80 FR 26487 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 89 (May 8, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 89 (May 8, 2015)
| Page Range | 26487-26490 | |
| FR Document | 2015-10948 |
[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)] [Proposed Rules] [Pages 26487-26490] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-10948] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-155-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This proposed AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would require replacing the clips, the shear webs, and angles, including doing all applicable related investigative [[Page 26488]] actions, and repair if necessary. We are proposing this AD to prevent fatigue damage on the clips, shear webs, and angles, which could affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 22, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1277; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-155-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a limit of validity (LOV) of the engineering data that support the structural maintenance program under 14 CFR 26.21. This proposed AD is the result of an assessment of the previously established programs by the DAH during the process of establishing the LOV for Airbus Model A319, A320, and A321 series airplanes. The actions specified in this proposed AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0177, dated July 25, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319, A320, and A321 series airplanes. The MCAI states: During the A320 fatigue test campaign for Extended Service Goal (ESG), it was determined that fatigue damage could appear on the clips, shear webs and angles at rear fuselage section 19, on Frame (FR) 72 and FR74. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus developed a modification, which has been published through Airbus Service Bulletin (SB) A320-53-1266 for in-service application to allow aeroplanes to operate up to the new ESG limit. For the reasons described above, this [EASA] AD requires replacement of the affected clips, shear webs and angles at rear fuselage section 19, FR72 and FR74 [including all applicable related investigative actions and repair if any cracking is found]. Related investigative actions include rotating probe testing for cracking of the fastener holes and high frequency eddy current inspections for cracking of the stringers. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-1277. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-53-1266, Revision 01, dated June 20, 2013. This service information describes procedures for replacing clips, shear webs, and angles at rear fuselage section 19, FR72 and FR74. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 44 airplanes of U.S. registry. We also estimate that it would take about 110 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $411,400, or $9,350 per product. We have received no definitive data on the costs of required parts. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby [[Page 26489]] 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2015-1277; Directorate Identifier 2014-NM- 155-AD. (a) Comments Due Date We must receive comments by June 22, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 30975 has been embodied in production. (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (2) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Replace the clips, shear webs, and angles at rear fuselage section 19, frame (FR)72 and FR74, and do all applicable related investigative actions before further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1266, Revision 01, dated June 20, 2013. If any crack is found during any related investigative action required by this AD: 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). (1) Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since the airplane's first flight. (2) Within 30 days after the effective date of this AD. (h) Additional Replacement for Airplanes on Which the Replacement Required by Paragraph (g) of This AD Is Done Before 30,000 Flight Cycles or 60,000 Flight Hours For airplanes on which the replacement of clips, shear webs, and angles specified in Airbus Service Bulletin A320-53-1266 is done before accumulating 30,000 flight cycles or 60,000 flight hours, whichever occurred first since the airplane's first flight: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after that replacement, do the replacement specified in paragraph (g) of this AD. (i) Credit for Previous Actions Except as required by paragraph (h) of this AD: This paragraph provides credit for the replacement required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1266, dated January 11, 2013, which is not incorporated by reference in this AD. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0177, dated July 25, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by [[Page 26490]] searching for and locating Docket No. FAA-2015-1277. (2) 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 service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on April 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-10948 Filed 5-7-15; 8:45 am] BILLING CODE 4910-13-P
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(h) Retained Restrictions on Alternative or within 90 days the effective date of this the approval must include the DOA-
Actions, Intervals, and/or CDCCLs, With a AD, whichever occurs later. authorized signature.
New Exception
(j) New Restrictions on Alternative Actions, (m) Related Information
This paragraph restates the requirements of Intervals, and/or (CDCCLs) (1) Refer to Mandatory Continuing
paragraph (k) of AD 2011–21–06,
After the maintenance or inspection Airworthiness Information (MCAI) EASA
Amendment 39–16829 (76 FR 64788, October
program, as applicable, has been revised as Airworthiness Directive 2014–0043, dated
19, 2011), with a new exception. Except as
required by paragraph (i) of this AD, no February 21, 2014, for related information.
required by paragraph (i) of this AD, after
alternative actions (e.g., inspections), This MCAI may be found in the AD docket
accomplishing the revision required by
intervals, and/or CDCCLs may be used unless on the Internet at http://www.regulations.gov
paragraph (g) of this AD, no alternative the actions, intervals, and/or CDCCLs are
actions (e.g., inspections), intervals, and/or by searching for and locating Docket No.
approved as an AMOC in accordance with FAA–2015–1279.
CDCCLs may be used unless the actions, the procedures specified in paragraph (l) of
intervals, and/or CDCCLs are approved as an (2) For service information identified in
this AD. this AD, contact BAE SYSTEMS (Operations)
alternative method of compliance (AMOC) in
accordance with the procedures specified in (k) Credit for Previous Actions Limited, Customer Information Department,
paragraph (l) of this AD. Prestwick International Airport, Ayrshire,
This paragraph restates the provisions of KA9 2RW, Scotland, United Kingdom;
(i) New Maintenance or Inspection Program paragraph (j) of AD 2011–21–06, Amendment telephone +44 1292 675207; fax +44 1292
Revision 39–16829 (76 FR 64788, October 19, 2011). 675704; email RApublications@
This paragraph provides credit for actions baesystems.com; Internet http://
Within 90 days after the effective date of required by paragraph (g) of this AD, if those
this AD: Revise the maintenance or www.baesystems.com/Businesses/
actions were performed before November 23, RegionalAircraft/index.htm. You may view
inspection program, as applicable, by 2011 (the effective date of AD 2011–21–06),
incorporating Subjects 05–10–10, this service information at the FAA,
in accordance with Subjects 05–10–10, Transport Airplane Directorate, 1601 Lind
‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Airworthiness Limitations’’; 05–10–20,
‘‘Certification Maintenance Requirements’’; Avenue SW., Renton, WA. For information
‘‘Certification Maintenance Requirements’’; on the availability of this material at the
and 05–10–30, ‘‘Critical Design Configuration and 05–10–30, ‘‘Critical Design Configuration
Control Limitations (CDCCL)—Fuel System’’; FAA, call 425–227–1221.
Control Limitations (CDCCL)—Fuel System’’;
of Chapter 05, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ Issued in Renton, Washington, on April 29,
of the BAE Systems (Operations) Limited J41 of the BAE Systems (Operations) Limited 2015.
AMM, Revision 38, dated September 15, Jetstream Series 4100 AMM, Revision 33,
2013. The initial compliance times for the Jeffrey E. Duven,
dated February 15, 2010; which are not Manager, Transport Airplane Directorate,
tasks are at the applicable times specified in incorporated by reference in this AD.
paragraphs (i)(1), (i)(2), and (i)(3) of this AD. Aircraft Certification Service.
Doing the actions required by this paragraph (l) Other FAA AD Provisions [FR Doc. 2015–11023 Filed 5–7–15; 8:45 am]
terminates the requirements of paragraph (g) The following provisions also apply to this BILLING CODE 4910–13–P
of this AD. AD:
(1) For replacement tasks of life limited (1) Alternative Methods of Compliance
parts specified in Subject 05–10–10, (AMOCs): The Manager, International
‘‘Airworthiness Limitations,’’ of Chapter 05,
DEPARTMENT OF TRANSPORTATION
Branch, ANM–116, Transport Airplane
‘‘Airworthiness Limitations,’’ of the BAE Directorate, FAA, has the authority to
Systems (Operations) Limited J41 AMM, Federal Aviation Administration
approve AMOCs for this AD, if requested
Revision 38, dated September 15, 2013: Prior using the procedures found in 14 CFR 39.19.
to the applicable flight cycles (landings) or 14 CFR Part 39
In accordance with 14 CFR 39.19, send your
flight hours (flying hours) on the part request to your principal inspector or local [Docket No. FAA–2015–1277; Directorate
specified in the ‘‘Mandatory Life Limits’’ Flight Standards District Office, as Identifier 2014–NM–155–AD]
column in Subject 05–10–10, or within 90 appropriate. If sending information directly
days after the effective date of this AD, to the International Branch, send it to ATTN: RIN 2120–AA64
whichever occurs later. Todd Thompson, Aerospace Engineer,
(2) For structurally significant item tasks International Branch, ANM–116, Transport Airworthiness Directives; Airbus
specified in Subject 05–10–10, Airplane Directorate, FAA, 1601 Lind Airplanes
‘‘Airworthiness Limitations,’’ of Chapter 05, Avenue SW., Renton, WA 98057–3356;
‘‘Airworthiness Limitations,’’ of the BAE telephone: 425–227–1175; fax 425–227–1149. AGENCY: Federal Aviation
Systems (Operations) Limited J41 AMM, Information may be emailed to: 9-ANM-116- Administration (FAA), DOT.
Revision 38, dated September 15, 2013: Prior AMOC-REQUESTS@faa.gov. ACTION: Notice of proposed rulemaking
to the accumulation of the applicable flight (i) Before using any approved AMOC, (NPRM).
cycles specified in the ‘‘Initial Inspection’’ notify your appropriate principal inspector,
column in Subject 05–10–10, or within 90 or lacking a principal inspector, the manager SUMMARY: We propose to adopt a new
days after the effective date of this AD, of the local flight standards district office/ airworthiness directive (AD) for certain
whichever occurs later. certificate holding district office. The AMOC Airbus Model A319, A320, and A321
(3) For certification maintenance approval letter must specifically reference series airplanes. This proposed AD was
requirements tasks specified in Subject 05– this AD.
10–20, ‘‘Certification Maintenance prompted by fatigue testing that
(ii) AMOCs approved previously for AD
Requirements,’’ of Chapter 05, 2011–21–06, Amendment 39–16829 (76 FR determined fatigue damage could
‘‘Airworthiness Limitations,’’ of the BAE 64788, October 19, 2011), are not approved appear on clips, shear webs, and angles
Systems (Operations) Limited J41 AMM, as AMOCs with this AD. at certain rear fuselage sections and
Revision 38, dated September 15, 2013: Prior (2) Contacting the Manufacturer: As of the certain frames. This proposed AD is
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
to the accumulation of the applicable flight effective date of this AD, for any requirement intended to complete certain mandated
hours specified in the ‘‘Time Between in this AD to obtain corrective actions from programs intended to support the
Checks’’ column in Subject 05–10–20, or a manufacturer, the action must be airplane reaching its limit of validity
within 90 days after the effective date of this accomplished using a method approved by (LOV) of the engineering data that
AD, whichever occurs later; except for tasks the Manager, International Branch, ANM–
that specify ‘‘first flight of the day’’ in the 116, Transport Airplane Directorate, FAA; or
support the established structural
‘‘Time Between Checks’’ column in Subject the European Aviation Safety Agency maintenance program. This proposed
05–10–20, the initial compliance time is the (EASA); or BAE Systems (Operations) AD would require replacing the clips,
first flight of the next day after doing the Limited’s EASA Design Organization the shear webs, and angles, including
revision required by paragraph (j) of this AD, Approval (DOA). If approved by the DOA, doing all applicable related investigative
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actions, and repair if necessary. We are Comments Invited been published through Airbus Service
proposing this AD to prevent fatigue Bulletin (SB) A320–53–1266 for in-service
We invite you to send any written application to allow aeroplanes to operate up
damage on the clips, shear webs, and relevant data, views, or arguments about to the new ESG limit.
angles, which could affect the structural this proposed AD. Send your comments For the reasons described above, this
integrity of the airplane. to an address listed under the [EASA] AD requires replacement of the
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. affected clips, shear webs and angles at rear
this proposed AD by June 22, 2015. FAA–2015–1277; Directorate Identifier fuselage section 19, FR72 and FR74
2014–NM–155–AD’’ at the beginning of [including all applicable related investigative
ADDRESSES: You may send comments, actions and repair if any cracking is found].
using the procedures found in 14 CFR your comments. We specifically invite
11.43 and 11.45, by any of the following comments on the overall regulatory, Related investigative actions include
methods: economic, environmental, and energy rotating probe testing for cracking of the
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will fastener holes and high frequency eddy
http://www.regulations.gov. Follow the consider all comments received by the current inspections for cracking of the
instructions for submitting comments. closing date and may amend this stringers. You may examine the MCAI
proposed AD based on those comments. in the AD docket on the Internet at
• Fax: 202–493–2251.
We will post all comments we http://www.regulations.gov by searching
• Mail: U.S. Department of for and locating Docket No. FAA–2015–
Transportation, Docket Operations, receive, without change, to http://
www.regulations.gov, including any 1277.
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey personal information you provide. We Related Service Information Under 1
Avenue SE., Washington, DC 20590. will also post a report summarizing each CFR Part 51
substantive verbal contact we receive
• Hand Delivery: U.S. Department of Airbus has issued Service Bulletin
about this proposed AD.
Transportation, Docket Operations, A320–53–1266, Revision 01, dated June
M–30, West Building Ground Floor, Discussion 20, 2013. This service information
Room W12–140, 1200 New Jersey As described in FAA Advisory describes procedures for replacing clips,
Avenue SE., Washington, DC, between 9 Circular 120-104 (http://www.faa.gov/ shear webs, and angles at rear fuselage
a.m. and 5 p.m., Monday through documentLibrary/media/Advisory_ section 19, FR72 and FR74. The actions
Friday, except Federal holidays. Circular/120-104.pdf), several programs described in this service information are
For service information identified in have been developed to support intended to correct the unsafe condition
this proposed AD, contact Airbus, initiatives that will ensure the identified in the MCAI. This service
Airworthiness Office—EIAS, 1 Rond continued airworthiness of aging information is reasonably available
Point Maurice Bellonte, 31707 Blagnac airplane structure. The last element of because the interested parties have
Cedex, France; telephone +33 5 61 93 36 those initiatives is the requirement to access to it through their normal course
96; fax +33 5 61 93 44 51; email establish a limit of validity (LOV) of the of business or by the means identified
account.airworth-eas@airbus.com; engineering data that support the in the ADDRESSES section of this NPRM.
Internet http://www.airbus.com. You structural maintenance program under
may view this referenced service FAA’s Determination and Requirements
14 CFR 26.21. This proposed AD is the of This Proposed AD
information at the FAA, Transport result of an assessment of the previously
Airplane Directorate, 1601 Lind Avenue established programs by the DAH This product has been approved by
SW., Renton, WA. For information on during the process of establishing the the aviation authority of another
the availability of this material at the LOV for Airbus Model A319, A320, and country, and is approved for operation
FAA, call 425–227–1221. A321 series airplanes. The actions in the United States. Pursuant to our
specified in this proposed AD are bilateral agreement with the State of
Examining the AD Docket Design Authority, we have been notified
necessary to complete certain programs
You may examine the AD docket on to ensure the continued airworthiness of of the unsafe condition described in the
the Internet at http:// aging airplane structure and to support MCAI and service information
www.regulations.gov by searching for an airplane reaching its LOV. referenced above. We are proposing this
and locating Docket No. FAA–2015– The European Aviation Safety Agency AD because we evaluated all pertinent
1277; or in person at the Docket (EASA), which is the Technical Agent information and determined an unsafe
Management Facility between 9 a.m. for the Member States of the European condition exists and is likely to exist or
and 5 p.m., Monday through Friday, Union, has issued EASA Airworthiness develop on other products of these same
except Federal holidays. The AD docket Directive 2014–0177, dated July 25, type designs.
contains this proposed AD, the 2014 (referred to after this as the Costs of Compliance
regulatory evaluation, any comments Mandatory Continuing Airworthiness
received, and other information. The We estimate that this proposed AD
Information, or ‘‘the MCAI’’), to correct
street address for the Docket Operations affects 44 airplanes of U.S. registry.
an unsafe condition for certain Airbus We also estimate that it would take
office (telephone 800–647–5527) is in Model A319, A320, and A321 series
the ADDRESSES section. Comments will about 110 work-hours per product to
airplanes. The MCAI states: comply with the basic requirements of
be available in the AD docket shortly
During the A320 fatigue test campaign for this proposed AD. The average labor
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
after receipt. Extended Service Goal (ESG), it was rate is $85 per work-hour. Based on
FOR FURTHER INFORMATION CONTACT: determined that fatigue damage could appear these figures, we estimate the cost of
Sanjay Ralhan, Aerospace Engineer, on the clips, shear webs and angles at rear
this proposed AD on U.S. operators to
International Branch, ANM–116, fuselage section 19, on Frame (FR) 72 and
FR74. be $411,400, or $9,350 per product.
Transport Airplane Directorate, FAA, We have received no definitive data
1601 Lind Avenue SW., Renton, WA This condition, if not detected and
corrected, could affect the structural integrity on the costs of required parts.
98057–3356; telephone 425–227–1405; of the aeroplane. According to the manufacturer, some
fax 425–227–1149. To address this potential unsafe condition, of the costs of this proposed AD may be
SUPPLEMENTARY INFORMATION: Airbus developed a modification, which has covered under warranty, thereby
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reducing the cost impact on affected PART 39—AIRWORTHINESS Safety Agency (EASA); or Airbus’s EASA
individuals. We do not control warranty DIRECTIVES Design Organization Approval (DOA).
coverage for affected individuals. As a (1) Before exceeding 48,000 flight cycles or
■ 1. The authority citation for part 39 96,000 flight hours, whichever occurs first
result, we have included all costs in our since the airplane’s first flight.
cost estimate. continues to read as follows:
(2) Within 30 days after the effective date
Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. of this AD.
§ 39.13 [Amended] (h) Additional Replacement for Airplanes on
Title 49 of the United States Code
■ 2. The FAA amends § 39.13 by adding Which the Replacement Required by
specifies the FAA’s authority to issue Paragraph (g) of This AD Is Done Before
rules on aviation safety. Subtitle I, the following new airworthiness 30,000 Flight Cycles or 60,000 Flight Hours
section 106, describes the authority of directive (AD):
For airplanes on which the replacement of
the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2015–1277; clips, shear webs, and angles specified in
Aviation Programs,’’ describes in more Directorate Identifier 2014–NM–155–AD. Airbus Service Bulletin A320–53–1266 is
detail the scope of the Agency’s (a) Comments Due Date done before accumulating 30,000 flight
authority. cycles or 60,000 flight hours, whichever
We must receive comments by June 22, occurred first since the airplane’s first flight:
We are issuing this rulemaking under 2015.
the authority described in ‘‘Subtitle VII, Within 30,000 flight cycles or 60,000 flight
(b) Affected ADs hours, whichever occurs first after that
Part A, Subpart III, Section 44701: replacement, do the replacement specified in
General requirements.’’ Under that None. paragraph (g) of this AD.
section, Congress charges the FAA with (c) Applicability
promoting safe flight of civil aircraft in (i) Credit for Previous Actions
This AD applies to the airplanes identified Except as required by paragraph (h) of this
air commerce by prescribing regulations
in paragraphs (c)(1), (c)(2), and (c)(3) of this AD: This paragraph provides credit for the
for practices, methods, and procedures AD, certificated in any category, all
the Administrator finds necessary for replacement required by paragraph (g) of this
manufacturer serial numbers, except those on AD, if those actions were performed before
safety in air commerce. This regulation which Airbus Modification 30975 has been the effective date of this AD using Airbus
is within the scope of that authority embodied in production. Service Bulletin A320–53–1266, dated
because it addresses an unsafe condition (1) Airbus Model A319–111, –112, –113, January 11, 2013, which is not incorporated
that is likely to exist or develop on –114, –115, –131, –132, and –133 airplanes. by reference in this AD.
products identified in this rulemaking (2) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes. (j) Other FAA AD Provisions
action.
(3) Airbus Model A321–111, –112, –131, The following provisions also apply to this
Regulatory Findings –211, –212, –213, –231, and –232 airplanes. AD:
(1) Alternative Methods of Compliance
We determined that this proposed AD (d) Subject
(AMOCs): The Manager, International
would not have federalism implications Air Transport Association (ATA) of Branch, ANM–116, Transport Airplane
under Executive Order 13132. This America Code 53, Fuselage. Directorate, FAA, has the authority to
proposed AD would not have a (e) Reason approve AMOCs for this AD, if requested
substantial direct effect on the States, on using the procedures found in 14 CFR 39.19.
This AD was prompted by fatigue testing In accordance with 14 CFR 39.19, send your
the relationship between the national that determined fatigue damage could appear
Government and the States, or on the request to your principal inspector or local
on clips, shear webs, and angles at certain Flight Standards District Office, as
distribution of power and rear fuselage sections and certain frames. appropriate. If sending information directly
responsibilities among the various This AD is intended to complete certain to the International Branch, send it to ATTN:
levels of government. mandated programs intended to support the Sanjay Ralhan, Aerospace Engineer,
For the reasons discussed above, I airplane reaching its limit of validity (LOV) International Branch, ANM–116, Transport
certify this proposed regulation: of the engineering data that support the Airplane Directorate, FAA, 1601 Lind
established structural maintenance program. Avenue SW., Renton, WA 98057–3356;
1. Is not a ‘‘significant regulatory We are issuing this AD to prevent fatigue telephone 425–227–1405; fax 425–227–1149.
action’’ under Executive Order 12866; damage on the clips, shear webs, and angles, Information may be emailed to: 9-ANM-116-
2. Is not a ‘‘significant rule’’ under the which could affect the structural integrity of AMOC-REQUESTS@faa.gov. Before using
DOT Regulatory Policies and Procedures the airplane. any approved AMOC, notify your appropriate
(44 FR 11034, February 26, 1979); principal inspector, or lacking a principal
(f) Compliance
inspector, the manager of the local flight
3. Will not affect intrastate aviation in Comply with this AD within the standards district office/certificate holding
Alaska; and compliance times specified, unless already district office. The AMOC approval letter
4. Will not have a significant done. must specifically reference this AD.
economic impact, positive or negative, (g) Replacement (2) Contacting the Manufacturer: For any
on a substantial number of small entities requirement in this AD to obtain corrective
At the later of the times specified in actions from a manufacturer, the action must
under the criteria of the Regulatory paragraphs (g)(1) and (g)(2) of this AD:
Flexibility Act. be accomplished using a method approved
Replace the clips, shear webs, and angles at by the Manager, International Branch, ANM–
List of Subjects in 14 CFR Part 39 rear fuselage section 19, frame (FR)72 and 116, Transport Airplane Directorate, FAA; or
FR74, and do all applicable related
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the EASA; or Airbus’s EASA DOA. If
Air transportation, Aircraft, Aviation investigative actions before further flight, in approved by the DOA, the approval must
safety, Incorporation by reference, accordance with the Accomplishment include the DOA-authorized signature.
Safety. Instructions of Airbus Service Bulletin A320–
53–1266, Revision 01, dated June 20, 2013. (k) Related Information
The Proposed Amendment If any crack is found during any related (1) Refer to Mandatory Continuing
investigative action required by this AD: Airworthiness Information (MCAI) EASA
Accordingly, under the authority Before further flight, repair using a method Airworthiness Directive 2014–0177, dated
delegated to me by the Administrator, approved by the Manager, International July 25, 2014, for related information. This
the FAA proposes to amend 14 CFR part Branch, ANM–116, Transport Airplane MCAI may be found in the AD docket on the
39 as follows: Directorate, FAA; or the European Aviation Internet at http://www.regulations.gov by
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![26490 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
searching for and locating Docket No. FAA– 11.43 and 11.45, by any of the following economic, environmental, and energy
2015–1277. methods: aspects of this proposed AD. We will
(2) For service information identified in • Federal eRulemaking Portal: Go to consider all comments received by the
this AD, contact Airbus, Airworthiness http://www.regulations.gov. Follow the closing date and may amend this
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
instructions for submitting comments. proposed AD based on those comments.
telephone +33 5 61 93 36 96; fax +33 5 61 • Fax: 202–493–2251. We will post all comments we
93 44 51; email account.airworth-eas@ • Mail: U.S. Department of receive, without change, to http://
airbus.com; Internet http://www.airbus.com. Transportation, Docket Operations, www.regulations.gov, including any
You may view this service information at the M–30, West Building Ground Floor, personal information you provide. We
FAA, Transport Airplane Directorate, 1601 Room W12–140, 1200 New Jersey will also post a report summarizing each
Lind Avenue SW., Renton, WA. For Avenue SE., Washington, DC 20590. substantive verbal contact we receive
information on the availability of this • Hand Delivery: U.S. Department of about this proposed AD.
material at the FAA, call 425–227–1221. Transportation, Docket Operations,
Issued in Renton, Washington, on April 29, M–30, West Building Ground Floor, Discussion
2015. Room W12–140, 1200 New Jersey
Jeffrey E. Duven, Avenue SE., Washington, DC, between 9 Transport Canada Civil Aviation
Manager, Transport Airplane Directorate, a.m. and 5 p.m., Monday through (TCCA), which is the aviation authority
Aircraft Certification Service. Friday, except Federal holidays. for Canada, has issued Canadian
[FR Doc. 2015–10948 Filed 5–7–15; 8:45 am] For service information identified in Airworthiness Directive CF–2014–32,
this proposed AD, contact Bombardier, dated September 8, 2014 (referred to
BILLING CODE 4910–13–P
Inc., 400 Côte Vertu Road West, Dorval, after this as the Mandatory Continuing
Québec H4S 1Y9, Canada; telephone: Airworthiness Information, or ‘‘the
DEPARTMENT OF TRANSPORTATION 514–855–5000; fax: 514–855–7401; MCAI’’), to correct an unsafe condition
email thd.crj@aero.bombardier.com; for certain Bombardier, Inc. Model BD–
Federal Aviation Administration Internet http://www.bombardier.com. 100–1A10 (Challenger 300) airplanes.
You may view this referenced service The MCAI states:
14 CFR Part 39 information at the FAA, Transport There have been multiple in-service
[Docket No. FAA–2015–0929; Directorate Airplane Directorate, 1601 Lind Avenue reports of chafing found on an electrical
Identifier 2014–NM–218–AD] SW., Renton, WA. For information on wiring harness in the aft equipment bay. An
the availability of this material at the investigation determined that the chafing was
RIN 2120–AA64 attributed to contact between the wiring
FAA, call 425–227–1221.
harness and a neighboring hydraulic line.
Airworthiness Directives; Bombardier, Examining the AD Docket This chafing could cause an electrical short
Inc. Airplanes circuit or lead to a malfunction of the flight
You may examine the AD docket on
AGENCY: Federal Aviation the Internet at http:// control system, the engine indication system,
Administration (FAA), DOT. www.regulations.gov by searching for or the hydraulic power control system; which
and locating Docket No. FAA–2015– could adversely affect the continued safe
ACTION: Notice of proposed rulemaking
0929; or in person at the Docket operation and landing of the aeroplane.
(NPRM). This [Canadian] AD mandates the
Management Facility between 9 a.m.
SUMMARY: We propose to adopt a new inspection [general visual inspection],
and 5 p.m., Monday through Friday,
airworthiness directive (AD) for certain rectification as required [repair of damage
except Federal holidays. The AD docket
(including wear and chafing)], and
Bombardier, Inc. Model BD–100–1A10 contains this proposed AD, the
modification of the wiring harness
(Challenger 300) airplanes. This regulatory evaluation, any comments installation to ensure the correct wiring
proposed AD was prompted by multiple received, and other information. The routing and a minimum clearance between
reports of chafing found on an electrical street address for the Docket Operations the wire and the hydraulic line is
wiring harness in the aft equipment bay, office (telephone: 800–647–5527) is in maintained.
caused by contact between the wiring the ADDRESSES section. Comments will
harness and a neighboring hydraulic be available in the AD docket shortly You may examine the MCAI in the
line. This proposed AD would require after receipt. AD docket on the Internet at http://
an inspection, repair if necessary, and FOR FURTHER INFORMATION CONTACT: www.regulations.gov by searching for
modification of the wiring harness Assata Dessaline, Aerospace Engineer, and locating Docket No. FAA–2015–
installation to ensure that the wiring Avionics and Service Branch, ANE–172, 0929.
harness routing is correct and a FAA, New York Aircraft Certification
minimum clearance between the wire Related Service Information Under 1
Office, 1600 Stewart Avenue, Suite 410, CFR Part 51
and the hydraulic line is maintained. Westbury, NY 11590; telephone: 516–
We are proposing this AD to detect and 228–7301; fax: 516–794–5531. Bombardier, Inc. has issued Service
correct chafing on an electrical wiring Bulletin 100–24–24, dated June 6, 2014.
SUPPLEMENTARY INFORMATION:
harness, which could cause an electrical The service information describes
short circuit or lead to a malfunction of Comments Invited procedures for an inspection, repair if
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the flight control system, the engine We invite you to send any written necessary, and modification to reroute
indication system, or the hydraulic relevant data, views, or arguments about wiring harness installation to prevent
power control system, and adversely this proposed AD. Send your comments contact with the hydraulic line. This
affect the continued safe operation and to an address listed under the service information is reasonably
landing of the airplane. ADDRESSES section. Include ‘‘Docket No. available because the interested parties
DATES: We must receive comments on FAA–2015–0929; Directorate Identifier have access to it through their normal
this proposed AD by June 22, 2015. 2014–NM–218–AD’’ at the beginning of course of business or by the means
ADDRESSES: You may send comments, your comments. We specifically invite identified in the ADDRESSES section of
using the procedures found in 14 CFR comments on the overall regulatory, this NPRM.
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Document Created: 2018-02-21 10:24:39
Document Modified: 2018-02-21 10:24:39
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 22, 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 26487 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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