Airworthiness Directives; Airbus Airplanes
Federal Register, Volume 81 Issue 91 (Wednesday, May 11, 2016)
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
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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).
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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: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
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
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Acceptable
Affected P/N replacement P/N Area
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D2127245500000................ D2127245500000....... Cabin
D2127247600200................ D2127247600200....... Cabin
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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
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Table 2 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
Installed
Airbus Service Bulletin A320-53-1293
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Acceptable
Affected P/N replacement P/N Area
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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
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Table 3 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
Installed
Airbus Service Bulletin A320-53-1294
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Acceptable
Affected P/N replacement P/N Area
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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
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(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 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: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 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
