81 FR 1504 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 8 (January 13, 2016)

Page Range		1504-1508
FR Document		2015-33289
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re-protected against corrosion after inspection or maintenance actions were accomplished. This AD requires for certain MLG units, determining which revision of the component maintenance manual (CMM) was used to accomplish the most recent MLG unit overhaul; a detailed inspection for missing or damaged paint, and if necessary, a detailed inspection of the cadmium plating for discrepancies, measurement of the depth of the cadmium plating, a general visual inspection of the base metal for corrosion or damage, a detailed inspection of repaired areas for cracking or corrosion; and corrective actions if necessary. We are issuing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants.
Federal Register, Volume 81 Issue 8 (Wednesday, January 13, 2016)
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Rules and Regulations]
[Pages 1504-1508]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-33289]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1981; Directorate Identifier 2014-NM-204-AD; 
Amendment 39-18362; AD 2016-01-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

[[Page 1505]]


ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and 
A340-300 series airplanes. This AD was prompted by reports that the 
inner bore of some main landing gear (MLG) unit bogie beams were 
insufficiently re-protected against corrosion after inspection or 
maintenance actions were accomplished. This AD requires for certain MLG 
units, determining which revision of the component maintenance manual 
(CMM) was used to accomplish the most recent MLG unit overhaul; a 
detailed inspection for missing or damaged paint, and if necessary, a 
detailed inspection of the cadmium plating for discrepancies, 
measurement of the depth of the cadmium plating, a general visual 
inspection of the base metal for corrosion or damage, a detailed 
inspection of repaired areas for cracking or corrosion; and corrective 
actions if necessary. We are issuing this AD to detect and correct 
corrosion in the bore of each MLG unit bogie beam, which could result 
in collapse of a MLG unit, and subsequent damage to the airplane and 
injury to occupants.

DATES: This AD becomes effective February 17, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 17, 
2016.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1981; 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 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. For Messier-Dowty service information contact Messier-
Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH, England; telephone 
+44(0) 1452 712424; fax+ 44(0) 1452 713821; Internet http://www.safranmbd.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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1981.

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-
200 Freighter, A330-200, A330-300, A340-200, and A340-300 series 
airplanes. The NPRM published in the Federal Register on June 15, 2015 
(80 FR 34098).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0222, dated October 6, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series 
airplanes. The MCAI states:

    From in-service experience, it was found that the inner bore of 
some bogie beams had been insufficiently re-protected against 
corrosion after inspection and/or possible maintenance actions 
accomplished in this area (absence of corrosion inhibitor and damage 
to paint have been found in some specific areas).
    This condition, if not detected and corrected, could lead to 
corrosion on the bore of the bogie beam, potentially resulting in 
Main Landing Gear (MLG) collapse, ultimately resulting in damage to 
the aeroplane and injury to the occupants.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A32L004-14, providing inspection 
instructions for some aeroplane configurations.
    For the reasons described above, this [EASA] AD requires 
identification of the MLG units that are possibly affected, [a 
detailed] inspection [for missing or damaged paint] of the MLG Bogie 
Beam bore and, depending on findings, accomplishment of the 
applicable corrective actions.
    This [EASA] AD also prohibits the installation of MLG units that 
have been overhauled by using instructions from an earlier 
Components Maintenance Manual (CMM) revision.

    Required actions also include a detailed inspection of the cadmium 
plating for discrepancies (gray in color), measurement of the depth of 
the cadmium plating if necessary, and a general visual inspection of 
the base metal for corrosion or damage, and a detailed inspection of 
repaired areas for cracking or corrosion. Corrective actions include 
removing cadmium plating and repairing any cracked, corroded, or 
damaged areas; re-applying cadmium plating and paint; and re-applying 
temporary corrosion protection to the bores of the MLG bogie beams.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1981-0002.

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 NPRM (80 FR 34098, June 15, 2015) 
and the FAA's response to each comment.

Request for Clarification of Optional Method of Compliance

    Air France and American Airlines (AA) requested that paragraph (j) 
of the proposed AD (80 FR 34098, June 15, 2015) be revised to clarify 
that after accomplishment of the actions in the Accomplishment 
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated 
November 16, 2007, including Appendixes A, B, C, and D, dated November 
16, 2007; or Service Bulletin A33/34-32-272, Revision 1, dated 
September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008; the actions specified in the Messier-Dowty service 
information identified in paragraphs (j)(1) through (j)(5) of the 
proposed AD must not be accomplished on that same MLG unit.
    We agree with the commenters' request and have revised paragraph 
(j) of this AD to clarify that after accomplishment of the actions in 
the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-272, dated November 16, 2007, including Appendixes A, B, C, and 
D, dated November 16, 2007; or Service Bulletin A33/34-32-272, Revision 
1, dated September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008; the actions specified in the Messier-Dowty service 
information identified in paragraphs (j)(1) through (j)(5) of this AD 
must not be accomplished on that same MLG unit. The actions in the 
Accomplishment Instructions of Messier-Dowty service information 
identified in paragraphs (j)(1) through (j)(5) do not provide 
sufficient corrosion protection for the MLG units.

[[Page 1506]]

Request To Correct Service Information Reference

    Air France requested that the references to the Airbus component 
maintenance manual in paragraph (g) of the proposed AD be changed to 
Messier-Dowty component maintenance manual.
    We agree with the commenter's request because the component 
maintenance manuals were published by Messier-Dowty, not Airbus. We 
have revised paragraphs (g) and (k) of this AD accordingly.

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 
NPRM (80 FR 34098, June 15, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 34098, June 15, 2015).
    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 Alert Operators Transmission A32L004-14, dated 
July 28, 2014, including Appendixes 1, 2, 3, and 4. This service 
information describes procedures for inspections of the bogie beam bore 
of the MLG.
    Messier-Dowty has issued the following service information, which 
describes procedures for inspections of the internal diameter of the 
bogie beam for corrosion.
     Service Bulletin A33/34-32-272, dated November 16, 2007, 
including Appendixes A, B, C, and D, dated November 16, 2007.
     Service Bulletin A33/34-32-272, Revision 1, dated 
September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008.
    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 89 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, and 1 work-hour to 
report the inspection findings. 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 $98,345, or $1,105 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for any necessary follow-on actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1981; 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):

2016-01-03 Airbus: Amendment 39-18362. Docket No. FAA-2015-1981; 
Directorate Identifier 2014-NM-204-AD.

(a) Effective Date

    This AD becomes effective February 17, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.

[[Page 1507]]

    (1) Model A330-201, A330-202, A330-203, A330-223, A330-223F, 
A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-
322, A330-323, A330-341, A330-342, and A330-343 airplanes; all 
manufacturer serial numbers; except those on which Airbus 
Modification 58896 has been embodied in production or embodied 
through Airbus Service Bulletin A330-32-3237.
    (2) Model A340-211, A340-212, A340-213, A340-311, A340-312, and 
A340-313 airplanes; all manufacturer serial numbers; except those on 
which Airbus Modification 58896 has been embodied in production or 
embodied through Airbus Service Bulletin A340-32-4279.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports that the inner bore of some main 
landing gear (MLG) unit bogie beams were insufficiently re-protected 
against corrosion after inspection or maintenance actions were 
accomplished. We are issuing this AD to detect and correct corrosion 
in the bore of each MLG unit bogie beam, which could result in 
collapse of a MLG unit, and subsequent damage to the airplane and 
injury to occupants.

(f) Compliance

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

(g) Identification of Affected MLG Units

    Within 12 months after the effective date of this AD: For MLG 
units having a 201252 series or 201490 series part number, determine 
the revision of the Messier-Dowty component maintenance manual (CMM) 
used to do the most recent MLG unit overhaul. If it is determined 
that the Messier-Dowty CMM revision specified in paragraph (g)(1) or 
(g)(2) of this AD was used to accomplish the most recent MLG unit 
overhaul: Within 12 months after the effective date of this AD, 
clean the area between the bogie pivot pin and the bogie beam bore 
of each MLG unit and do a detailed inspection for missing or damaged 
paint, in accordance with Airbus Alert Operators Transmission 
A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 
4, which do not have a date.
    (1) For MLG units having a part number in the 201252 series: 
Messier-Dowty CMM 32-11-74, Revision 25 or earlier.
    (2) For MLG units having a part number in the 201490 series: 
Messier-Dowty CMM 32-12-05, Revision 20 or earlier.

(h) Inspection of Cadmium Plating

    If, during the inspection required by paragraph (g) of this AD, 
any missing or damaged paint is found: Before further flight, do a 
detailed inspection of the cadmium plating for discrepancies, 
measure the depth of the plating as applicable, and do a general 
visual inspection of the base metal for corrosion or damage, in 
accordance with Airbus Alert Operators Transmission A32L004-14, 
dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do 
not have a date. If any discrepancy, damage, or corrosion is found, 
before further flight, do all applicable corrective actions, and do 
a detailed inspection of repaired areas for cracking or corrosion, 
in accordance with Airbus Alert Operators Transmission A32L004-14, 
dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do 
not have a date, except where Airbus Alert Operators Transmission 
A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 
4, specifies to contact Messier-Dowty if cracking or corrosion is 
found in a repaired area, 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).

(i) Reporting Requirement

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD, report the findings of the inspection required by 
paragraph (g) of this AD to Airbus, Customer Services Engineering--
SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA-32, 
Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12 05; 
email [email protected]. The report must include the 
information specified in Appendix 2 of Airbus Alert Operators 
Transmission A32L004-14, dated July 28, 2014.
    (1) If the inspection was done on or after the effective date of 
this AD: Within 90 days after that inspection.
    (2) If the inspection was done before the effective date of this 
AD: Within 90 days after the effective date of this AD.

(j) Optional Method of Compliance

    Accomplishment of the boroscope inspection of the internal 
diameter of the bogie beam for corrosion or damage to the protective 
treatments, measurement of the depth of the protective treatments as 
applicable, and accomplishment of all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-272, dated November 16, 2007, including 
Appendixes A, B, C, and D, dated November 16, 2007; or Revision 1, 
dated September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008; are acceptable for the corresponding actions 
required by paragraphs (g) and (h) of this AD for that MLG unit; 
however, after accomplishment of the actions in the Accomplishment 
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated 
November 16, 2007, including Appendixes A, B, C, and D, dated 
November 16, 2007; or Service Bulletin A33/34-32-272, Revision 1, 
dated September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008; the actions specified in the Messier-Dowty 
service information identified in paragraphs (j)(1) through (j)(5) 
of this AD must not be accomplished on that same MLG unit. Where 
Messier-Dowty Service Bulletin A33/34-32-272, dated November 16, 
2007, including Appendixes A, B, C, and D, dated November 16, 2007; 
or Revision 1, dated September 22, 2008, including Appendixes A, B, 
C, and D, dated September 22, 2008; specify to contact Messier-Dowty 
for repair information, the repair 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.
    (1) Messier-Dowty Service Bulletin A33/34 32-285, dated July 9, 
2010.
    (2) Messier-Dowty Service Bulletin A33/34 32-285, Revision 1, 
dated October 4, 2011.
    (3) Messier-Dowty Service Bulletin A33/34 32-285, Revision 2, 
dated October 4, 2012.
    (4) Messier-Dowty Service Bulletin A33/34 32-285, Revision 3, 
dated September 11, 2013.
    (5) Messier-Dowty Service Bulletin A33/34 32-285, Revision 4, 
dated January 23, 2014.
    Note 1 to paragraph (j) of this AD: Inspections done using the 
instructions in Messier-Dowty Service Bulletin A33/34-32-285, 
Revision 5, dated August 14, 2014, do not affect the optional method 
of compliance provided by this paragraph.

(k) Parts Installation Limitation

    As of the effective date of this AD, any overhauled MLG unit 
having a 201252 series or 201490 series part number may be installed 
on an airplane, provided the most recent MLG overhaul was done using 
a Messier-Dowty CMM that is not specified in paragraph (g)(1) or 
(g)(2) of this AD, or, prior to installation, the MLG unit passes 
the inspection required by paragraph (g) of this AD.

(l) 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: 9 [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. 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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a

[[Page 1508]]

person is not required to respond to, nor shall a person be subject 
to a penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES 200.

(m) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2014-0222, dated October 6, 2014, for 
related information. This MCAI may be found in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-
1981-0002.

(n) 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 A32L004-14, dated July 
28, 2014, including Appendixes 1, 2, 3, and 4, which are not dated.
    (ii) Messier-Dowty Service Bulletin A33/34-32-272, dated 
November 16, 2007, including Appendixes A, B, C, and D, dated 
November 16, 2007.
    (iii) Messier-Dowty Service Bulletin A33/34-32-272, Revision 1, 
dated September 22, 2008, including Appendixes A, B, C, and D, dated 
September 22, 2008.
    (3) 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.
    (4) For Messier-Dowty service information identified in this AD, 
contact Messier-Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH, 
England; telephone +44(0) 1452 712424; fax+ 44(0) 1452 713821; 
Internet http://www.safranmbd.com.
    (5) 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.
    (6) 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 December 29, 2015.
Philip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-33289 Filed 1-12-16; 8:45 am]
BILLING CODE 4910-13-P
1504 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

(f) Compliance (2) If any visible deformation is found (2) Before using any approved AMOC,
Comply with this AD within the during the inspection required in paragraph notify your appropriate principal inspector,
compliance times specified, unless already (j) of this AD, before further flight, obtain and or lacking a principal inspector, the manager
done. implement an FAA-approved corrective of the local flight standards district office/
action, approved specifically for this AD. At certificate holding district office
(g) Inspect the Upper Skin Joints for the operator’s discretion, assistance may be
Adequate Sealant (o) Related Information
provided by contacting Piper Aircraft, Inc. at
Within the next 100 hours time-in-service the address identified in paragraph (p)(3) of For more information about this AD,
(TIS) after February 17, 2016 (the effective this AD. After obtaining and implementing contact Gregory ‘‘Keith’’ Noles, Aerospace
date of this AD) or 12 months after February an FAA-approved corrective action, Engineer, FAA, Atlanta ACO, 1701 Columbia
17, 2016 (the effective date of this AD), approved specifically for this AD, before Avenue, College Park, Georgia 30337;
whichever occurs first, inspect the upper telephone: (404) 474–5551; fax: (404) 474–
further flight, rework the stringers and apply
skin joints for adequate sealant following Part 5606; email: gregory.noles@faa.gov.
sealant as required in paragraph (k) of this
I of Piper Aircraft, Inc. Service Bulletin No. AD. (p) Material Incorporated by Reference
1262B, dated April 23, 2015. No further
(k) Rework Stringers and Seal Skin Joints (1) The Director of the Federal Register
action per this AD is required if adequate
approved the incorporation by reference
sealant is already applied. If any inspection required by paragraphs (IBR) of the service information listed in this
(h) Inspect for Evidence of Water Intrusion/ (g) through (j) of this AD reveals paragraph under 5 U.S.C. 552(a) and 1 CFR
Moisture discrepancies (no sealant/inadequate sealant, part 51.
evidence of water intrusion/moisture, (2) You must use this service information
If you find missing or inadequate sealant corrosion, or deformation), before further
during the inspection required by paragraph as applicable to do the actions required by
flight, after completing any necessary this AD, unless the AD specifies otherwise.
(g) of this AD, before further flight, inspect corrective actions, rework wing stringers and
for evidence of water intrusion/moisture (i) Piper Aircraft, Inc. Service Bulletin No.
seal skin joints following Part II of Piper 1262B, dated April 23, 2015.
following Part II of Piper Aircraft, Inc. Aircraft, Inc. Service Bulletin No. 1262B,
Service Bulletin No. 1262B, dated April 23, (ii) Reserved.
dated April 23, 2015. (3) For Piper Aircraft, Inc. service
2015.
(1) If no evidence of water intrusion/ (l) Credit for Actions Done in Accordance information identified in this AD, contact
moisture is found during the inspection Piper Aircraft, Inc., Customer Service, 2926
With Previous Service Information
required in paragraph (h) of this AD, before Piper Drive, Vero Beach, Florida 32960;
Actions done before February 17, 2016 (the telephone: (877) 879–0275; fax: None; email:
further flight, rework the stringers and apply effective date of this AD) following Part I and
sealant as required in paragraph (k) of this customer.service@piper.com; Internet:
Part II of Piper Aircraft, Inc. Service Bulletin www.piper.com.
AD.
No. 1262, dated October 16, 2013, or Part I (4) You may view this service information
(2) If evidence of water intrusion/moisture
and Part II of Piper Aircraft, Inc. Service at FAA, Small Airplane Directorate, 901
is found during the inspection required in
Bulletin No. 1262A, dated November 14, Locust, Kansas City, Missouri 64106. For
paragraph (h) of this AD, before further flight,
2013, as applicable, are considered information on the availability of this
do the actions required in paragraphs (i) and
(j) of this AD. acceptable for compliance with the material at the FAA, call (816) 329–4148. It
corresponding actions specified in is also available on the Internet at http://
(i) Inspect for Corrosion paragraphs (g), (h), (i), and (k) (including www.regulations.gov by searching for
If you find, as a result of the inspection subparagraphs) of this AD. Additional locating Docket No. FAA–2015–4213.
required by paragraph (h) of this AD, inspections beyond Service Bulletin No. 1262 (5) You may view this service information
evidence of water intrusion/moisture, before are required to fully comply with paragraph that is incorporated by reference at the
further flight, inspect for corrosion following (j) of this AD. National Archives and Records
Part II of Piper Aircraft, Inc. Service Bulletin Administration (NARA). For information on
(m) Special Flight Permit
No. 1262B, dated April 23, 2015. the availability of this material at NARA, call
(1) If no evidence of corrosion is found (1) In accordance with 14 CFR 39.23, a 202–741–6030, or go to: http://
during the inspection required in paragraph single flight is allowed to a location to do the www.archives.gov/federal-register/cfr/ibr-
(i) of this AD, before further flight, rework the actions in paragraph (g) of this AD. locations.html.
stringers and apply sealant as required in (2) In accordance with 14 CFR 39.23, a
Issued in Kansas City, Missouri, on
paragraph (k) of this AD. single flight is allowed to a location to do the
December 24, 2015.
(2) If evidence of corrosion is found during inspections, rework and installation of
sealant required in paragraphs (h) through (k) Pat Mullen,
the inspection required in paragraph (i) of
this AD, before further flight, obtain and of this AD. Prior to the flight to perform the Acting Manager, Small Airplane Directorate,
implement an FAA-approved corrective inspections, rework, and installation of Aircraft Certification Service.
action approved specifically for this AD. At sealant, the following inspection must be [FR Doc. 2015–33170 Filed 1–12–16; 8:45 am]
the operator’s discretion, assistance may be performed: If the inspection required by BILLING CODE 4910–13–P
provided by contacting Piper Aircraft, Inc. at paragraph (g) of this AD reveals no sealant,
the address identified in paragraph (p)(3) of inspect for evidence of wing damage (skin or
this AD. After obtaining and implementing stringer deformation, e.g. buckling). Any
wing damage that is found must be repaired
DEPARTMENT OF TRANSPORTATION
an FAA-approved corrective action,
approved specifically for this AD, before before further flight and before any special
flight permit is authorized.
Federal Aviation Administration
further flight, rework the stringers and apply
sealant as required in paragraph (k) of this (n) Alternative Methods of Compliance
AD. 14 CFR Part 39
(AMOCs)
(j) Inspect for Deformation [Docket No. FAA–2015–1981; Directorate
(1) The Manager, Atlanta Aircraft Identifier 2014–NM–204–AD; Amendment
If you find, as a result of the inspection Certification Office (ACO), FAA, has the 39–18362; AD 2016–01–03]
asabaliauskas on DSK5VPTVN1PROD with RULES

required by paragraph (h) of this AD, authority to approve AMOCs for this AD, if
evidence of water intrusion/moisture, before requested using the procedures found in 14 RIN 2120–AA64
further flight, do a visual inspection for skin CFR 39.19. In accordance with 14 CFR 39.19,
or stringer deformation. send your request to your principal inspector Airworthiness Directives; Airbus
(1) If no evidence of deformation is found or local Flight Standards District Office, as Airplanes
during the inspection required in paragraph appropriate. If sending information directly
(j) of this AD, before further flight, rework the to the manager of the ACO, send it to the AGENCY: Federal Aviation
stringers and apply sealant as required in attention of the person identified in Administration (FAA), Department of
paragraph (k) of this AD. paragraph (l)(1) of this AD. Transportation (DOT).

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1506 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

Request To Correct Service Information inspection findings. The average labor or on the distribution of power and
Reference rate is $85 per work-hour. Based on responsibilities among the various
Air France requested that the these figures, we estimate the cost of levels of government.
references to the Airbus component this AD on U.S. operators to be $98,345, For the reasons discussed above, I
maintenance manual in paragraph (g) of or $1,105 per product. certify that this AD:
We have received no definitive data 1. Is not a ‘‘significant regulatory
the proposed AD be changed to Messier-
that would enable us to provide cost action’’ under Executive Order 12866;
Dowty component maintenance manual. 2. Is not a ‘‘significant rule’’ under the
We agree with the commenter’s estimates for any necessary follow-on
actions. DOT Regulatory Policies and Procedures
request because the component
(44 FR 11034, February 26, 1979);
maintenance manuals were published Paperwork Reduction Act 3. Will not affect intrastate aviation in
by Messier-Dowty, not Airbus. We have A federal agency may not conduct or Alaska; and
revised paragraphs (g) and (k) of this AD sponsor, and a person is not required to 4. Will not have a significant
accordingly. respond to, nor shall a person be subject economic impact, positive or negative,
Conclusion to penalty for failure to comply with a on a substantial number of small entities
collection of information subject to the under the criteria of the Regulatory
We reviewed the relevant data,
requirements of the Paperwork Flexibility Act.
considered the comments received, and
determined that air safety and the Reduction Act unless that collection of Examining the AD Docket
public interest require adopting this AD information displays a current valid
OMB control number. The control You may examine the AD docket on
with the changes described previously the Internet at http://
and minor editorial changes. We have number for the collection of information
required by this AD is 2120–0056. The www.regulations.gov/
determined that these minor changes: #!docketDetail;D=FAA-2015-1981; or in
• Are consistent with the intent that paperwork cost associated with this AD
has been detailed in the Costs of person at the Docket Management
was proposed in the NPRM (80 FR Facility between 9 a.m. and 5 p.m.,
34098, June 15, 2015) for correcting the Compliance section of this document
and includes time for reviewing Monday through Friday, except Federal
unsafe condition; and holidays. The AD docket contains this
• Do not add any additional burden instructions, as well as completing and
reviewing the collection of information. AD, the regulatory evaluation, any
upon the public than was already comments received, and other
proposed in the NPRM (80 FR 34098, Therefore, all reporting associated with
this AD is mandatory. Comments information. The street address for the
June 15, 2015). Docket Operations office (telephone
We also determined that these concerning the accuracy of this burden
and suggestions for reducing the burden 800–647–5527) is in the ADDRESSES
changes will not increase the economic
should be directed to the FAA at 800 section.
burden on any operator or increase the
scope of this AD. Independence Ave. SW., Washington, List of Subjects in 14 CFR Part 39
DC 20591, ATTN: Information
Related Service Information Under 1 Air transportation, Aircraft, Aviation
Collection Clearance Officer, AES–200.
CFR Part 51 safety, Incorporation by reference,
Authority for This Rulemaking Safety.
Airbus has issued Alert Operators
Transmission A32L004–14, dated July Title 49 of the United States Code Adoption of the Amendment
28, 2014, including Appendixes 1, 2, 3, specifies the FAA’s authority to issue
Accordingly, under the authority
and 4. This service information rules on aviation safety. Subtitle I,
delegated to me by the Administrator,
describes procedures for inspections of section 106, describes the authority of
the FAA amends 14 CFR part 39 as
the bogie beam bore of the MLG. the FAA Administrator. ‘‘Subtitle VII:
follows:
Messier-Dowty has issued the Aviation Programs,’’ describes in more
following service information, which detail the scope of the Agency’s PART 39—AIRWORTHINESS
describes procedures for inspections of authority. DIRECTIVES
the internal diameter of the bogie beam We are issuing this rulemaking under
for corrosion. the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39
• Service Bulletin A33/34–32–272, Part A, Subpart III, Section 44701: continues to read as follows:
dated November 16, 2007, including General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
Appendixes A, B, C, and D, dated section, Congress charges the FAA with
November 16, 2007. promoting safe flight of civil aircraft in § 39.13 [Amended]
• Service Bulletin A33/34–32–272, air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding
Revision 1, dated September 22, 2008, for practices, methods, and procedures the following new airworthiness
including Appendixes A, B, C, and D, the Administrator finds necessary for directive (AD):
dated September 22, 2008. safety in air commerce. This regulation
is within the scope of that authority 2016–01–03 Airbus: Amendment 39–18362.
This service information is reasonably
Docket No. FAA–2015–1981; Directorate
available because the interested parties because it addresses an unsafe condition Identifier 2014–NM–204–AD.
have access to it through their normal that is likely to exist or develop on
course of business or by the means products identified in this rulemaking (a) Effective Date
identified in the ADDRESSES section. action. This AD becomes effective February 17,
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2016.
Costs of Compliance Regulatory Findings
(b) Affected ADs
We estimate that this AD affects 89 We determined that this AD will not
have federalism implications under None.
airplanes of U.S. registry.
We also estimate that it will take Executive Order 13132. This AD will (c) Applicability
about 12 work-hours per product to not have a substantial direct effect on This AD applies to Airbus airplanes,
comply with the basic requirements of the States, on the relationship between certificated in any category, identified in
this AD, and 1 work-hour to report the the national government and the States, paragraphs (c)(1) and (c)(2) of this AD.

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1508 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

person is not required to respond to, nor 202–741–6030, or go to: http:// 400 Côte Vertu Road West, Dorval,
shall a person be subject to a penalty for www.archives.gov/federal-register/cfr/ibr- Québec H4S 1Y9, Canada; telephone
failure to comply with a collection of locations.html. 514–855–5000; fax 514–855–7401; email
information subject to the requirements of thd.crj@aero.bombardier.com; Internet
Issued in Renton, Washington, on
the Paperwork Reduction Act unless that
collection of information displays a current
December 29, 2015. http://www.bombardier.com. You may
valid OMB Control Number. The OMB Philip Forde, view this referenced service information
Control Number for this information Acting Manager, Transport Airplane at the FAA, Transport Airplane
collection is 2120–0056. Public reporting for Directorate, Aircraft Certification Service. Directorate, 1601 Lind Avenue SW.,
this collection of information is estimated to [FR Doc. 2015–33289 Filed 1–12–16; 8:45 am] Renton, WA. For information on the
be approximately 5 minutes per response, BILLING CODE 4910–13–P availability of this material at the FAA,
including the time for reviewing instructions, call 425–227–1221. It is also available
completing and reviewing the collection of on the Internet at http://
information. All responses to this collection www.regulations.gov by searching for
DEPARTMENT OF TRANSPORTATION
of information are mandatory. Comments and locating Docket No. FAA–2014–
concerning the accuracy of this burden and
Federal Aviation Administration 1049.
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence FOR FURTHER INFORMATION CONTACT:
Ave. SW., Washington, DC 20591, Attn: 14 CFR Part 39 Luke Walker, Aerospace Engineer,
Information Collection Clearance Officer, [Docket No. FAA–2014–1049; Directorate Airframe and Propulsion Branch, ANE–
AES 200. Identifier 2013–NM–110–AD; Amendment 171, FAA, New York Aircraft
(m) Related Information 39–18361; AD 2016–01–02] Certification Office, 1600 Stewart
Refer to Mandatory Continuing RIN 2120–AA64 Avenue, Suite 410, Westbury, NY
Airworthiness Information (MCAI) EASA 11590; telephone 516–228–7363; fax
Airworthiness Directive 2014–0222, dated Airworthiness Directives; Bombardier, 516–794–5531.
October 6, 2014, for related information. This Inc. Airplanes SUPPLEMENTARY INFORMATION:
MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov/ AGENCY: Federal Aviation Discussion
#!documentDetail;D=FAA-2015-1981-0002. Administration (FAA), Department of We issued a notice of proposed
(n) Material Incorporated by Reference
Transportation (DOT). rulemaking (NPRM) to amend 14 CFR
ACTION: Final rule. part 39 by adding an AD that would
(1) The Director of the Federal Register
approved the incorporation by reference
apply to certain Bombardier, Inc. Model
SUMMARY: We are adopting a new CL–600–2B19 (Regional Jet Series 100 &
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR airworthiness directive (AD) for certain 440) airplanes. The NPRM published in
part 51. Bombardier, Inc. Model CL–600–2B19 the Federal Register on January 23,
(2) You must use this service information (Regional Jet Series 100 & 440) 2015 (80 FR 3522).
as applicable to do the actions required by airplanes. This AD was prompted by Transport Canada Civil Aviation
this AD, unless this AD specifies otherwise. reports that the horizontal stabilizer (TCCA), which is the aviation authority
(i) Airbus Alert Operators Transmission trim actuator (HSTA) spur gear bolts for Canada, has issued Canadian
A32L004–14, dated July 28, 2014, including inside the gearbox were found loose, Airworthiness Directive CF–2013–14,
Appendixes 1, 2, 3, and 4, which are not broken, or backed out due to incorrect dated June 4, 2013 (referred to after this
dated.
bending of the anti-rotation tab washer as the Mandatory Continuing
(ii) Messier-Dowty Service Bulletin A33/
34–32–272, dated November 16, 2007, and the improper application of Loctite Airworthiness Information, or ‘‘the
including Appendixes A, B, C, and D, dated glue during installation. This AD MCAI’’), to correct an unsafe condition
November 16, 2007. requires replacing certain HSTAs with a for certain Bombardier, Inc. Model CL–
(iii) Messier-Dowty Service Bulletin A33/ new HSTA. This AD also requires 600–2B19 (Regional Jet Series 100 &
34–32–272, Revision 1, dated September 22, revising the airplane flight manual 440) airplanes. The MCAI states:
2008, including Appendixes A, B, C, and D, (AFM) and the maintenance or There have been a number of reports where
dated September 22, 2008. inspection program, as applicable. We the HSTA spur gear bolts inside the gearbox
(3) For Airbus service information are issuing this AD to prevent failure of were found loose, broken or backed out.
identified in this AD, contact Airbus SAS,
the HSTA and subsequent loss of Investigation revealed that the root cause is
Airworthiness Office—EAL, 1 Rond Point
control of the airplane. incorrect bending of the anti-rotation tab
Maurice Bellonte, 31707 Blagnac Cedex, washer and the improper application of
France; telephone +33 5 61 93 36 96; fax +33 DATES: This AD becomes effective
Loctite glue during installation.
5 61 93 45 80; email airworthiness.A330- February 17, 2016. The function of these bolts is to generate
A340@airbus.com; Internet http:// The Director of the Federal Register sufficient preload between the two spur gears
www.airbus.com. approved the incorporation by reference such that the full torque is transferred by
(4) For Messier-Dowty service information of certain publications listed in this AD friction between the two spur gears.
identified in this AD, contact Messier-Dowty as of February 17, 2016. Loosening of the bolts would reduce the pre-
Limited, Cheltenham Road, Gloucester, GL2 load between two spur gears and decrease the
9QH, England; telephone +44(0) 1452 ADDRESSES: You may examine the AD
torque transfer. Partial or full torque would
712424; fax+ 44(0) 1452 713821; Internet docket on the Internet at http:// be re-distributed to the secondary load path
http://www.safranmbd.com. www.regulations.gov/ (Tie-Rod) in torsion. The Tie-Rod is designed
(5) You may view this service information #!docketDetail;D=FAA-2014-1049; or in to withstand axial load only in case of failure
asabaliauskas on DSK5VPTVN1PROD with RULES

at the FAA, Transport Airplane Directorate, person at the Docket Management of the primary load path (ACME screw), and
1601 Lind Avenue SW., Renton, WA. For Facility, U.S. Department of not torsional load. The secondary load path
information on the availability of this Transportation, Docket Operations, M– (Tie-Rod) is therefore considered ineffective
material at the FAA, call 425–227–1221. and no longer provides protection as a
(6) You may view this service information
30, West Building Ground Floor, Room
failsafe design of the system. Loose bolt(s) on
that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE., the HSTA spur gear combined with the
National Archives and Records Washington, DC. failure of the primary load path, could lead
Administration (NARA). For information on For service information identified in to failure of the HSTA and subsequent loss
the availability of this material at NARA, call this final rule, contact Bombardier, Inc., of the aeroplane.

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Document Created: 2016-01-13 01:00:38
Document Modified: 2016-01-13 01:00:38
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective February 17, 2016.
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.
FR Citation		81 FR 1504
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 1504 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 8 (January 13, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
