[Federal Register Volume 82, Number 10 (Tuesday, January 17, 2017)]
[Rules and Regulations]
[Pages 4773-4775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31961]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9110; Directorate Identifier 2015-NM-196-AD; 
Amendment 39-18773; AD 2017-01-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-
213, and A321-231 airplanes. This AD was prompted by a report of 
certain tie rod assemblies installed on the hinged fairing assembly of 
the main landing gear (MLG) with no cadmium plating on the rod end 
threads. This AD requires inspection and replacement of certain tie rod 
assemblies installed on the hinged fairing assembly of the MLG. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective February 21, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 21, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; 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-
9110.

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-
9110; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A319-
115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 
airplanes. The NPRM published in the Federal Register on September 19, 
2016 (81 FR 64083).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0234, dated December 8, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-
231 airplanes. The MCAI states:

    A production quality issue was identified concerning tie rod 
assemblies, having Part Number (P/N) starting with D52840212000 or 
D52840212002, which are installed on the main landing gear (MLG) 
hinged fairing assembly. This quality issue affects the cadmium 
plating surface treatment which

[[Page 4774]]

was inadvertently omitted from the rod end threads of the assembly. 
The absence of cadmium plating reduces the corrosion protection 
scheme.
    This condition, if not detected and corrected, could lead to 
galvanic corrosion of the tie rod end threads, possibly resulting in 
rod end failure, loss of a MLG door, and consequent injury to 
persons on ground.
    To address this unsafe condition, Airbus identified the affected 
[manufacturer serial number] MSN and issued [service bulletin] SB 
A320-52-1167 to provide inspection instructions.
    For the reason described above, this [EASA] AD requires a one-
time inspection of the affected MLG hinged fairing tie rod 
assemblies [for the presence of cadmium plating], and, depending on 
findings, replacement of the affected tie rod assembly.

    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-
9110.

Comments

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

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
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 Service Bulletin A320-52-1167, dated August 6, 
2015. The service information describes procedures for a detailed 
inspection for the presence of cadmium plating on tie rod assemblies 
having certain part numbers, and procedures for replacement of tie rod 
assemblies with no cadmium plating on the rod end threads. 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 20 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                        Cost per    Cost on U.S.
               Action                            Labor cost              Parts cost      product      operators
----------------------------------------------------------------------------------------------------------------
Inspection.........................  2 work-hours x $85 per hour =               $0          $170        $3,400
                                      $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that will be required based on the results of the inspection. We have 
no way of determining the number of airplanes that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                Action                            Labor cost                   Parts cost             product
----------------------------------------------------------------------------------------------------------------
Replacement...........................  13 work-hours x $85 per hour =  Not available...........          $1,105
                                         $1,105.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

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 4775]]

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-01-06 Airbus: Amendment 39-18773; Docket No. FAA-2016-9110; 
Directorate Identifier 2015-NM-196-AD.

(a) Effective Date

    This AD is effective February 21, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A319-115, A319-132, A320-214, 
A320-232, A321-211, A321-213, and A321-231 airplanes, certificated 
in any category, as identified in Airbus Service Bulletin A320-52-
1167, dated August 6, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report of certain tie rod assemblies 
installed on the hinged fairing assembly of the main landing gear 
(MLG) with no cadmium plating on the rod end threads. We are issuing 
this AD to detect and correct the absence of cadmium plating on the 
rod end threads of the tie rod assemblies. The absence of cadmium 
plating could lead to galvanic corrosion of the tie rod end threads, 
resulting in rod end failure, loss of a MLG door, and consequent 
damage to the airplane.

(f) Compliance

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

(g) Inspection and Corrective Action

    Within 80 months after the airplane's first flight, do a 
detailed inspection of each tie rod assembly having a part number 
(P/N) D52840212000 or D52840212002 at the MLG hinged fairing for the 
presence of cadmium plating (gold colored threads), in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-52-1167, dated August 6, 2015. If during the inspection any tie 
rod assembly is found that does not have cadmium plating, before 
further flight, replace the tie rod assembly with a serviceable part 
having the same part number and cadmium plating, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-52-
1167, dated August 6, 2015.

(h) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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: 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) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(i) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2015-0234, dated December 8, 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-2016-9110.

(j) 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 A320-52-1167, dated August 6, 2015.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; 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 December 23, 2016.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-31961 Filed 1-13-17; 8:45 am]
 BILLING CODE 4910-13-P