[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Proposed Rules]
[Pages 8575-8577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-02683]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0086; Directorate Identifier 2014-NM-191-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A310-203 airplanes. This proposed AD is intended to 
complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This proposed 
AD was prompted by reports that side link clevis bolts of the front 
engine mount do not meet the Design Service Goal (DSG) requirements on 
airplanes equipped with General Electric Company CF6-80A3 engines. This 
proposed AD would require repetitive replacement of all side link 
clevis engine mount bolts. We are proposing this AD to prevent failure 
of the front engine mount, and consequent possible departure of the 
engine.

DATES: We must receive comments on this proposed AD by April 6, 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 [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-2015-
0086; 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, Washington 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-2015-0086; 
Directorate Identifier 2014-NM-191-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

    As described in FAA Advisory Circular 120 104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a LOV of the 
engineering data that support the structural maintenance program under 
14 CFR 26.21. This proposed AD is the result of an assessment of the 
previously established programs by Airbus during the process of 
establishing the LOV for Airbus Model A310-203 airplanes. The actions 
specified in this proposed AD are necessary to complete certain 
programs to ensure the continued airworthiness of aging airplane 
structure and to support an airplane reaching its LOV.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0191, dated August 29, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A310-203 airplanes. The MCAI states:

    During fatigue analysis performed in the scope of the Extended 
Service Goal, taking into account the certification loads and the 
new lift-off loads, Airbus determined that side link clevis engine 
mount bolts do not meet the Design Service Goal (DSG) requirements 
on aeroplanes equipped with CF6-80A3 engines.
    This condition, if not corrected, could lead to failure of the 
front engine mount, possibly resulting in-flight separation of the 
engine from the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A310-71-2038 to introduce a life limit on the 
side link clevis engine mount bolts.
    For the reason described above, this [EASA] AD requires 
implementation of the new life limit and replacement of all side 
link clevis engine mount bolts that have exceeded the new limit.


[[Page 8576]]


    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-
0086.

Relevant Service Information Under 1 CFR Part 51

    Airbus has issued Mandatory Service Bulletin A310-71-2038, 
including Appendices 01 and 02, dated April 8, 2014. The service 
information describes procedures for replacement of all side link 
clevis bolts on the CF6-80A3 front engine mount and subsequent re-
identification of the newly installed bolts with a cross (to 
differentiate them from the old ones). 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 13 airplanes of U.S. 
registry.
    We also estimate that it would take about 142 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $2,900 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $194,610, or $14,970 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-2015-0086; Directorate Identifier 2014-NM-
191-AD.

(a) Comments Due Date

    We must receive comments by April 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203 airplanes, certificated 
in any category, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports that side link clevis bolts of 
the front engine mount do not meet the Design Service Goal (DSG) 
requirements on airplanes equipped with General Electric Company 
CF6-80A3 engines. We are issuing this AD to prevent failure of the 
front engine mount, and consequent possible departure of the engine.

(f) Compliance

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

(g) Repetitive Bolt Replacement

    Within 18 months after the effective date of this AD, replace 
the side link clevis bolts, nuts, and bushings of the front engine 
mount on both engines, and re-identify the new installed bolts with 
a cross (to differentiate them from the old ones), in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A310-71-2038, including Appendices 01 and 02, dated April 
8, 2014. Repeat the replacement thereafter at intervals not to 
exceed 29 years.

(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 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: [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 Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

[[Page 8577]]

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0191, dated August 29, 
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-2015-0086.
    (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 January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02683 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P