
[Federal Register Volume 80, Number 91 (Tuesday, May 12, 2015)]
[Rules and Regulations]
[Pages 27077-27081]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10181]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0636; Directorate Identifier 2012-NM-037-AD; 
Amendment 39-18154; AD 2015-09-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-601, B4-603, and B4-605R airplanes; Model A300 F4-
605R airplanes; Model A300 C4-605R Variant F airplanes; and Model A310-
204 and -304 airplanes; powered by General Electric (GE) Model CF6-80C2 
series engines. This AD was prompted by reports of two single-engine 
flameout events during inclement weather. This AD requires installing a 
shunt of the rotary selector (introducing an auto-relight function); 
and, for certain airplanes, a wiring modification to a certain circuit 
breaker panel. We are issuing this AD to prevent a long engine restart 
sequence after a non-selection of continuous relight by the crew and a 
flameout event of both engines, which could result in reduced 
controllability of the airplane, especially at low altitude.

DATES: This AD becomes effective June 16, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 16, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2012-0636; 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 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

[[Page 27078]]

SW., Renton, WA. For information on the availability of this material 
at the FAA, call 425-227-1221. It is also available on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2012-0636.

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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to certain Airbus 
Model A300 B4-601, B4-603, and B4-605R airplanes; Model A300 F4-605R 
airplanes; Model A300 C4-605R Variant F airplanes; and Model A310-204 
and -304 airplanes; powered by GE Model CF6-80C2 series engines. The 
SNPRM published in the Federal Register on March 5, 2014 (79 FR 12424). 
We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that 
published in the Federal Register on June 18, 2012 (77 FR 36211).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0156, dated July 3, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on Airbus Model A300 B4-
601, B4-603, and B4-605R airplanes; Model A300 F4-605R airplanes; Model 
A300 C4-605R Variant F airplanes; and Model A310-204 and -304 
airplanes; powered by GE Model CF6-80C2 series engines. The MCAI 
states:

    Two single flame-out events, attributed to inclement weather, 
occurred on Airbus Wide Body (WB) aeroplanes powered with GE CF6-
80C2 engines.
    In the original design of Airbus WB aeroplanes, no auto-relight 
function is embodied. This means that, in case where the flight crew 
does not select continuous relight and a flame-out event occurs, a 
long engine restart sequence is necessary.
    This condition, if not corrected (if both engines have flamed 
out simultaneously), could possibly result in significantly reduced 
control of the aeroplane, especially at low altitude.
    To address this potentially unsafe condition, Airbus designed a 
modification by introducing auto-relight function for aeroplanes 
powered by GE CF6-80C2 engines and EASA issued AD 2011-0113 to 
require installation of that auto-relight function to increase 
restart capability without flight crew action.
    Since that [EASA] AD was issued, erroneous instructions have 
been identified in various revisions of related Airbus Service 
Bulletins (SB) A310-74-2003, SB A300-74-6003 and SB A300-74-9001, 
which meant that some of the instructions could not be accomplished 
and resulted in additional work for aeroplanes already modified.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0113, which is superseded, allows 
additional compliance time and requires the modification of the 
aeroplanes in accordance with the instructions of the latest 
applicable Airbus SB revision.
    For aeroplanes that have already been partially modified by an 
earlier (incorrect) issue of an SB, as applicable, this [EASA] AD 
requires additional work.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-0636-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. The following 
presents the comments received on the SNPRM (79 FR 12424, March 5, 
2014) and the FAA's response to each comment.

Request To Withdraw the SNPRM (79 FR 12424, March 5, 2014) Based on the 
Rarity of Flameout Events

    FedEx stated that data presented by GE showed that since January 
2008, a total of seven engine flameouts attributed to inclement weather 
have been reported across the entire global population of all GE Model 
CF6-80C2 and CF6-80El series engines. FedEx pointed out that this 
corresponds to around 30 million flight hours and over 7 million flight 
departures. FedEx stated that the last event affecting an Airbus 
airplane was reported in 2006 and involved a power management 
controlled (PMC) engine. FedEx asserted that there has never been an 
inclement-weather-related engine flameout on a full authority digital 
engine control (FADEC) CF6-80C2-powered Airbus airplane reported to GE. 
FedEx stated that, in the text of the SNPRM (79 FR 12424, March 5, 
2014), the FAA cites the occurrence of two single-engine flameout 
events. FedEx stated that, while it cannot be certain which events the 
FAA is referring to, it can confidently assert that those events did 
not occur on a FedEx-operated airplane. FedEx remarked that, if an 
event has occurred within the last eight years and involved a FADEC-
controlled engine, GE is unaware of it. FedEx asked that the FAA 
consider, based on this experience, the extreme unlikelihood of such a 
rare event occurring on a GE-powered Airbus airplane simultaneously 
with the non-selection of continuous relight by well-trained crew 
members.
    From these statements, we infer that FedEx is requesting that we 
withdraw the SNPRM (79 FR 12424, March 5, 2014) based on the rarity of 
engine flameout events. We disagree with this request. EASA's 
determination for corrective action in the MCAI is based on a risk 
assessment of the worldwide fleet, and not limited to the experience of 
the commenter's operations. While these events might not have happened 
on the commenter's airplanes, inclement weather is likely to occur 
during any flight, and at any altitude. Both the PMC-controlled and 
FADEC-controlled engines remain susceptible to flameout during 
inclement weather without corrective actions to address the unsafe 
condition. While we frequently utilize flightcrew procedures as interim 
actions to address an unsafe condition, when available we consider a 
design solution to mitigate the unsafe condition to be more effective 
than relying on flightcrew procedures alone. We have determined that it 
is necessary to proceed with issuing this AD to adequately address the 
identified unsafe condition. Affected operators, however, may request 
approval of an alternative method of compliance (AMOC), as specified in 
paragraph (j)(1) of this AD (designated as paragraph (i)(1) of the 
SNPRM (79 FR 12424, March 5, 2014), by submitting data substantiating 
that the AMOC would provide an acceptable level of safety. We have not 
changed this AD in this regard.

Request To Withdraw the SNPRM (79 FR 12424, March 5, 2014) Based on 
Unreasonable Risk Factor

    FedEx stated that one of the primary justifications the FAA is 
using to establish the need for the SNPRM (79 FR 12424, March 5, 2014) 
is the concern that a long engine restart sequence could result in 
reduced controllability of the airplane ``especially at low altitude.'' 
FedEx agreed that an inability to achieve timely relight at low 
altitude would present a greater risk of an unsafe condition occurring 
and would perhaps provide ample justification for the subject 
modification. However, FedEx asserted that all data provided by GE 
indicate that this phenomenon does not occur at low altitudes. FedEx 
also stated that analysis of the primary root cause for the engine 
flameouts suggests that the flight envelope of concern is between 
approximately 10,000 feet above sea level (ASL) and 35,000 feet ASL 
during idle descent. FedEx

[[Page 27079]]

remarked that the average altitude at which these events have 
historically occurred is 22,000 feet ASL, with the lowest recorded 
altitude for a multi-engine event being 17,500 feet ASL. FedEx stated 
that in every recorded event, the flameout engines were restarted and 
continued to operate normally. FedEx concluded that, based on all the 
empirical data collected to date regarding the altitude at which these 
events occur, the momentary delay in restart time that is intended to 
be corrected by the modification does not seem to be significant enough 
to qualify as a reasonable risk factor.
    From these statements, we infer that FedEx is requesting that we 
withdraw the SNPRM (79 FR 12424, March 5, 2014) based on data showing 
that the events do not indicate a reasonable risk factor. We disagree 
with the request. Any delay in the ability to restart engines could 
result in an unsafe condition regardless of the altitude where the 
flameout occurs. Inclement weather may exist below 10,000 feet ASL and 
the possibility of terrain could also reduce altitude available to 
allow an engine restart. As we stated previously, we consider a design 
solution to be a more effective mitigating action to address an unsafe 
condition rather than relying on flightcrew procedures alone and the 
past experience of flightcrews having difficulty restarting engines 
following flameout. We have not changed this AD in this regard.

Request To Reduce the Proposed Applicability

    FedEx requested that the FAA consider reducing the applicability 
stated in the SNPRM (79 FR 12424, March 5, 2014) to include only the 
(relatively) higher-risk PMC-powered airplanes. FedEx stated that a 
factor specific to its operation addresses a point raised by the FAA, 
which is the small size of its non-FADEC fleet of Airbus airplanes. 
FedEx highlighted that data suggest that, since the implementation of 
the FADEC software, improvements of the rate of flameout events on all 
FADEC-controlled engines has dropped significantly and is well below 
corresponding rates on PMC-controlled Model CF6-80C2 series engines. 
FedEx stated that there are no recorded instances of a dual-engine 
flameout in inclement weather on any FADEC-controlled Model CF6-80C2 
series engine installed on Airbus airplanes. FedEx also stated that it 
operates a much larger GE-powered Airbus fleet with FADEC-controlled 
engines than with PMC-controlled engines. FedEx agreed with the FAA 
statement that ``not all affected airplanes have FADEC-controlled 
engines installed,'' and that FedEx's exposure in this area is very 
limited.
    We disagree with the commenter's request to reduce the 
applicability of this AD. The identified unsafe condition addressed in 
this AD applies to both types of GE Model CF6-80C2 series engines. The 
comparatively better in-flight shutdown rate of FADEC-controlled 
engines to PMC-controlled engines is inconsequential to the 
vulnerability in both engine designs due to flameout from icing 
conditions. Icing conditions are anticipated to occur, and no 
mitigating actions have been offered to address icing vulnerability in 
both engine designs. As we stated previously, a design solution is more 
effective than reliance on flightcrew procedures alone. We have not 
changed this AD in this regard.

Actions Since SNPRM (79 FR 12424, March 5, 2014) was Issued

    Since the SNPRM (79 FR 12424, March 5, 2014) was issued, EASA has 
issued AD 2014-0156, dated July 3, 2014, which supersedes EASA AD 2011-
0113, dated June 17, 2011. EASA AD 2014-0156 adds revised service 
information (Airbus Service Bulletin A300-74-6003, Revision 06, dated 
January 27, 2014, and Airbus Service Bulletin A310-74-2003, Revision 
06, dated January 27, 2014). The revised service information includes 
actions for previously modified airplanes. We have changed paragraph 
(g) of this AD to reference the revised service information. We also 
added a new paragraph (h) to this AD to specify actions for previously 
modified airplanes. We have re-designated subsequent paragraphs 
accordingly.
    The revised service information also reduces a certain compliance 
time to 12 months. However, for that action, this AD retains the 
compliance time proposed in the SNPRM: Within 2,200 flight hours or 30 
months after the effective date of this AD, whichever occurs later. We 
have determined that this compliance time adequately addresses the 
identified unsafe condition. We have determined that the compliance 
time, as proposed, represents the maximum interval of time allowable 
for the affected airplanes to continue to safely operate before the 
modification is done.

Conclusion

    We reviewed the relevant data, considered the comments received, 
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:
     Are consistent with the intent that was proposed in the 
SNPRM (79 FR 12424, March 5, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (79 FR 12424, March 5, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-74-6003, Revision 06, dated 
January 27, 2014, and Service Bulletin A310-74-2003, Revision 06, dated 
January 27, 2014. The service information describes installing a shunt 
of the rotary selector; and, for certain airplanes, a wiring 
modification to a certain circuit breaker panel. This service 
information is reasonably available at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0636. Or see ADDRESSES 
for other ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 47 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
              Action                    Labor cost            Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Modification.....................  Up to 98 work-hours   Up to $18,417......          $26,747        $1,257,109
                                    x $85 per hour =
                                    $8,330.
----------------------------------------------------------------------------------------------------------------


[[Page 27080]]

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-2012-0636; 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):

2015-09-08 Airbus: Amendment 39-18154. Docket No. FAA-2012-0636; 
Directorate Identifier 2012-NM-037-AD.

(a) Effective Date

    This AD becomes effective June 16, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-601, B4-603, and B4-605R 
airplanes; Model A300 F4-605R airplanes; Model A300 C4-605R Variant 
F airplanes; and Model A310-204 and -304 airplanes; certificated in 
any category; all serial numbers, powered by General Electric (GE) 
Model CF6-80C2 series engines.

(d) Subject

    Air Transport Association (ATA) of America Code 74, Ignition.

(e) Reason

    This AD was prompted by reports of two single-engine flameout 
events during inclement weather. We are issuing this AD to prevent a 
long engine restart sequence after a non-selection of continuous 
relight by the crew and a flameout event of both engines, which 
could result in reduced controllability of the airplane, especially 
at low altitude.

(f) Compliance

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

(g) Modification

    Within 6,000 flight hours or 30 months after the effective date 
of this AD, whichever occurs later: Modify the airplane by 
installing a shunt of the rotary selector (introducing an auto-
relight function), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-74-6003, Revision 06, 
dated January 27, 2014 (for Model A300 B4-601, B4-603, and B4-605R 
airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R 
Variant F airplanes); or Airbus Service Bulletin A310-74-2003, 
Revision 06, dated January 27, 2014 (for Model A310-204 and -304 
airplanes).

(h) Actions for Previously Modified Airplanes

    For airplanes which have already been modified in accordance 
with the requirements of paragraph (g) of this AD before the 
effective date of this AD: Within 2,200 flight hours or 30 months 
after the effective date of this AD, whichever occurs later, 
accomplish the work tasks, in accordance with the Accomplishment 
Instructions of the service information specified in Table 1 to this 
paragraph of this AD.

             Table 1 to Paragraph (h) of This AD--Work Tasks
------------------------------------------------------------------------
                                                       Accomplish the
                                    Previously     identified work tasks
          For Model--            modified using--    in accordance with
                                                   the instructions of--
------------------------------------------------------------------------
A300 B4-601, B4-603, and B4-    Airbus Service     Work Tasks 831-802001
 605R airplanes, Model A300 F4-  Bulletin A300-74-  and 831-803001 using
 605R airplanes, and Model       6003, dated July   Airbus Service
 A300 C4-605R Variant F          2, 2010.           Bulletin A300-74-
 airplanes.                                         6003, Revision 06,
                                                    dated January 27,
                                                    2014.
A300 B4-601, B4-603, and B4-    Airbus Service     Work Tasks 831-802001
 605R airplanes, Model A300 F4-  Bulletin A300-74-  and 831-803001 using
 605R airplanes, and Model       6003, Revision     Airbus Service
 A300 C4-605R Variant F          01, dated April    Bulletin A300-74-
 airplanes.                      1, 2011.           6003, Revision 06,
                                                    dated January 27,
                                                    2014.
A300 B4-601, B4-603, and B4-    Airbus Service     Work Tasks 831-802001
 605R airplanes, Model A300 F4-  Bulletin A300-74-  and 831-803001 using
 605R airplanes, and Model       6003, Revision     Airbus Service
 A300 C4-605R Variant F          02, dated          Bulletin A300-74-
 airplanes.                      February 9, 2012.  6003, Revision 06,
                                                    dated January 27,
                                                    2014.
A300 B4-601, B4-603, and B4-    Airbus Service     Work Task 831-803001
 605R airplanes, Model A300 F4-  Bulletin A300-74-  using Airbus Service
 605R airplanes, and Model       6003, Revision     Bulletin A300-74-
 A300 C4-605R Variant F          03, dated May      6003, Revision 06,
 airplanes.                      10, 2012.          dated January 27,
                                                    2014.

[[Page 27081]]

 
A310-204 and -304 airplanes...  Airbus Service     Work Tasks 831-802001
                                 Bulletin A310-74-  and 831-803001 using
                                 2003, dated July   Airbus Service
                                 2, 2010.           Bulletin A310-74-
                                                    2003, Revision 06,
                                                    dated January 27,
                                                    2014.
A310-204 and -304 airplanes...  Airbus Service     Work Tasks 831-802001
                                 Bulletin A310-74-  and 831-803001 using
                                 2003, Revision     Airbus Service
                                 01, dated April    Bulletin A310-74-
                                 1, 2011.           2003, Revision 06,
                                                    dated January 27,
                                                    2014.
A310-204 and -304 airplanes...  Airbus Service     Work Tasks 831-802001
                                 Bulletin A310-74-  and 831-803001 using
                                 2003, Revision     Airbus Service
                                 02, dated          Bulletin A310-74-
                                 February 9, 2012.  2003, Revision 06,
                                                    dated January 27,
                                                    2014.
A310-204 and -304 airplanes...  Airbus Service     Work Task 831-803001
                                 Bulletin A310-74-  using Airbus Service
                                 2003, Revision     Bulletin A310-74
                                 03, dated May      2003, Revision 06,
                                 10, 2012.          dated January 27,
                                                    2014.
------------------------------------------------------------------------

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraphs (i)(1)(i) and (i)(2)(ii) of this AD, and 
provided that the additional work in Airbus Service Bulletin A300-
74-6003, Revision 06, dated January 27, 2014; or Airbus Service 
Bulletin A310-74-2003, Revision 06, dated January 27, 2014; is done, 
as required by paragraph (g) of this AD.
    (i) For Model A300 B4-601, B4-603, and B4-605R airplanes, Model 
A300 F4-605R airplanes, and Model A300 C4-605R Variant F airplanes: 
Airbus Mandatory Service Bulletin A300-74-6003, Revision 04, dated 
January 9, 2013, which is not incorporated by reference in this AD.
    (ii) For Model A310-204 and -304 airplanes: Airbus Mandatory 
Service Bulletin A310-74-2003, Revision 04, dated January 9, 2013, 
which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
    (i) For Model A300 B4-601, B4-603, and B4-605R airplanes, Model 
A300 F4-605R airplanes, and Model A300 C4-605R Variant F airplanes: 
Airbus Service Bulletin A300-74-6003, Revision 05, dated May 23, 
2013, which is not incorporated by reference in this AD.
    (ii) For Model A310-204 and -304 airplanes: Airbus Service 
Bulletin A310-74-2003, Revision 05, dated May 23, 2013, which is not 
incorporated by reference in 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, 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 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 2014-0156, dated July 3, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2012-0636-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (l)(3) and (l)(4) of this AD.

(l) 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 A300-74-6003, Revision 06, dated 
January 27, 2014.
    (ii) Airbus Service Bulletin A310-74-2003, Revision 06, dated 
January 27, 2014.
    (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 account.airworth-eas@airbus.com; 
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 April 10, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10181 Filed 5-11-15; 8:45 am]
 BILLING CODE 4910-13-P


