AD 2014-16-13

[Federal Register Volume 79, Number 166 (Wednesday, August 27, 2014)]
[Rules and Regulations]
[Pages 51083-51088]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-19708]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0236; Directorate Identifier 2013-NM-184-AD; 
Amendment 39-17937; AD 2014-16-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This AD was prompted by our 
determination of the need to incorporate new life limits for the main 
landing gear (MLG) barrel assembly, retraction actuator assembly 
linkage, and flange duct. This AD requires revising the maintenance or 
inspection program, as applicable, to include the new life limits. We 
are issuing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

DATES: This AD becomes effective October 1, 2014.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2014-0236 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email <a href="/cdn-cgi/l/email-protection#ee8f8d8d819b809ac08f879c99819c9a86c38b8f9dae8f879c8c9b9dc08d8183"><span class="__cf_email__" data-cfemail="b3d2d0d0dcc6ddc79dd2dac1c4dcc1c7db9ed6d2c0f3d2dac1d1c6c09dd0dcde">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 
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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM 116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A300 
series airplanes. The NPRM published in the Federal Register on April 
17, 2014 (79 FR 21651).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0210, dated September 11, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition all Airbus Model A300 
series airplanes. The MCAI states:

    Some life limits previously defined in Revision 00 of A300 ALS 
[airworthiness limitations section] Part 1 have been removed [from] 
that document at Revision 01 and should normally be included in an 
ALS Part 4.
    At this time, there are no plans to issue an ALS Part 4 for A300 
aeroplanes.
    Nevertheless, failure to comply with these life limits could 
result in an unsafe condition.
    For the reasons described above, it has been decided to require 
the application of these life limits through a separate [EASA] AD. 
Consequently, this [EASA] AD requires application of life limits 
applicable to Main Landing Gear (MLG) barrel assembly, retraction 
actuator assembly linkage assembly and flanged duct which were 
previously contained in Airbus ALS Part 1 Revision 00.
    EASA AD 2007-0293 [which corresponds with FAA AD 2009-18-15, 
Amendment 39-16011 (74 FR 48143, September 22, 2009)], which 
required compliance with the actions specified in ALS Part 1, will 
be superseded by a new [EASA] AD, requiring compliance with ALS Part 
1 at Revision 1.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2014-0236-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We

[[Page 51084]]

received no comments on the NPRM (79 FR 21651, April 17, 2014) or on 
the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this AD.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 21651, April 17, 2014) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 21651, April 17, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 7 airplanes of U.S. registry.
    We also estimate that it takes about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $595, or $85 per product.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2014-0236; 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 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 51085]]

Sec.  39.13  [Amended]

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

2014-16-13 Airbus: Amendment 39-17937. Docket No. FAA-2014-0236; 
Directorate Identifier 2013-NM-184-AD.

(a) Effective Date

    This AD becomes effective October 1, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear; and 36, Pneumatic.

(e) Reason

    This AD was prompted by our determination of the need to 
incorporate new life limits for the main landing gear (MLG) barrel 
assembly, retraction actuator assembly linkage, and flange duct. We 
are issuing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

(f) Compliance

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

(g) Revise the Maintenance or Inspection Program

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
life limits specified in Appendix 1 of this AD into the Airbus A300 
Airworthiness Limitations Section (ALS) Part 1. The initial 
compliance time for the replacement is identified in Appendix 1 of 
this AD and is prior to the applicable life limits specified in 
Appendix 1 of this AD, or within 90 days after the effective date of 
this AD, whichever occurs later.

(h) No Alternative Actions and Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (i)(1) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: <a href="/cdn-cgi/l/email-protection#edd4c0aca3a0c0dcdcdbc0aca0a2aec0bfa8bcb8a8beb9bead8b8c8cc38a829b"><span class="__cf_email__" data-cfemail="4871650906056579797e650905070b651a0d191d0d1b1c1b082e2929662f273e">[email&#160;protected]</span></a>. 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 Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2013-0210, 
dated September 11, 2013, for related information. This MCAI may be 
found in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetailD=FAA-2014-0236-0002">http://www.regulations.gov/#!documentDetailD=FAA-2014-0236-0002</a>.

(k) Material Incorporated by Reference

    None.

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    Issued in Renton, Washington, on August 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-19708 Filed 8-26-14; 8:45 am]
BILLING CODE 4910-13-P