[Federal Register Volume 80, Number 20 (Friday, January 30, 2015)]
[Rules and Regulations]
[Pages 5032-5034]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-01184]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0525; Directorate Identifier 2013-NM-235-AD; 
Amendment 39-18078; AD 2015-02-11]
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 certain 
Airbus Model A330-300, A340-200, and A340-300 series airplanes. This AD 
was prompted by a report of substantial inner skin disbonding damage 
found on a rudder. This AD requires performing an inspection for damage 
of certain rudders, and repair if necessary. We are issuing this AD to 
detect and correct damage of the rudder, which could result in reduced 
structural integrity of the rudder.

DATES: This AD becomes effective March 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 6, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0525; 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--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email <a href="/cdn-cgi/l/email-protection#1879716a6f776a6c7071767d6b6b36592b2b2835592b2c285879716a7a6d6b367b7775"><span class="__cf_email__" data-cfemail="e4858d96938b96908c8d8a819797caa5d7d7d4c9a5d7d0d4a4858d96869197ca878b89">[email protected]</span></a>; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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 certain Airbus Model A330-
300, A340-200, and A340-300 series airplanes. The NPRM published in the 
Federal Register on August 13, 2014 (79 FR 47387).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0270R1, dated November 27, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for Airbus Model A330-
300, A340-200, and A340-300 series airplanes. The MCAI states:

    One A310 operator found substantial inner skin disbonding damage 
on a rudder. The results of the subsequent investigation revealed 
that the most probable cause of this damage was a blunt impact with 
no visible damage from outside during the rudder handling. Such type 
of damage might grow with pressure variation during ground-air-
ground cycles, and tests performed with other rudders showed a rapid 
propagation of damage during artificial pressure cycling.
    This condition, if not detected and corrected, could affect the 
structural integrity of the rudder.
    For the affected A310 and A300-600 aeroplanes, EASA issued AD 
2013-0039 [http://ad.easa.europa.eu/blob/easa_ad_2013_0039.pdf/AD_2013-0039], to address and correct this potential unsafe 
condition.
    As potentially affected rudders can also be installed on A330 
and A340 aeroplanes, Airbus issued Alert Operator Transmission (AOT) 
A55L001-12 [dated December 20, 2012], pending Aircraft Maintenance 
Manual (AMM) 27-21-41 PB401 revision, to provide operators with 
updated rudder handling procedures.
    EASA issued AD 2013-0270 [http://ad.easa.europa.eu/blob/easa_ad_2013_0270.pdf/AD_2013-0270], to require identification of 
affected rudders P/N [part number] A55471500XXX (where XXX stands 
for any numerical value), a one-time ultrasonic test (UT) inspection 
of each affected rudder to detect signs of disbonding and, depending 
on findings, accomplishment of applicable corrective action(s).
    After [EASA] AD 2013-0270 was issued, operators commented that 
the batch of rudders to be inspected was not correctly defined.
    For the reason described above, [EASA] AD 2013-0270 is revised 
to clarify that no action is required for rudders previously 
inspected in accordance with Airbus Service Bulletin (ASB) A330-55-
3038 or SB A340-55-4034 [which are required by FAA AD 2009-10-11, 
Amendment 39-15907 (74 FR 23622, May 20, 2009)], as applicable to 
aeroplane model, provided the rudder has never been removed and/or 
installed on an aeroplane since this inspection.

    Required actions include an elasticity of laminate checker 
inspection of the rudder side panel to detect external and internal 
disbonding, and a woodpecker or tap test inspection to detect external 
disbonding, and repair if necessary. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0525-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
47387, August 13, 2014) and the FAA's response.

Request To Correct Certain Document Numbers

    Lufthansa Technik (Lufthansa) asked that we correct certain 
document

[[Page 5033]]

numbers for the service information identified in paragraph (h) of the 
NPRM (79 FR 47387, August 13, 2014). Lufthansa stated that paragraph 
(h) of the NPRM incorrectly refers to Airbus Service Bulletins A300-55-
3038 and A310-55-4034, instead of Airbus Service Bulletins A330-55-3038 
and A340-55-4034, both dated November 7, 2007.
    We agree with the commenter for the reason provided. We have 
corrected the document numbers for the service information identified 
in paragraph (h) of this AD accordingly.

Compliance Time Change

    We revised the compliance time in paragraph (g) of this AD for the 
part numbers and serial numbers that cannot be identified from ``before 
further flight'' to ``within 3 months after the effective date of this 
AD.'' We have also revised the compliance time in paragraph (h) of this 
AD for the ultrasonic test inspection from ``before further flight'' to 
``within 3 months after the effective date of this AD.'' This 
compliance time corresponds to the compliance time specified in the 
MCAI. We have determined this compliance time will provide an 
acceptable level of safety.

Conclusion

    We reviewed the relevant data, considered the comment 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 47387, August 13, 2014) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 47387, August 13, 2014).

Related Service Information

    Airbus has issued Alert Operators Transmission A55L001-12, dated 
December 20, 2012. The service information describes procedures for an 
inspection for damage of certain rudders. You can find this information 
at http://www.regulations.gov by searching for and locating Docket No. 
FAA-2014-0525.

Costs of Compliance

    We estimate that this AD affects 74 airplanes of U.S. registry.
    We also estimate that it will take about 12 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 $0 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $75,480, or $1,020 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition 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-2014-0525; 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):

2015-02-11 Airbus: Amendment 39-18078. Docket No. FAA-2014-0525; 
Directorate Identifier 2013-NM-235-AD.

(a) Effective Date

    This AD becomes effective March 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-301, -302, -303, -321, -
322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, 
-213, -311, -312, and -313 airplanes; certificated in any category; 
except airplanes on which Airbus Modification 41800 has been 
embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Reason

    This AD was prompted by a report of substantial inner skin 
disbonding damage on a rudder. We are issuing this AD to detect and 
correct damage of the rudder, which could result in reduced 
structural integrity of the rudder.

(f) Compliance

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

(g) Rudder Assembly Identification

    Within 3 months after the effective date of this AD, inspect for 
the rudder assembly part number and serial number, in accordance 
with Airbus Alert Operators Transmission (AOT) A55L001-12, dated 
December 20, 2012. If the part number or serial number cannot be 
identified, within 3 months after the effective date of this AD, 
identify the part number and serial number using a method

[[Page 5034]]

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.

(h) Inspection

    If a rudder assembly having any part number starting with 
A55471500 or A55471500XXX (where XXX stands for any numerical value) 
is found during the inspection required by paragraph (g) of this AD, 
and that rudder assembly has been inspected before the effective 
date of this AD, as specified in Airbus Service Bulletin A330-55-
3038, dated November 7, 2007 (which is not incorporated by reference 
in this AD); or Airbus Service Bulletin A340-55-4034, dated November 
7, 2007 (which is not incorporated by reference in this AD); as 
applicable; and that rudder assembly has been removed and installed 
on any airplane after the inspection or that has been inspected off-
wing: Within 3 months after the effective date of this AD, do an 
ultrasonic test inspection for damage (e.g., disbonding and liquid 
ingress) of the rudder side panel along the Z-profile and in the 
booster area, in accordance with Airbus AOT A55L001-12, dated 
December 20, 2012. If any damage is found, before further flight, do 
the inspections specified in paragraphs (h)(1) and (h)(2) of this AD 
to confirm disbonding damage, in accordance with Airbus AOT A55L001-
12, dated December 20, 2012.
    (1) Do an elasticity of laminate checker inspection to detect 
external and internal disbonding.
    (2) Do a woodpecker or tap test inspection to detect external 
disbonding.

(i) Repair

    If any disbonding or damage (e.g. liquid ingress) is confirmed 
during any inspection required by paragraphs (h), (h)(1), and (h)(2) 
of this AD, repair at the time specified in paragraph (i)(1), 
(i)(2), or (i)(3) of this AD, as applicable.
    (1) If the disbonding is less than or equal to 50 millimeters 
(mm) in width and less than or equal to 150 mm in length: Before 
further flight, vent the rudder core using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA. Within 100 flight 
cycles after venting the rudder core, do a permanent repair 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 for the venting and repair 
methods must include the DOA-authorized signature.
    (2) If the disbonding is greater than 50 mm in width, or greater 
than 150 mm in length: Before further flight, repair 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.
    (3) If any damage other than disbonding (e.g., liquid ingress) 
is confirmed during any inspection required by paragraph (h) of this 
AD, before further flight, repair, 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.

(j) Parts Installation Limitation

    As of the effective date of this AD, you may install, on any 
airplane, a rudder assembly having part number A55471500XXX (where 
XXX stands for any numerical value), provided the inspection 
required by paragraph (h) of this AD and all applicable repair 
actions required by paragraph (i) of this AD are done before further 
flight.

(k) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#cef7e38f8083e3fffff8e38f83818de39c8b9f9b8b9d9a9d8ea8afafe0a9a1b8"><span class="__cf_email__" data-cfemail="d6effb97989bfbe7e7e0fb979b9995fb849387839385828596b0b7b7f8b1b9a0">[email protected]</span></a>. 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0270R1, dated November 27, 
2013, 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-2014-0525.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 Alert Operators Transmission A55L001-12, dated 
December 20, 2012, including Inspection Flow Chart AOpT ref.: 
A55L001-12, not dated. The document number and date of this document 
are identified on only the first page of this AOT.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#b5d4dcc7c2dac7c1dddcdbd0c6c69bf486868598f4868185f5d4dcc7d7c0c69bd6dad8"><span class="__cf_email__" data-cfemail="fa9b93888d95888e9293949f8989d4bbc9c9cad7bbc9cecaba9b9388988f89d4999597">[email protected]</span></a>; 
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 January 15, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01184 Filed 1-29-15; 8:45 am]
BILLING CODE 4910-13-P


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