Airworthiness Directives; Airbus Airplanes, 29209-29212 [2016-11094]

Download as PDF Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules Issued in Renton, Washington, on May 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–10915 Filed 5–10–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6431; Directorate Identifier 2015–NM–182–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This proposed AD would require a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are proposing this AD to detect and replace structural parts made of aluminum alloy with inadequate heat treatment. This condition could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 27, 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 https://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. mstockstill on DSK3G9T082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 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: https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6431; 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–2016–6431; Directorate Identifier 2015–NM–182–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 https:// 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 PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 29209 Directive 2015–0219, 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 airplanes, A319–111, –112, –115, –132, and –133 airplanes, A320–214, –232, and –233 airplanes, 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 aluminum alloy with inadequate heat treatment were delivered by a supplier for several structural parts. The results of the investigations highlighted that 1% 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 aeroplane structural integrity following fatigue load. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 53–1292, SB A320–53–1293, and SB A320– 53–1294 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [i.e., eddy current conductivity measurement] of certain cabin, cargo compartment and frame 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6431. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A320–53– 1292, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. • Airbus Service Bulletin A320–53– 1293, dated July 30, 2015; including Appendices 01 and 02, dated July 30, 2015. • Airbus Service Bulletin A320–53– 1294, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. The service information describes procedures for a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment 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. E:\FR\FM\11MYP1.SGM 11MYP1 29210 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 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. mstockstill on DSK3G9T082PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 46 airplanes of U.S. registry. We also estimate that it would take about 6 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 $23,460, or $510 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. (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 4895, 4903, 4911, 4919, 4929, 4938, 4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544, 5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566, 5570, 5572, 5576, and 5578. (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 on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. We are issuing this AD to detect and replace structural parts made of aluminum alloy with inadequate heat treatment. 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. The Proposed Amendment (g) One-time Measurement Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Within 6 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 measurement of the cabin, cargo compartment, and frame structural parts identified in the ‘‘Affected P/ N (part number)’’ column of tables 1, 2, and 3 to paragraphs (g) and (h) of this AD to determine if aluminum alloy with inadequate heat treatment was used, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For cabin structural parts: Airbus Service Bulletin A320–53–1292, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. (2) For cargo compartment structural parts: Airbus Service Bulletin A320–53–1293, dated July 30, 2015; including Appendices 01 and 02, dated July 30, 2015. (3) For frame structural parts: Airbus Service Bulletin A320–53–1294, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–6431; Directorate Identifier 2015–NM–182–AD. (a) Comments Due Date We must receive comments by June 27, 2016. (b) Affected ADs None. TABLE 1 TO PARAGRAPHS (G) AND (H) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED [Airbus Service Bulletin A320–53–1292] Affected P/N Acceptable replacement P/N D2127245500000 ......................................................................... D2127247600200 ......................................................................... D2127245500000 ........................................................................ D2127247600200 ........................................................................ VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 E:\FR\FM\11MYP1.SGM 11MYP1 Area Cabin Cabin 29211 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules TABLE 1 TO PARAGRAPHS (G) AND (H) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED—Continued [Airbus Service Bulletin A320–53–1292] Affected P/N D2127247600300 D2127399900200 D2127399900300 D2127698900800 D2127698902400 D2527075131200 D2527075131300 D2527075138000 D2527075138100 D2527075138200 D2527075138300 D2527075138600 D2527075138800 D2527240220600 D2527240220700 D2527240220800 D9249591201000 D9249591201800 D9249591227800 D9249591227900 D9249591228000 D9249591228100 Acceptable replacement P/N ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... D2127247600300 D2127399900200 D2127399900300 D2127698900800 D2127698902400 D2527075131251 D2527075131351 D2527075138000 D2527075138100 D2527075138200 D2527075138300 D2527075138651 D2527075138851 D2527240220651 D2527240220751 D2527240220851 D9249591201000 D9249591201800 D9249591227851 D9249591227951 D9249591228051 D9249591228151 ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ Area Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin Cabin TABLE 2 TO PARAGRAPHS (G) AND (H) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED [Airbus Service Bulletin A320–53–1293] Affected P/N D2707033520000 D2827027120000 D2827093500400 D2907013701200 D2907013800400 D3247012900000 D3817003820000 D3817012320200 D3837021201600 D3837033300400 D4918518320200 D5347043420400 D9248511000000 D9249254100200 D9249282300000 Acceptable replacement P/N ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... D2707033520000 D2827027120000 D2827093500400 D2907013701251 D2907013800451 D3247012900051 D3817003820000 D3817012320251 D3837021201600 D3837033300400 D4918518320200 D5347043420451 D9248511000051 D9249254100251 D9249282300000 ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ Area Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo Cargo TABLE 3 TO PARAGRAPHS (G) AND (H) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED [Airbus Service Bulletin A320–53–1294] mstockstill on DSK3G9T082PROD with PROPOSALS Affected P/N D2827098326800 D5347051620600 D5347051720600 D5347057120000 D5347067520600 D5347067521400 D5347067520800 D5347067521000 D5347067521600 D5347067620600 D5347067720200 D5347067720400 D5347986520200 VerDate Sep<11>2014 Acceptable replacement P/N ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... ......................................................................... 16:58 May 10, 2016 Jkt 238001 PO 00000 Frm 00043 D2827098326851 D5347051620651 D5347051720651 D5347057120051 D5347067520651 D5347067521451 D5347067520851 D5347067521051 D5347067521651 D5347067620600 D5347067720251 D5347067720451 D5347986520251 Fmt 4702 Sfmt 4702 ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ E:\FR\FM\11MYP1.SGM 11MYP1 Area Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame 29212 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules mstockstill on DSK3G9T082PROD with PROPOSALS (h) Replacement If during the measurement required by paragraph (g) of this AD, any affected P/N specified in table 1, 2, or 3 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A–GFAAA, Sheet 01, ‘‘Inspection Flowchart,’’ of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further flight, replace the affected part with the corresponding acceptable replacement part specified in table 1, 2, or 3 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (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: 9ANM-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 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 2015–0219, dated November 3, 2015, for VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–6431. (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: https://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 4, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–11094 Filed 5–10–16; 8:45 am] BILLING CODE 4910–13–P SOCIAL SECURITY ADMINISTRATION 20 CFR Parts 404, 411, and 416 [Docket No. SSA–2014–0016] RIN 0960–AH66 Unsuccessful Work Attempts and Expedited Reinstatement Eligibility Social Security Administration. Notice of proposed rulemaking. AGENCY: ACTION: We propose to remove some of the requirements for evaluation of an unsuccessful work attempt (UWA) that lasts between 3 and 6 months. We also propose to allow previously entitled beneficiaries to apply for expedited reinstatement (EXR) in the same month they stop performing substantial gainful activity (SGA). Provisional benefits will begin the month after the request for EXR if the beneficiary stops performing SGA in the month of the EXR request. These changes would simplify our policies and make them easier for the public to understand. DATES: To ensure that your comments are considered, we must receive them no later than July 11, 2016. ADDRESSES: You may submit comments by any one of three methods—Internet, fax, or mail. Do not submit the same comments multiple times or by more than one method. Regardless of which method you choose, please state that your comments refer to Docket No. SSA–2014–0016 so that we may associate your comments with the correct regulation. CAUTION: You should be careful to include in your comments only information that you wish to make publicly available. We strongly urge you SUMMARY: PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 not to include in your comments any personal information, such as Social Security numbers or medical information. 1. Internet: We strongly recommend that you submit your comments via the Internet. Please visit the Federal eRulemaking portal at https:// www.regulations.gov. Use the Search function to find docket number SSA– 2014–0016. The system will issue a tracking number to confirm your submission. You will not be able to view your comment immediately because we must post each comment manually. It may take up to a week for your comment to be viewable. 2. Fax: Fax comments to (410) 966– 2830. 3. Mail: Mail your comments to the Office of Regulations and Reports Clearance, Social Security Administration, 3100 West High Rise Building, 6401 Security Boulevard, Baltimore, Maryland 21235–6401. Comments are available for public viewing on the Federal eRulemaking portal at https://www.regulations.gov or in person, during regular business hours, by arranging with the contact person identified below. FOR FURTHER INFORMATION CONTACT: Kristine Erwin-Tribbitt, Office of Retirement and Disability Policy, Office of Research, Demonstration, and Employment Support, Social Security Administration, 6401 Security Boulevard, Robert Ball Building 3–A– 26, Baltimore, MD 21235–6401, (410) 965–3353. For information on eligibility or filing for benefits, call our national toll-free number, 1–800–772–1213 or TTY 1–800–325–0778, or visit our Internet site, Social Security Online, at https://www.socialsecurity.gov. SUPPLEMENTARY INFORMATION: SGA and UWA To be eligible for disability benefits, an individual must be unable to engage in any SGA.1 SGA is work activity that is both substantial and gainful.2 Work activity is substantial if it involves the performance of significant physical or mental activities.3 ‘‘Gainful work activity’’ is work done for pay or profit, or if it is the kind of work usually done for pay or profit, whether or not a profit is realized.4 We will not determine that an individual is disabled or continues to be disabled if he or she is able to perform SGA. We use several rules to decide whether an individual has performed 1 42 U.S.C. 223(d)(1), 42 U.S.C. 1382c(a)(3)(A). CFR 404.1572 and 416.972. 3 20 CFR 404.1572(a) and 416.972(a). 4 20 CFR 404.1572(b) and 416.972(b). 2 20 E:\FR\FM\11MYP1.SGM 11MYP1

Agencies

[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29209-29212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11094]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6431; Directorate Identifier 2015-NM-182-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 aluminum alloy with inadequate heat treatment had been delivered
and used on several structural parts. This proposed AD would require a
one-time eddy current conductivity measurement of certain cabin, cargo
compartment, and frame structural parts to determine if aluminum alloy
with inadequate heat treatment was used, and replacement if necessary.
We are proposing this AD to detect and replace structural parts made of
aluminum alloy with inadequate heat treatment. This condition could
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 27, 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 https://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: https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6431; 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-2016-6431;
Directorate Identifier 2015-NM-182-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 https://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 2015-0219, 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 airplanes, A319-111, -112, -115, -132, and -133 airplanes,
A320-214, -232, and -233 airplanes, 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 aluminum alloy with inadequate heat
treatment were delivered by a supplier for several structural parts.
The results of the investigations highlighted that 1% 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
aeroplane structural integrity following fatigue load.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-53-1292, SB A320-53-1293, and SB A320-53-
1294 to provide inspection instructions.
For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [i.e., eddy current
conductivity measurement] of certain cabin, cargo compartment and
frame 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6431.

Related Service Information Under 1 CFR Part 51

Airbus has issued the following service information:
Airbus Service Bulletin A320-53-1292, dated July 23, 2015;
including Appendices 01 and 02, dated July 23, 2015.
Airbus Service Bulletin A320-53-1293, dated July 30, 2015;
including Appendices 01 and 02, dated July 30, 2015.
Airbus Service Bulletin A320-53-1294, dated July 23, 2015;
including Appendices 01 and 02, dated July 23, 2015.
The service information describes procedures for a one-time eddy
current conductivity measurement of certain cabin, cargo compartment,
and frame structural parts to determine if aluminum alloy with
inadequate heat treatment 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.

[[Page 29210]]

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 46 airplanes of U.S.
registry.
We also estimate that it would take about 6 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 $23,460, or $510
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.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

Airbus: Docket No. FAA-2016-6431; Directorate Identifier 2015-NM-
182-AD.

(a) Comments Due Date

We must receive comments by June 27, 2016.

(b) Affected ADs

None.

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 4895, 4903, 4911, 4919, 4929, 4938,
4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544,
5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566,
5570, 5572, 5576, and 5578.
(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 on the final
assembly line, which determined that aluminum alloy with inadequate
heat treatment had been delivered and used on several structural
parts. We are issuing this AD to detect and replace structural parts
made of aluminum alloy with inadequate heat treatment. 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 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 measurement of the cabin, cargo compartment, and frame
structural parts identified in the ``Affected P/N (part number)''
column of tables 1, 2, and 3 to paragraphs (g) and (h) of this AD to
determine if aluminum alloy with inadequate heat treatment was used,
in accordance with the Accomplishment Instructions of the applicable
service information identified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD.
(1) For cabin structural parts: Airbus Service Bulletin A320-53-
1292, dated July 23, 2015; including Appendices 01 and 02, dated
July 23, 2015.
(2) For cargo compartment structural parts: Airbus Service
Bulletin A320-53-1293, dated July 30, 2015; including Appendices 01
and 02, dated July 30, 2015.
(3) For frame structural parts: Airbus Service Bulletin A320-53-
1294, dated July 23, 2015; including Appendices 01 and 02, dated
July 23, 2015.

Table 1 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
Installed
[Airbus Service Bulletin A320-53-1292]
------------------------------------------------------------------------
Acceptable
Affected P/N replacement P/N Area
------------------------------------------------------------------------
D2127245500000................ D2127245500000....... Cabin
D2127247600200................ D2127247600200....... Cabin

[[Page 29211]]

D2127247600300................ D2127247600300....... Cabin
D2127399900200................ D2127399900200....... Cabin
D2127399900300................ D2127399900300....... Cabin
D2127698900800................ D2127698900800....... Cabin
D2127698902400................ D2127698902400....... Cabin
D2527075131200................ D2527075131251....... Cabin
D2527075131300................ D2527075131351....... Cabin
D2527075138000................ D2527075138000....... Cabin
D2527075138100................ D2527075138100....... Cabin
D2527075138200................ D2527075138200....... Cabin
D2527075138300................ D2527075138300....... Cabin
D2527075138600................ D2527075138651....... Cabin
D2527075138800................ D2527075138851....... Cabin
D2527240220600................ D2527240220651....... Cabin
D2527240220700................ D2527240220751....... Cabin
D2527240220800................ D2527240220851....... Cabin
D9249591201000................ D9249591201000....... Cabin
D9249591201800................ D9249591201800....... Cabin
D9249591227800................ D9249591227851....... Cabin
D9249591227900................ D9249591227951....... Cabin
D9249591228000................ D9249591228051....... Cabin
D9249591228100................ D9249591228151....... Cabin
------------------------------------------------------------------------

Table 2 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
Installed
[Airbus Service Bulletin A320-53-1293]
------------------------------------------------------------------------
Acceptable
Affected P/N replacement P/N Area
------------------------------------------------------------------------
D2707033520000................ D2707033520000....... Cargo
D2827027120000................ D2827027120000....... Cargo
D2827093500400................ D2827093500400....... Cargo
D2907013701200................ D2907013701251....... Cargo
D2907013800400................ D2907013800451....... Cargo
D3247012900000................ D3247012900051....... Cargo
D3817003820000................ D3817003820000....... Cargo
D3817012320200................ D3817012320251....... Cargo
D3837021201600................ D3837021201600....... Cargo
D3837033300400................ D3837033300400....... Cargo
D4918518320200................ D4918518320200....... Cargo
D5347043420400................ D5347043420451....... Cargo
D9248511000000................ D9248511000051....... Cargo
D9249254100200................ D9249254100251....... Cargo
D9249282300000................ D9249282300000....... Cargo
------------------------------------------------------------------------

Table 3 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
Installed
[Airbus Service Bulletin A320-53-1294]
------------------------------------------------------------------------
Acceptable
Affected P/N replacement P/N Area
------------------------------------------------------------------------
D2827098326800................ D2827098326851....... Frame
D5347051620600................ D5347051620651....... Frame
D5347051720600................ D5347051720651....... Frame
D5347057120000................ D5347057120051....... Frame
D5347067520600................ D5347067520651....... Frame
D5347067521400................ D5347067521451....... Frame
D5347067520800................ D5347067520851....... Frame
D5347067521000................ D5347067521051....... Frame
D5347067521600................ D5347067521651....... Frame
D5347067620600................ D5347067620600....... Frame
D5347067720200................ D5347067720251....... Frame
D5347067720400................ D5347067720451....... Frame
D5347986520200................ D5347986520251....... Frame
------------------------------------------------------------------------

[[Page 29212]]

(h) Replacement

If during the measurement required by paragraph (g) of this AD,
any affected P/N specified in table 1, 2, or 3 to paragraphs (g) and
(h) of this AD is found to have a measured value greater than that
specified in Figure A-GFAAA, Sheet 01, ``Inspection Flowchart,'' of
the applicable service information identified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD: Before further flight, replace the
affected part with the corresponding acceptable replacement part
specified in table 1, 2, or 3 to paragraphs (g) and (h) of this AD,
in accordance with the Accomplishment Instructions of the applicable
service information identified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD.

(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 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 2015-0219, dated November 3, 2015, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2016-6431.
(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:
https://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 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-11094 Filed 5-10-16; 8:45 am]
BILLING CODE 4910-13-P

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