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[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)]
[Rules and Regulations]
[Pages 44994-44996]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16316]

[[Page 44994]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0459; Directorate Identifier 2015-NM-081-AD; 
Amendment 39-18589; AD 2016-14-08]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2015-10-03 for 
certain Airbus Model A330-200 and -300 series airplanes, and Model 
A340-200 and -300 series airplanes. AD 2015-10-03 required a detailed 
inspection for visible chrome of each affected main landing gear (MLG) 
sidestay upper cardan pin, associated nuts, and retainer assembly; pin 
replacement if needed; measurement of cardan pin clearance dimensions 
(gap check); corrective actions if necessary; and a report of all 
findings. This new AD requires a detailed inspection of the upper 
cardan pin and nut threads for any corrosion, pitting, or thread 
damage, and if necessary, replacement of the cardan pin and nut. This 
new AD also revises the applicability to include additional airplane 
models. This AD was prompted by a report that an MLG sidestay upper 
cardan pin migration event had been caused by corrosion due to lack of 
jointing compound and inadequate sealant application during the MLG 
installation. We are issuing this AD to detect and correct migration of 
the sidestay upper cardan pin, which could result in disconnection of 
the sidestay upper arm from the airplane structure, and could result in 
a landing gear collapse and consequent damage to the airplane and 
injury to occupants.

DATES: This AD is effective August 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 16, 
2016.

ADDRESSES: For 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 airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0459.

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-2016-
0459; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-10-03, Amendment 39-18158 (80 FR 30608, 
May 29, 2015) (``AD 2015-10-03''). AD 2015-10-03 applied to certain 
Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and 
-300 series airplanes. The NPRM published in the Federal Register on 
January 21, 2016 (81 FR 3346) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0079, dated May 7, 2015 (referred to after 
this as the Mandatory Continuing Airworthiness Information, or ``the 
MCAI''), to correct an unsafe condition for certain Airbus Model A330-
200 and -300 series airplanes, Model A340-200 and -300 series 
airplanes, and Model A340-541 and -642 airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic MLG was rolling out after 
landing when it experienced a nose wheel steering fault (unrelated 
to the safety subject addressed by this AD), which resulted in the 
crew stopping the aeroplane on the taxiway after vacating the 
runway. The subsequent investigation revealed that the right-hand 
MLG sidestay upper cardan pin had migrated out of position. The 
sidestay upper cardan nut and retainer had detached from the upper 
cardan pin and were found, still bolted together, in the landing 
gear bay.
    Prompted by these findings, Airbus published Alert Operators 
Transmission (AOT) A32L003-14, providing inspection instructions 
and, as an interim solution, EASA issued AD 2014-0066 [which 
corresponds to FAA AD 2015-10-03, Amendment 39-18158 (80 FR 30608, 
May 29, 2015)] to require repetitive detailed inspections (DET) of 
the MLG upper cardan pin, nut and retainer. That AD also required 
accomplishment of a one-time gap check between wing rear spar 
fitting lugs and the bush flanges and, depending on findings, 
corrective action(s). The gap check (including corrections, as 
necessary) terminated the repetitive DET.
    Since that [EASA] AD was issued, further investigation concluded 
that the reported MLG sidestay upper cardan pin migration event had 
been caused by corrosion, due to lack of jointing compound and 
inadequate sealant application during MLG installation. Therefore, 
this issue affects any MLG that had an upper cardan pin replacement 
or re-installation, irrespective of MLG overhaul. Any corrosion on 
the upper cardan pin and nut threads would not have been detected 
during the previously required DET.
    This condition, if not detected and corrected, could lead to a 
complete migration of the sidestay upper cardan pin and a 
disconnection of the sidestay upper arm from the aeroplane 
structure, possibly resulting in MLG collapse with consequent damage 
to the aeroplane and injury to occupants.
    To address this potential unsafe condition, Airbus published 
Service Bulletin (SB) A330-32-3269, SB A340-32-4301 and SB A340-32-
5115 providing inspection instructions. In addition, to prevent any 
improper re-installation of an upper cardan pin on a MLG, Airbus 
amended the applicable Aircraft Maintenance Manual (AMM) on 01 
October 2014.
    For the reasons described above, this [EASA] AD supersedes EASA 
[AD] 2014-0066 and requires a one-time DET of the MLG upper cardan 
pin and nut threads to check for corrosion or damage on the upper 
cardan pin and nut threads, and, depending on findings, replacement 
of the damaged part(s).
    As this unsafe condition could also develop on A330 freighters 
and A340-500/ -600 aeroplanes, this [EASA] AD also applies to those 
aeroplanes.

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-2016-
0459.

Comments

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

[[Page 44995]]

Request To Use the Latest Service Information

    American Airlines (AA) requested that we use the latest service 
information in the NPRM. AA stated that since the NPRM was issued, 
Airbus released Service Bulletin A330-32-3269, Revision 01, dated 
December 3, 2015.
    We agree with the commenter for the reasons stated above. We have 
reviewed Airbus Service Bulletin A330-32-3269, Revision 01, dated 
December 3, 2015, and there are no substantial changes. In addition, we 
have also reviewed Airbus Service Bulletin A340-32-4301, Revision 01, 
dated December 3, 2015; and Airbus Service Bulletin A340-32-5115, 
Revision 01, dated December 11, 2015. There are no substantial changes. 
We have revised this AD accordingly.

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 changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:

 Airbus Service Bulletin A330-32-3269, Revision 01, dated 
December 3, 2015.
 Airbus Service Bulletin A340-32-4301, Revision 01, dated 
December 3, 2015.
 Airbus Service Bulletin A340-32-5115, Revision 01, dated 
December 11, 2015.

    The service information describes procedures for a detailed 
inspection of the upper cardan pin and nut threads for any corrosion, 
pitting, or thread damage, and replacement of the cardan pin and nut. 
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 95 airplanes of U.S. registry.
    We also estimate that it will take about 11 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $88,825, or $935 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 12 work-hours and require parts costing $78,136, for a cost 
of $79,156 per product. We have no way of determining the number of 
aircraft that might need this action.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015), and adding 
the following new AD:

2016-14-08 Airbus: Amendment 39-18589. Docket No. FAA-2016-0459; 
Directorate Identifier 2015-NM-081-AD.

(a) Effective Date

    This AD is effective August 16, 2016.

(b) Affected ADs

    This AD replaces 2015-10-03, Amendment 39-18158 (80 FR 30608, 
May 29, 2015).

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, 
except airplanes on which an upper cardan pin on a main landing gear 
(MLG) has never been replaced or reinstalled since first entry into 
service of the airplane.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, 
all manufacturer serial numbers.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all manufacturer serial numbers.
    (3) Airbus Model A340-541 and -642 airplanes, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that an MLG sidestay upper 
cardan pin migration event had been caused by corrosion due to lack 
of jointing compound and inadequate sealant application during the 
MLG installation. We are issuing this AD to detect and correct 
migration of the sidestay upper cardan pin, which could result in 
disconnection of the sidestay upper arm from the airplane structure, 
and could result in a landing gear collapse and consequent damage to 
the airplane and injury to occupants.

(f) Compliance

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

(g) Definition

    For the purpose of this AD, an upper cardan pin on a MLG is 
affected if it has been

[[Page 44996]]

installed as a replacement part, or reinstalled since first entry of 
the airplane into service, and if the installation was accomplished 
using the applicable airplane maintenance manual at a revision level 
prior to October 1, 2014.

(h) Inspection and Replacement

    (1) For an affected upper cardan pin on an MLG: Before exceeding 
96 months since its latest installation on an airplane, or within 12 
months after the effective date of this AD, whichever occurs later, 
do a detailed inspection of the upper cardan pin and nut threads for 
any corrosion, pitting, or thread damage, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (i) of this AD.
    (2) If, during the detailed inspection specified in paragraph 
(h)(1) of this AD, any corrosion, pitting, or thread damage is 
found, before further flight, replace the upper cardan pin and/or 
nut, as applicable, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraph (i) of this AD.

(i) Applicable Service Information

    Do the actions required by paragraph (h) of this AD in 
accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD.
    (1) Airbus Service Bulletin A330-32-3269, Revision 01, dated 
December 3, 2015 (for Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes).
    (2) Airbus Service Bulletin A340-32-4301, Revision 01, dated 
December 3, 2015 (for Airbus Model A340-211, -212, -213, -311, -312, 
and -313 airplanes).
    (3) Airbus Service Bulletin A340-32-5115, Revision 01, dated 
December 11, 2015 (for Airbus Model A340-541 and -642 airplanes).

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. This 
service information is not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-32-3269, dated February 17, 
2015.
    (2) Airbus Service Bulletin A340-32-4301, dated February 17, 
2015.
    (3) Airbus Service Bulletin A340-32-5115, dated February 17, 
2015.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM 116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0079, dated May 7, 2015, 
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-2016-0459.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-32-3269, Revision 01, dated 
December 3, 2015.
    (ii) Airbus Service Bulletin A340-32-4301, Revision 01, dated 
December 3, 2015.
    (iii) Airbus Service Bulletin A340-32-5115, Revision 01, dated 
December 11, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 28, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-16316 Filed 7-11-16; 8:45 am]
 BILLING CODE 4910-13-P
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