81_FR_66706 81 FR 66518 - Airworthiness Directives; Airbus Airplanes

81 FR 66518 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 188 (September 28, 2016)

Page Range66518-66523
FR Document2016-21150

We are superseding Airworthiness Directive (AD) 2009-15-17 for certain Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2009-15-17 required an inspection for damage to the protective treatments or any corrosion of all main landing gear (MLG) bogie beams, and application of protective treatments if no damage or corrosion was found. If any damage or corrosion was found, corrective action followed by the application of protective treatments was required. This new AD continues to require inspections for damage to the protective treatments or any corrosion of all MLG bogie beams, application of protective treatments, and corrective action if necessary. This new AD also requires modification of the MLG bogie beams, which terminates the repetitive inspections for any modified bogie beam. This new AD allows optional methods of compliance for certain actions, and adds Airbus Model A330-200 Freighter series airplanes to the applicability. This new AD revises the compliance times and adds a one-time inspection for airplanes that were inspected too early. This AD was prompted by reports of thin paint coats and paint degradation on enhanced main landing gear (MLG) bogie beams, as well as reports that some airplanes have been inspected too early and not re-inspected as needed. We are issuing this AD to detect and correct damage or corrosion of the MLG bogie beams, which could cause a runway excursion event, bogie beam detachment from the airplane, or MLG collapse, and could result in damage to the airplane and injury to the occupants.

Federal Register, Volume 81 Issue 188 (Wednesday, September 28, 2016) 
[Federal Register Volume 81, Number 188 (Wednesday, September 28, 2016)]
[Rules and Regulations]
[Pages 66518-66523]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-21150]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0828; Directorate Identifier 2012-NM-036-AD; 
Amendment 39-18637; AD 2016-18-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2009-15-17 for 
certain Airbus Model A330-200 and -300 series airplanes; and Model 
A340-200 and -300 series airplanes. AD 2009-15-17 required an 
inspection for damage to the protective treatments or any corrosion of 
all main landing gear (MLG) bogie beams, and application of protective 
treatments if no damage or corrosion was found. If any damage or 
corrosion was found, corrective action followed by the application of 
protective treatments was required. This new AD continues to require 
inspections for damage to the protective treatments or any corrosion of 
all MLG bogie beams, application of protective treatments, and 
corrective action if necessary. This new AD also requires modification 
of the MLG bogie beams, which terminates the repetitive inspections for 
any modified bogie beam. This new AD allows optional methods of 
compliance for certain actions, and adds Airbus Model A330-200 
Freighter series airplanes to the applicability. This new AD revises 
the compliance times and adds a one-time inspection for airplanes that 
were inspected too early. This AD was prompted by reports of thin paint 
coats and paint degradation on enhanced main landing gear (MLG) bogie 
beams, as well as reports that some airplanes have been inspected too 
early and not re-inspected as needed. We are issuing this AD to detect 
and correct damage or corrosion of the MLG bogie beams, which could 
cause a runway excursion event, bogie beam detachment from the 
airplane, or MLG collapse, and could result in damage to the airplane 
and injury to the occupants.

DATES: This AD is effective November 2, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 2, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 2, 2009 (74 FR 37523, July 29, 2009).

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-Dowty 
service information identified in this final rule, contact Messier-
Dowty: Messier Services Americas, Customer Support Center, 45360 Severn 
Way, Sterling, VA 20166-8910; telephone: 703-450-8233; fax: 703-404-
1621; Internet: https://techpubs.services/messier-dowty.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-2013-0828.

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-2013-
0828; 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-

[[Page 66519]]

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 second supplemental notice of proposed rulemaking 
(SNPRM) to amend 14 CFR part 39 to supersede AD 2009-15-17, Amendment 
39-15980 (74 FR 37523, July 29, 2009) (``AD 2009-15-17''). AD 2009-15-
17 applied to certain Airbus Model A330-200 and -300 series airplanes, 
and Model A340-200 and -300 series airplanes. The second SNPRM 
published in the Federal Register on February 5, 2016 (81 FR 6185) 
(``the second SNPRM''). We preceded the second SNPRM with the first 
SNPRM, which was published in the Federal Register on March 5, 2014 (79 
FR 12414) (``the first SNPRM''). We preceded the first SNPRM with a 
notice of proposed rulemaking (NPRM) that published in the Federal 
Register on September 25, 2013 (78 FR 58978) (``the NPRM''). The NPRM 
was prompted by reports of thin paint coats and paint degradation on 
enhanced MLG bogie beams. The NPRM proposed to continue to require 
inspections for damage to the protective treatments or any corrosion of 
all MLG bogie beams, application of protective treatments, and 
corrective action if necessary. The NPRM also proposed to require 
modification of the MLG bogie beams, which would terminate the 
repetitive inspections for any modified bogie beam. In addition, the 
NPRM proposed to allow optional methods of compliance for certain 
actions, and to add Airbus Model A330-200 Freighter series airplanes to 
the applicability. The first SNPRM proposed to revise the compliance 
times and add a one-time inspection for airplanes that were inspected 
too early. The second SNPRM proposed to clarify the required actions 
and the specific configurations to which the actions must be applied. 
We are issuing this AD to detect and correct damage or corrosion of the 
MLG bogie beams, which could cause a runway excursion event, bogie beam 
detachment from the airplane, or MLG collapse, and could result in 
damage to the airplane and injury to the occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0267R1, dated March 4, 2014; corrected May 8, 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, -200, and -300 series airplanes; and Model A340-200 
and -300 series airplanes. The MCAI states:

    The operator of an A330 aeroplane (which has a common bogie beam 
with the A340) reported a fracture of the Right Hand (RH) main 
landing gear (MLG) bogie beam, which occurred while turning during 
low speed taxi maneuvers. The bogie fractured aft of the pivot point 
and remained attached to the sliding tube by the brake torque 
reaction rods. After this RH bogie failure, the aeroplane continued 
for approximately 40 meters on the forks of the sliding member 
before coming to rest on the taxiway.
    The investigations revealed that this event was due to corrosion 
pitting occurring on the bore of the bogie beam.
    This condition, if not detected and corrected, could lead to a 
runway excursion event or to detachment of the bogie from the 
aeroplane, or to MLG collapse, possibly resulting in damage to the 
aeroplane and injury to the occupants.
    To enable early detection and repair of corrosion of the 
internal surfaces, EASA issued EASA AD 2007-0314 to require a one-
time inspection of all MLG bogie beams, except Enhanced MLG bogie 
beams, and the reporting of the results to Airbus. EASA AD 2007-0314 
was revised and later superseded by EASA AD 2008-0093, reducing the 
inspection threshold period.
    The results of subsequent investigations showed thin paint coats 
and paint degradation, confirmed as well on Enhanced MLG bogie 
beams. To address this additional concern, EASA issued AD 2011-0141 
[which was not mandated by the FAA], retaining the requirements of 
EASA AD 2008-0093, which was superseded, to require a one-time 
visual inspection of all MLG bogie beams, including a visual 
examination of the internal diameter for corrosion or damage to 
protective treatments of the bogie beam and measurement of the paint 
thickness on the internal bore, accomplishment of the applicable 
corrective actions and a modification of the MLG bogie beam to 
improve the coat paint application method, and application of 
corrosion protection.
    Prompted by in-service requests, EASA issued EASA AD 2012-0015 
retaining the requirements of EASA AD 2011-0141, which was 
superseded, and introducing repetitive inspections of the MLG bogie 
beams, which allows extension of the compliance time for the MLG 
bogie beam modification from 15 years to 21 years. Modification of a 
MLG bogie beam constitutes terminating action for the repetitive 
inspections for that MLG bogie beam.
    Reports on inspection results provided to Airbus show that some 
aeroplanes were initially inspected too early (before 4 years and 6 
months since aeroplane first flight with bogie beam installed/
installed after overhaul) and have not been re-inspected as 
required.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0015, which is superseded, and 
redefines the inspection periodicity. This [EASA] AD also introduces 
a specific one-time inspection for aeroplanes that have been 
inspected too early.
    Prompted by operator comments, this [EASA] AD is revised to 
clarify the required actions and the specific configurations to 
which the actions must be applied. Appendix 1 of this [EASA] AD has 
been amended accordingly.
    This [EASA] AD is republished to editorially correct paragraph 
(4).

    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-2013-
0828.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the second 
SNPRM and the FAA's response.

Request To Revise the Applicability of the Second SNPRM

    American Airlines (AAL) requested that we revise the applicability 
of the proposed AD (in the second SNPRM) to exclude airplanes with MLG 
bogie beams that have had Airbus modification 58896 embodied in-
service, as specified in Airbus Service Bulletin A330-32-3237. AAL 
pointed out that paragraph (c) of the proposed AD (in the second SNPRM) 
does not reflect MLG bogie beams that were modified in-service.
    We disagree with the request to revise the applicability of the 
proposed AD (in the second SNPRM). Paragraph (k) of this AD 
specifically requires inspection, repair, modification, and re-
identification of the MLG bogie beams. However, paragraph (f) of this 
AD states that actions already done need not be repeated. If an 
operator has already accomplished the actions required by paragraph (k) 
of this AD before the effective date of this AD, then the modified 
airplane is already in compliance with the corresponding requirements 
of this AD. We have not made any changes to this AD in this regard.

Additional Changes Made in This AD

    We have revised paragraph (m)(1) of this AD to remove reference to 
paragraph (g) of this AD; the reporting requirement specified in 
paragraph (m)(1) of this AD is required only for the

[[Page 66520]]

inspection required by paragraph (k) of this AD.
    We have also revised paragraph (m)(2) of this AD to reference the 
correct service information for reporting inspection findings for the 
inspection required by paragraph (h) of this AD.

Conclusion

    We reviewed the available data, including 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:
     Are consistent with the intent that was proposed in the 
second SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the second SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-32-3225, Revision 02, 
including Appendix 1, dated October 26, 2012. This service information 
describes procedures for cleaning the internal bore and accomplishing a 
detailed inspection of internal surfaces of the left-hand (LH) and 
right-hand (RH) MLG bogie beams to detect any damage to the protective 
treatments and any corrosion, and measuring the paint thickness on the 
internal bore.
     Airbus Service Bulletin A330-32-3237, Revision 01, 
including Reporting Sheet, dated October 14, 2011. This service 
information describes procedures for a detailed inspection for damage 
and corrosion of the internal bores of the LH and RH MLG bogie beam and 
repair, as well as modification and re-identification.
     Airbus Service Bulletin A340-32-4268, Revision 03, 
including Appendix 1, dated January 14, 2013. This service information 
describes procedures for cleaning the internal bore and accomplishing a 
detailed inspection of internal surfaces of the LH and RH MLG bogie 
beams to detect any damage to the protective treatments and any 
corrosion, and measuring the paint thickness on the internal bore.
     Airbus Service Bulletin A340-32-4279, Revision 01, 
including Reporting Sheet, dated October 14, 2011. This service 
information describes procedures for a detailed inspection for damage 
and corrosion of the internal bores of the LH and RH MLG bogie beam, 
repair, modification, and reidentification.
    Messier-Bugatti-Dowty has issued the following service information.
     Messier-Dowty Service Bulletin A33/34-32-278, Revision 1, 
including Appendixes A and B, dated August 24, 2011. This service 
information describes procedures for inspections for damage and 
corrosion to the protective treatment of the internal bores of the LH 
and RH MLG bogie beam, and repairs.
     Messier-Dowty Service Bulletin A33/34-32-283, Revision 1, 
including Appendix A, dated July 10, 2012. This service information 
describes procedures for modification of the LH and RH MLG bogie beams.
     Messier-Dowty Service Bulletin A33/34-32-284, Revision 1, 
including Appendix A, dated July 10, 2012. This service information 
describes procedures for modification of the LH and RH MLG bogie beams.
    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 51 airplanes of U.S. registry.
    We also estimate that it takes about 34 work-hours per product to 
comply with this AD, and 1 work-hour per product for reporting. 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 $151,725, or 
$2,975 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 10 work-hours at a labor rate of $85 per work-hour, for a 
cost of $850 per product. We have no way of determining the number of 
aircraft that might need these 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.

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:

[[Page 66521]]

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) 
2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009), and adding 
the following new AD:

2016-18-07 Airbus: Amendment 39-18637; Docket No. FAA-2013-0828; 
Directorate Identifier 2012-NM-036-AD.

(a) Effective Date

    This AD is effective November 2, 2016.

(b) Affected ADs

    This AD replaces AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009) (``AD 2009-15-17'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers (MSN), except those on which Airbus 
modification 58896 has been embodied in production.
    (1) Airbus Model A330-223F, -243F, -201, -202, -203, -223, -243, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of thin paint coats and paint 
degradation on enhanced main landing gear (MLG) bogie beams, as well 
as reports that some airplanes have been inspected too early and not 
re-inspected as needed. We are issuing this AD to detect and correct 
damage or corrosion of the MLG bogie beams, which could cause a 
runway excursion event, bogie beam detachment from the airplane, or 
MLG collapse, and could result in damage to the airplane and injury 
to the occupants.

(f) Compliance

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

(g) Repetitive Inspections for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series): After 54 months at the earliest, but no later 
than 72 months since the left-hand (LH) or right-hand (RH) MLG bogie 
beam's first flight on an airplane, or since its first flight on an 
airplane after overhaul, as applicable, clean the internal bore and 
accomplish a detailed inspection of internal surfaces of the LH and 
RH MLG bogie beams to detect any damage to the protective treatments 
and any corrosion, and measure the paint thickness on the internal 
bore, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-32-3225, Revision 02, including Appendix 1, 
dated October 26, 2012; or Airbus Service Bulletin A340-32-4268, 
Revision 03, including Appendix 1, dated January 14, 2013; as 
applicable. Repeat the inspections thereafter at intervals not less 
than 54 months, but not exceeding 72 months, after the most recent 
inspection. During overhaul of a MLG bogie beam, any corrosion will 
be removed, which means that the first inspection after overhaul of 
that MLG bogie beam, as required by this paragraph, is between 54 
months and 72 months since its first flight on an airplane after 
overhaul.

(h) One-Time Detailed Inspection for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series) having a LH or RH MLG bogie beam that has 
already exceeded 72 months since its first flight on an airplane, or 
since its first flight on an airplane after overhaul, as applicable, 
as of the effective date of this AD; and that has been inspected as 
specified in Airbus Service Bulletin A330-32-3225 or Airbus Service 
Bulletin A340-32-4268, as applicable, earlier than 54 months since 
first flight of the affected MLG bogie beam on an airplane, or since 
its first flight on an airplane after its most recent overhaul, as 
applicable: Within the applicable compliance time indicated in 
paragraphs (h)(1) through (h)(4) of this AD, clean the internal bore 
and accomplish a detailed inspection of the internal surfaces of the 
LH and RH MLG bogie beams to detect any damage to the protective 
treatments and any corrosion, and measure the paint thickness on the 
internal bore, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340-
32-4268, Revision 03, including Appendix 1, dated January 14, 2013; 
as applicable.
    (1) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(1)(i) and (h)(1)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 9 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 51 months and before 54 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (2) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(2)(i) and (h)(2)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 3 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 45 months and before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (3) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(3)(i) and (h)(3)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 3 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 96 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which have accumulated, at the effective 
date of this AD, less than 96 months and on which the first 
inspection was done before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the after the MLG bogie beam's most 
recent overhaul, as applicable.
    (4) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(4)(i) and (h)(4)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 1 month after the effective date of this AD.
    (i) MLG bogie beams having between 96 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which has accumulated, at the effective 
date of this AD, 96 months or more and on which the first inspection 
was done before 45 months since first flight of the MLG bogie beam 
on an airplane, or since the MLG bogie beam's first flight on an 
airplane after the MLG bogie beam's most recent overhaul, as 
applicable.

(i) Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, no damage or corrosion is found: Before further flight, 
apply the protective treatments to the MLG bogie beam, in accordance 
with the Accomplishment Instructions of Messier-Dowty Service 
Bulletin A33/34-32-272, Revision 1, including Appendixes A, B, C, 
and D, dated September 22, 2008.

(j) Repair and Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, any damage or corrosion is found: Before further flight, 
repair and apply the protective treatments to the MLG bogie beam, in 
accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-272, Revision 1, including Appendixes A, 
B, C, and D, dated September 22, 2008.

[[Page 66522]]

(k) Inspection and Corrective Actions

    For airplanes equipped with basic MLG (201252 series), growth 
MLG (201490 series), or enhanced MLG (10-210 series): Before the 
accumulation of 252 total months on an MLG bogie beam, or within 90 
days after the effective date of this AD, whichever occurs later, do 
the actions specified in paragraphs (k)(1) and (k)(2) of this AD 
concurrently and in sequence.
    (1) Except as provided by paragraph (k)(3) of this AD: Do a 
detailed inspection for damage and corrosion of the internal bores 
of the LH and RH MLG bogie beam, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3237 
or A340-32-4279, both Revision 01, both including Reporting Sheet, 
both dated October 14, 2011, as applicable. If any damage or 
corrosion is found, before further flight, repair in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-32-
3237 or A340-32-4279, both Revision 01, both including Reporting 
Sheet, both dated October 14, 2011, as applicable.
    (2) Except as provided by paragraph (k)(3) of this AD: Modify 
and re-identify, as applicable, the LH and RH MLG bogie beams, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3237 or A340-32-4279, both Revision 01, both 
including Reporting Sheet, both dated October 14, 2011, as 
applicable.
    (3) The inspection requirements of paragraph (k)(1) of this AD, 
and the modification requirements only of paragraph (k)(2) of this 
AD, do not apply to any MLG bogie beam with a serial number listed 
in Appendix A of Messier-Dowty Service Bulletin A33/34-32-283 or 
A33/34-32-284, both Revision 1, both dated July 10, 2012, as 
applicable.

(l) Optional Methods of Compliance for Certain Airplane Configurations

    Inspections and corrective actions on both MLG bogie beams done 
in accordance with the instructions of Messier-Dowty Service 
Bulletin A33/34-32-271, Revision 1, including Appendixes A and B, 
dated November 16, 2007; or Messier-Dowty Service Bulletin A33/34-
32-272, Revision 1, including Appendixes A, B, C, and D, dated 
September 22, 2008; as applicable; are acceptable methods of 
compliance for the requirements of paragraph (g) of this AD, 
provided each inspection is accomplished between 54 months and 72 
months since the first flight of the affected MLG bogie beam on an 
airplane, or since the MLG bogie beam's first flight after the MLG 
bogie beam's most recent overhaul, as applicable.

(m) Reporting Requirement

    (1) Submit a report of the findings (both positive and negative) 
of each inspection required by paragraph (k) of this AD, as 
applicable, to Airbus, Customer Service Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France, using the applicable 
Reporting Sheet in Airbus Service Bulletin A330-32-3237, Revision 
01, including Reporting Sheet, dated October 14, 2011; or Airbus 
Service Bulletin A340-32-4279, Revision 01, including Reporting 
Sheet, dated October 14, 2011; at the applicable time specified in 
paragraph (m)(1)(i) or (m)(1)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.
    (2) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (h) of this AD to Airbus, 
Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, using the applicable Reporting Sheet in 
Airbus Service Bulletin A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340-
32-4268, Revision 03, including Appendix 1, dated January 14, 2013; 
at the applicable time specified in paragraph (m)(2)(i) or 
(m)(2)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(n) Optional Method of Compliance for Certain Requirements

    (1) Inspections for damage and corrosion to the protective 
treatment of the internal bores of the LH and RH MLG bogie beam, and 
repairs, done in accordance with Messier-Dowty Service Bulletin A33/
34-32-278, Revision 1, including Appendixes A and B, dated August 
24, 2011, are acceptable methods of compliance with the 
corresponding requirements of paragraph (k)(1) of this AD.
    (2) Modification of the LH and RH MLG bogie beams, done in 
accordance with Messier-Dowty Service Bulletins A33/34-32-283 or 
A33/34-32-284, both Revision 1, both including Appendix A, both 
dated July 10, 2012, as applicable, is an acceptable method of 
compliance with the corresponding requirements of paragraph (k)(2) 
of this AD.

(o) Optional Terminating Action for Certain Requirements

    Modification of both LH and RH MLG bogie beams on an airplane, 
done in accordance with paragraph (k) of this AD, or as specified in 
paragraphs (n)(1) and (n)(2) of this AD, terminates the repetitive 
inspections required by paragraph (g) of this AD for this airplane.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-32-3225, dated November 21, 2007; or Revision 1, dated 
October 30, 2008; provided the inspections and corrective actions 
were accomplished between 54 months and 72 months since first flight 
of the affected MLG bogie beam on an airplane, or since its first 
flight after the MLG bogie beam's most recent overhaul, as 
applicable. Airbus Service Bulletin A330-32-3225, dated November 21, 
2007, is not incorporated by reference in this AD. Airbus Mandatory 
Service Bulletin A330-32-3225, Revision 01, including Appendix 1, 
dated October 30, 2008, was incorporated by reference in AD 2009-15-
07.
    (2) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A340-32-4268, dated November 21, 2007; 
Revision 01, including Appendix 1, dated October 30, 2008; or 
Revision 02, dated October 26, 2012; provided these inspections and 
corrective actions were accomplished between 54 months and 72 months 
since first flight of the affected MLG bogie beam on an airplane, or 
since its first flight after the MLG bogie beam's most recent 
overhaul, as applicable. Airbus Service Bulletin A340-32-4268, dated 
November 21, 2007; and Revision 02, dated October 26, 2012; are not 
incorporated by reference in this AD. Airbus Mandatory Service 
Bulletin A340-32-4268, Revision 01, including Appendix 1, dated 
October 30, 2008, was incorporated by reference in AD 2009-15-17.
    (3) This paragraph provides credit for the corresponding actions 
required by paragraph (n)(1) of this AD, if those actions were 
performed before the effective date of this AD using Messier-Dowty 
Service Bulletin A33/34-32-271, dated September 13, 2007, which is 
not incorporated by reference in this AD.
    (4) This paragraph provides credit for the corresponding actions 
required by paragraphs (j) and (n)(1) of this AD, if those actions 
were performed before the effective date of this AD using Messier-
Dowty Service Bulletin A33/34-32-272, including Appendixes A, B, C, 
and D, dated November 16, 2007, which is not incorporated by 
reference in this AD.
    (5) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Service Bulletin A330-32-3237, including Reporting Sheet, 
dated January 18, 2011.
    (6) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Service Bulletin A340-32-4279, including Reporting Sheet, 
dated January 18, 2011.
    (7) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) 
of this AD, if those actions were performed before the effective 
date of this AD using Messier-Dowty Service Bulletin A33/34-32-283, 
including Appendix A, dated May 11, 2010, which is not incorporated 
by reference in this AD.
    (8) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) 
of this AD, if those actions were performed before the effective 
date of this AD

[[Page 66523]]

using Messier-Dowty Service Bulletin A33/34-32-284, including 
Appendix A, dated May 11, 2010, which is not incorporated by 
reference in this AD.
    (9) This paragraph provides credit for the corresponding actions 
required by paragraphs (n)(1) and (r)(1)(ii) of this AD, if those 
actions were performed before the effective date of this AD using 
Messier-Dowty Service Bulletin A33/34-32-278, including Appendixes A 
and B, dated February 17, 2010, which is not incorporated by 
reference in this AD.

(q) Clarification of Inspection Compliance Times

    After accomplishment of the one-time detailed inspection 
required by paragraph (h) of this AD, the repetitive actions 
required by paragraph (g) of this AD remain applicable, and must be 
done within the compliance times specified in paragraph (g) of this 
AD.

(r) Parts Installation Limitations

    (1) After modification of an airplane, as required by paragraph 
(k) of this AD, or as specified in paragraphs (n)(1) and (n)(2) of 
this AD, do not install an MLG bogie beam on any airplane unless it 
is done in compliance with the requirements of paragraph (r)(1)(i), 
(r)(1)(ii), or (r)(1)(iii) of this AD.
    (i) The MLG bogie beam has been modified and re-identified in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3237 or A340-32-4279, both Revision 01, both 
including Reporting Sheet, both dated October 14, 2011, as 
applicable.
    (ii) The MLG bogie beam has been inspected and all applicable 
corrective actions have been done in accordance with the 
Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-278, Revision 1, dated August 24, 2011; and modified in 
accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-283 or A33/34-32-284, both Revision 1, 
both including Appendix A, both dated July 10, 2012.
    (iii) The MLG bogie beam has a serial number listed in Appendix 
A of Messier-Dowty Service Bulletin A33/34-32-283 or A33/34-32-284, 
both Revision 1, both dated July 10, 2012, as applicable.
    (2) As of the effective date of this AD, except as specified in 
paragraph (r)(1) of this AD, installation of an MLG bogie beam on an 
airplane is allowed, provided that following the installation it is 
inspected and all applicable repairs and corrective actions have 
been done in accordance with the requirements of this AD.

(s) 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: [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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a 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.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) AD 2013-0267R1, dated March 4, 2014; corrected March 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-2013-0828.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5), (u)(6), and (u)(7) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 2, 2016.
    (i) Airbus Service Bulletin A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012.
    (ii) Airbus Service Bulletin A330-32-3237, Revision 01, 
including Reporting Sheet, dated October 14, 2011.
    (iii) Airbus Service Bulletin A340-32-4268, Revision 03, 
including Appendix 1, dated January 14, 2013.
    (iv) Airbus Service Bulletin A340-32-4279, Revision 01, 
including Reporting Sheet, dated October 14, 2011.
    (v) Messier-Dowty Service Bulletin A33/34-32-278, Revision 1, 
including Appendixes A and B, dated August 24, 2011.
    (vi) Messier-Dowty Service Bulletin A33/34-32-283, Revision 1, 
including Appendix A, dated July 10, 2012.
    (vii) Messier-Dowty Service Bulletin A33/34-32-284, Revision 1, 
including Appendix A, dated July 10, 2012.
    (4) The following service information was approved for IBR on 
September 2, 2009 (74 FR 37523, July 29, 2009).
    (i) Messier-Dowty Service Bulletin A33/34-32-271, Revision 1, 
including Appendixes A and B, dated November 16, 2007.
    (ii) Messier-Dowty Service Bulletin A33/34-32-272, Revision 1, 
including Appendixes A, B, C, and D, dated September 22, 2008.
    (5) 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.
    (6) For Messier-Dowty service information identified in this AD, 
contact Messier-Dowty: Messier Services Americas, Customer Support 
Center, 45360 Severn Way, Sterling, VA 20166-8910; telephone 703-
450-8233; fax 703-404-1621; Internet: https://techpubs.services/messier-dowty.com.
    (7) 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.
    (8) 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 August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21150 Filed 9-27-16; 8:45 am]
 BILLING CODE 4910-13-P

66518 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations Instructions of Bombardier Service Bulletin aero.bombardier.com; Internet: http:// compliance times and adds a one-time 84–30–10, Revision E, dated October 10, www.bombardier.com. inspection for airplanes that were 2014, within the compliance times specified (4) You may view this service information inspected too early. This AD was in paragraph (g) of this AD. at the FAA, Transport Airplane Directorate, (2) Bombardier Service Bulletin 84–30–10, 1601 Lind Avenue SW., Renton, WA. For prompted by reports of thin paint coats Revision A, dated April 7, 2008. information on the availability of this and paint degradation on enhanced (3) Bombardier Service Bulletin 84–30–10, material at the FAA, call 425–227–1221. main landing gear (MLG) bogie beams, Revision B, dated January 20, 2010. (5) You may view this service information as well as reports that some airplanes (4) Bombardier Service Bulletin 84–30–10, that is incorporated by reference at the have been inspected too early and not Revision C, dated July 14, 2011. National Archives and Records re-inspected as needed. We are issuing (5) Bombardier Service Bulletin 84–30–10, Administration (NARA). For information on this AD to detect and correct damage or Revision D, dated December 20, 2011. the availability of this material at NARA, call corrosion of the MLG bogie beams, 202–741–6030, or go to: http:// (j) Other FAA AD Provisions www.archives.gov/federal-register/cfr/ibr- which could cause a runway excursion The following provisions also apply to this locations.html. event, bogie beam detachment from the AD: airplane, or MLG collapse, and could (1) Alternative Methods of Compliance Issued in Renton, Washington, on result in damage to the airplane and (AMOCs): The Manager, New York ACO, September 12, 2016. injury to the occupants. ANE–170, FAA, has the authority to approve Michael Kaszycki, DATES: This AD is effective November 2, AMOCs for this AD, if requested using the Acting Manager, Transport Airplane procedures found in 14 CFR 39.19. In Directorate, Aircraft Certification Service. 2016. accordance with 14 CFR 39.19, send your The Director of the Federal Register [FR Doc. 2016–22705 Filed 9–27–16; 8:45 am] request to your principal inspector or local approved the incorporation by reference BILLING CODE 4910–13–P Flight Standards District Office, as of certain publications listed in this AD appropriate. If sending information directly as of November 2, 2016. to the ACO, send it to ATTN: Program The Director of the Federal Register Manager, Continuing Operational Safety, DEPARTMENT OF TRANSPORTATION approved the incorporation by reference FAA, New York ACO, 1600 Stewart Avenue, of certain other publications listed in Suite 410, Westbury, NY 11590; telephone Federal Aviation Administration 516–228–7300; fax 516–794–5531. Before this AD as of September 2, 2009 (74 FR using any approved AMOC, notify your 14 CFR Part 39 37523, July 29, 2009). appropriate principal inspector, or lacking a ADDRESSES: For Airbus service principal inspector, the manager of the local [Docket No. FAA–2013–0828; Directorate information identified in this final rule, flight standards district office/certificate Identifier 2012–NM–036–AD; Amendment 39–18637; AD 2016–18–07] contact Airbus SAS, Airworthiness holding district office. Office—EAL, 1 Rond Point Maurice (2) Contacting the Manufacturer: For any RIN 2120–AA64 requirement in this AD to obtain corrective Bellonte, 31707 Blagnac Cedex, France; actions from a manufacturer, the action must telephone: +33 5 61 93 36 96; fax: +33 Airworthiness Directives; Airbus 5 61 93 45 80; email: be accomplished using a method approved Airplanes by the Manager, New York ACO, ANE–170, airworthiness.A330–A340@airbus.com; Engine and Propeller Directorate, FAA; or AGENCY: Federal Aviation Internet: http://www.airbus.com. For TCCA; or Bombardier, Inc.’s TCCA DAO. If Administration (FAA), Department of Messier-Dowty service information approved by the DAO, the approval must Transportation (DOT). identified in this final rule, contact include the DAO-authorized signature. Messier-Dowty: Messier Services ACTION: Final rule. (k) Related Information Americas, Customer Support Center, (1) Refer to Mandatory Continuing SUMMARY: We are superseding 45360 Severn Way, Sterling, VA 20166– Airworthiness Information (MCAI) Canadian Airworthiness Directive (AD) 2009–15– 8910; telephone: 703–450–8233; fax: Airworthiness Directive CF–2015–24, dated 17 for certain Airbus Model A330–200 703–404–1621; Internet: https:// August 24, 2015, for related information. and –300 series airplanes; and Model techpubs.services/messier-dowty.com. This MCAI may be found in the AD docket A340–200 and –300 series airplanes. AD You may view this referenced service on the Internet at http://www.regulations.gov 2009–15–17 required an inspection for information at the FAA, Transport by searching for and locating Docket No. damage to the protective treatments or Airplane Directorate, 1601 Lind Avenue FAA–2016–6148. any corrosion of all main landing gear (2) Service information identified in this SW., Renton, WA. For information on AD that is not incorporated by reference is (MLG) bogie beams, and application of the availability of this material at the available at the addresses specified in protective treatments if no damage or FAA, call 425–227–1221. It is also paragraphs (l)(3) and (l)(4) of this AD. corrosion was found. If any damage or available on the Internet at http:// corrosion was found, corrective action www.regulations.gov by searching for (l) Material Incorporated by Reference followed by the application of and locating Docket No. FAA–2013– (1) The Director of the Federal Register protective treatments was required. This 0828. approved the incorporation by reference new AD continues to require (IBR) of the service information listed in this Examining the AD Docket paragraph under 5 U.S.C. 552(a) and 1 CFR inspections for damage to the protective part 51. treatments or any corrosion of all MLG You may examine the AD docket on (2) You must use this service information bogie beams, application of protective the Internet at http:// as applicable to do the actions required by treatments, and corrective action if www.regulations.gov by searching for this AD, unless this AD specifies otherwise. necessary. This new AD also requires and locating Docket No. FAA–2013– (i) Bombardier Service Bulletin 84–30–10, modification of the MLG bogie beams, 0828; or in person at the Docket sradovich on DSK3GMQ082PROD with RULES Revision E, dated October 10, 2014. which terminates the repetitive Management Facility between 9 a.m. (ii) Reserved. inspections for any modified bogie and 5 p.m., Monday through Friday, (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series beam. This new AD allows optional except Federal holidays. The AD docket Technical Help Desk, 123 Garratt Boulevard, methods of compliance for certain contains this AD, the regulatory Toronto, Ontario M3K 1Y5, Canada; actions, and adds Airbus Model A330– evaluation, any comments received, and telephone: 416–375–4000; fax: 416–375– 200 Freighter series airplanes to the other information. The address for the 4539; email: thd.qseries@ applicability. This new AD revises the Docket Office (telephone: 800–647– VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1

Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 66519 5527) is Docket Management Facility, The European Aviation Safety Agency initially inspected too early (before 4 years U.S. Department of Transportation, (EASA), which is the Technical Agent and 6 months since aeroplane first flight with Docket Operations, M–30, West for the Member States of the European bogie beam installed/installed after overhaul) Union, has issued EASA AD 2013– and have not been re-inspected as required. Building Ground Floor, Room W12–140, For the reasons described above, this 1200 New Jersey Avenue SE., 0267R1, dated March 4, 2014; corrected [EASA] AD retains the requirements of EASA Washington, DC 20590. May 8, 2014 (referred to after this as the AD 2012–0015, which is superseded, and FOR FURTHER INFORMATION CONTACT: Mandatory Continuing Airworthiness redefines the inspection periodicity. This Vladimir Ulyanov, Aerospace Engineer, Information, or ‘‘the MCAI’’), to correct [EASA] AD also introduces a specific one- International Branch, ANM–116, an unsafe condition for certain Airbus time inspection for aeroplanes that have been Transport Airplane Directorate, FAA, Model A330–200 Freighter, –200, and inspected too early. 1601 Lind Avenue SW., Renton, WA –300 series airplanes; and Model A340– Prompted by operator comments, this 200 and –300 series airplanes. The [EASA] AD is revised to clarify the required 98057–3356; telephone: 425–227–1138; actions and the specific configurations to fax: 425–227–1149. MCAI states: which the actions must be applied. Appendix SUPPLEMENTARY INFORMATION: The operator of an A330 aeroplane (which 1 of this [EASA] AD has been amended has a common bogie beam with the A340) accordingly. Discussion reported a fracture of the Right Hand (RH) This [EASA] AD is republished to We issued a second supplemental main landing gear (MLG) bogie beam, which editorially correct paragraph (4). notice of proposed rulemaking (SNPRM) occurred while turning during low speed taxi maneuvers. The bogie fractured aft of the You may examine the MCAI in the to amend 14 CFR part 39 to supersede pivot point and remained attached to the AD docket on the Internet at http:// AD 2009–15–17, Amendment 39–15980 sliding tube by the brake torque reaction www.regulations.gov by searching for (74 FR 37523, July 29, 2009) (‘‘AD 2009– rods. After this RH bogie failure, the and locating Docket No. FAA–2013– 15–17’’). AD 2009–15–17 applied to aeroplane continued for approximately 40 0828. certain Airbus Model A330–200 and meters on the forks of the sliding member –300 series airplanes, and Model A340– before coming to rest on the taxiway. Comments 200 and –300 series airplanes. The The investigations revealed that this event We gave the public the opportunity to second SNPRM published in the was due to corrosion pitting occurring on the bore of the bogie beam. participate in developing this AD. The Federal Register on February 5, 2016 following presents the comment This condition, if not detected and (81 FR 6185) (‘‘the second SNPRM’’). corrected, could lead to a runway excursion received on the second SNPRM and the We preceded the second SNPRM with event or to detachment of the bogie from the FAA’s response. the first SNPRM, which was published aeroplane, or to MLG collapse, possibly in the Federal Register on March 5, resulting in damage to the aeroplane and Request To Revise the Applicability of 2014 (79 FR 12414) (‘‘the first SNPRM’’). injury to the occupants. the Second SNPRM We preceded the first SNPRM with a To enable early detection and repair of American Airlines (AAL) requested notice of proposed rulemaking (NPRM) corrosion of the internal surfaces, EASA that we revise the applicability of the that published in the Federal Register issued EASA AD 2007–0314 to require a one- proposed AD (in the second SNPRM) to time inspection of all MLG bogie beams, on September 25, 2013 (78 FR 58978) exclude airplanes with MLG bogie except Enhanced MLG bogie beams, and the (‘‘the NPRM’’). The NPRM was reporting of the results to Airbus. EASA AD beams that have had Airbus prompted by reports of thin paint coats 2007–0314 was revised and later superseded modification 58896 embodied in- and paint degradation on enhanced by EASA AD 2008–0093, reducing the service, as specified in Airbus Service MLG bogie beams. The NPRM proposed inspection threshold period. Bulletin A330–32–3237. AAL pointed to continue to require inspections for The results of subsequent investigations out that paragraph (c) of the proposed damage to the protective treatments or showed thin paint coats and paint AD (in the second SNPRM) does not any corrosion of all MLG bogie beams, degradation, confirmed as well on Enhanced reflect MLG bogie beams that were application of protective treatments, and MLG bogie beams. To address this additional modified in-service. concern, EASA issued AD 2011–0141 [which corrective action if necessary. The We disagree with the request to revise was not mandated by the FAA], retaining the NPRM also proposed to require requirements of EASA AD 2008–0093, which the applicability of the proposed AD (in modification of the MLG bogie beams, was superseded, to require a one-time visual the second SNPRM). Paragraph (k) of which would terminate the repetitive inspection of all MLG bogie beams, including this AD specifically requires inspection, inspections for any modified bogie a visual examination of the internal diameter repair, modification, and re- beam. In addition, the NPRM proposed for corrosion or damage to protective identification of the MLG bogie beams. to allow optional methods of treatments of the bogie beam and However, paragraph (f) of this AD states compliance for certain actions, and to measurement of the paint thickness on the that actions already done need not be add Airbus Model A330–200 Freighter internal bore, accomplishment of the repeated. If an operator has already series airplanes to the applicability. The applicable corrective actions and a modification of the MLG bogie beam to accomplished the actions required by first SNPRM proposed to revise the improve the coat paint application method, paragraph (k) of this AD before the compliance times and add a one-time and application of corrosion protection. effective date of this AD, then the inspection for airplanes that were Prompted by in-service requests, EASA modified airplane is already in inspected too early. The second SNPRM issued EASA AD 2012–0015 retaining the compliance with the corresponding proposed to clarify the required actions requirements of EASA AD 2011–0141, which requirements of this AD. We have not and the specific configurations to which was superseded, and introducing repetitive made any changes to this AD in this the actions must be applied. We are inspections of the MLG bogie beams, which regard. sradovich on DSK3GMQ082PROD with RULES issuing this AD to detect and correct allows extension of the compliance time for damage or corrosion of the MLG bogie the MLG bogie beam modification from 15 Additional Changes Made in This AD years to 21 years. Modification of a MLG beams, which could cause a runway bogie beam constitutes terminating action for We have revised paragraph (m)(1) of excursion event, bogie beam detachment the repetitive inspections for that MLG bogie this AD to remove reference to from the airplane, or MLG collapse, and beam. paragraph (g) of this AD; the reporting could result in damage to the airplane Reports on inspection results provided to requirement specified in paragraph and injury to the occupants. Airbus show that some aeroplanes were (m)(1) of this AD is required only for the VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1

66520 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations inspection required by paragraph (k) of Messier-Bugatti-Dowty has issued the should be directed to the FAA at 800 this AD. following service information. Independence Ave. SW., Washington, We have also revised paragraph (m)(2) • Messier-Dowty Service Bulletin DC 20591, ATTN: Information of this AD to reference the correct A33/34–32–278, Revision 1, including Collection Clearance Officer, AES–200. service information for reporting Appendixes A and B, dated August 24, inspection findings for the inspection 2011. This service information describes Authority for This Rulemaking required by paragraph (h) of this AD. procedures for inspections for damage Title 49 of the United States Code and corrosion to the protective specifies the FAA’s authority to issue Conclusion treatment of the internal bores of the LH rules on aviation safety. Subtitle I, We reviewed the available data, and RH MLG bogie beam, and repairs. section 106, describes the authority of including the comment received, and • Messier-Dowty Service Bulletin the FAA Administrator. ‘‘Subtitle VII: determined that air safety and the A33/34–32–283, Revision 1, including Aviation Programs,’’ describes in more public interest require adopting this AD Appendix A, dated July 10, 2012. This detail the scope of the Agency’s with the changes described previously service information describes authority. and minor editorial changes. We have procedures for modification of the LH determined that these minor changes: and RH MLG bogie beams. We are issuing this rulemaking under • Are consistent with the intent that • Messier-Dowty Service Bulletin the authority described in ‘‘Subtitle VII, was proposed in the second SNPRM for A33/34–32–284, Revision 1, including Part A, Subpart III, Section 44701: correcting the unsafe condition; and Appendix A, dated July 10, 2012. This General requirements.’’ Under that • Do not add any additional burden service information describes section, Congress charges the FAA with upon the public than was already procedures for modification of the LH promoting safe flight of civil aircraft in proposed in the second SNPRM. and RH MLG bogie beams. air commerce by prescribing regulations This service information is reasonably for practices, methods, and procedures Related Service Information Under 1 available because the interested parties the Administrator finds necessary for CFR Part 51 have access to it through their normal safety in air commerce. This regulation Airbus has issued the following course of business or by the means is within the scope of that authority service information. identified in the ADDRESSES section. because it addresses an unsafe condition • Airbus Service Bulletin A330–32– that is likely to exist or develop on Costs of Compliance 3225, Revision 02, including Appendix products identified in this rulemaking We estimate that this AD affects 51 action. 1, dated October 26, 2012. This service airplanes of U.S. registry. information describes procedures for We also estimate that it takes about 34 Regulatory Findings cleaning the internal bore and work-hours per product to comply with accomplishing a detailed inspection of this AD, and 1 work-hour per product We determined that this AD will not internal surfaces of the left-hand (LH) for reporting. The average labor rate is have federalism implications under and right-hand (RH) MLG bogie beams $85 per work-hour. Based on these Executive Order 13132. This AD will to detect any damage to the protective figures, we estimate the cost of this AD not have a substantial direct effect on treatments and any corrosion, and on U.S. operators to be $151,725, or the States, on the relationship between measuring the paint thickness on the $2,975 per product. the national government and the States, internal bore. In addition, we estimate that any or on the distribution of power and • Airbus Service Bulletin A330–32– necessary follow-on actions would take responsibilities among the various 3237, Revision 01, including Reporting about 10 work-hours at a labor rate of levels of government. Sheet, dated October 14, 2011. This $85 per work-hour, for a cost of $850 For the reasons discussed above, I service information describes per product. We have no way of certify that this AD: procedures for a detailed inspection for determining the number of aircraft that 1. Is not a ‘‘significant regulatory damage and corrosion of the internal might need these actions. action’’ under Executive Order 12866; bores of the LH and RH MLG bogie beam and repair, as well as modification Paperwork Reduction Act 2. Is not a ‘‘significant rule’’ under the and re-identification. A federal agency may not conduct or DOT Regulatory Policies and Procedures • Airbus Service Bulletin A340–32– sponsor, and a person is not required to (44 FR 11034, February 26, 1979); 4268, Revision 03, including Appendix respond to, nor shall a person be subject 3. Will not affect intrastate aviation in 1, dated January 14, 2013. This service to penalty for failure to comply with a Alaska; and information describes procedures for collection of information subject to the 4. Will not have a significant cleaning the internal bore and requirements of the Paperwork economic impact, positive or negative, accomplishing a detailed inspection of Reduction Act unless that collection of on a substantial number of small entities internal surfaces of the LH and RH MLG information displays a current valid under the criteria of the Regulatory bogie beams to detect any damage to the OMB control number. The control Flexibility Act. protective treatments and any corrosion, number for the collection of information and measuring the paint thickness on required by this AD is 2120–0056. The List of Subjects in 14 CFR Part 39 the internal bore. paperwork cost associated with this AD • Airbus Service Bulletin A340–32– has been detailed in the Costs of Air transportation, Aircraft, Aviation 4279, Revision 01, including Reporting Compliance section of this document safety, Incorporation by reference, sradovich on DSK3GMQ082PROD with RULES Sheet, dated October 14, 2011. This and includes time for reviewing Safety. service information describes instructions, as well as completing and Adoption of the Amendment procedures for a detailed inspection for reviewing the collection of information. damage and corrosion of the internal Therefore, all reporting associated with Accordingly, under the authority bores of the LH and RH MLG bogie this AD is mandatory. Comments delegated to me by the Administrator, beam, repair, modification, and concerning the accuracy of this burden the FAA amends 14 CFR part 39 as reidentification. and suggestions for reducing the burden follows: VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1

Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 66521 PART 39—AIRWORTHINESS corrosion, and measure the paint thickness (i) MLG bogie beams having between 72 DIRECTIVES on the internal bore, in accordance with the and 120 months since first flight on an Accomplishment Instructions of Airbus airplane, or since the MLG bogie beam’s first ■ 1. The authority citation for part 39 Service Bulletin A330–32–3225, Revision 02, flight on an airplane after the MLG bogie continues to read as follows: including Appendix 1, dated October 26, beam’s most recent overhaul, as applicable. 2012; or Airbus Service Bulletin A340–32– (ii) MLG bogie beams on which the first Authority: 49 U.S.C. 106(g), 40113, 44701. 4268, Revision 03, including Appendix 1, inspection was done after 45 months and dated January 14, 2013; as applicable. Repeat before 51 months since first flight of the MLG § 39.13 [Amended] the inspections thereafter at intervals not less bogie beam on an airplane, or since the MLG ■ 2. The FAA amends § 39.13 by than 54 months, but not exceeding 72 bogie beam’s first flight on an airplane after removing Airworthiness Directive (AD) months, after the most recent inspection. the MLG bogie beam’s most recent overhaul, 2009–15–17, Amendment 39–15980 (74 During overhaul of a MLG bogie beam, any as applicable. corrosion will be removed, which means that (3) For MLG bogie beams having the FR 37523, July 29, 2009), and adding the the first inspection after overhaul of that configurations specified in both paragraphs following new AD: MLG bogie beam, as required by this (h)(3)(i) and (h)(3)(ii) of this AD: Do the 2016–18–07 Airbus: Amendment 39–18637; paragraph, is between 54 months and 72 detailed inspection specified in the Docket No. FAA–2013–0828; Directorate months since its first flight on an airplane introductory text of paragraph (h) of this AD Identifier 2012–NM–036–AD. after overhaul. within 3 months after the effective date of (a) Effective Date (h) One-Time Detailed Inspection for Certain this AD. Airplane Configurations (i) MLG bogie beams having between 72 This AD is effective November 2, 2016. and 96 months since first flight on an For airplanes equipped with basic MLG airplane, or since the MLG bogie beam’s first (b) Affected ADs (201252 series), or growth MLG (201490 flight on an airplane after the MLG bogie This AD replaces AD 2009–15–17, series) having a LH or RH MLG bogie beam beam’s most recent overhaul, as applicable. Amendment 39–15980 (74 FR 37523, July 29, that has already exceeded 72 months since its (ii) MLG bogie beams which have 2009) (‘‘AD 2009–15–17’’). first flight on an airplane, or since its first accumulated, at the effective date of this AD, (c) Applicability flight on an airplane after overhaul, as less than 96 months and on which the first applicable, as of the effective date of this AD; inspection was done before 51 months since This AD applies to the airplanes identified and that has been inspected as specified in first flight of the MLG bogie beam on an in paragraphs (c)(1) and (c)(2) of this AD, Airbus Service Bulletin A330–32–3225 or airplane, or since the MLG bogie beam’s first certificated in any category, all manufacturer Airbus Service Bulletin A340–32–4268, as serial numbers (MSN), except those on which flight on an airplane after the after the MLG applicable, earlier than 54 months since first bogie beam’s most recent overhaul, as Airbus modification 58896 has been flight of the affected MLG bogie beam on an embodied in production. applicable. airplane, or since its first flight on an (4) For MLG bogie beams having the (1) Airbus Model A330–223F, –243F, –201, airplane after its most recent overhaul, as –202, –203, –223, –243, –301, –302, –303, configurations specified in both paragraphs applicable: Within the applicable compliance (h)(4)(i) and (h)(4)(ii) of this AD: Do the –321, –322, –323, –341, –342, and –343 time indicated in paragraphs (h)(1) through airplanes. detailed inspection specified in the (h)(4) of this AD, clean the internal bore and introductory text of paragraph (h) of this AD (2) Airbus Model A340–211, –212, –213, accomplish a detailed inspection of the –311, –312, and –313 airplanes. within 1 month after the effective date of this internal surfaces of the LH and RH MLG AD. (d) Subject bogie beams to detect any damage to the (i) MLG bogie beams having between 96 Air Transport Association (ATA) of protective treatments and any corrosion, and and 120 months since first flight on an America Code 32, Landing gear. measure the paint thickness on the internal airplane, or since the MLG bogie beam’s first bore, in accordance with the flight on an airplane after the MLG bogie (e) Reason Accomplishment Instructions of Airbus beam’s most recent overhaul, as applicable. This AD was prompted by reports of thin Service Bulletin A330–32–3225, Revision 02, (ii) MLG bogie beams which has paint coats and paint degradation on including Appendix 1, dated October 26, accumulated, at the effective date of this AD, enhanced main landing gear (MLG) bogie 2012; or Airbus Service Bulletin A340–32– 96 months or more and on which the first beams, as well as reports that some airplanes 4268, Revision 03, including Appendix 1, inspection was done before 45 months since have been inspected too early and not re- dated January 14, 2013; as applicable. first flight of the MLG bogie beam on an inspected as needed. We are issuing this AD (1) For MLG bogie beams having the airplane, or since the MLG bogie beam’s first to detect and correct damage or corrosion of configurations specified in both paragraphs flight on an airplane after the MLG bogie the MLG bogie beams, which could cause a (h)(1)(i) and (h)(1)(ii) of this AD: Do the beam’s most recent overhaul, as applicable. runway excursion event, bogie beam detailed inspection specified in the introductory text of paragraph (h) of this AD (i) Application of Protective Treatment detachment from the airplane, or MLG collapse, and could result in damage to the within 9 months after the effective date of If, during any inspection required by airplane and injury to the occupants. this AD. paragraph (g) or (h) of this AD, no damage (i) MLG bogie beams having between 72 or corrosion is found: Before further flight, (f) Compliance and 120 months since first flight on an apply the protective treatments to the MLG Comply with this AD within the airplane, or since the MLG bogie beam’s first bogie beam, in accordance with the compliance times specified, unless already flight on an airplane after the MLG bogie Accomplishment Instructions of Messier- done. beam’s most recent overhaul, as applicable. Dowty Service Bulletin A33/34–32–272, (ii) MLG bogie beams on which the first Revision 1, including Appendixes A, B, C, (g) Repetitive Inspections for Certain inspection was done after 51 months and and D, dated September 22, 2008. Airplane Configurations before 54 months since first flight of the MLG For airplanes equipped with basic MLG bogie beam on an airplane, or since the MLG (j) Repair and Application of Protective (201252 series), or growth MLG (201490 bogie beam’s first flight on an airplane after Treatment series): After 54 months at the earliest, but no the MLG bogie beam’s most recent overhaul, If, during any inspection required by sradovich on DSK3GMQ082PROD with RULES later than 72 months since the left-hand (LH) as applicable. paragraph (g) or (h) of this AD, any damage or right-hand (RH) MLG bogie beam’s first (2) For MLG bogie beams having the or corrosion is found: Before further flight, flight on an airplane, or since its first flight configurations specified in both paragraphs repair and apply the protective treatments to on an airplane after overhaul, as applicable, (h)(2)(i) and (h)(2)(ii) of this AD: Do the the MLG bogie beam, in accordance with the clean the internal bore and accomplish a detailed inspection specified in the Accomplishment Instructions of Messier- detailed inspection of internal surfaces of the introductory text of paragraph (h) of this AD Dowty Service Bulletin A33/34–32–272, LH and RH MLG bogie beams to detect any within 3 months after the effective date of Revision 1, including Appendixes A, B, C, damage to the protective treatments and any this AD. and D, dated September 22, 2008. 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66522 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations (k) Inspection and Corrective Actions Sheet, dated October 14, 2011; at the beam’s most recent overhaul, as applicable. For airplanes equipped with basic MLG applicable time specified in paragraph Airbus Service Bulletin A330–32–3225, (201252 series), growth MLG (201490 series), (m)(1)(i) or (m)(1)(ii) of this AD. dated November 21, 2007, is not incorporated or enhanced MLG (10–210 series): Before the (i) If the inspection was done on or after by reference in this AD. Airbus Mandatory accumulation of 252 total months on an MLG the effective date of this AD: Submit the Service Bulletin A330–32–3225, Revision 01, bogie beam, or within 90 days after the report within 90 days after the inspection. including Appendix 1, dated October 30, effective date of this AD, whichever occurs (ii) If the inspection was done before the 2008, was incorporated by reference in AD later, do the actions specified in paragraphs effective date of this AD: Submit the report 2009–15–07. (k)(1) and (k)(2) of this AD concurrently and within 90 days after the effective date of this (2) This paragraph provides credit for the in sequence. AD. corresponding inspections and corrective (1) Except as provided by paragraph (k)(3) (2) Submit a report of the findings (both actions done on an LH or RH MLG bogie of this AD: Do a detailed inspection for positive and negative) of the inspection beam required by paragraph (g) of this AD, damage and corrosion of the internal bores of required by paragraph (h) of this AD to if those actions were performed before the the LH and RH MLG bogie beam, in Airbus, Customer Service Directorate, 1 Rond effective date of this AD using Airbus accordance with the Accomplishment Point Maurice Bellonte, 31707 Blagnac Mandatory Service Bulletin A340–32–4268, Instructions of Airbus Service Bulletin A330– Cedex, France, using the applicable dated November 21, 2007; Revision 01, 32–3237 or A340–32–4279, both Revision 01, Reporting Sheet in Airbus Service Bulletin including Appendix 1, dated October 30, both including Reporting Sheet, both dated A330–32–3225, Revision 02, including 2008; or Revision 02, dated October 26, 2012; October 14, 2011, as applicable. If any Appendix 1, dated October 26, 2012; or provided these inspections and corrective damage or corrosion is found, before further Airbus Service Bulletin A340–32–4268, actions were accomplished between 54 flight, repair in accordance with the Revision 03, including Appendix 1, dated months and 72 months since first flight of the Accomplishment Instructions of Airbus January 14, 2013; at the applicable time affected MLG bogie beam on an airplane, or Service Bulletin A330–32–3237 or A340–32– specified in paragraph (m)(2)(i) or (m)(2)(ii) since its first flight after the MLG bogie 4279, both Revision 01, both including of this AD. beam’s most recent overhaul, as applicable. Reporting Sheet, both dated October 14, (i) If the inspection was done on or after Airbus Service Bulletin A340–32–4268, 2011, as applicable. the effective date of this AD: Submit the dated November 21, 2007; and Revision 02, (2) Except as provided by paragraph (k)(3) report within 30 days after the inspection. dated October 26, 2012; are not incorporated of this AD: Modify and re-identify, as (ii) If the inspection was done before the by reference in this AD. Airbus Mandatory applicable, the LH and RH MLG bogie beams, effective date of this AD: Submit the report Service Bulletin A340–32–4268, Revision 01, in accordance with the Accomplishment within 30 days after the effective date of this including Appendix 1, dated October 30, Instructions of Airbus Service Bulletin A330– AD. 2008, was incorporated by reference in AD 32–3237 or A340–32–4279, both Revision 01, (n) Optional Method of Compliance for 2009–15–17. both including Reporting Sheet, both dated Certain Requirements (3) This paragraph provides credit for the October 14, 2011, as applicable. corresponding actions required by paragraph (1) Inspections for damage and corrosion to (n)(1) of this AD, if those actions were (3) The inspection requirements of the protective treatment of the internal bores paragraph (k)(1) of this AD, and the performed before the effective date of this AD of the LH and RH MLG bogie beam, and using Messier-Dowty Service Bulletin A33/ modification requirements only of paragraph repairs, done in accordance with Messier- (k)(2) of this AD, do not apply to any MLG 34–32–271, dated September 13, 2007, which Dowty Service Bulletin A33/34–32–278, is not incorporated by reference in this AD. bogie beam with a serial number listed in Revision 1, including Appendixes A and B, Appendix A of Messier-Dowty Service (4) This paragraph provides credit for the dated August 24, 2011, are acceptable corresponding actions required by Bulletin A33/34–32–283 or A33/34–32–284, methods of compliance with the both Revision 1, both dated July 10, 2012, as paragraphs (j) and (n)(1) of this AD, if those corresponding requirements of paragraph actions were performed before the effective applicable. (k)(1) of this AD. date of this AD using Messier-Dowty Service (l) Optional Methods of Compliance for (2) Modification of the LH and RH MLG Bulletin A33/34–32–272, including Certain Airplane Configurations bogie beams, done in accordance with Appendixes A, B, C, and D, dated November Messier-Dowty Service Bulletins A33/34–32– Inspections and corrective actions on both 16, 2007, which is not incorporated by 283 or A33/34–32–284, both Revision 1, both MLG bogie beams done in accordance with reference in this AD. including Appendix A, both dated July 10, the instructions of Messier-Dowty Service (5) This paragraph provides credit for the 2012, as applicable, is an acceptable method Bulletin A33/34–32–271, Revision 1, corresponding actions required by of compliance with the corresponding including Appendixes A and B, dated paragraphs (k), (m), and (r)(1)(i) of this AD, requirements of paragraph (k)(2) of this AD. November 16, 2007; or Messier-Dowty if those actions were performed before the Service Bulletin A33/34–32–272, Revision 1, (o) Optional Terminating Action for Certain effective date of this AD using Airbus Service including Appendixes A, B, C, and D, dated Requirements Bulletin A330–32–3237, including Reporting September 22, 2008; as applicable; are Modification of both LH and RH MLG Sheet, dated January 18, 2011. acceptable methods of compliance for the bogie beams on an airplane, done in (6) This paragraph provides credit for the requirements of paragraph (g) of this AD, accordance with paragraph (k) of this AD, or corresponding actions required by provided each inspection is accomplished as specified in paragraphs (n)(1) and (n)(2) of paragraphs (k), (m), and (r)(1)(i) of this AD, between 54 months and 72 months since the this AD, terminates the repetitive inspections if those actions were performed before the first flight of the affected MLG bogie beam on required by paragraph (g) of this AD for this effective date of this AD using Airbus Service an airplane, or since the MLG bogie beam’s airplane. Bulletin A340–32–4279, including Reporting first flight after the MLG bogie beam’s most Sheet, dated January 18, 2011. recent overhaul, as applicable. (p) Credit for Previous Actions (7) This paragraph provides credit for the (1) This paragraph provides credit for the corresponding actions required by (m) Reporting Requirement corresponding inspections and corrective paragraphs (k)(3), (n)(2), (r)(1)(ii), and (1) Submit a report of the findings (both actions done on an LH or RH MLG bogie (r)(1)(iii) of this AD, if those actions were positive and negative) of each inspection beam required by paragraph (g) of this AD, performed before the effective date of this AD required by paragraph (k) of this AD, as if those actions were performed before the using Messier-Dowty Service Bulletin A33/ sradovich on DSK3GMQ082PROD with RULES applicable, to Airbus, Customer Service effective date of this AD using Airbus Service 34–32–283, including Appendix A, dated Directorate, 1 Rond Point Maurice Bellonte, Bulletin A330–32–3225, dated November 21, May 11, 2010, which is not incorporated by 31707 Blagnac Cedex, France, using the 2007; or Revision 1, dated October 30, 2008; reference in this AD. applicable Reporting Sheet in Airbus Service provided the inspections and corrective (8) This paragraph provides credit for the Bulletin A330–32–3237, Revision 01, actions were accomplished between 54 corresponding actions required by including Reporting Sheet, dated October 14, months and 72 months since first flight of the paragraphs (k)(3), (n)(2), (r)(1)(ii), and 2011; or Airbus Service Bulletin A340–32– affected MLG bogie beam on an airplane, or (r)(1)(iii) of this AD, if those actions were 4279, Revision 01, including Reporting since its first flight after the MLG bogie performed before the effective date of this AD VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1

Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 66523 using Messier-Dowty Service Bulletin A33/ appropriate. If sending information directly (3) The following service information was 34–32–284, including Appendix A, dated to the International Branch, send it to ATTN: approved for IBR on November 2, 2016. May 11, 2010, which is not incorporated by Vladimir Ulyanov, Aerospace Engineer, (i) Airbus Service Bulletin A330–32–3225, reference in this AD. International Branch, ANM–116, Transport Revision 02, including Appendix 1, dated (9) This paragraph provides credit for the Airplane Directorate, FAA, 1601 Lind October 26, 2012. corresponding actions required by Avenue SW., Renton, WA 98057–3356; (ii) Airbus Service Bulletin A330–32–3237, paragraphs (n)(1) and (r)(1)(ii) of this AD, if telephone: 425–227–1138; fax: 425–227– those actions were performed before the Revision 01, including Reporting Sheet, 1149. Information may be emailed to: 9- effective date of this AD using Messier-Dowty ANM-116-AMOC-REQUESTS@faa.gov. dated October 14, 2011. Service Bulletin A33/34–32–278, including Before using any approved AMOC, notify (iii) Airbus Service Bulletin A340–32– Appendixes A and B, dated February 17, your appropriate principal inspector, or 4268, Revision 03, including Appendix 1, 2010, which is not incorporated by reference lacking a principal inspector, the manager of dated January 14, 2013. in this AD. the local flight standards district office/ (iv) Airbus Service Bulletin A340–32– (q) Clarification of Inspection Compliance certificate holding district office. The AMOC 4279, Revision 01, including Reporting Times approval letter must specifically reference Sheet, dated October 14, 2011. this AD. (v) Messier-Dowty Service Bulletin A33/ After accomplishment of the one-time (2) Contacting the Manufacturer: As of the detailed inspection required by paragraph (h) 34–32–278, Revision 1, including effective date of this AD, for any requirement Appendixes A and B, dated August 24, 2011. of this AD, the repetitive actions required by in this AD to obtain corrective actions from paragraph (g) of this AD remain applicable, (vi) Messier-Dowty Service Bulletin A33/ a manufacturer, the action must be and must be done within the compliance accomplished using a method approved by 34–32–283, Revision 1, including Appendix times specified in paragraph (g) of this AD. the Manager, International Branch, ANM– A, dated July 10, 2012. (r) Parts Installation Limitations 116, Transport Airplane Directorate, FAA; or (vii) Messier-Dowty Service Bulletin A33/ the European Aviation Safety Agency 34–32–284, Revision 1, including Appendix (1) After modification of an airplane, as (EASA); or Airbus’s EASA Design A, dated July 10, 2012. required by paragraph (k) of this AD, or as Organization Approval (DOA). If approved by (4) The following service information was specified in paragraphs (n)(1) and (n)(2) of this AD, do not install an MLG bogie beam the DOA, the approval must include the approved for IBR on September 2, 2009 (74 on any airplane unless it is done in DOA-authorized signature. FR 37523, July 29, 2009). compliance with the requirements of (3) Reporting Requirements: A federal (i) Messier-Dowty Service Bulletin A33/ paragraph (r)(1)(i), (r)(1)(ii), or (r)(1)(iii) of agency may not conduct or sponsor, and a 34–32–271, Revision 1, including this AD. person is not required to respond to, nor Appendixes A and B, dated November 16, (i) The MLG bogie beam has been modified shall a person be subject to a penalty for failure to comply with a collection of 2007. and re-identified in accordance with the (ii) Messier-Dowty Service Bulletin A33/ Accomplishment Instructions of Airbus information subject to the requirements of the Paperwork Reduction Act unless that 34–32–272, Revision 1, including Service Bulletin A330–32–3237 or A340–32– collection of information displays a current Appendixes A, B, C, and D, dated September 4279, both Revision 01, both including valid OMB Control Number. The OMB 22, 2008. Reporting Sheet, both dated October 14, 2011, as applicable. Control Number for this information (5) For Airbus service information (ii) The MLG bogie beam has been collection is 2120–0056. Public reporting for identified in this AD, contact Airbus SAS, inspected and all applicable corrective this collection of information is estimated to Airworthiness Office—EAL, 1 Rond Point actions have been done in accordance with be approximately 5 minutes per response, Maurice Bellonte, 31707 Blagnac Cedex, the Accomplishment Instructions of Messier- including the time for reviewing instructions, France; telephone: +33 5 61 93 36 96; fax: Dowty Service Bulletin A33/34–32–278, completing and reviewing the collection of +33 5 61 93 45 80; email: Revision 1, dated August 24, 2011; and information. All responses to this collection airworthiness.A330-A340@airbus.com; modified in accordance with the of information are mandatory. Comments Internet: http://www.airbus.com. Accomplishment Instructions of Messier- concerning the accuracy of this burden and suggestions for reducing the burden should (6) For Messier-Dowty service information Dowty Service Bulletin A33/34–32–283 or identified in this AD, contact Messier-Dowty: A33/34–32–284, both Revision 1, both be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Messier Services Americas, Customer including Appendix A, both dated July 10, 2012. Information Collection Clearance Officer, Support Center, 45360 Severn Way, Sterling, (iii) The MLG bogie beam has a serial AES–200. VA 20166–8910; telephone 703–450–8233; number listed in Appendix A of Messier- fax 703–404–1621; Internet: https:// (t) Related Information Dowty Service Bulletin A33/34–32–283 or techpubs.services/messier-dowty.com. A33/34–32–284, both Revision 1, both dated (1) Refer to Mandatory Continuing (7) You may view this service information July 10, 2012, as applicable. Airworthiness Information (MCAI) AD 2013– at the FAA, Transport Airplane Directorate, (2) As of the effective date of this AD, 0267R1, dated March 4, 2014; corrected 1601 Lind Avenue SW., Renton, WA. For except as specified in paragraph (r)(1) of this March 8, 2014, for related information. This information on the availability of this AD, installation of an MLG bogie beam on an MCAI may be found in the AD docket on the material at the FAA, call 425–227–1221. airplane is allowed, provided that following Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– (8) You may view this service information the installation it is inspected and all 2013–0828. that is incorporated by reference at the applicable repairs and corrective actions have been done in accordance with the (2) Service information identified in this National Archives and Records requirements of this AD. AD that is not incorporated by reference is Administration (NARA). For information on available at the addresses specified in the availability of this material at NARA, call (s) Other FAA AD Provisions paragraphs (u)(5), (u)(6), and (u)(7) of this 202–741–6030, or go to: http:// The following provisions also apply to this AD. www.archives.gov/federal-register/cfr/ibr- AD: locations.html. (1) Alternative Methods of Compliance (u) Material Incorporated by Reference Issued in Renton, Washington, on August sradovich on DSK3GMQ082PROD with RULES (AMOCs): The Manager, International (1) The Director of the Federal Register Branch, ANM–116, Transport Airplane approved the incorporation by reference 24, 2016. Directorate, FAA, has the authority to (IBR) of the service information listed in this John P. Piccola, Jr., approve AMOCs for this AD, if requested paragraph under 5 U.S.C. 552(a) and 1 CFR Acting Manager, Transport Airplane using the procedures found in 14 CFR 39.19. part 51. Directorate, Aircraft Certification Service. In accordance with 14 CFR 39.19, send your (2) You must use this service information request to your principal inspector or local as applicable to do the actions required by [FR Doc. 2016–21150 Filed 9–27–16; 8:45 am] Flight Standards District Office, as this AD, unless this AD specifies otherwise. BILLING CODE 4910–13–P VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1


Document Created: 2016-09-28 01:08:08
Document Modified: 2016-09-28 01:08:08
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective November 2, 2016.
ContactVladimir 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 Citation81 FR 66518 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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