[Federal Register Volume 83, Number 111 (Friday, June 8, 2018)]
[Rules and Regulations]
[Pages 26559-26564]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12268]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD; Amendment 
39-19306; AD 2018-12-02]
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 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 AD was prompted by a review of maintenance instructions for a 
blend repair of the snout diameter of the main beam assembly of the 
forward engine mount that would create an excessive gap between the 
bearing mono-ball and the snout. This AD requires modifying the main 
beam assembly of the forward engine mount. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective July 13, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 13, 
2018.

ADDRESSES: For Airbus 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. For Goodrich service information 
identified in this final rule, 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 referenced 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. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-1020.

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-2017-
1020; 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 Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198-6547; 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 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 NPRM published in 
the Federal Register on October 24, 2017 (82 FR 49146) (``the NPRM''). 
The NPRM was prompted by a review of maintenance instructions for a 
blend repair of the snout diameter of the main beam assembly of the 
forward engine mount that would create an excessive gap between the 
bearing mono-ball and the snout. The NPRM proposed to require modifying 
the main beam assembly of the forward engine mount. We are issuing this 
AD to prevent in-flight failure of a forward engine mount, and 
consequent detachment of an engine, which could result in reduced 
controllability of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0132R1, dated November 22, 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:

    A review of maintenance instructions revealed that the Goodrich 
Aerospace CFM56-5B, Forward Engine Mount Component Maintenance 
Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive), 
repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides 
instructions to blend the wear on the forward engine mount assembly, 
Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating 
an excessive gap between the bearing mono-ball and the snout of the 
forward engine mount main beam assembly, P/N 642-2006-501, or P/N 
642-2006-503.
    This condition, if not detected and corrected, could lead to in-
flight failure of a forward engine mount and consequent detachment 
of an engine, possibly resulting in reduced control of the aeroplane 
and injury to persons on the ground.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and

[[Page 26560]]

Goodrich Aerospace issued SB RA32071-159, providing instructions for 
an in-shop inspection(s) for the main beam snout and, depending on 
findings, applicable corrective action(s) and re-identification.
    Consequently, EASA issued AD 2017-0132, requiring replacement of 
the affected forward engine mount main beam assemblies. As the same 
main beam assemblies are certified for CFM56-5A engine installation, 
that [EASA] AD also applied to aeroplanes with that engine.
    Since that [EASA] AD was issued, it was determined that, for 
aeroplanes equipped with an affected forward engine mount main beam 
assembly, installation of an affected assembly can still be allowed 
until replacement, as required by this [EASA] AD.
    For the reason described above, this [EASA] AD is revised 
accordingly.

    Required actions include modifying the main beam assembly of the 
forward engine mount. The modification includes repairing, replacing, 
or reworking the main beam 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-2017-1020.

Comments

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

Support for the NPRM

    The Air Line Pilots Association, International (ALPA) and Jake 
Watson stated their support for the proposed AD. American Airlines 
(AAL) stated that it has no objection to the intent of the NPRM.

Request To Use Revised Vendor Service Information

    AAL stated that the proposed AD should require Goodrich Aerospace 
Service Bulletin RA32071-159, Rev 1, dated July 25, 2017 (``SB RA32071-
159 Rev 1''), which corrects part number references, revises 
illustrations, and clarifies the procedure. Alternatively, AAL asserted 
that the proposed AD should allow the use of RA32071-159 Rev 1, or 
later revisions. AAL stated that Goodrich Aerospace Service Bulletin 
RA32071-159, dated November 20, 2016, is not useable due to multiple 
issues.
    We do not agree to require RA32071-159 Rev 1. Goodrich Aerospace 
Service Bulletin RA32071-159 is referenced as an additional source of 
guidance in Airbus Service Bulletin A320-71-1065, Revision 01, dated 
July 28, 2017; and Airbus Service Bulletin A320-71-1066, dated December 
1, 2016; for inspecting and corrective actions. We acknowledge that 
RA32071-159 Rev 1 contains several improvements. Therefore, we 
recommend operators incorporate the latest approved service 
information. However, in paragraphs (g)(2)(ii) and (h) of this AD, we 
refer to ``Goodrich Aerospace Service Bulletin RA32071-159'' and not to 
any specific revision. Therefore, we have not changed this AD in this 
regard.

Request To Exclude Certain Actions

    AAL stated that Goodrich Aerospace Service Bulletin RA32071-159 
requires operators to ``fully disassemble the engine mount assembly'', 
which is not necessary for the dimensional inspection of the snout. AAL 
noted that, as long as the mount is not installed on the engine, the 
bearing assembly can be removed to expose the snout, clean, and measure 
the snout. AAL added that if an operator is forced to fully disassemble 
the mount, it will drive the mount to an overhaul, which is time 
consuming and costly.
    We infer that the commenter is asking that we exclude full 
disassembly of the engine mount assembly from the inspection specified 
in paragraph (h) of the proposed AD. We do not agree. Neither Airbus 
nor the state of design authority, EASA, has informed the FAA that the 
snout diameter can be conclusively measured without full disassembly of 
the engine mount assembly. AAL did not provide any justification 
supported by approval from EASA; or Airbus's EASA Design Organization 
Approval (DOA) to allow deviation from the required for compliance 
section of the service information. However, under the provisions of 
paragraph (n) of this AD, we will consider requests for approval of an 
alternative method of compliance if sufficient data are submitted to 
substantiate that a deviation would provide an acceptable level of 
safety. We have made no change to this AD in this regard.

Request To Compel Goodrich Aerospace To Use ``Required for Compliance 
(RC)'' Language in Goodrich Aerospace Service Bulletin RA32071-159

    AAL also asked that the FAA compel Goodrich Aerospace to 
incorporate FAA Advisory Circular 20-176A, dated June 16, 2014, into 
Goodrich Aerospace Service Bulletin RA32071-159 for the purpose of ``. 
. . distinguishing which steps in an SB will have a direct effect on 
detecting, preventing, resolving, or eliminating the unsafe condition 
identified in an AD.'' AAL asserted that Goodrich Aerospace has had 7 
years to evaluate and incorporate the best practices for drafting 
service bulletins related to ADs.
    We disagree with the commenter's request. FAA Advisory Circular 20-
176A, dated June 16, 2014, provides best practices for drafting service 
bulletins related to ADs. Although we recommend that the original 
equipment manufacturer (OEM) specify ``RC'' steps in service 
information, the FAA advisory circular is not mandatory, only a 
recommendation as best practices. We have not changed this AD in this 
regard.

Request To Remove Revision Level for Vendor Service Information

    Delta Airlines (Delta) asked that the proposed AD not specify a 
revision level for Goodrich Aerospace Service Bulletin RA32071-159. 
Delta added that, if one must be specified, all revisions published 
prior to the effective date of the AD should be acceptable methods of 
compliance.
    We agree with the commenter's request that the revision level of 
Goodrich Aerospace Service Bulletin RA32071-159 not be specified. As 
previously explained, this AD does not specify a revision level for 
Goodrich Aerospace Service Bulletin RA32071-159. Therefore, no change 
to this AD is necessary in this regard.

Request To Specify Confirmation That a Certain Discrepant Repair Has 
Never Been Installed

    Delta requested that paragraph (g)(1) of the proposed AD be revised 
to specify that maintenance records must confirm that Repair 10 of 
Component Maintenance Manual (CMM) 71-21-08, Revisions 1 through 46, 
has never been performed. Delta stated that, based on the NPRM and 
service information, it is clear that the discrepant repair is Repair 
10 of CMM 71-21-08, Revisions 1 through 46. Delta added that paragraph 
(g)(1) of the proposed AD does not specify that maintenance records 
must show only that forward mount main beams have not been repaired per 
the discrepant Repair 10 of CMM 71-21-08, Revisions 1 through 46, which 
would classify them as affected main beams.
    We disagree with the commenter's request; however, we provide the 
following clarification. The intent of paragraph (g)(1) of this AD is 
that if no maintenance record exists then there is a possibility that 
the main beam has been repaired using Repair 10 of CMM 71-21-08 
Revisions 1 through 46, and, therefore, qualifies as an ``affected main 
beam.'' We have not changed this AD in this regard.

[[Page 26561]]

Request To Apply Exceptions to Parts Without Maintenance Records of 
Repair History

    Delta asked that the exceptions in paragraphs (g)(2)(i) through 
(g)(2)(iii) of the proposed AD also apply to parts for which 
maintenance records are not available to confirm repair history. Delta 
stated that this will account for mounts that are not installed on-wing 
and future spare purchases. Delta added that paragraph (g)(2) of the 
proposed AD does not permit parts with unknown repair history to be 
excluded if the criteria in paragraphs (g)(2)(i) through (g)(2)(iii) of 
the proposed AD are met. Delta noted that paragraph (g)(1) of the 
proposed AD, parts with unknown repair history, are considered 
``affected main beams'' and have the same compliance requirements as 
parts that have been repaired per discrepant Repair 10 of CMM 71-21-08, 
Revisions 1 through 46.
    We do not agree with the commenter's request. Exceptions in 
paragraphs (g)(2)(i) through (g)(2)(iii) of this AD are based on the 
fact that maintenance records exist. Therefore, these exceptions do not 
apply to parts with unknown repair history in paragraph (g)(1) of this 
AD. We have not changed this AD in this regard.

Requests To Use Later Revisions of CMM Repairs

    Delta and Lufthansa Technik (Lufthansa) asked that we allow use of 
later revisions of the CMM repairs in paragraphs (g)(2)(ii) and (h) of 
the proposed AD. Delta noted that paragraph (g)(2)(ii) doesn't specify 
that a repair per the corrected Repair 10 of CMM 71-21-08, Revision 47 
(and later), or Repair 21 of CMM 71-21-06, Revision 59 (and later), 
excludes forward mount main beams from the effectivity. Delta added 
that the dimensional requirements of corrected Repair 10 and Repair 21 
are equivalent to the requirements of Goodrich Aerospace Service 
Bulletin RA32071-159, and ensure that any main beams repaired will meet 
the intent of the proposed AD.
    Delta stated that paragraph (h) of the proposed AD doesn't specify 
that a qualifying inspection can be done as specified in the 
instructions of the later revisions of CMMs 71-21-08 and 71-21-06 that 
introduced the corrected Repair 10 and Repair 21. Delta explained that 
CMM 71-21-08, Revision 48 (and later), and CMM 71-21-06, Revision 60 
(and later), contain the correct snout diameters as specified in Repair 
10 of CMM 71-21-08, Revision 47, and Repair 21 of CMM 71-21-06, 
Revision 59. Delta further noted that EASA AD 2017-0132R1, dated 
November 22, 2017, permits the use of later revisions of the CMMs with 
corrected Repairs 10 and 21.
    We disagree with the commenters' requests. We cannot use the 
phrase, ``or later approved revisions,'' in an AD when referring to the 
service document because doing so violates Office of the Federal 
Register (OFR) regulations for approval of materials ``incorporated by 
reference'' in rules. In general terms, we are required by these OFR 
regulations to either publish the service document contents as part of 
the actual AD language; or submit the service document to the OFR for 
approval as ``referenced'' material, in which case we may only refer to 
such material in the text of an AD. The AD may refer to the service 
document only if the OFR approved it for ``incorporation by 
reference.'' To allow operators to use later revisions of the 
referenced document (issued after publication of the AD), either we 
must revise the AD to reference specific later revisions, or operators 
must request approval to use later revisions as an alternative method 
of compliance (AMOC) with this AD under the provisions of paragraph (n) 
of this AD. We have not changed this AD in this regard.

Request To Define Airplane Group

    Delta asked that paragraph (i) of the proposed AD clarify that 
airplanes on which the main beams have never been replaced are 
considered Group 2 airplanes. Delta stated that paragraph (i) of the 
proposed AD doesn't specify that airplanes on which the main beams have 
never been replaced (and thus never repaired) since aircraft delivery 
should be considered Group 2 airplanes. Delta added that an airplane on 
which the forward mounts have never been replaced since aircraft 
delivery will not have the discrepant Repair 10 of CMM 71-21-08, 
Revisions 1 through 46.
    We do not agree to revise paragraph (i) of this AD; however, we 
have clarified the airplane group as follows. Paragraph (i) of this AD 
specifies Group 2 airplanes are airplanes on which an affected main 
beam has not been installed as of the effective date of this AD. 
Therefore, airplanes with main beams that have never been replaced 
since aircraft delivery might be considered Group 2 airplanes, if the 
original main beam is not an affected main beam as defined in paragraph 
(g) of this AD. However, if for example, an airplane with main beams 
that have never been replaced does not have maintenance records to 
conclusively confirm the part has never been repaired, as specified in 
paragraph (g)(1) of this AD, then it is a Group 1 airplane. We have not 
changed this AD in this regard.

Request To Change ``Modify'' to ``Inspect and Disposition''

    Delta asked that the proposed AD use the language ``inspect and 
disposition'' instead of ``modify'' to describe the action required by 
paragraph (j) of the proposed AD. Additionally, Delta asked that the 
proposed AD specify that replacement of a forward mount assembly 
containing an affected main beam with a forward mount assembly that 
contains an AD-compliant main beam is an acceptable means of 
compliance. Delta stated that paragraph (j) of the proposed AD uses the 
term ``modify'' to describe compliance with the requirements of the 
inspection and repair of the mounts. Delta added that, based on the 
instructions in the service information, the intent of the work 
instructions is to inspect affected main beams and disposition based on 
inspection findings; the dispositions range from scrapping the main 
beam to blending, based on measured snout diameter. Delta noted that 
the replacement of a forward mount assembly that contains an affected 
main beam with a forward mount assembly with an AD-compliant main beam 
meets the intent of the proposed AD to remove affected main beams from 
service.
    We partially agree. We do not agree to replace ``modify'' with 
``inspect and disposition,'' because corrective action cannot be 
defined by the term ``disposition,'' which is open to interpretation. 
Operators must follow the instructions in the Airbus service 
information referenced in paragraph (j) of this AD for the applicable 
method of compliance. However, we acknowledge that, while the 
Accomplishment Instructions of Airbus Service Bulletin A320-71-1066, 
dated December 1, 2016, specify to do a ``Modification of the FWD 
Engine Mount Assembly on Engine 1 and Engine 2,'' the Accomplishment 
Instructions of Airbus Service Bulletin A320-71-1065, Revision 01, 
dated July 28, 2017, specify to do inspections and applicable 
corrective actions. Therefore, we have changed paragraph (j) of this AD 
to replace ``modify'' with ``modify, including doing all applicable 
inspections and corrective actions.''

Request To Include Goodrich Aerospace Service Bulletin for the Required 
Modification

    Lufthansa requested that we include Goodrich Aerospace Service 
Bulletin

[[Page 26562]]

RA32071-159 in paragraph (j) of the proposed AD to ``make it more 
clear.''
    We do not agree. The commenter provided no explanation of what is 
unclear in paragraph (j) or how adding the Goodrich Aerospace service 
bulletin will clarify the requirements of paragraph (j). Therefore, we 
have not changed this AD in this regard.

Requests To Provide Credit for Previous Actions Done Using Other 
Service Information

    Delta and Lufthansa asked that the proposed AD include credit for 
doing previous actions by accomplishing Goodrich Aerospace Service 
Bulletin RA32071-159; Repair 10 of CMM 71-21-08, Revision 47 (and 
later); or Repair 21 of CMM 71-21-06, Revision 59 (and later). Delta 
stated that paragraph (l) of the proposed AD includes credit for 
previous actions only for compliance with Airbus Service Bulletin A320-
71-1065, Revision 01, dated July 28, 2017. Delta asserted that the 
intent of the proposed AD is met by the accomplishment of Goodrich 
Aerospace Service Bulletin RA32071-159; Repair 10 of CMM 71-21-08, 
Revision 47 (and later); or Repair 21 of CMM 71-21-06, Revision 59 (and 
later); due to the correction of the inspection and repair 
requirements.
    We do not agree with the commenter's request. Goodrich Aerospace 
Service Bulletin RA32071-159 is referenced in the airplane level Airbus 
service information as a secondary document; therefore, it is not an 
alternate for the instructions in the airplane level service 
information. All of the steps in paragraph 3.C. of Airbus Service 
Bulletin A320-71-1065, Revision 01, dated July 28, 2017, are required 
for compliance and must be done to comply with this AD. If not done 
before the effective date of this AD, paragraph (f) of this AD states 
that you must comply with the actions in the AD, ``unless already 
done.''
    Regarding future revisions of CMM repairs, we may not refer to any 
document that does not yet exist. To allow operators to use later 
revisions of a required document (issued after publication of the AD), 
either we must revise the AD to reference specific later revisions, or 
operators must request approval to use later revisions as an 
alternative method of compliance with the requirements of an AD under 
the provisions of the AMOC paragraph of the AD. However, as explained 
previously, the identified CMM repairs are not required for 
accomplishment of any action in this AD; therefore, no change to this 
AD is necessary in this regard.

Request To Change Parts Installation Prohibition

    Delta asked that paragraph (m) of the proposed AD, ``Parts 
Installation Prohibition,'' be changed to permit the same allowance to 
install an affected main beam onto an aircraft equipped with an 
affected forward engine mount assembly within the compliance windows 
defined in paragraph (j) of the proposed AD. Delta stated that 
paragraph (m) of the proposed AD prohibits the installation of an 
affected main beam on any airplane after the effective date of the AD. 
Delta further points out that the parallel EASA AD 2017-0132R1, dated 
November 22, 2017, permits the installation of an affected main beam 
onto an aircraft equipped with an affected forward engine mount 
assembly within the compliance times defined in paragraph (j) of the 
proposed AD.
    We agree with the commenter's request. After the NPRM was issued, 
EASA issued AD 2017-0132R1, dated November 22, 2017, which revised its 
parts installation requirement. We have revised paragraph (m) of this 
AD to match the EASA AD. In addition, we have revised this AD to refer 
to EASA AD 2017-0132R1, dated November 22, 2017.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously, with 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1065, Revision 01, dated 
July 28, 2017. This service information describes procedures for 
modifying the main beam assembly of the forward engine mount. The 
modification includes, among other things, repair or replacement of the 
main beam assembly.
    Airbus has also issued Service Bulletin A320-71-1066, dated 
December 1, 2016. This service information describes procedures for 
modifying the main beam assembly of the forward engine mount. The 
modification includes, among other things, rework of the main beam 
assembly.
    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 500 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Modification..................  Up to 76 work-hours             $778  Up to $7,238........  Up to $3,619,000.
                                 x $85 per hour =
                                 $6,460.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 26563]]

    This 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 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 adding the following new airworthiness 
directive (AD):

2018-12-02 Airbus: Amendment 39-19306; Docket No. FAA-2017-1020; 
Product Identifier 2017-NM-114-AD.

(a) Effective Date

    This AD is effective July 13, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to 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; certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by a review of maintenance instructions for 
a blend repair of the diameter of the snout of the main beam 
assembly of the forward engine mount that would create an excessive 
gap between the bearing mono-ball and the snout. We are issuing this 
AD to prevent in-flight failure of a forward engine mount, and 
consequent detachment of an engine, which could result in reduced 
controllability of the airplane.

(f) Compliance

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

(g) Definition of Affected Parts

    For the purposes of this AD: An ``affected main beam'' is any 
main beam assembly of the forward engine mount, part number (P/N) 
642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or 
(g)(2) of this AD.
    (1) Any part for which no maintenance records are available to 
confirm the part has never been repaired.
    (2) Any part that was repaired as specified in Repair 10, of 
Goodrich Aerospace Component Maintenance Manual (CMM) 71-21-08, 
Revisions 1 through 46, except for parts identified in paragraphs 
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
    (i) Any part on which a qualifying inspection identified in 
paragraph (h) of this AD has been done and there were no findings 
(the inspection was passed).
    (ii) Any part on which a qualifying inspection identified in 
paragraph (h) of this AD has been done and that part has been 
repaired as specified in Goodrich Aerospace Service Bulletin 
RA32071-159.
    (iii) Any part that has been repaired in accordance with other 
instructions 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).

(h) Definition of Qualifying Inspection

    For the purposes of this AD: ``A qualifying inspection'' is an 
inspection done as specified in Goodrich Aerospace Service Bulletin 
RA32071-159; or for CFM56-5B engines, an inspection done as 
specified in Repair 10 of Goodrich Aerospace CMM 71-21-08, Revision 
47; or for CFM56-5A engines, an inspection done as specified in 
Repair 21 of Goodrich Aerospace CMM 71-21-06, Revision 59.

(i) Definition of Airplane Groups

    For the purposes of this AD: ``Group 1 airplanes'' are airplanes 
on which an affected main beam has been installed as of the 
effective date of this AD. ``Group 2 airplanes'' are airplanes on 
which an affected main beam has not been installed as of the 
effective date of this AD; this includes airplanes with an original 
certificate of airworthiness or original export certificate of 
airworthiness that was issued after the effective date of this AD.

(j) Modification of Affected Main Beam Assemblies

    For Group 1 airplanes as identified in paragraph (i) of this AD: 
At the earliest of the compliance times specified in paragraphs 
(j)(1), (j)(2), and (j)(3) of this AD, modify, including doing all 
applicable inspections and corrective actions, for each affected 
main beam identified in paragraph (g) of this AD, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017; or Airbus Service Bulletin 
A320-71-1066, dated December 1, 2016; as applicable; except as 
required by paragraph (k) of this AD.
    (1) Within 48 months after the effective date of this AD.
    (2) Within 10,000 flight cycles after the effective date of this 
AD.
    (3) Within 15,000 flight hours after the effective date of this 
AD.

(k) Exception to Service Information

    Where Airbus Service Bulletin A320-71-1065, Revision 01, dated 
July 28, 2017, specifies to contact a manufacturer for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (n)(2) of this 
AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (j) of this AD involving Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-71-1065, dated December 1, 2016.

(m) Parts Installation Prohibition

    Do not install on any airplane an affected main beam or a 
forward engine mount assembly equipped with an affected main beam, 
as specified in paragraph (m)(1) or (m)(2) of this AD, as 
applicable.
    (1) For Group 1 airplanes: After modification of the airplane as 
required by paragraph (j) of this AD.
    (2) For Group 2 airplanes: As of the effective date of this AD.

(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

[[Page 26564]]

directly to the manager of the International Section, send it to the 
attention of the person identified in paragraph (o)(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): Except as required by 
paragraph (k) of this AD: 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0132R1, dated November 22, 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-2017-1020.
    (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 98198-6547; 
telephone 425-227-1405; fax 425-227-1149.
    (3) Airbus service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(4) and (p)(5) of this AD.
    (4) Goodrich service information identified in this AD that is 
not incorporated by reference is available at Goodrich Corporation, 
Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 
619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs.

(p) 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 A320-71-1065, Revision 01, dated 
July 28, 2017.
    (ii) Airbus Service Bulletin A320-71-1066, dated December 1, 
2016.
    (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 service information identified in this final 
rule, 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.
    (5) 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.
    (6) 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 Des Moines, Washington, on May 29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-12268 Filed 6-7-18; 8:45 am]
 BILLING CODE 4910-13-P