce Canyon,
paragraph under 5 U.S.C. 552(a) and 1 CFR visitation of the park (30% increase
UT 84764–0201. Phone: (435) 834–4720. between 2008 and 2012) are leading to
part 51.
(2) You must use this service information
Email: daniel_cloud@nps.gov. transportation system capacity problems
as applicable to do the actions required by SUPPLEMENTARY INFORMATION: and traffic congestion. Cyclists and
this AD, unless this AD specifies otherwise. pedestrians need a way to travel to and
(i) Airbus Service Bulletin A320–54–1019, Background
within the park that is safer, provides a
Revision 02, dated April 15, 2014. Bryce Canyon National Park (BRCA or better visitor experience, and promotes
(ii) Airbus Service Bulletin A320–54–1022, park) is in south-central Utah. The park non-motorized travel between nearby
Revision 03, dated April 15, 2014. encompasses approximately 35,835 communities and the park as well as
(3) For service information identified in
acres and ranges between 6,600 and between key destinations in the park.
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice 9,100 feet in elevation. BRCA was The path will enhance the park’s
Bellonte, 31707 Blagnac Cedex, France; originally established as a national transportation system by connecting the
telephone +33 5 61 93 36 96; fax +33 5 61 monument by presidential proclamation park’s gateway communities with high
93 44 51; email account.airworth-eas@ in 1923. The park was renamed Utah visitor use areas along the canyon rim
airbus.com; Internet http://www.airbus.com. National Park in 1924, and the name in the Bryce Amphitheater and with
(4) You may view this service information was changed to Bryce Canyon National other key features of the park. The
at the FAA, Transport Airplane Directorate, Park in 1928. proposed path will also connect to the
1601 Lind Avenue SW., Renton, WA. For The park’s most noted feature is the existing transportation system,
rmajette on DSK2VPTVN1PROD with RULES
information on the availability of this eroded landscape below the east rim of including visitor shuttle buses, hiking
material at the FAA, call 425–227–1221.
(5) You may view this service information
the Paunsaugunt Plateau. The erosional trails and walking paths, parking lots,
that is incorporated by reference at the force of frost-wedging and the and roads. This will link major visitor
National Archives and Records dissolving power of rainwater have attractions and facilities with both non-
Administration (NARA). For information on worn away the colorful and weak motorized and motorized transportation
the availability of this material at NARA, call limestone rock into bizarre shapes, modes. Visitor safety will be improved
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Document Created: 2018-02-21 10:14:56
Document Modified: 2018-02-21 10:14:56
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective June 4, 2015. | |
| 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. | |
| FR Citation | 80 FR 24207 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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