
[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)]
[Proposed Rules]
[Pages 7992-7994]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02535]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0084; Directorate Identifier 2014-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 A300 B4-2C, B4-103, and B4-203 airplanes; Airbus 
Model A300 B4-600 series airplanes; and Airbus Model A300 B4-600R 
series airplanes. This proposed AD was prompted by reports indicating 
that, on airplanes that received a certain repair following crack 
findings, cracks can re-initiate. This proposed AD would require 
repetitive inspections for cracking of the frame (FR) 40 forward 
fittings for airplanes previously repaired. We are proposing this AD to 
detect and correct cracking on the FR 40 forward fittings, which could 
result in rupture of the forward fittings and reduction of in-flight 
structural strength.

DATES: We must receive comments on this proposed AD by March 30, 2015.

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: 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 proposed 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 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-2015-
0084; 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, Transport Airplane Directorate, FAA, 
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-2015-0084; 
Directorate Identifier 2014-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 2014-0199, dated September 05, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-2C, B4-103, and B4-203 airplanes; Airbus Model A300 B4-600 
series airplanes; and Airbus Model A300 B4-600R series airplanes. The 
MCAI states:

    During routine inspection on an A300-600 aeroplane, a crack was 
found in the right-hand frame (FR) 40 forward fitting between 
stringer (STRG) 32 and STRG 33. The subject aeroplane had previously 
been modified, as a crack prevention measure, in accordance with 
Airbus SB A300-57-6053 (mod 10453).
    To ensure the structural integrity of FR 40, pending completion 
of the full root cause analysis using a refined Finite Element Model 
(FEM), EASA issued AD 2009-0094 [dated April 21, 2009, http://ad.easa.europa.eu/ad/2009-0094], to require, a one-time Detailed 
Visual Inspection (DVI) of A300 and A300-600 aeroplanes on which 
Airbus SB A300-53-0297 or SB A300-57-6053, as applicable, was 
embodied as a crack prevention measure.
    Thereafter, cracks were found during maintenance check in the FR 
40 forward fitting on two aeroplanes, one A300 with Airbus SB A300-
53-0297 embodied and one A300-600 with Airbus SB A300-57-6053 
embodied. EASA AD 2009-0094 had been accomplished on both 
aeroplanes.
    Consequently, EASA issued AD 2011-0163 [dated August 30, 2011, 
http://ad.easa.europa.eu/ad/2011-0163], superseding EASA AD 2009-
0094, to require, for aeroplanes modified preventively, repetitive 
DVI of the FR 40 forward fitting (without nut removal), 
accomplishment of a one-time Eddy Current (EC) inspection or liquid 
penetrant inspection of this area (with nut removal) and, depending 
on findings, the accomplishment of associated corrective actions.
    A detailed FEM study was recently completed which demonstrated 
that, on aeroplanes repaired following crack findings in accordance 
with the instructions of Airbus SB A300-53-0297 or SB A300-57-6053 
at any revision, as applicable, cracks can re-initiate.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections of the FR 40 forward fitting for aeroplanes 
repaired in accordance with the instructions of Airbus SB A300-53-
0297 or SB A300-57-6053 following crack findings.

    The corrective actions include a repair 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).
    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-2015-
0084.

[[Page 7993]]

Relevant Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information:
     Airbus A300 Alert Operators Transmission (AOT) A53W002-14, 
dated April 02, 2014.
     Airbus A300 AOT A57W003-14, Revision 01, dated April 17, 
2014.
    Airbus A300 Alert Operators Transmission (AOT) A53W002-14, dated 
April 02, 2014, describes procedures for repetitive inspections of the 
FR40 forward fitting on A300 aircraft post MOD 10453S20571. Airbus A300 
AOT A57W003-14, Revision 01, dated April 17, 2014, describes procedures 
for repetitive inspections of the FR40 forward fitting on A300-600 
aircraft pre MOD 10221S20394 and post MOD 10453S20571. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

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.

Costs of Compliance

    We estimate that this proposed AD affects 26 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 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 $6,630, or $255 
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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-
181-AD.

(a) Comments Due Date

    We must receive comments by March 30, 2015.

(b) Affected ADs

    None

(c) Applicability

    (1) This AD applies to the airplanes identified in paragraphs 
(c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category.
    (i) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes, all 
manufacturer serial numbers (MSN), on which modification 10453 has 
been embodied as a repair following a crack finding, as specified in 
Airbus Service Bulletin A300-53-0297 (modification 10453).
    (ii) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
and B4-622R airplanes, all MSN as specified in Airbus Service 
Bulletin A300-57-6053.
    (2) This AD does not apply to airplanes that have been modified, 
as a preventive measure, as specified in Airbus Service Bulletin 
A300-53-0297 or A300-57-6053 (modification 10453), as applicable to 
airplane model.

(d) Subject

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

(e) Reason

    This AD was prompted by reports indicating that, on airplanes 
that received a certain repair following crack findings, cracks can 
re-initiate. We are issuing this AD to detect and correct cracking 
on the frame (FR) 40 forward fittings, which could result in rupture 
of the forward fittings and reduction of in-flight structural 
strength.

(f) Compliance

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

(g) Repetitive Inspections

    Within 300 flight cycles after the effective date of this AD, do 
a detailed inspection of the forward fitting at FR 40 without nut 
removal to detect cracks on both left-hand and right-hand sides of 
the airplane, in accordance with Airbus A300 Alert Operators 
Transmission (AOT) A53W002-14, dated April 2, 2014 (for Airbus Model 
A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus A300AOT 
A57W003-14, Revision 01, dated April 17, 2014 (for Airbus Model A300 
B4-600 series airplanes, and Airbus Model A300 B4-600R series 
airplanes); as applicable. If any crack is detected, repair before 
further flight 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). Repeat the inspection thereafter at 
intervals not to exceed 300 flight cycles.

(h) 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

[[Page 7994]]

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: 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0199, dated September 5, 
2014, 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-2015-0084.
    (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 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 January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02535 Filed 2-12-15; 8:45 am]
BILLING CODE 4910-13-P


