[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)]
[Proposed Rules]
[Pages 10411-10415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04727]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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 A320-211, -212, -214, and -216 
airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. 
This proposed AD was prompted by a report of a production quality 
deficiency on the

[[Page 10412]]

inner retainer installed on link assemblies of the aft engine mount, 
which could result in failure of the retainer. This proposed AD would 
require modifying and re-identifying the aft engine mount assemblies. 
We are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by April 23, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, 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.
    For Goodrich Aerospace service information identified in this NPRM, 
contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; phone: 619-691-2719; email: 
[email protected]; internet: http://www.goodrich.com/TechPubs.
    You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195.

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-2018-
0165; 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 NPRM, 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 Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0165; 
Product Identifier 2017-NM-122-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0251, dated December 15, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111 and -112 airplanes, Model A319-111, -112, -113, -114, and -115 
airplanes, Model A320-211, -212, -214, and -216 airplanes, and Model 
A321-111, -112, -211, -212, and -213 airplanes. The MCAI states:

    During in-service inspections, several aft engine mount inner 
retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, 
were found broken. Investigation identified that the main cause of 
crack initiation was the vibration dynamic effect that affects the 
retainers, and that the ``dull'' surface finish pitting is an 
aggravating factor when compared with the ``bright'' surface 
finishing.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft engine mount link, possibly resulting in 
damage to the aeroplane and/or injury to persons on the ground.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A71N001-12 (later revised) and EASA 
issued AD 2013-0050 [which corresponds to FAA AD 2014-14-06, 
Amendment 39-17901 (79 FR 42655, July 23, 2014)], later superseded 
by EASA AD 2015-0021 [which corresponds to FAA AD 2016-14-09, 
Amendment 39-18590 (81 FR 44989, July 12, 2016) (``AD 2016-14-
09'')], requiring repetitive detailed inspections (DET) of all aft 
engine mount inner retainers and, depending on findings, their 
replacement.
    After EASA AD 2015-0021 was issued, a production quality 
deficiency was identified by Airbus and Goodrich Aerostructures, the 
engine mount retainer manufacturer, on the inner retainer, Part 
Number (P/N) 238-0252-505, installed in the three link assemblies of 
the engine mount fitted on CFM56-5A/5B engines. Airbus issued AOT 
A71N011-15 and Service Bulletin (SB) A320-71-1070, providing a list 
of affected parts and applicable corrective actions.
    Consequently, EASA issued AD 2016-0010 (later revised), 
retaining the requirements of EASA AD 2015-0021, which was 
superseded, and in addition requiring the identification and 
replacement of all non-conforming aft engine mount inner retainers 
[EASA AD 2016-0010 R1 corresponds to FAA AD 2017-04-10, Amendment 
39-18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'')].
    After that [EASA] AD was issued, a new engine mount retainer was 
developed by Goodrich Aerostructures to improve the retainer 
efficiency. For retrofit purposes, Goodrich Aerostructures issued SB 
RA32071-164, and Airbus issued SB A320-71-1071, providing 
instructions to modify and re-identify the engine mount assemblies 
as instructed in the Goodrich Aerostructures SB. Subsequently, it 
was observed that, on aeroplanes equipped with certain engines 
fitted with a Turbine Rear Frame (TRF) with 4 lugs configuration, 
the installation of the new engine mount retainers can lead to 
interference, and Goodrich Aerostructures revised SB RA32071-164, 
providing instructions not to install the new engine retainers on 
affected engines. Airbus SB A320-71-1071 is expected to be revised 
accordingly. For engines fitted with a TRF with 4 lugs, a new 
installation (potentially requiring different engine mount 
retainers) is being developed by Goodrich Aerospace and Airbus.
    Consequently, EASA issued AD 2017-0138, retaining the 
requirements of EASA AD 2016-0010R1, which was superseded, and, 
except for aeroplanes equipped with engines fitted with a TRF with 4 
lugs configuration, requiring modification and identification of aft 
engine mount assemblies as terminating action for the repetitive 
inspections of the retainers. That [EASA] AD also included 
additional instructions applicable to installation of engines fitted 
with a TRF with 4 lugs configuration.
    Since EASA AD 2017-0138 was issued, it was determined that 
installation of new engine mount assemblies must not be allowed for 
some specific engine configurations, and that installation of 
Goodrich Aerostructures SB RA32071-164 alone can be referred to, in 
order to accomplish the terminating action as required by that 
[EASA] AD.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2017-0138, which is superseded, adds 
reference to Goodrich Aerostructures SB RA32071-164 * * *, and 
introduces new requirement for aeroplanes equipped with engines 
fitted with a TRF with 4 lugs configuration.


[[Page 10413]]


    This NPRM would not supersede AD 2017-04-10. Rather, we have 
determined that a stand-alone AD would be more appropriate to address 
the changes in the MCAI. This NPRM would require modifying and re-
identifying the aft engine mount assemblies. Accomplishment of the 
proposed actions would then terminate the repetitive detailed 
inspections required by paragraph (l) of AD 2016-14-09, and serve as a 
method of compliance for the requirements of paragraph (g) of AD 2017-
04-10. 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-2018-0165.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1071, dated November 8, 
2016. Goodrich Aerostructures has issued Service Bulletin RA32071-164, 
Revision 1, dated July 19, 2017. The service information describes 
procedures for modifying and re-identifying the aft engine mount 
retainer assembly. These documents are distinct since they apply to 
different airplane models in different configurations.
    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.

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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 500 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification.  20 work-hours x $85 per              $3,152          $4,852      $2,426,000
                                      hour = $1,700.
----------------------------------------------------------------------------------------------------------------

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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

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-2018-0165; Product Identifier 2017-NM-122-AD.

(a) Comments Due Date

    We must receive comments by April 23, 2018.

(b) Affected ADs

    This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 44989, 
July 12, 2016) (``AD 2016-14-09''); and AD 2017-04-10, Amendment 39-
18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'').

(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) Model A318-111 and -112 airplanes.
    (2) Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Model A320-211, -212, -214, and -216 airplanes.
    (4) Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

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

[[Page 10414]]

(e) Reason

    This AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. We 
are issuing this AD to address non-conforming retainers of the aft 
engine mount. This condition could result in 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, possibly resulting in damage to the airplane.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD: A Group 1 airplane has an aft 
engine mount assembly installed, having a part number (P/N) 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD. A Group 2 airplane does not have any 
aft engine mount assembly installed having a part number identified 
as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), 
and (l) of this AD.
    (2) For the purpose of this AD, a 4-lugs engine is a CFM56-5A1, 
CFM56-5A3, CFM56-5A4, CFM56-5A4/F, CFM56-5A5, or CFM56-5A5/F engine, 
fitted with a turbine rear frame (TRF) having a part number as 
identified in figure 2 to paragraph (g) of this AD.

Figure 1 to Paragraphs (g), (h), (i), (j), (k), and (l) of this AD--Part
                            Re-Identification
------------------------------------------------------------------------
                Old P/N                              New P/N
------------------------------------------------------------------------
238-0230-11............................  238M0230-11
238-0230-15............................  238M0230-15
238-0230-5.............................  238M0230-5
642-2300-3.............................  642-2300-11
------------------------------------------------------------------------


   Figure 2 to Paragraph (g) of This AD--TRF With 4-Lugs Configuration
------------------------------------------------------------------------
                                Part No.
-------------------------------------------------------------------------
                               336-031-615-0
                               336-031-617-0
                               336-031-618-0
                               336-031-621-0
                               336-031-650-0
                               336-031-651-0
                               336-031-652-0
                               336-031-653-0
                               336-031-660-0
                               336-031-661-0
                               336-031-662-0
                               336-031-663-0
                               336-031-670-0
                               336-031-671-0
                               336-031-672-0
                               336-031-673-0
                               336-031-640-0
                               336-031-642-0
------------------------------------------------------------------------

(h) Modification

    For Group 1 airplanes: Within 48 months after the effective date 
of this AD, except for 4-lugs engines, modify the aft engine mount 
assembly, having a part number identified as ``Old P/N'' in figure 1 
to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, and re-
identify it with the corresponding part number identified as ``New 
P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-71-1071, dated November 8, 2016; or 
Goodrich Aerostructures Service Bulletin RA32071-164, Revision 1, 
dated July 19, 2017.

(i) Other Acceptable Method of Compliance

    Replacement on an airplane of each aft engine mount assembly, 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD, with a corresponding aft engine mount 
assembly, identified as ``New P/N'' in figure 1 to paragraphs (g), 
(h), (i), (j), (k), and (l) of this AD, is an acceptable method to 
comply with the requirements of paragraph (h) of this AD for that 
airplane.

(j) Identification of Certain Airplanes That Do Not Have Affected Parts

    An airplane on which Airbus modification 158435 has been 
embodied in production and on which it can be positively determined 
that no aft engine mount assembly, identified as ``Old P/N'' in 
figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, 
is installed, is considered a Group 2 airplane. A review of airplane 
maintenance records is acceptable to make this determination, if it 
can be conclusively determined that no aft engine mount assembly 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD is installed. Group 2 airplanes are not 
affected by the requirements of paragraph (h) of this AD.

(k) Parts Installation Prohibition

    (1) For Group 1 airplanes: Do not install an aft engine mount 
assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), 
(h), (i), (j), (k), and (l) of this AD on any airplane after 
modification of the airplane as required by paragraph (h) of this 
AD, or after any replacement specified in paragraph (i) of this AD.
    (2) For Group 2 airplanes: As of the effective date of this AD, 
do not install an aft engine mount assembly identified as ``Old P/
N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of 
this AD on any airplane.
    (3) For airplanes equipped with a 4-lugs engine (left-hand (LH) 
or right-hand (RH) side): As of the effective date of this AD, do 
not modify any aft engine mount assembly identified as ``Old P/N'' 
in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this 
AD, as required by paragraph (h) of this AD, and do not install on 
an affected engine pylon (LH or RH) any aft engine mount assembly 
identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD.

 (l) 4-Lugs Engine Installation

    (1) From the effective date of this AD, it is allowed to install 
or reinstall a 4-lugs engine on an airplane (LH or RH) provided that 
the airplane is equipped with an aft engine mount assembly 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD on the affected engine pylon (LH or 
RH).
    (2) For airplanes equipped with a 4-lugs engine (LH or RH), and 
on which, prior to the effective date of this AD, an aft engine 
mount assembly identified as ``New P/N'' in figure 1 to paragraphs 
(g), (h), (i), (j), (k), and (l) of this AD has been installed on 
the affected engine pylon (LH or RH), or on which the aft engine 
part assembly has been modified as specified in paragraph (h) of 
this AD: Within 30 days after the effective date of this AD, obtain 
repair instructions using a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA), and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(m) Terminating Action and Method of Compliance

    (1) Modification of an airplane as required by paragraph (h) of 
this AD, or as specified in paragraph (i) of this AD, constitutes 
terminating action for the repetitive detailed inspections required 
by paragraph (l) of AD 2016-14-09 for that airplane.
    (2) Modification of an airplane as required by paragraph (h) of 
this AD, or as specified in paragraph (i) of this AD, is a method of 
compliance with the requirements of paragraph (g) of AD 2017-04-10 
for that airplane.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (p)(2) of this AD. 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.
    (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 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
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

[[Page 10415]]

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.

(o) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0251 dated December 15, 
2017, 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-2018-0165.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) 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 [email protected]; 
internet http://www.airbus.com.
    (4) For Goodrich Aerospace service information identified in 
this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon 
Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: 
[email protected]; internet: http://www.goodrich.com/TechPubs. 
You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.

    Issued in Renton, Washington, on March 5, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-04727 Filed 3-8-18; 8:45 am]
 BILLING CODE 4910-13-P