[Federal Register Volume 80, Number 136 (Thursday, July 16, 2015)]
[Rules and Regulations]
[Pages 42005-42007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17202]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0086; Directorate Identifier 2014-NM-191-AD; 
Amendment 39-18206; AD 2015-14-08]
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 A310-203 airplanes. This 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 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 AD requires 
repetitive replacement of all side link clevis engine mount bolts. We 
are issuing this AD to prevent failure of the front engine mount, and 
consequent possible departure of the engine.

DATES: This AD becomes effective August 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 20, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0086or 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: [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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0086.

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 A310-203 
airplanes. The NPRM published in the Federal Register on February 18, 
2015 (80 FR 8575). The NPRM 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. The NPRM was prompted by reports that 
side link clevis bolts of the front engine mount do not meet the DSG 
requirements on airplanes equipped with General Electric Company CF6-
80A3 engines. The NPRM proposed to require repetitive replacement of 
all side link clevis engine mount bolts. We are issuing this AD to 
prevent failure of the front engine mount, and consequent possible 
departure of the engine.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
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.

    You may examine the MCAI in the AD docket on the Internet at http:/
/www.regulations.gov/

[[Page 42006]]

#!documentDetail;D=FAA-2015-0086-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 8575, February 18, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 8575, February 18, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 8575, February 18, 2015).

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus 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). 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 of this 
AD.

Costs of Compliance

    We estimate that this AD affects 13 airplanes of U.S. registry.
    We also estimate that it will take about 142 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $2,900 per 
product. Based on these figures, we estimate the cost of this 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 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 http://www.regulations.gov/#!docketDetail;D=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 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.


Sec.  39.13  [Amended]

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

2015-14-08 Airbus: Amendment 39-18206. Docket No. FAA-2015-0086; 
Directorate Identifier 2014-NM-191-AD.

(a) Effective Date

    This AD becomes effective August 20, 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 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

[[Page 42007]]

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.

(i) Related Information

    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/#!documentDetail;D=FAA-2015-
0086-0003.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A310-71-2038, including Appendices 
01 and 02, dated April 8, 2014.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17202 Filed 7-15-15; 8:45 am]
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