81 FR 33438 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 102 (May 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 102 (May 26, 2016)
| Page Range | 33438-33441 | |
| FR Document | 2016-12352 |
[Federal Register Volume 81, Number 102 (Thursday, May 26, 2016)] [Proposed Rules] [Pages 33438-33441] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-12352] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-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 A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, - 212, -213, -231, and -232 airplanes. This proposed AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This proposed AD would require a one-time eddy current conductivity measurements of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are proposing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by July 11, 2016. 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. 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-2016- 6893; 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. [[Page 33439]] 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-2016-6893; Directorate Identifier 2015-NM-181-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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0218, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318-112, A319-111, -112, -115, -132, and -133, A320-214, -232, and - 233, and A321-211, -212, -213, -231, and -232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that wrong aluminum alloy were delivered by a supplier for several structural parts. The results of the investigations highlighted that 0.04% of the stock could be impacted by this wrong material. Structural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-53-1298 and SB A320-53-1299 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one- time Special Detailed Inspection (SDI) [eddy current conductivity measurements] of certain cabin and cargo compartment parts for material identification and, depending on findings, replacement with serviceable parts. 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-2016- 6893. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A320-53-1298 and A320-53-1299, both dated February 16, 2015; both including Appendices 01, 02, and 03, dated February 16, 2015. The service information describes procedures for a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement of any affected part with a serviceable part. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This 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 167 airplanes of U.S. registry. We also estimate that it would take about 1 work-hour 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 $14,195, or $85 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed 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 available 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. [[Page 33440]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2016-6893; Directorate Identifier 2015-NM- 181-AD. (a) Comments Due Date We must receive comments by July 11, 2016. (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; manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 6159 inclusive, 6161 and 6162. (1) Airbus Model A318-112 airplanes. (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes. (3) Airbus Model A320-214, -232, and -233 airplanes. (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a quality control review of the final assembly line which determined that the wrong aluminum alloy was used to manufacture several structural parts. We are issuing this AD to detect and correct structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Measurement Within 6 years after the effective date of this AD, but not exceeding 12 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurements (with 60kHz and 480kHz) of the cabin and cargo compartment structural parts identified in the ``Affected P/ N'' column of table 1 to paragraphs (g) and (h) of this AD to determine if an incorrect aluminum alloy was used, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320-53-1298, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cabin parts); and A320-53-1299, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cargo parts). Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/ Installed ------------------------------------------------------------------------ Acceptable Affected P/N replacement P/N Area ------------------------------------------------------------------------ D5347120720000.................. D5347120720051.... Cabin. D5347120720100.................. D5347120720151.... Cabin. D5347120920000.................. D5347120920051.... Cabin. D5347120920100.................. D5347120920151.... Cabin. D5347118820400.................. D5347118820451.... Cabin. D5347717620000.................. D5347717620051.... Cargo. D5357020620000.................. D5357020620051.... Cargo. D5358526421200.................. D5358526421251.... Cargo. D5358526421400.................. D5358526421400.... Cargo. D5358526421000.................. D5358526421051.... Cargo. D5358513120001.................. D5358513120051.... Cargo. ------------------------------------------------------------------------ (h) Replacement If during the inspection required by paragraph (g) of this AD, any affected part having a part number (P/N) specified in table 1 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of the applicable service information identified in paragraph (g) of this AD: Before further flight, replace with an acceptable replacement part having a P/N specified in table 1 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320-53- 1298, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cabin parts); and A320-53-1299, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cargo parts). (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using 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 European Aviation Safety Agency (EASA); or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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 an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0218, dated November 3, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6893. [[Page 33441]] (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: account.airworth-eas@airbus.com; 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 May 17, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-12352 Filed 5-25-16; 8:45 am] BILLING CODE 4910-13-P
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Participation at the Public Meetings in advance will be allowed to speak airplanes, and A321–211, –212, –213,
Commenters who wish to present oral first, others will be scheduled on a first- –231, and –232 airplanes. This proposed
statements at the July 7, 2016, public come-first-served basis. The FAA AD was prompted by a quality control
meeting should submit requests to the reserves the right to exclude some review on the final assembly line, which
FAA no later than June 29, 2016. speakers, if necessary, to obtain determined that the wrong aluminum
Requests should be submitted as balanced viewpoints. The meeting may alloy was used to manufacture several
described in the FOR FURTHER adjourn early if scheduled speakers structural parts. This proposed AD
complete their statements in less time would require a one-time eddy current
INFORMATION CONTACT section of this
than is scheduled for the meeting. conductivity measurements of certain
document and should include a written
(3) The FAA will prepare agendas of cabin and cargo compartment structural
summary of oral remarks to be
speakers and presenters and make the parts to determine if an incorrect
presented and an estimate of time
agendas available at the meeting. aluminum alloy was used, and
needed for the presentation. Preferably,
(4) Speaker time slots may be limited replacement if necessary. We are
please submit requests via email to:
to 3-minute statements. If possible, the proposing this AD to detect and replace
Michael.Hughlett@faa.gov. Requests
FAA will notify speakers if additional structural parts made of incorrect
received after the dates specified above
time is available. aluminum alloy. This condition could
will be scheduled if there is time
(5) The FAA will review and consider result in reduced structural integrity of
available during the meeting; however,
all material presented by participants at the airplane.
the speakers’ names may not appear on
the public meeting. Position papers or DATES: We must receive comments on
the written agenda. To accommodate as
many speakers as possible, the amount materials presenting views or this proposed AD by July 11, 2016.
of time allocated to each speaker may be information related to the draft policy ADDRESSES: You may send comments,
less than the amount of time requested may be accepted at the discretion of the using the procedures found in 14 CFR
to ensure various views can be heard. presiding officer and will be 11.43 and 11.45, by any of the following
See ‘‘Public Meeting Procedures’’ below. subsequently placed in the public methods:
The FAA may have available a docket. The FAA requests that • Federal eRulemaking Portal: Go to
projector and a computer capable of presenters at the meeting provide at http://www.regulations.gov. Follow the
accommodating Word and PowerPoint least 10 copies of all materials for instructions for submitting comments.
distribution to the panel members. • Fax: 202–493–2251.
presentations. Persons requiring any • Mail: U.S. Department of
other kind of audiovisual equipment Presenters may provide other copies to
the audience at their discretion. Transportation, Docket Operations, M–
should notify the FAA when requesting 30, West Building Ground Floor, Room
to be placed on the agenda. (6) We ask each person presenting
comments to provide the technical basis W12–140, 1200 New Jersey Avenue SE.,
The FAA will make every effort to Washington, DC 20590.
accommodate all persons wishing to to support the comments. The most
helpful comments reference a specific • Hand Delivery: Deliver to Mail
attend. Sign and oral interpretation can address above between 9 a.m. and 5
be made available at the meeting, as portion of the policy statement and
explain the reason for any p.m., Monday through Friday, except
well as an assistive listening device, if Federal holidays.
requested 10 calendar days before the recommended change.
For service information identified in
meeting. Issued in Fort Worth, Texas, on May 18, this NPRM, contact Airbus,
2016. Airworthiness Office—EIAS, 1 Rond
Public Meeting Procedures Jorge R. Castillo, Point Maurice Bellonte, 31707 Blagnac
A panel of representatives from the Acting Manager, Rotorcraft Directorate, Cedex, France; telephone: +33 5 61 93
FAA will be present to facilitate the Aircraft Certification Service. 36 96; fax: +33 5 61 93 44 51; email:
meeting in accordance with the [FR Doc. 2016–12526 Filed 5–25–16; 8:45 am] account.airworth-eas@airbus.com;
following procedures: BILLING CODE 4910–13–P Internet: http://www.airbus.com.
(1) The meeting is designed to You may view this referenced service
facilitate the public comment process. information at the FAA, Transport
The meeting will be informal and non- DEPARTMENT OF TRANSPORTATION Airplane Directorate, 1601 Lind Avenue
adversarial. No individual will be SW., Renton, WA. For information on
subject to cross-examination by any Federal Aviation Administration the availability of this material at the
other participant. Government FAA, call 425–227–1221.
representatives on the panel may ask 14 CFR Part 39
questions to clarify statements and to Examining the AD Docket
[Docket No. FAA–2016–6893; Directorate
ensure an accurate record. Any Identifier 2015–NM–181–AD] You may examine the AD docket on
statement made during the meetings by the Internet at http://
a panel member should not be RIN 2120–AA64 www.regulations.gov by searching for
construed as an official position of the and locating Docket No. FAA–2016–
Airworthiness Directives; Airbus
government. 6893; or in person at the Docket
Airplanes
(2) There will be no admission fees or Management Facility between 9 a.m.
other charges to attend or to participate AGENCY: Federal Aviation and 5 p.m., Monday through Friday,
in the public meeting. The meeting will Administration (FAA), DOT. except Federal holidays. The AD docket
jstallworth on DSK7TPTVN1PROD with PROPOSALS
be open to all persons, subject to ACTION: Notice of proposed rulemaking contains this proposed AD, the
availability of space in the meeting (NPRM). regulatory evaluation, any comments
room. The FAA asks that participants received, and other information. The
sign in between 8:30 and 9:00 a.m. on SUMMARY: We propose to adopt a new street address for the Docket Operations
the day of the meeting. The FAA will try airworthiness directive (AD) for certain office (telephone: 800–647–5527) is in
to accommodate all speakers; however if Airbus Model A318–112 airplanes, the ADDRESSES section. Comments will
available time does not allow this, A319–111, –112, –115, –132, and –133 be available in the AD docket shortly
speakers who have contacted the FAA airplanes, A320–214, –232, and –233 after receipt.
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![Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules 33439
FOR FURTHER INFORMATION CONTACT: identification and, depending on findings, Authority for This Rulemaking
Sanjay Ralhan, Aerospace Engineer, replacement with serviceable parts.
Title 49 of the United States Code
International Branch, ANM–116, You may examine the MCAI in the specifies the FAA’s authority to issue
Transport Airplane Directorate, FAA, AD docket on the Internet at http:// rules on aviation safety. Subtitle I,
1601 Lind Avenue SW., Renton, WA www.regulations.gov by searching for section 106, describes the authority of
98057–3356; telephone: 425–227–1405; and locating Docket No. FAA–2016– the FAA Administrator. ‘‘Subtitle VII:
fax: 425–227–1149. 6893. Aviation Programs,’’ describes in more
SUPPLEMENTARY INFORMATION: detail the scope of the Agency’s
Related Service Information Under 1
Comments Invited CFR Part 51 authority.
We are issuing this rulemaking under
We invite you to send any written Airbus has issued Service Bulletins the authority described in ‘‘Subtitle VII,
relevant data, views, or arguments about A320–53–1298 and A320–53–1299, both Part A, Subpart III, Section 44701:
this proposed AD. Send your comments dated February 16, 2015; both including General requirements.’’ Under that
to an address listed under the Appendices 01, 02, and 03, dated section, Congress charges the FAA with
ADDRESSES section. Include ‘‘Docket No. February 16, 2015. The service promoting safe flight of civil aircraft in
FAA–2016–6893; Directorate Identifier information describes procedures for a air commerce by prescribing regulations
2015–NM–181–AD’’ at the beginning of one-time eddy current conductivity for practices, methods, and procedures
your comments. We specifically invite measurement of certain cabin and cargo the Administrator finds necessary for
comments on the overall regulatory, compartment structural parts to safety in air commerce. This regulation
economic, environmental, and energy determine if an incorrect aluminum is within the scope of that authority
aspects of this proposed AD. We will alloy was used, and replacement of any because it addresses an unsafe condition
consider all comments received by the affected part with a serviceable part. that is likely to exist or develop on
closing date and may amend this This service information is reasonably products identified in this rulemaking
proposed AD based on those comments. available because the interested parties action.
We will post all comments we have access to it through their normal
receive, without change, to http:// course of business or by the means Regulatory Findings
www.regulations.gov, including any identified in the ADDRESSES section. We determined that this proposed AD
personal information you provide. We would not have federalism implications
FAA’s Determination and Requirements
will also post a report summarizing each under Executive Order 13132. This
of This Proposed AD
substantive verbal contact we receive proposed AD would not have a
about this proposed AD. This product has been approved by substantial direct effect on the States, on
the aviation authority of another the relationship between the national
Discussion
country, and is approved for operation Government and the States, or on the
The European Aviation Safety Agency in the United States. Pursuant to our distribution of power and
(EASA), which is the Technical Agent bilateral agreement with the State of responsibilities among the various
for the Member States of the European Design Authority, we have been notified levels of government.
Union, has issued EASA Airworthiness of the unsafe condition described in the For the reasons discussed above, I
Directive 2015–0218, dated November 3, MCAI and service information certify this proposed regulation:
2015 (referred to after this as the referenced above. We are proposing this 1. Is not a ‘‘significant regulatory
Mandatory Continuing Airworthiness AD because we evaluated all pertinent action’’ under Executive Order 12866;
Information, or ‘‘the MCAI’’), to correct information and determined an unsafe 2. Is not a ‘‘significant rule’’ under the
an unsafe condition for certain Airbus condition exists and is likely to exist or DOT Regulatory Policies and Procedures
Model A318–112, A319–111, –112, develop on other products of these same (44 FR 11034, February 26, 1979);
–115, –132, and –133, A320–214, –232, type designs. 3. Will not affect intrastate aviation in
and –233, and A321–211, –212, –213, Alaska; and
Costs of Compliance
–231, and –232 airplanes. The MCAI 4. Will not have a significant
states: We estimate that this proposed AD economic impact, positive or negative,
Following an Airbus quality control review affects 167 airplanes of U.S. registry. on a substantial number of small entities
on the final assembly line, it was discovered We also estimate that it would take under the criteria of the Regulatory
that wrong aluminum alloy were delivered about 1 work-hour per product to Flexibility Act.
by a supplier for several structural parts. The comply with the basic requirements of
results of the investigations highlighted that this proposed AD. The average labor List of Subjects in 14 CFR Part 39
0.04% of the stock could be impacted by this rate is $85 per work-hour. Based on
wrong material.
Air transportation, Aircraft, Aviation
these figures, we estimate the cost of safety, Incorporation by reference,
Structural investigations demonstrated the
this proposed AD on U.S. operators to Safety.
capability to sustain the static limits loads,
and sufficient fatigue life up to a certain be $14,195, or $85 per product.
We have received no definitive data The Proposed Amendment
inspection threshold.
This condition, if not detected and that would enable us to provide cost Accordingly, under the authority
corrected, could reduce the structural estimates for the on-condition actions delegated to me by the Administrator,
integrity of the aeroplane. specified in this proposed AD. the FAA proposes to amend 14 CFR part
jstallworth on DSK7TPTVN1PROD with PROPOSALS
To address this potential unsafe condition, According to the manufacturer, some 39 as follows:
Airbus issued Service Bulletin (SB) A320– of the costs of this proposed AD may be
53–1298 and SB A320–53–1299 to provide covered under warranty, thereby PART 39—AIRWORTHINESS
inspection instructions. DIRECTIVES
For the reasons described above, this
reducing the cost impact on affected
[EASA] AD requires a one-time Special individuals. We do not control warranty
coverage for affected individuals. As a ■ 1. The authority citation for part 39
Detailed Inspection (SDI) [eddy current
conductivity measurements] of certain cabin result, we have included all available continues to read as follows:
and cargo compartment parts for material costs in our cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13 [Amended] 3826 through 4329 inclusive, 4331 through in reduced structural integrity of the
■ 2. The FAA amends § 39.13 by adding 6051 inclusive, 6053 through 6061 inclusive, airplane.
6063 through 6072 inclusive, 6074 through
the following new airworthiness (f) Compliance
6100 inclusive, 6102 through 6115 inclusive,
directive (AD): Comply with this AD within the
6117 through 6126 inclusive, 6128 through
Airbus: Docket No. FAA–2016–6893; 6136 inclusive, 6138 through 6143 inclusive, compliance times specified, unless already
Directorate Identifier 2015–NM–181–AD. 6145 through 6150 inclusive, 6152 through done.
(a) Comments Due Date 6159 inclusive, 6161 and 6162. (g) One-Time Measurement
(1) Airbus Model A318–112 airplanes. Within 6 years after the effective date of
We must receive comments by July 11, (2) Airbus Model A319–111, –112, –115,
2016. this AD, but not exceeding 12 years since the
–132, and –133 airplanes. date of issuance of the original certificate of
(b) Affected ADs (3) Airbus Model A320–214, –232, and airworthiness or the date of issuance of the
None. –233 airplanes. original export certificate of airworthiness:
(4) Airbus Model A321–211, –212, –213, Do a one-time eddy current conductivity
(c) Applicability –231, and –232 airplanes. measurements (with 60kHz and 480kHz) of
This AD applies to the Airbus airplanes the cabin and cargo compartment structural
(d) Subject
identified in paragraphs (c)(1) through (c)(4) parts identified in the ‘‘Affected P/N’’
of this AD, certificated in any category; Air Transport Association (ATA) of column of table 1 to paragraphs (g) and (h)
manufacturer serial numbers 3586, 3588, America Code 53, Fuselage. of this AD to determine if an incorrect
3589, 3590, 3595, 3604, 3608, 3614, 3615, (e) Reason aluminum alloy was used, in accordance
3620, 3632, 3634, 3638, 3647, 3651, 3657, with the Accomplishment Instructions of
3660, 3661, 3663, 3671, 3675, 3680, 3683 This AD was prompted by a quality control Airbus Service Bulletins A320–53–1298,
through 3687 inclusive, 3689, 3691, 3694, review of the final assembly line which dated February 16, 2015, including
3700, 3702, 3704, 3705, 3710, 3720, 3727, determined that the wrong aluminum alloy Appendices 01, 02, and 03, dated February
3728, 3733, 3735, 3742, 3744, 3746, 3754, was used to manufacture several structural 16, 2015 (for cabin parts); and A320–53–
3757, 3759, 3763, 3768, 3770, 3772, 3774, parts. We are issuing this AD to detect and 1299, dated February 16, 2015, including
3775, 3779, 3788, 3790, 3794, 3797, 3799, correct structural parts made of incorrect Appendices 01, 02, and 03, dated February
3801, 3803, 3808, 3810, 3818, 3822, 3824, aluminum alloy. This condition could result 16, 2015 (for cargo parts).
TABLE 1 TO PARAGRAPHS (g) AND (h) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED
Affected P/N Acceptable replacement P/N Area
D5347120720000 ...................................................................... D5347120720051 ...................................................................... Cabin.
D5347120720100 ...................................................................... D5347120720151 ...................................................................... Cabin.
D5347120920000 ...................................................................... D5347120920051 ...................................................................... Cabin.
D5347120920100 ...................................................................... D5347120920151 ...................................................................... Cabin.
D5347118820400 ...................................................................... D5347118820451 ...................................................................... Cabin.
D5347717620000 ...................................................................... D5347717620051 ...................................................................... Cargo.
D5357020620000 ...................................................................... D5357020620051 ...................................................................... Cargo.
D5358526421200 ...................................................................... D5358526421251 ...................................................................... Cargo.
D5358526421400 ...................................................................... D5358526421400 ...................................................................... Cargo.
D5358526421000 ...................................................................... D5358526421051 ...................................................................... Cargo.
D5358513120001 ...................................................................... D5358513120051 ...................................................................... Cargo.
(h) Replacement Directorate, FAA, has the authority to (EASA); or Airbus’s EASA DOA. If approved
If during the inspection required by approve AMOCs for this AD, if requested by the DOA, the approval must include the
paragraph (g) of this AD, any affected part using the procedures found in 14 CFR 39.19. DOA-authorized signature.
having a part number (P/N) specified in table In accordance with 14 CFR 39.19, send your (3) Required for Compliance (RC): If any
request to your principal inspector or local service information contains procedures or
1 to paragraphs (g) and (h) of this AD is
Flight Standards District Office, as tests that are identified as RC, those
found to have a measured value greater than
appropriate. If sending information directly procedures and tests must be done to comply
that specified in Figure A–GFAAA, Sheet 02, to the International Branch, send it to ATTN:
‘‘Inspection Flowchart,’’ of the applicable with this AD; any procedures or tests that are
Sanjay Ralhan, Aerospace Engineer, not identified as RC are recommended. Those
service information identified in paragraph International Branch, ANM–116, Transport
(g) of this AD: Before further flight, replace procedures and tests that are not identified
Airplane Directorate, FAA, 1601 Lind as RC may be deviated from using accepted
with an acceptable replacement part having Avenue SW., Renton, WA 98057–3356;
a P/N specified in table 1 to paragraphs (g) methods in accordance with the operator’s
telephone: 425–227–1405; fax: 425–227–
and (h) of this AD, in accordance with the maintenance or inspection program without
1149. Information may be emailed to: 9-
Accomplishment Instructions of Airbus ANM-116-AMOC-REQUESTS@faa.gov. obtaining approval of an AMOC, provided
Service Bulletins A320–53–1298, dated Before using any approved AMOC, notify the procedures and tests identified as RC can
February 16, 2015, including Appendices 01, your appropriate principal inspector, or be done and the airplane can be put back in
02, and 03, dated February 16, 2015 (for lacking a principal inspector, the manager of an airworthy condition. Any substitutions or
cabin parts); and A320–53–1299, dated the local flight standards district office/ changes to procedures or tests identified as
February 16, 2015, including Appendices 01, certificate holding district office. The AMOC RC require approval of an AMOC.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
02, and 03, dated February 16, 2015 (for approval letter must specifically reference (j) Related Information
cargo parts). this AD.
(2) Contacting the Manufacturer: For any (1) Refer to Mandatory Continuing
(i) Other FAA AD Provisions requirement in this AD to obtain corrective Airworthiness Information (MCAI) EASA AD
The following provisions also apply to this actions from a manufacturer, the action must 2015–0218, dated November 3, 2015, for
AD: be accomplished using a method approved related information. This MCAI may be
(1) Alternative Methods of Compliance by the Manager, International Branch, ANM– found in the AD docket on the Internet at
(AMOCs): The Manager, International 116, Transport Airplane Directorate, FAA; or http://www.regulations.gov by searching for
Branch, ANM–116, Transport Airplane the European Aviation Safety Agency and locating Docket No. FAA–2016–6893.
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![Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules 33441
(2) For service information identified in electronically using word processing by NERC for inclusion in the NERC
this AD, contact Airbus, Airworthiness software should be filed in native Glossary of Terms Used in NERC
Office—EIAS, 1 Rond Point Maurice applications or print-to-PDF format and Reliability Standards (NERC Glossary)
Bellonte, 31707 Blagnac Cedex, France; not in a scanned format. and to retire currently-effective
telephone: +33 5 61 93 36 96; fax: +33 5 61
93 44 51; email: account.airworth-eas@
• Mail/Hand Delivery: Those unable Reliability Standard BAL–002–1
airbus.com; Internet: http://www.airbus.com. to file electronically may mail or hand- immediately prior to the effective date
You may view this service information at the deliver comments to: Federal Energy of proposed Reliability Standard BAL–
FAA, Transport Airplane Directorate, 1601 Regulatory Commission, Secretary of the 002–2. The Commission also proposes
Lind Avenue SW., Renton, WA. For Commission, 888 First Street NE., to approve, with certain modifications,
information on the availability of this Washington, DC 20426. the associated violation risk factors and
material at the FAA, call 425–227–1221. Instructions: For detailed instructions violation severity levels, and
Issued in Renton, Washington, on May 17, on submitting comments and additional implementation plan.
2016. information on the rulemaking process, 2. Pursuant to section 215(d)(5) of the
Dionne Palermo, see the Comment Procedures Section of FPA,3 the Commission proposes to
Acting Manager, Transport Airplane this document. direct NERC to modify Reliability
Directorate, Aircraft Certification Service. FOR FURTHER INFORMATION CONTACT: Standard BAL–002–2 to address
[FR Doc. 2016–12352 Filed 5–25–16; 8:45 am] Enakpodia Agbedia (Technical concerns related to the possible
BILLING CODE 4910–13–P Information), Office of Electric extension or delay of the periods for
Reliability, Division of Reliability ACE recovery and contingency reserve
Standards, Federal Energy Regulatory restoration. The Commission also
DEPARTMENT OF ENERGY Commission, 888 First Street NE., proposes to direct NERC to address a
Washington, DC 20426, Telephone: reliability gap regarding megawatt losses
Federal Energy Regulatory (202) 502–6750, Enakpodia.Agbedia@ above the most severe single
Commission ferc.gov. contingency.
Mark Bennett (Legal Information), I. Background
18 CFR Part 40 Office of the General Counsel, Federal
Energy Regulatory Commission, 888 A. Mandatory Reliability Standards and
[Docket No. RM16–7–000]
First Street NE., Washington, DC 20426, Order No. 693 Directives
Disturbance Control Standard— Telephone: (202) 502–8524,
3. Section 215 of the FPA requires a
Contingency Reserve for Recovery Mark.Bennett@ferc.gov.
Commission-certified Electric
From a Balancing Contingency Event SUPPLEMENTARY INFORMATION: 1. Under Reliability Organization (ERO) to
Reliability Standard section 215 of the Federal Power Act develop mandatory and enforceable
(FPA),1 the Commission proposes to Reliability Standards that are subject to
AGENCY: Federal Energy Regulatory approve proposed Reliability Standard
Commission, DOE. Commission review and approval. The
BAL–002–2 (Disturbance Control Commission may approve, by rule or
ACTION: Notice of proposed rulemaking. Standard—Contingency Reserve for order, a proposed Reliability Standard
Recovery from a Balancing Contingency or modification to a Reliability Standard
SUMMARY: The Federal Energy
Event). The North American Electric if it determines that the Standard is just,
Regulatory Commission proposes to
Reliability Corporation (NERC), the reasonable, not unduly discriminatory
approve Reliability Standard BAL–002–
Commission-certified Electric or preferential and in the public
2 (Disturbance Control Standard—
Reliability Organization (ERO), interest.4 Once approved, the Reliability
Contingency Reserve for Recovery from
submitted proposed Reliability Standard Standards may be enforced by NERC,
a Balancing Contingency Event)
BAL–002–2 for Commission approval. subject to Commission oversight, or by
submitted by the North American
Proposed Reliability Standard BAL– the Commission independently.5
Electric Reliability Corporation (NERC).
002–2 applies to balancing authorities Pursuant to section 215 of the FPA, the
Proposed Reliability Standard BAL–
and reserve sharing groups. Proposed Commission established a process to
002–2 is designed to ensure that
Reliability Standard BAL–002–2 is select and certify an ERO,6 and
applicable entities balance resources
designed to ensure that these entities are subsequently certified NERC.7
and demand and return their Area
able to recover from system 4. On March 16, 2007, the
Control Error to defined values
contingencies by deploying adequate Commission issued Order No. 693,
following a Reportable Balancing
reserves to return their Area Control approving 83 of the 107 Reliability
Contingency Event. In addition, the
Error (ACE) to defined values and by Standards filed by NERC, including
Commission proposes to direct NERC to
replacing the capacity and energy lost Reliability Standard BAL–002–0.8 In
modify Reliability Standard BAL–002–2
due to generation or transmission
to address concerns related to the
equipment outages.2 In addition, the 3 16 U.S.C. 824o(d)(5).
possible extension or delay of the
Commission proposes to approve eight 4 Id. 824o(d)(2).
periods for Area Control Error recovery
new and revised definitions proposed 5 Id. 824o(e).
and contingency reserve restoration. 6 Rules Concerning Certification of the Electric
The Commission also proposes to direct 1 16 U.S.C. 824(o). Proposed Reliability Standard Reliability Organization; and Procedures for the
NERC to address a reliability gap BAL–002–2 is available on the Commission’s Establishment, Approval, and Enforcement of
jstallworth on DSK7TPTVN1PROD with PROPOSALS
regarding megawatt losses above the eLibrary document retrieval system in Docket No. Electric Reliability Standards, Order No. 672, FERC
most severe single contingency. RM16–7–000 and on the NERC Web site, Stats. & Regs. ¶ 31,204, order on reh’g, Order No.
www.nerc.com. 672–A, FERC Stats. & Regs. ¶ 31,212 (2006).
DATES: Comments are due July 25, 2016. 2 ACE is the instantaneous difference between a 7 North American Electric Reliability Corp., 116
ADDRESSES: Comments, identified by balancing authority’s Net Actual and Scheduled FERC ¶ 61,062, order on reh’g and compliance, 117
docket number, may be filed in the Interchange, taking into account the effects of FERC ¶ 61,126 (2006), aff’d sub nom. Alcoa, Inc. v.
Frequency Bias, correction for meter error, and FERC, 564 F.3d 1342 (D.C. Cir. 2009).
following ways: Automatic Time Error Correction, if operating in 8 Mandatory Reliability Standards for the Bulk-
• Electronic Filing through http:// that mode. NERC Glossary of Terms Used in NERC Power System, Order No. 693, FERC Stats. & Regs.
www.ferc.gov. Documents created Reliability Standards at 7 (updated April 20, 2016). Continued
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Document Created: 2016-05-26 01:13:15
Document Modified: 2016-05-26 01:13:15
| 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 July 11, 2016. | |
| 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 | 81 FR 33438 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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