[Federal Register Volume 81, Number 102 (Thursday, May 26, 2016)]
[Proposed Rules]
[Pages 33438-33441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12352]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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 the wrong aluminum alloy was used to manufacture several 
structural parts. This proposed AD would require a one-time eddy 
current conductivity measurements of certain cabin and cargo 
compartment structural parts to determine if an incorrect aluminum 
alloy was used, and replacement if necessary. We are proposing this AD 
to detect and replace structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by July 11, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: [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-
6893; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

[[Page 33439]]


FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6893; 
Directorate Identifier 2015-NM-181-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0218, dated November 3, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318-112, A319-111, -112, -115, -132, and -133, A320-214, -232, and -
233, and A321-211, -212, -213, -231, and -232 airplanes. The MCAI 
states:

    Following an Airbus quality control review on the final assembly 
line, it was discovered that wrong aluminum alloy were delivered by 
a supplier for several structural parts. The results of the 
investigations highlighted that 0.04% of the stock could be impacted 
by this wrong material.
    Structural investigations demonstrated the capability to sustain 
the static limits loads, and sufficient fatigue life up to a certain 
inspection threshold.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1298 and SB A320-53-1299 to provide 
inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [eddy current conductivity 
measurements] of certain cabin and cargo compartment parts for 
material identification and, depending on findings, replacement with 
serviceable parts.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6893.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A320-53-1298 and A320-53-1299, 
both dated February 16, 2015; both including Appendices 01, 02, and 03, 
dated February 16, 2015. The service information describes procedures 
for a one-time eddy current conductivity measurement of certain cabin 
and cargo compartment structural parts to determine if an incorrect 
aluminum alloy was used, and replacement of any affected part with a 
serviceable part. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 167 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $14,195, or $85 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 33440]]

Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-
181-AD.

(a) Comments Due Date

    We must receive comments by July 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category; 
manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 
3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 
3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 
3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 
3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 
3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 
3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 
6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 
inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 
6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 
through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 
6159 inclusive, 6161 and 6162.
    (1) Airbus Model A318-112 airplanes.
    (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
    (3) Airbus Model A320-214, -232, and -233 airplanes.
    (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a quality control review of the final 
assembly line which determined that the wrong aluminum alloy was 
used to manufacture several structural parts. We are issuing this AD 
to detect and correct structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity 
of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) One-Time Measurement

    Within 6 years after the effective date of this AD, but not 
exceeding 12 years since the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness: Do a one-time eddy current 
conductivity measurements (with 60kHz and 480kHz) of the cabin and 
cargo compartment structural parts identified in the ``Affected P/
N'' column of table 1 to paragraphs (g) and (h) of this AD to 
determine if an incorrect aluminum alloy was used, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletins 
A320-53-1298, dated February 16, 2015, including Appendices 01, 02, 
and 03, dated February 16, 2015 (for cabin parts); and A320-53-1299, 
dated February 16, 2015, including Appendices 01, 02, and 03, dated 
February 16, 2015 (for cargo parts).

  Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
                                Installed
------------------------------------------------------------------------
                                      Acceptable
          Affected P/N              replacement P/N          Area
------------------------------------------------------------------------
D5347120720000..................  D5347120720051....  Cabin.
D5347120720100..................  D5347120720151....  Cabin.
D5347120920000..................  D5347120920051....  Cabin.
D5347120920100..................  D5347120920151....  Cabin.
D5347118820400..................  D5347118820451....  Cabin.
D5347717620000..................  D5347717620051....  Cargo.
D5357020620000..................  D5357020620051....  Cargo.
D5358526421200..................  D5358526421251....  Cargo.
D5358526421400..................  D5358526421400....  Cargo.
D5358526421000..................  D5358526421051....  Cargo.
D5358513120001..................  D5358513120051....  Cargo.
------------------------------------------------------------------------

(h) Replacement

    If during the inspection required by paragraph (g) of this AD, 
any affected part having a part number (P/N) specified in table 1 to 
paragraphs (g) and (h) of this AD is found to have a measured value 
greater than that specified in Figure A-GFAAA, Sheet 02, 
``Inspection Flowchart,'' of the applicable service information 
identified in paragraph (g) of this AD: Before further flight, 
replace with an acceptable replacement part having a P/N specified 
in table 1 to paragraphs (g) and (h) of this AD, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletins A320-53-
1298, dated February 16, 2015, including Appendices 01, 02, and 03, 
dated February 16, 2015 (for cabin parts); and A320-53-1299, dated 
February 16, 2015, including Appendices 01, 02, and 03, dated 
February 16, 2015 (for cargo parts).

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be 
emailed to: [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 
European Aviation Safety Agency (EASA); or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0218, dated November 3, 2015, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-6893.

[[Page 33441]]

    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 44 51; email: [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 17, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12352 Filed 5-25-16; 8:45 am]
 BILLING CODE 4910-13-P