81 FR 29209 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 91 (May 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 91 (May 11, 2016)
| Page Range | 29209-29212 | |
| FR Document | 2016-11094 |
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)] [Proposed Rules] [Pages 29209-29212] From the Federal Register Online [www.thefederalregister.org] [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 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: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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 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 2015-0219, 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 http://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. (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. (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: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (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 http://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: [email protected]; Internet: http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on 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
![Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 29209
Issued in Renton, Washington, on May 3, For service information identified in Directive 2015–0219, dated November 3,
2016. this NPRM, contact Airbus, 2015 (referred to after this as the
Michael Kaszycki, Airworthiness Office—EIAS, 1 Rond Mandatory Continuing Airworthiness
Acting Manager, Transport Airplane Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Directorate, Aircraft Certification Service. Cedex, France; telephone: +33 5 61 93 an unsafe condition for certain Airbus
[FR Doc. 2016–10915 Filed 5–10–16; 8:45 am] 36 96; fax: +33 5 61 93 44 51; email: Model A318–112 airplanes, A319–111,
BILLING CODE 4910–13–P account.airworth-eas@airbus.com; –112, –115, –132, and –133 airplanes,
Internet: http://www.airbus.com. You A320–214, –232, and –233 airplanes,
may view this referenced service and A321–211, –212, –213, –231, and
DEPARTMENT OF TRANSPORTATION information at the FAA, Transport –232 airplanes. The MCAI states:
Airplane Directorate, 1601 Lind Avenue Following an Airbus quality control review
Federal Aviation Administration SW., Renton, WA. For information on on the final assembly line, it was discovered
the availability of this material at the that aluminum alloy with inadequate heat
14 CFR Part 39 FAA, call 425–227–1221. treatment were delivered by a supplier for
[Docket No. FAA–2016–6431; Directorate several structural parts. The results of the
Examining the AD Docket investigations highlighted that 1% of the
Identifier 2015–NM–182–AD]
You may examine the AD docket on stock could be impacted by this wrong
RIN 2120–AA64 the Internet at http:// material.
www.regulations.gov by searching for Structural investigations demonstrated the
Airworthiness Directives; Airbus capability to sustain the static limits loads,
and locating Docket No. FAA–2016–
Airplanes and sufficient fatigue life up to a certain
6431; or in person at the Docket inspection threshold.
AGENCY: Federal Aviation Management Facility between 9 a.m. This condition, if not detected and
Administration (FAA), DOT. and 5 p.m., Monday through Friday, corrected, could reduce the aeroplane
ACTION: Notice of proposed rulemaking except Federal holidays. The AD docket structural integrity following fatigue load.
(NPRM). contains this proposed AD, the To address this potential unsafe condition,
regulatory evaluation, any comments Airbus issued Service Bulletin (SB) A320–
SUMMARY: We propose to adopt a new received, and other information. The 53–1292, SB A320–53–1293, and SB A320–
airworthiness directive (AD) for certain 53–1294 to provide inspection instructions.
street address for the Docket Operations
Airbus Model A318–112 airplanes, For the reasons described above, this
office (telephone: 800–647–5527) is in [EASA] AD requires a one-time Special
A319–111, –112, –115, –132, and –133 the ADDRESSES section. Comments will Detailed Inspection (SDI) [i.e., eddy current
airplanes, A320–214, –232, and –233 be available in the AD docket shortly conductivity measurement] of certain cabin,
airplanes, and A321–211, –212, –213, after receipt. cargo compartment and frame parts [for
–231, and –232 airplanes. This proposed FOR FURTHER INFORMATION CONTACT: material identification] and, depending on
AD was prompted by a quality control Sanjay Ralhan, Aerospace Engineer, findings, replacement with serviceable parts.
review on the final assembly line, which International Branch, ANM–116, You may examine the MCAI in the
determined that aluminum alloy with Transport Airplane Directorate, FAA, AD docket on the Internet at http://
inadequate heat treatment had been 1601 Lind Avenue SW., Renton, WA www.regulations.gov by searching for
delivered and used on several structural 98057–3356; telephone: 425–227–1405; and locating Docket No. FAA–2016–
parts. This proposed AD would require fax: 425–227–1149. 6431.
a one-time eddy current conductivity SUPPLEMENTARY INFORMATION:
measurement of certain cabin, cargo Related Service Information Under 1
compartment, and frame structural parts Comments Invited CFR Part 51
to determine if aluminum alloy with We invite you to send any written Airbus has issued the following
inadequate heat treatment was used, relevant data, views, or arguments about service information:
and replacement if necessary. We are this proposed AD. Send your comments • Airbus Service Bulletin A320–53–
proposing this AD to detect and replace to an address listed under the 1292, dated July 23, 2015; including
structural parts made of aluminum alloy ADDRESSES section. Include ‘‘Docket No. Appendices 01 and 02, dated July 23,
with inadequate heat treatment. This FAA–2016–6431; Directorate Identifier 2015.
condition could result in reduced 2015–NM–182–AD’’ at the beginning of • Airbus Service Bulletin A320–53–
structural integrity of the airplane. your comments. We specifically invite 1293, dated July 30, 2015; including
DATES: We must receive comments on comments on the overall regulatory, Appendices 01 and 02, dated July 30,
this proposed AD by June 27, 2016. economic, environmental, and energy 2015.
ADDRESSES: You may send comments, aspects of this proposed AD. We will • Airbus Service Bulletin A320–53–
using the procedures found in 14 CFR consider all comments received by the 1294, dated July 23, 2015; including
11.43 and 11.45, by any of the following closing date and may amend this Appendices 01 and 02, dated July 23,
methods: proposed AD based on those comments. 2015.
• Federal eRulemaking Portal: Go to We will post all comments we The service information describes
http://www.regulations.gov. Follow the receive, without change, to http:// procedures for a one-time eddy current
instructions for submitting comments. www.regulations.gov, including any conductivity measurement of certain
• Fax: 202–493–2251. personal information you provide. We cabin, cargo compartment, and frame
• Mail: U.S. Department of will also post a report summarizing each structural parts to determine if
mstockstill on DSK3G9T082PROD with PROPOSALS
Transportation, Docket Operations, M– substantive verbal contact we receive aluminum alloy with inadequate heat
30, West Building Ground Floor, Room about this proposed AD. treatment was used, and replacement of
W12–140, 1200 New Jersey Avenue SE., any affected part with a serviceable part.
Washington, DC 20590. Discussion This service information is reasonably
• Hand Delivery: Deliver to Mail The European Aviation Safety Agency available because the interested parties
address above between 9 a.m. and 5 (EASA), which is the Technical Agent have access to it through their normal
p.m., Monday through Friday, except for the Member States of the European course of business or by the means
Federal holidays. Union, has issued EASA Airworthiness identified in the ADDRESSES section.
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![29210 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
FAA’s Determination and Requirements because it addresses an unsafe condition (c) Applicability
of This Proposed AD that is likely to exist or develop on This AD applies to the Airbus airplanes
This product has been approved by products identified in this rulemaking identified in paragraphs (c)(1) through (c)(4)
the aviation authority of another action. of this AD, certificated in any category;
manufacturer serial numbers 4895, 4903,
country, and is approved for operation Regulatory Findings 4911, 4919, 4929, 4938, 4942, 4944, 4946,
in the United States. Pursuant to our 4948, and 4951, 4956 through 5541 inclusive,
bilateral agreement with the State of We determined that this proposed AD
would not have federalism implications 5544, 5547, 5550, 5551, 5553, 5556, 5559,
Design Authority, we have been notified 5561, 5562, 5563, 5565, 5566, 5570, 5572,
of the unsafe condition described in the under Executive Order 13132. This
proposed AD would not have a 5576, and 5578.
MCAI and service information (1) Airbus Model A318–112 airplanes.
referenced above. We are proposing this substantial direct effect on the States, on
(2) Airbus Model A319–111, –112, –115,
AD because we evaluated all pertinent the relationship between the national –132, and –133 airplanes.
information and determined an unsafe Government and the States, or on the (3) Airbus Model A320–214, –232, and
condition exists and is likely to exist or distribution of power and –233 airplanes.
develop on other products of these same responsibilities among the various (4) Airbus Model A321–211, –212, –213,
type designs. levels of government. –231, and –232 airplanes.
For the reasons discussed above, I
Costs of Compliance (d) Subject
certify this proposed regulation:
1. Is not a ‘‘significant regulatory Air Transport Association (ATA) of
We estimate that this proposed AD
action’’ under Executive Order 12866; America Code 53, Fuselage.
affects 46 airplanes of U.S. registry.
We also estimate that it would take 2. Is not a ‘‘significant rule’’ under the (e) Reason
about 6 work-hours per product to DOT Regulatory Policies and Procedures This AD was prompted by a quality control
comply with the basic requirements of (44 FR 11034, February 26, 1979); review on the final assembly line, which
this proposed AD. The average labor 3. Will not affect intrastate aviation in determined that aluminum alloy with
rate is $85 per work-hour. Based on Alaska; and inadequate heat treatment had been delivered
these figures, we estimate the cost of 4. Will not have a significant and used on several structural parts. We are
this proposed AD on U.S. operators to economic impact, positive or negative, issuing this AD to detect and replace
be $23,460, or $510 per product. on a substantial number of small entities structural parts made of aluminum alloy with
We have received no definitive data under the criteria of the Regulatory inadequate heat treatment. This condition
that would enable us to provide cost Flexibility Act. could result in reduced structural integrity of
estimates for the on-condition actions the airplane.
List of Subjects in 14 CFR Part 39
specified in this proposed AD. (f) Compliance
According to the manufacturer, some Air transportation, Aircraft, Aviation
Comply with this AD within the
of the costs of this proposed AD may be safety, Incorporation by reference, compliance times specified, unless already
covered under warranty, thereby Safety. done.
reducing the cost impact on affected The Proposed Amendment
individuals. We do not control warranty (g) One-time Measurement
coverage for affected individuals. As a Accordingly, under the authority Within 6 years since the date of issuance
result, we have included all available delegated to me by the Administrator, of the original certificate of airworthiness or
costs in our cost estimate. the FAA proposes to amend 14 CFR part the date of issuance of the original export
39 as follows: certificate of airworthiness: Do a one-time
Authority for This Rulemaking eddy current conductivity measurement of
Title 49 of the United States Code PART 39—AIRWORTHINESS the cabin, cargo compartment, and frame
DIRECTIVES structural parts identified in the ‘‘Affected P/
specifies the FAA’s authority to issue
N (part number)’’ column of tables 1, 2, and
rules on aviation safety. Subtitle I, 3 to paragraphs (g) and (h) of this AD to
section 106, describes the authority of ■ 1. The authority citation for part 39
continues to read as follows: determine if aluminum alloy with inadequate
the FAA Administrator. ‘‘Subtitle VII: heat treatment was used, in accordance with
Aviation Programs,’’ describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. the Accomplishment Instructions of the
detail the scope of the Agency’s applicable service information identified in
§ 39.13 [Amended]
authority. paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by adding (1) For cabin structural parts: Airbus
the authority described in ‘‘Subtitle VII, the following new airworthiness Service Bulletin A320–53–1292, dated July
Part A, Subpart III, Section 44701: directive (AD): 23, 2015; including Appendices 01 and 02,
General requirements.’’ Under that Airbus: Docket No. FAA–2016–6431; dated July 23, 2015.
section, Congress charges the FAA with Directorate Identifier 2015–NM–182–AD. (2) For cargo compartment structural parts:
Airbus Service Bulletin A320–53–1293,
promoting safe flight of civil aircraft in (a) Comments Due Date dated July 30, 2015; including Appendices 01
air commerce by prescribing regulations and 02, dated July 30, 2015.
We must receive comments by June 27,
for practices, methods, and procedures 2016. (3) For frame structural parts: Airbus
the Administrator finds necessary for Service Bulletin A320–53–1294, dated July
safety in air commerce. This regulation (b) Affected ADs 23, 2015; including Appendices 01 and 02,
is within the scope of that authority
mstockstill on DSK3G9T082PROD with PROPOSALS
None. 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]
Affected P/N Acceptable replacement P/N Area
D2127245500000 ......................................................................... D2127245500000 ........................................................................ Cabin
D2127247600200 ......................................................................... D2127247600200 ........................................................................ Cabin
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](https://thefederalregister.org/doc/81_FR_29300/page/2.svg)
![Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 29211
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 Acceptable replacement P/N Area
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]
Affected P/N Acceptable 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]
Affected P/N Acceptable 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
mstockstill on DSK3G9T082PROD with PROPOSALS
D5347067720200 ......................................................................... D5347067720251 ........................................................................ Frame
D5347067720400 ......................................................................... D5347067720451 ........................................................................ Frame
D5347986520200 ......................................................................... D5347986520251 ........................................................................ Frame
VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 E:\FR\FM\11MYP1.SGM 11MYP1](https://thefederalregister.org/doc/81_FR_29300/page/3.svg)
![29212 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
(h) Replacement related information. This MCAI may be not to include in your comments any
If during the measurement required by found in the AD docket on the Internet at personal information, such as Social
paragraph (g) of this AD, any affected P/N http://www.regulations.gov by searching for Security numbers or medical
specified in table 1, 2, or 3 to paragraphs (g) and locating Docket No. FAA–2016–6431. information.
and (h) of this AD is found to have a (2) For service information identified in
1. Internet: We strongly recommend
measured value greater than that specified in this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
that you submit your comments via the
Figure A–GFAAA, Sheet 01, ‘‘Inspection Internet. Please visit the Federal
Flowchart,’’ of the applicable service Bellonte, 31707 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33 5 61 eRulemaking portal at http://
information identified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD: Before further 93 44 51; email: account.airworth-eas@ www.regulations.gov. Use the Search
flight, replace the affected part with the airbus.com; Internet: http://www.airbus.com. function to find docket number SSA–
corresponding acceptable replacement part You may view this service information at the 2014–0016. The system will issue a
specified in table 1, 2, or 3 to paragraphs (g) FAA, Transport Airplane Directorate, 1601 tracking number to confirm your
and (h) of this AD, in accordance with the Lind Avenue SW., Renton, WA. For submission. You will not be able to
Accomplishment Instructions of the information on the availability of this view your comment immediately
applicable service information identified in material at the FAA, call 425–227–1221.
because we must post each comment
paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Issued in Renton, Washington, on May 4, manually. It may take up to a week for
(i) Other FAA AD Provisions 2016. your comment to be viewable.
The following provisions also apply to this Michael Kaszycki, 2. Fax: Fax comments to (410) 966–
AD: Acting Manager, Transport Airplane 2830.
(1) Alternative Methods of Compliance Directorate, Aircraft Certification Service. 3. Mail: Mail your comments to the
(AMOCs): The Manager, International [FR Doc. 2016–11094 Filed 5–10–16; 8:45 am] Office of Regulations and Reports
Branch, ANM–116, Transport Airplane BILLING CODE 4910–13–P Clearance, Social Security
Directorate, FAA, has the authority to Administration, 3100 West High Rise
approve AMOCs for this AD, if requested Building, 6401 Security Boulevard,
using the procedures found in 14 CFR 39.19.
SOCIAL SECURITY ADMINISTRATION Baltimore, Maryland 21235–6401.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Comments are available for public
Flight Standards District Office, as 20 CFR Parts 404, 411, and 416 viewing on the Federal eRulemaking
appropriate. If sending information directly portal at http://www.regulations.gov or
[Docket No. SSA–2014–0016] in person, during regular business
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer, RIN 0960–AH66 hours, by arranging with the contact
International Branch, ANM–116, Transport person identified below.
Airplane Directorate, FAA, 1601 Lind Unsuccessful Work Attempts and FOR FURTHER INFORMATION CONTACT:
Avenue SW., Renton, WA 98057–3356; Expedited Reinstatement Eligibility Kristine Erwin-Tribbitt, Office of
telephone: 425–227–1405; fax: 425–227–
1149. Information may be emailed to: 9- AGENCY: Social Security Administration. Retirement and Disability Policy, Office
ANM-116-AMOC-REQUESTS@faa.gov. of Research, Demonstration, and
ACTION: Notice of proposed rulemaking.
Before using any approved AMOC, notify Employment Support, Social Security
your appropriate principal inspector, or SUMMARY: We propose to remove some Administration, 6401 Security
lacking a principal inspector, the manager of of the requirements for evaluation of an Boulevard, Robert Ball Building 3–A–
the local flight standards district office/ unsuccessful work attempt (UWA) that 26, Baltimore, MD 21235–6401, (410)
certificate holding district office. The AMOC 965–3353. For information on eligibility
lasts between 3 and 6 months. We also
approval letter must specifically reference or filing for benefits, call our national
this AD. propose to allow previously entitled
beneficiaries to apply for expedited toll-free number, 1–800–772–1213 or
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective reinstatement (EXR) in the same month TTY 1–800–325–0778, or visit our
actions from a manufacturer, the action must they stop performing substantial gainful Internet site, Social Security Online, at
be accomplished using a method approved activity (SGA). Provisional benefits will http://www.socialsecurity.gov.
by the Manager, International Branch, ANM– begin the month after the request for SUPPLEMENTARY INFORMATION:
116, Transport Airplane Directorate, FAA; or EXR if the beneficiary stops performing
the EASA; or Airbus’s EASA DOA. If SGA and UWA
SGA in the month of the EXR request.
approved by the DOA, the approval must To be eligible for disability benefits,
These changes would simplify our
include the DOA-authorized signature. an individual must be unable to engage
(3) Required for Compliance (RC): If any policies and make them easier for the
public to understand. in any SGA.1 SGA is work activity that
service information contains procedures or
DATES: To ensure that your comments
is both substantial and gainful.2 Work
tests that are identified as RC, those
procedures and tests must be done to comply are considered, we must receive them activity is substantial if it involves the
with this AD; any procedures or tests that are no later than July 11, 2016. performance of significant physical or
not identified as RC are recommended. Those mental activities.3 ‘‘Gainful work
ADDRESSES: You may submit comments
procedures and tests that are not identified activity’’ is work done for pay or profit,
as RC may be deviated from using accepted by any one of three methods—Internet, or if it is the kind of work usually done
methods in accordance with the operator’s fax, or mail. Do not submit the same for pay or profit, whether or not a profit
maintenance or inspection program without comments multiple times or by more is realized.4 We will not determine that
obtaining approval of an AMOC, provided than one method. Regardless of which an individual is disabled or continues to
the procedures and tests identified as RC can method you choose, please state that
mstockstill on DSK3G9T082PROD with PROPOSALS
be disabled if he or she is able to
be done and the airplane can be put back in your comments refer to Docket No.
an airworthy condition. Any substitutions or perform SGA.
SSA–2014–0016 so that we may We use several rules to decide
changes to procedures or tests identified as associate your comments with the
RC require approval of an AMOC. whether an individual has performed
correct regulation.
(j) Related Information CAUTION: You should be careful to 1 42 U.S.C. 223(d)(1), 42 U.S.C. 1382c(a)(3)(A).
(1) Refer to Mandatory Continuing include in your comments only 2 20 CFR 404.1572 and 416.972.
Airworthiness Information (MCAI) EASA AD information that you wish to make 3 20 CFR 404.1572(a) and 416.972(a).
2015–0219, dated November 3, 2015, for publicly available. We strongly urge you 4 20 CFR 404.1572(b) and 416.972(b).
VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 E:\FR\FM\11MYP1.SGM 11MYP1](https://thefederalregister.org/doc/81_FR_29300/page/4.svg)
Document Created: 2016-05-11 01:11:58
Document Modified: 2016-05-11 01:11:58
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 27, 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 29209 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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