[Federal Register Volume 81, Number 176 (Monday, September 12, 2016)]
[Proposed Rules]
[Pages 62679-62681]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21149]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9066; Directorate Identifier 2014-NM-113-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-10-
17, for all Airbus Model A300 and A310 series airplanes, and Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R 
Variant F airplanes (collectively called A300-600 series airplanes). AD 
2011-10-17 currently requires revising the maintenance program by 
incorporating certain airworthiness limitation items (ALIs). Since we 
issued AD 2011-10-17, the manufacturer has revised certain ALI 
documents, which specify more restrictive instructions and/or 
airworthiness limitations. This proposed AD would require revising the 
maintenance or inspection program, as applicable, to incorporate new or 
revised structural inspection requirements. This proposed AD would also 
remove Model A310 and A300-600 series airplanes from the applicability. 
We are proposing this AD to detect and correct fatigue cracking, 
damage, and corrosion in certain structure; such fatigue cracking, 
damage, and corrosion could result in reduced structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by October 27, 
2016.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 [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-
9066; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
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-2016-9066; 
Directorate Identifier 2014-NM-113-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

    On May 2, 2011, we issued AD 2011-10-17, Amendment 39-16698 (76 FR 
27875, May 13, 2011) (``AD 2011-10-17''). AD 2011-10-17 requires 
actions intended to address an unsafe condition on all Airbus Model 
A300 and A310 series airplanes, and Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model C4-605R Variant F airplanes 
(collectively called A300-600 series airplanes).
    Since we issued AD 2011-10-17, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, has issued Airworthiness Directive 2015-0115, dated 
June 23, 2015; (collectively referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI'') to correct an 
unsafe condition. The MCAI states:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALIs) are currently listed in the 
Airbus Airworthiness Limitations Sections [ALS] Part 2.
    Airbus recently revised the A300 ALS Part 2 and this Revision 02 
was approved by EASA. Airbus A300 ALS Part 2 Revision 02 introduces 
more restrictive maintenance requirements and airworthiness 
limitations, which have been identified as mandatory actions for 
continued airworthiness.
    EASA issued AD 2014-0124 to require compliance with the 
maintenance requirements and associated airworthiness limitations 
defined in Airbus A300 ALS Part 2 Revision 01.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0124 for A300 aeroplanes and requires 
implementation of new or more restrictive maintenance instructions 
and/or airworthiness limitations as specified in Airbus A300 ALS 
Part 2 Revision 02.
    The requirements for A310 and A300-600 aeroplanes remain 
unchanged and are covered by EASA AD 2014-0124R1 [FAA AD 2013-13-13, 
Amendment 39-17501 (79 FR 47857, August 19, 2014), contains the 
corresponding requirements for the Model A300-600 and A310 series 
airplanes].

    The unsafe condition is fatigue cracking, damage, or corrosion in 
certain structure (principal structural

[[Page 62680]]

elements), which could result in reduced structural integrity of the 
airplane. 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-2016-9066.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus A300 Airworthiness Limitations Section 
Part 2, Damage-Tolerant Airworthiness Limitation Items (DT ALIs), 
Revision 02, dated October 3, 2014. This service information describes 
airworthiness limitations applicable to the DT ALIs.
    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 the same 
type design.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new inspections. Compliance with these inspections 
is required by 14 CFR 91.403(c). For airplanes that have been 
previously modified, altered, or repaired in the areas addressed by 
these inspections, the operator may not be able to accomplish the 
inspections described in the revisions. In this situation, to comply 
with 14 CFR 91.403(c), the operator must request approval for an 
alternative method of compliance according to paragraph (j)(1) of this 
proposed AD. The request should include a description of changes to the 
required inspections that will ensure the continued damage tolerance of 
the affected structure.

Costs of Compliance

    We estimate that this proposed AD affects 11 airplanes of U.S. 
registry.
    The actions that are required by AD 2011-10-17 and retained in this 
proposed AD take about 1 work-hour per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2011-10-17 is $85 per product.
    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 $935, 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 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 removing Airworthiness Directive (AD) 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-9066; Directorate Identifier 2014-NM-
113-AD.

(a) Comments Due Date

    We must receive comments by October 27, 2016.

(b) Affected ADs

    This AD replaces AD 2011-10-17, Amendment 39-16698 (76 FR 27875, 
May 13, 2011) (``AD 2011-10-17'').

(c) Applicability

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

(d) Subject

    Air Transport Association (ATA) of America Codes 52, Doors; 53, 
Fuselage; 54, Nacelles/pylons; 55, Stabilizers; and 57, Wings.

(e) Reason

    This AD was prompted by a revision of certain airworthiness 
limitations items (ALI) documents, which specify more restrictive 
instructions and/or airworthiness limitations. We are issuing this 
AD to detect and correct fatigue cracking, damage, and corrosion in 
certain structure; such fatigue cracking, damage, and corrosion 
could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Revision of the ALS of the Instructions for ICA, With 
Changes

    This paragraph restates the requirements of paragraph (s) of AD 
2011-10-17, with changes. Within 3 months after June 17, 2011 (the 
effective date of AD 2011-10-17): Revise the maintenance program to 
incorporate the structural inspections and inspection intervals 
defined in the Airbus A300 ALI Document AI/SE-M2/95A.1308/07, Issue 
4, dated June 2008. Thereafter, except as required by paragraph (h) 
of this AD and except as provided by paragraph (j)(1) of this AD, no 
alternative structural inspections and inspection intervals may be 
approved. The actions must be accomplished in accordance with the 
applicable issue of the ALI. The initial ALI tasks must be done at 
the times specified in Airbus A300 ALI Document AI/

[[Page 62681]]

SE-M2/95A.1308/07, Issue 4, dated June 2008.

(h) New Requirement of This AD: Maintenance or Inspection Program 
Revision

    Within 3 months the effective date of this AD: Revise the 
maintenance program or inspection program, as applicable, to 
incorporate the structural inspections and inspection intervals 
defined in Airbus A300 ALS Part 2, Damage-Tolerant Airworthiness 
Limitation Items, Revision 02, dated October 3, 2014. The initial 
compliance time for the ALI tasks identified in Airbus A300 ALS Part 
2, Damage-Tolerant Airworthiness Limitation Items, Revision 02, 
dated October 3, 2014, is at the applicable times specified in 
Airbus A300 ALS Part 2, Damage-Tolerant Airworthiness Limitation 
Items, Revision 02, dated October 3, 2014, or within 3 months after 
the effective date of this AD, whichever occurs later. Accomplishing 
the applicable initial ALI tasks constitutes terminating action for 
the requirements of paragraphs (g) of this AD for that airplane 
only.

 (i) No Alternative Actions and Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (h) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an AMOC in accordance with the procedures 
specified in paragraph (j)(1) of this AD.

(j) 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, FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone 425-227-2125; fax 425-227-1149. Information may be emailed 
to: [email protected].
    (i) 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.
    (ii) AMOCs approved previously for AD 2011-10-17 are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0124R1, dated June 23, 
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-2016-9066.
    (2) 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 [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 August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21149 Filed 9-9-16; 8:45 am]
 BILLING CODE 4910-13-P