[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24035-24039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10266]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD; 
Amendment 39-18898; AD 2017-10-24]
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) 2011-17-

[[Page 24036]]

09 for all Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes; and AD 2012-25-12 for all Airbus Model A330-200 and -300 
series airplanes. AD 2011-17-09 required revisions to certain operator 
maintenance documents to include new inspections. AD 2012-25-12 
required replacing certain main landing gear (MLG) bogie beams before 
reaching new reduced life limits. This new AD requires revising the 
maintenance or inspection program, as applicable, to incorporate new, 
more restrictive, or revised instructions and/or airworthiness 
limitation requirements. This AD was prompted by revisions to certain 
airworthiness limitation item (ALI) documents, which specify more 
restrictive instructions and/or airworthiness limitations. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 29, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 29, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 30, 2013 (77 FR 75825, December 26, 2012).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 30, 2011 (76 FR 53305, August 26, 2011).

ADDRESSES: For Airbus service information identified in this final 
rule, 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 [email protected]; 
Internet http://www.airbus.com.
    For Messier-Bugatti-Dowty service information identified in this 
final rule, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 
41094; telephone 859-525-8583; fax 859-485 8827; email 
[email protected].
    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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8428.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8428; 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 address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2011-17-09, Amendment 39-16773 (76 
FR 53305, August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, 
Amendment 39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-
12''). AD 2011-17-09 applied to all Airbus Model A330-200, -200 
Freighter, and -300 series airplanes. AD 2012-25-12 applied to all 
Airbus Model A330-200 and -300 series airplanes. The SNPRM published in 
the Federal Register on December 16, 2016 (81 FR 91062). We preceded 
the SNPRM with a notice of proposed rulemaking (NPRM) that published in 
the Federal Register on January 13, 2016 (81 FR 1570). The NPRM was 
prompted by a determination that more restrictive instructions and/or 
airworthiness limitations should be incorporated into the maintenance 
or inspection program, as applicable. The NPRM proposed to require 
revising the maintenance or inspection program, as applicable, to 
incorporate new or revised airworthiness limitation requirements. The 
SNPRM proposed to require revising the maintenance or inspection 
program, as applicable, to incorporate more restrictive instructions 
and/or airworthiness limitations that the manufacturer has recently 
issued. We are issuing this AD to detect and correct fatigue cracking, 
accidental damage, or corrosion in principal structural elements, and 
possible failure of certain life limited parts, which could result in 
reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive, 2014-0009, dated January 8, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:

    The airworthiness limitations for Airbus aeroplanes are 
currently published in Airworthiness Limitations Section (ALS) 
documents.
    The instructions and airworthiness limitations applicable to the 
Safe Life Airworthiness Limitation Items (SL ALI) are given in 
Airbus A330 ALS Part 1 and A340 ALS Part 1, which are approved by 
EASA.
    The revision 07 of Airbus A330 and A340 ALS Part 1 introduces 
more restrictive instructions and/or airworthiness limitations. 
Failure to comply with this revision could result in an unsafe 
condition.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0179, which is superseded, and requires 
accomplishment of the actions specified in Airbus A330 or A340 ALS 
Part 1 revision 07.
    In addition, this [EASA] AD also supersedes EASA AD 2011-0122-E 
and EASA AD 2011-0212, whose requirements have been transferred into 
Airbus A330 and A340 ALS Part 1 revision 07.

    The unsafe condition is fatigue cracking, accidental damage, or 
corrosion in certain principal structural elements, and possible 
failure of certain life limited parts, which could result in reduced 
structural integrity of the airplane. You may examine the MCAI in the 
AD docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-8428.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the available 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 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

[[Page 24037]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus A330 ALS Part 1, SL-ALI, Revision 08, 
dated April 11, 2016. Messier-Bugatti-Dowty has issued Service Letter 
A33-34 A20, Revision 7, including Appendixes A through F, dated July 
20, 2012. This service information describes SL-ALI for the landing 
gear. This service information is distinct since it was issued by two 
different manufacturers for different purposes.
    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.

Costs of Compliance

    We estimate that this AD affects 82 airplanes of U.S. registry.
    The actions that are required by AD 2011-17-09, and retained in 
this AD, take about 1 work-hour per product, at an average labor rate 
of $85 per work-hour. Based on these figures, the estimated cost of the 
actions that are required by AD 2011-17-09 is $85 per product.
    The actions that are required by AD 2012-25-12, and retained in 
this AD, take about 16 work-hours, at an average labor rate of $85 per 
work-hour, with required parts cost of about $255,000 per MLG bogie 
beam. Based on these figures, the estimated cost of the actions that 
are required by AD 2012-25-12 is up to $256,360 per MLG bogie beam.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic 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 $6,970, or $85 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.

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) 
2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011); and AD 
2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012); and 
adding the following new AD:

2017-10-24 Airbus: Amendment 39-18898; Docket No. FAA-2015-8428; 
Directorate Identifier 2014-NM-032-AD.

(a) Effective Date

    This AD is effective June 29, 2017.

(b) Affected ADs

    This AD replaces AD 2011-17-09, Amendment 39-16773 (76 FR 53305, 
August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, Amendment 
39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-12'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
with an original certificate of airworthiness or original export 
certificate of airworthiness issued on or before April 11, 2016.
    (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Airbus Model A330-223F and -243F airplanes.
    (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
inspections.

(e) Reason

    This AD was prompted by revisions to certain airworthiness 
limitation item documents, which specify more restrictive 
instructions and/or airworthiness limitations. We are issuing this 
AD to detect and correct fatigue cracking, accidental damage, or 
corrosion in principal structural elements, and possible failure of 
certain life limited parts, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Retained Maintenance Program Revision, With New Terminating Action

    This paragraph restates the requirements of paragraph (h) of AD 
2011-17-09, with new terminating action. Within 3 months after 
September 30, 2011 (the effective date of AD 2011-17-09): Revise the 
maintenance program by incorporating Airbus A330 Airworthiness 
Limitations Section (ALS) Part 1, Safe Life Airworthiness Limitation 
Items (SL-ALI), Revision 05, dated July 29, 2010. Comply with all 
ALIs in Airbus A330 ALS Part 1, SL-ALI, Revision 05, dated July 29, 
2010, at the times specified therein. Accomplishing the actions 
specified in paragraph (k) of this AD terminates the requirements of 
this paragraph.

(h) Retained Limitation of No Alternative Intervals or Limits, With 
Additional Exception

    This paragraph restates the requirements of paragraph (i) of AD 
2011-17-09, with additional exception. Except as provided by 
paragraphs (k) and (m)(1) of this AD, after accomplishment of the 
actions specified in paragraph (g) of this AD, no alternatives to 
the maintenance tasks, intervals, or limitations specified in 
paragraph (g) of this AD may be used.

(i) Retained Bogie Beam Replacement, With Specific Delegation Approval 
Language, New Terminating Action, and New Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-25-12, with specific delegation approval language and 
terminating action and new service information. For airplanes 
identified in paragraphs (c)(1) and (c)(3) of this AD: At the

[[Page 24038]]

later of the times specified in paragraphs (i)(1) and (i)(2) of this 
AD, replace all main landing gear (MLG) bogie beams having part 
number (P/N) 201485300, 201485301, 201272302, 201272304, 201272306, 
or 201272307, except those that have serial number (S/N) S2A, S2B, 
or S2C, as identified in Messier-Dowty Service Letter A33-34 A20, 
Revision 5, including Appendixes A through F, dated July 31, 2009; 
or Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7, 
including Appendixes A through F, dated July 20, 2012; with a new or 
serviceable part, 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). As of the effective date of this 
AD, the applicable MLG bogie beams specified in this paragraph must 
be replaced using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. Accomplishing the actions specified in paragraph 
(k) of this AD terminates the requirements of this paragraph.
    (1) At the applicable time specified in paragraphs (i)(1)(i), 
(i)(1)(ii), and (i)(1)(iii) of this AD.
    (i) For Model A330-201, -202, -203, -223, -243 series airplanes, 
weight variant (WV)02x, WV05x (except WV058), and WV06x series: 
Before the accumulation of a life limit of 50,000 landings or 72,300 
total flight hours, whichever occurs first from the first 
installation of a MLG bogie beam on the airplane.
    (ii) For Model A330-201, -202, -203, -223, -243 WV058 series 
airplanes: Before the accumulation of a life limit of 50,000 
landings or 57,900 total flight hours, whichever occurs first from 
the first installation of a MLG bogie beam on the airplane.
    (iii) For Model A330-301, -302, -303, -321, -322, -323, -341, -
342, -343 series airplanes, WV00x, WV01x, WV02x, and WV05x series: 
Before the accumulation of a life limit of 46,000 landings or 75,000 
total flight hours, whichever occurs first from the first 
installation of a MLG bogie beam on the airplane.
    (2) Within 6 months after January 30, 2013 (the effective date 
of AD 2012-25-12).

(j) Retained Parts Installation Limitation, With New Terminating Action

    This paragraph restates the requirements of paragraph (h) of AD 
2012-25-12, with new terminating action. For airplanes identified in 
paragraphs (c)(1) and (c)(3) of this AD, as of January 30, 2013 (the 
effective date of AD 2012-25-12), a MLG bogie beam having any part 
number identified in paragraph (i) of this AD may be installed on an 
airplane, provided its life has not exceeded the life limit 
specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 
this AD, and it is replaced with a new or serviceable part before 
reaching the life limit specified in paragraphs (i)(1)(i), 
(i)(1)(ii), and (i)(1)(iii) of this AD. Accomplishing the actions 
specified in paragraph (k) of this AD terminates the requirements of 
this paragraph.

(k) New Maintenance or Inspection Program Revision

    Within 3 months after the effective date of this AD: Revise the 
maintenance or inspection program, as applicable, by incorporating 
the information in Airbus A330 ALS Part 1, SL-ALI, Revision 08, 
dated April 11, 2016. The initial compliance times for the actions 
specified in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated 
April 11, 2016, are at the times specified in Airbus A330 ALS Part 
1, SL-ALI, Revision 08, dated April 11, 2016, or within 3 months 
after the effective date of this AD, whichever occurs later. 
Accomplishing the actions specified in this paragraph terminates the 
requirements specified in paragraphs (g) through (j) of this AD.

(l) New Limitation of No Alternative Actions or Intervals

    After the maintenance or inspection program, as applicable, has 
been revised, as required by paragraph (k) of this AD, no 
alternative actions (e.g., inspections) or intervals may be used 
unless the actions or intervals are approved as an alternative 
method of compliance (AMOC) in accordance with the procedures 
specified in paragraph (m)(1) of this AD.

(m) 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 manager of the International Branch, send it to the 
attention of the person identified in paragraph (n)(2) of this AD. 
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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0009, dated January 8, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-8428.
    (2) For more information about this AD, 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.

(o) 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 
June 29, 2017.
    (i) Airbus A330 Airworthiness Limitations Section Part 1, Safe 
Life Airworthiness Limitation Items, Revision 08, dated April 11, 
2016.
    (ii) Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 
7, including Appendixes A through F, dated July 20, 2012.
    (4) The following service information was approved for IBR on 
January 30, 2013 (77 FR 75825, December 26, 2012).
    (i) Messier-Dowty Service Letter A33-34 A20, Revision 5, 
including Appendixes A through F, dated July 31, 2009.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 30, 2011 (76 FR 53305, August 26, 2011).
    (i) Airbus A330 Airworthiness Limitations Section, Part 1, Safe 
Life Airworthiness Limitation Items, Revision 05, dated July 29, 
2010. The revision level of this document is indicated only on the 
title page and in the Record of Revisions; the revision date of this 
document is not indicated on the title page of this document.
    (ii) Reserved.
    (6) For Airbus 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 [email protected]; 
Internet http://www.airbus.com.
    (7) For Messier-Bugatti-Dowty service information identified in 
this AD, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 
41094; telephone 859-525-8583; fax 859-485 8827; email 
[email protected].
    (8) 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.
    (9) 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.


[[Page 24039]]


    Issued in Renton, Washington, on May 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10266 Filed 5-24-17; 8:45 am]
 BILLING CODE 4910-13-P