
[Federal Register Volume 78, Number 243 (Wednesday, December 18, 2013)]
[Proposed Rules]
[Pages 76572-76574]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-30030]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 78, No. 243 / Wednesday, December 18, 2013 / 
Proposed Rules  

[[Page 76572]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1028; Directorate Identifier 2013-NM-068-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318-111 and -112 airplanes, Model A319-111, -112, -113, -
114, and -115 airplanes, Model A320-111, -211, -212, and -214 
airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. 
This proposed AD was prompted by reports of broken aft engine mount 
retainers. This proposed AD would require inspecting the aft engine 
mount retainers for surface finish, and for cracks and failure, and 
replacement if necessary. We are proposing this AD to prevent failure 
of retainer brackets of the aft engine mount and consequent loss of the 
locking feature of the nuts of the inner and outer pins. Loss of the 
pins will result in the aft mount engine link no longer being secured 
to the aft engine mount.

DATES: We must receive comments on this proposed AD by February 3, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this proposed 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 account.airworth-eas@airbus.com; Internet 
http://www.airbus.com.
    For Goodrich Corporation service information identified in this 
proposed AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon 
Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: 
jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs.
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-1028; 
Directorate Identifier 2013-NM-068-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0050, dated March 5, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During in-service inspections, several aft engine mount 
retainers, fitted on aeroplanes equipped with CFM56-5/5B engines, 
have been found broken.
    The results of the investigations highlight that two different 
types of surface finish have been applied (respectively bright and 
dull material finishes), and that dull finish adversely affects the 
strength of the retainer with regard to fatigue properties of the 
part.
    The pins which attach the engine link to the aft mount are 
secured by two nuts, which do not have a self-locking feature; this 
function is provided by the retainer brackets. In case of failure of 
the retainer bracket, the locking feature of the nuts of the inner 
and outer pins is lost; as a result, these nuts could subsequently 
become loose.
    In case of full loss of the nuts, there is the potential to also 
lose the pins, in which case the aft mount link will no longer be 
secured to the aft engine mount. The same locking feature is used 
for the three link assemblies of the aft mount.
    For the reasons described above, this [EASA] AD requires a one-
time detailed visual inspection (DVI) of the aft engine mount to 
identify the affected dull finish retainers [and for cracks and 
failure] and replace these [retainers] with serviceable retainers. 
This [EASA] AD also prohibits installation of any dull finish aft 
engine mount retainers.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-
2013-1028.

[[Page 76573]]

Relevant Service Information

    Airbus has issued Airbus Alert Operators Transmission (AOT) 
A71N001-12, Rev. 2, dated February 27, 2013.
    Goodrich Corporation has issued Goodrich Service Bulletin RA32071-
146, Rev. 2, dated July 26, 2012.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  3 work-hours x $85               $0   $255 per inspection  $217,005 per
                                   per hour = $255                       cycle for two        inspection cycle
                                   per inspection                        engines.             for two engines.
                                   cycle for two
                                   engines.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost             Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Bracket replacement....................  1 work-hour x $85 per hour         $10,000   $10,085 per engine.
                                          = $85 per engine.
----------------------------------------------------------------------------------------------------------------

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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2013-1028; Directorate Identifier 2013-NM-
068-AD.

(a) Comments Due Date

    We must receive comments by February 3, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Airbus Model A320-111, -211, -212, and -214 airplanes.
    (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports of broken aft engine mount 
retainers. We are issuing this AD to prevent failure of retainer 
brackets of the aft engine mount and consequent loss of the locking 
feature of the nuts of the inner and outer pins. Loss of the

[[Page 76574]]

pins will result in the aft mount engine link no longer being 
secured to the aft engine mount.

(f) Compliance

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

(g) Inspection

    Within 3 months after the effective date of this AD: Do a 
detailed inspection of the aft engine mount retainers for surface 
finish (dull or bright), and for cracks and failure, in accordance 
with Section 4.2.2, ``Inspection Requirements,'' of Airbus Alert 
Operators Transmission (AOT) A71N001-12, Rev. 2, dated February 27, 
2013, except as specified in paragraph (h) of this AD.

(h) Exception to Paragraph (g) of This AD

    The actions required by paragraph (g) of this AD are not 
required to be done on airplanes with manufacturer serial numbers 
4942 and higher, provided a review of maintenance records verifies 
that no aft engine mount retainers have been replaced since first 
flight of the airplane.

(i) Repetitive Inspection and Retainer Replacement for Dull Finish 
Retainers

    If, during the detailed inspection required by paragraph (g) of 
this AD, any installed dull finish aft engine mount retainer is 
found without cracks and not failed: Do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD.
    (1) Within 25 flight cycles after doing the actions required by 
paragraph (g) of this AD, repeat the detailed inspection specified 
in paragraph (g) of this AD.
    (2) Within 50 flight cycles after doing the first detailed 
inspection specified in paragraph (g) of this AD: Replace all dull 
finish retainers with a new or serviceable retainer, in accordance 
with Section 4.2.3.1, ``Replacement Procedure,'' of Airbus AOT 
A71N001-12, Rev. 2, dated February 27, 2013.

(j) Replacement of Cracked or Failed Retainers

    If, during any detailed inspection specified in paragraph (g) of 
this AD, any installed aft engine mount retainer is found cracked or 
failed: Before further flight, replace all affected aft engine mount 
retainers with a new or serviceable retainer, in accordance with 
Section 4.2.3, ``Replacement Procedure,'' of Airbus AOT A71N001-12, 
Rev. 2, dated February 27, 2013.

(k) Parts Prohibition

    As of the effective date of this AD, no person may install any 
aft engine mount retainer with a dull finish on any airplane. The 
instructions of Airbus AOT A71N001-12, Revision 2, dated February 
27, 2013; or the Accomplishment Instructions of Goodrich Service 
Bulletin RA32071-146, Rev. 2, dated July 26, 2012; can be used to 
verify the correct finish of the part.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (i), and (j) of this AD, if those actions were 
performed before the effective date of this AD using Airbus AOT 
A71N001-12, Rev. 1, dated August 9, 2012.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the 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: 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or by the Design Approval Holder with a State of 
Design Authority's design organization approval). For a repair 
method to be approved, the repair approval must specifically refer 
to this AD. You are required to ensure the product is airworthy 
before it is returned to service.

(n) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided no dull 
finish aft engine mount retainers that are cracked or have failed 
are installed.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0050, dated March 5, 2013, 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 it in Docket No. FAA-2013-1028.
    (2) For Airbus 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 account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) For Goodrich Corporation service information identified in 
this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon 
Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: 
jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs.
    (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.

    Issued in Renton, Washington, on December 9, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-30030 Filed 12-17-13; 8:45 am]
BILLING CODE 4910-13-P


