[Federal Register Volume 79, Number 192 (Friday, October 3, 2014)]
[Rules and Regulations]
[Pages 59636-59639]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-23139]



[[Page 59636]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0058; Directorate Identifier 2013-NM-116-AD; 
Amendment 39-17977; AD 2014-20-04]
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 superseding Airworthiness Directive (AD) 94-12-03 for 
certain Airbus Model A320 series airplanes. AD 94-12-03 required 
modification of the belly fairing structure. This new AD requires 
repetitive inspections for cracking of the four titanium angles between 
the belly fairing and the keel beam side panel, an inspection for 
cracking of the open holes if any cracking is found in the titanium 
angles, and repair or replacement if necessary; this new AD also 
expands the applicability of AD 94-12-03. This AD was prompted by 
reports of cracks at the lower riveting of the four titanium angles 
that connect the belly fairing to the keel beam side panels on both 
sides of the fuselage. We are issuing this AD to detect and correct 
cracking of the titanium angles that connect the belly fairing to the 
keel beam side panels on both sides of the fuselage, which could affect 
the structural integrity of the airplane.

DATES: This AD becomes effective November 7, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 7, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
10, 1994 (59 FR 64875, December 10, 1993).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0058; 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, 
Airworthiness Office--EIAS, 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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 94-12-03, Amendment 39-8930 (59 FR 28763, June 
3, 1994). AD 94-12-03 applied to Model A320 series airplanes having 
serial numbers (S/Ns) 003 through 092 inclusive. These serial numbers 
apply to Model A320-111, -211, and -231 series airplanes. The NPRM 
published in the Federal Register on February 26, 2014 (79 FR 10707).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0122, dated June 5, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During the fatigue test campaign of the A320 family type design, 
cracks have been found at the lower riveting of the four titanium 
angles which connect the belly fairing to the keel beam side panels 
between frames FR40 and FR42, on both sides of the fuselage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    In 1992, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
DGAC France issued AD 92-201-030 (http://ad.easa.europa.eu/blob/19922010tb_superseded.pdf/AD_F-1992-201-030_1) (which corresponds to 
FAA AD 94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994)) to 
require reinforcement of the belly fairing structure, which 
addressed part of the unsafe condition.
    For the reason described above, this [EASA] AD retains the 
requirements of DGAC France AD 92-201-030, which is superseded, and 
requires repetitive detailed inspections [for cracking] of the 
affected titanium angles and, depending on findings, repair or 
replacement of parts.

    As an option to extend the repetitive inspection interval, after 
the first detailed inspection is accomplished and on condition of no 
crack findings, this AD allows operators to remove the four titanium 
angles, perform a rototest for cracking on the open holes and, provided 
no cracks are found on the open holes, install new titanium angles, 
followed by post-modification detailed inspections of the new titanium 
angles.
    For any titanium angle crack findings, this AD requires removing 
any cracked angle, performing a rototest for cracking on the open holes 
and, provided no cracks are found, installing a new titanium angle, 
followed by detailed inspections of the new titanium angles.
    For any open hole cracking found during any rototest required by 
this AD, this AD requires repairing any cracking 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).
    This AD expands the applicability of AD 94-12-03, Amendment 39-8930 
(59 FR 28763, June 3, 1994), to include all Airbus Model A318, A319, 
A320, and A321 series airplanes.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0058-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 10707, February 26, 2014) and the FAA's response to each comment.

Request To Extend Proposed Compliance Time for Inspection of Titanium 
Angles

    Delta Airlines (DAL) requested that we extend the compliance time 
for the inspection of the titanium angles specified in paragraph (h)(3) 
of the proposed AD (79 FR 10707, February 26, 2014). DAL stated that 
extending this compliance time from 3,000 flight cycles or 6,000 flight 
hours after the effective date of this AD, whichever occurs first, to 
5,000 flight cycles or 10,000 flight hours, whichever occurs first, 
would match the repetitive interval for the detailed inspection on 
those airplanes that have not had the modification accomplished, and it 
would give DAL and other operators the opportunity to schedule these 
inspections in a hangar environment.
    We do not agree with the commenter's request to extend the 
compliance time specified in paragraph (h)(3) of this AD. DAL has not 
provided data to

[[Page 59637]]

substantiate that extending this compliance time would provide an 
acceptable level of safety. This compliance time was developed after 
analyzing risk to the fleet, availability of in-service information and 
feasibility of performing inspection. We consider the overall risk to 
the fleet, including the severity of the failure and the likelihood of 
the failure's occurrence, to calculate appropriate compliance times. 
However, under the provisions of paragraph (o)(1) of this AD, we will 
consider requests for approval of an extension of the compliance time 
if sufficient data are submitted to substantiate that the extension 
would provide an acceptable level of safety. We have not changed this 
final rule in this regard.

Request To Allow Special Flight Permit When Cracking Is Found

    DAL requested that we add a provision in the NPRM (79 FR 10707, 
February 26, 2014) to allow operators to ferry airplanes with cracking 
found during the inspection specified in paragraph (h) of this AD. DAL 
stated that a ferry flight would allow an airplane to be moved to a 
more suitable location for maintenance in the event damage is found. 
DAL also stated that the ferry flight is necessary due to the extensive 
level of access and disassembly.
    We agree with the intent behind the commenter's request, but find 
it unnecessary to include a special flight provision in this AD. 
Special flight permits are currently allowed under Section 39.23 of the 
Federal Aviation Regulations (14 CFR 39.23), unless specifically 
prohibited or limited by an AD. No change is necessary to this final 
rule in this regard.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often 
directs the owner/operator to contact the manufacturer for corrective 
actions, such as a repair. Briefly, the Airworthy Product paragraph 
allowed owners/operators to use corrective actions provided by the 
manufacturer if those actions were FAA-approved. In addition, the 
paragraph stated that any actions approved by the State of Design 
Authority (or its delegated agent) are considered to be FAA-approved.
    In the NPRM (79 FR 10707, February 26, 2014), we proposed to 
prevent the use of repairs that were not specifically developed to 
correct the unsafe condition, by requiring that the repair approval 
provided by the State of Design Authority or its delegated agent 
specifically refer to this FAA AD. This change was intended to clarify 
the method of compliance and to provide operators with better 
visibility of repairs that are specifically developed and approved to 
correct the unsafe condition. In addition, we proposed to change the 
phrase ``its delegated agent'' to include a design approval holder 
(DAH) with State of Design Authority design organization approval 
(DOA), as applicable, to refer to a DAH authorized to approve required 
repairs for the proposed AD.
    No comments were provided to the NPRM (79 FR 10707, February 26, 
2014) about these proposed changes. However, a comment was provided for 
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285, 
December 26, 2013). The commenter stated the following: ``The proposed 
wording, being specific to repairs, eliminates the interpretation that 
Airbus messages are acceptable for approving minor deviations 
(corrective actions) needed during accomplishment of an AD mandated 
Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases 
the foreign manufacturer's service bulletin and the foreign authority's 
MCAI might have been issued some time before the FAA AD. Therefore, the 
DOA might have provided U.S. operators with an approved repair, 
developed with full awareness of the unsafe condition, before the FAA 
AD is issued. Under these circumstances, to comply with the FAA AD, the 
operator would be required to go back to the manufacturer's DOA and 
obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a 
requirement, the FAA will coordinate with affected DAHs and verify they 
are prepared to implement means to ensure that their repair approvals 
consider the unsafe condition addressed in this AD. Any such 
requirements will be adopted through the normal AD rulemaking process, 
including notice-and-comment procedures, when appropriate.

[[Page 59638]]

    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``DAH with State of Design Authority design 
organization approval,'' but instead we have provided the specific 
delegation approval granted by the State of Design Authority for the 
DAH throughout this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this final rule 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 
NPRM (79 FR 10707, February 26, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 10707, February 26, 2014).

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions that were required by AD 94-12-03, Amendment 39-8930 
(59 FR 28763, June 3, 1994), and retained in this AD take about 288 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $1,045 per product. Based on these figures, 
the estimated cost of the actions that were required by AD 94-12-03 is 
$25,525 per product.
    We also estimate that it will take about 7 work-hours per product 
to comply with the basic new requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $506,345, or $595 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition and optional actions specified in 
this AD.

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-2014-0058; 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 removing Airworthiness Directive (AD) 
94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994), and adding the 
following new AD:

2014-20-04 Airbus: Amendment 39-17977. Docket No. FAA-2014-0058; 
Directorate Identifier 2013-NM-116-AD.

(a) Effective Date

    This AD becomes effective November 7, 2014

(b) Affected ADs

    This AD replaces AD 94-12-03, Amendment 39-8930 (59 FR 28763, 
June 3, 1994).

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks at the lower riveting 
of the four titanium angles that connect the belly fairing to the 
keel beam side panels on both sides of the fuselage. We are issuing 
this AD to detect and correct cracking of the titanium angles that 
connect the belly fairing to the keel beam side panels on both sides 
of the fuselage, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Retained Modification

    This paragraph restates the requirements of paragraph (a) of AD 
94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994), with new 
service information. For Model A320-111, -211, and -231 series 
airplanes, manufacturer serial numbers 003 through 092 inclusive: 
Prior to the accumulation of 12,000 total landings on the airplane, 
or within 300 days after January 10, 1994 (the effective date of AD 
93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), 
whichever occurs later, modify the belly fairing structure, in 
accordance with the Accomplishment Instructions of an Airbus service 
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD. As of the effective date of this AD, use only the Airbus service 
bulletin specified in paragraph (g)(3) of this AD.
    (1) Airbus Industrie Service Bulletin A320-53-1014, dated June 
25, 1992.

[[Page 59639]]

    (2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, 
dated May 26, 1993.
    (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994.

(h) New Requirement of This AD: Repetitive Inspection

    At the latest of the compliance times specified in paragraphs 
(h)(1), (h)(2), and (h)(3) of this AD: Do a detailed inspection for 
cracking of the four titanium angles between the belly fairing and 
the keel beam side panel, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1259, dated November 
6, 2012.
    (1) Before the accumulation of 30,000 total flight cycles or 
60,000 total flight hours, whichever occurs first after first flight 
of the airplane.
    (2) Within 30,000 flight cycles or 60,000 flight hours, 
whichever occurs first after modification of the airplane as 
required by paragraph (g) of this AD, or after installation of new 
titanium angles, provided that, prior to installation, a rototest 
for cracking on the open holes has been accomplished with no crack 
findings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012.
    (3) Within 3,000 flight cycles or 6,000 flight hours, whichever 
occurs first after the effective date of this AD.

(i) New Requirement of This AD: Post-Inspection Actions for No Crack 
Findings

    If, during any inspection required by paragraph (h) of this AD, 
there is no crack finding: Accomplish the actions specified in 
either paragraph (i)(1) or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (h) of this AD 
at intervals not to exceed 5,000 flight cycles or 10,000 flight 
hours, whichever occurs first
    (2) Before further flight after the inspection required by 
paragraph (h) of this AD, remove all inspected titanium angles, 
accomplish a rototest for cracking on the open holes and, provided 
no cracks are found, install new titanium angles, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012.

(j) New Requirement of This AD: Post-Inspection Actions for Any Crack 
Findings

    If, during any inspection required by paragraph (h) of this AD, 
there is any crack finding: Before further flight, remove the 
affected titanium angle(s), accomplish a rototest for cracking on 
the open holes, and, provided no cracks are found, install new 
titanium angles, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-53-1259, dated November 6, 2012.

(k) New Requirement of This AD: Post-Installation Repetitive 
Inspections

    For airplanes on which new titanium angles were installed as 
specified in paragraph (i)(2) or (j) of this AD: Within 30,000 
flight cycles or 60,000 flight hours, whichever occurs first after 
the installation, accomplish a detailed inspection for cracking of 
the four titanium angles between the belly fairing and the keel beam 
side panel, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012. Repeat 
the inspection thereafter at intervals not to exceed 5,000 flight 
cycles or 10,000 flight hours, whichever occurs first.

(l) New Requirement of This AD: Post Inspection Actions for Any Crack 
Findings During Post-Installation Inspections

    If, during any inspection as required by paragraph (k) of this 
AD, there is any crack finding: Before further flight, remove the 
affected titanium angles, accomplish a rototest for cracking on the 
open holes, and, provided no cracks are found, install new titanium 
angles, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1259, dated November 6, 2012.

(m) New Requirement of This AD: Corrective Action for Rototest Crack 
Finding

    If, during any rototest as required by paragraph (i), (j), or 
(l) of this AD, any crack is found: Before further flight, 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).

(n) New Provision of This AD: No Termination Action for Repetitive 
Inspections

    Repair or replacement of parts as specified in this AD does not 
terminate the repetitive inspections required by this AD.

(o) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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.
    (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.

(p) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency, Airworthiness Directive 2013-0122, 
dated June 5, 2013, for related information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0058-0002.

(q) 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.
    (3) The following service information was approved for IBR on 
November 7, 2014.
    (i) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994, including supplementary page 7A. Pages 1-3, 15, 
19, 20, and 25 of this document are identified as Revision 2, dated 
September 1, 1994; pages 4-8, 10, 12, 16-18, and 21-24 are 
identified as Revision 1, dated May 26, 1993; and pages 9, 11, 13, 
14, and 26 are identified as the original, dated June 25, 1992.
    (ii) Airbus Service Bulletin A320-53-1259, dated November 6, 
2012.
    (4) The following service information was approved for IBR on 
January 10, 1994 (59 FR 64875, December 10, 1993).
    (i) Airbus Industrie Service Bulletin A320-53-1014, dated June 
25, 1992.
    (ii) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, 
dated May 26, 1993.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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.
    (6) 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.
    (7) 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 September 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-23139 Filed 10-2-14; 8:45 am]
BILLING CODE 4910-13-P