[Federal Register Volume 83, Number 154 (Thursday, August 9, 2018)]
[Rules and Regulations]
[Pages 39326-39331]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16504]


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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; Amendment 
39-19342; AD 2018-16-02]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS 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 SAS 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 report of a production quality deficiency on 
the inner retainer installed on link assemblies of the aft engine 
mount, which could result in

[[Page 39327]]

failure of the retainer. This AD requires modifying and re-identifying 
the aft engine mount assemblies. We are issuing this AD to address the 
unsafe condition on these products.

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

ADDRESSES: For Airbus SAS service information identified in this final 
rule, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 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 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-2018-
0165.

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 Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is Docket Operations, 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; telephone and fax 206-231-3223.

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 SAS 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 March 9, 2018 (83 FR 10411). The NPRM 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. The NPRM proposed to require 
modifying and re-identifying the aft engine mount assemblies.
    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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
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 SAS 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.

    This AD does not supersede AD 2017-04-10. Rather, we have

[[Page 39328]]

determined that a stand-alone AD is more appropriate to address the 
changes in the MCAI. This AD requires modifying and re-identifying the 
aft engine mount assemblies. Accomplishment of the required actions 
terminates 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.

Comments

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

Support for the NPRM

    Air Line Pilots Association, International (ALPA) supported the 
intent of the NPRM.

Request To Refer to Current Revision of Service Information

    Airbus SAS noted that it issued Service Bulletin A320-71-1071, 
Revision 01, dated October 17, 2017, and requested that this revision 
of the service bulletin be included in the final rule. The original 
issue of Service Bulletin A320-71-1071, dated November 8, 2016, was 
referred to in the proposed AD.
    We agree with the commenter's request. Airbus Service Bulletin 
A320-71-1071, Revision 01, dated October 17, 2017, clarifies certain 
notes and references but makes no substantive changes to Airbus Service 
Bulletin A320-71-1071, dated November 8, 2016, as proposed in the NPRM. 
Furthermore, while Airbus Service Bulletin A320-71-1071, Revision 01, 
dated October 17, 2017, expands the effectivity, the applicability of 
this AD has not been changed. We have revised the preamble of this 
final rule and paragraph (h) of this AD to include Airbus Service 
Bulletin A320-71-1071, Revision 01, dated October 17, 2017. We have 
also added paragraph (n) to this AD to provide credit for actions done 
prior to the effective date of this AD using the original issue of 
Airbus Service Bulletin A320-71-1071, dated November 8, 2016. We 
redesignated subsequent paragraphs accordingly.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A320-71-1071, Revision 01, 
dated October 17, 2017. 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.

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 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 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.


[[Page 39329]]



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):

2018-16-02 Airbus SAS: Amendment 39-19342; Docket No. FAA-2018-0165; 
Product Identifier 2017-NM-122-AD.

(a) Effective Date

    This AD is effective September 13, 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 SAS 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.

(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)(1), (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)(1), (h), 
(i), (j), (k), and (l) of this AD.
[GRAPHIC] [TIFF OMITTED] TR09AU18.000

    (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)(2) of this AD.

[[Page 39330]]

[GRAPHIC] [TIFF OMITTED] TR09AU18.001

(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)(1), (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)(1), (h), (i), (j), (k), 
and (l) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-71-1071, Revision 01, 
dated October 17, 2017; 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)(1), (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)(1), (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)(1), (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)(1), (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)(1), 
(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)(1), (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)(1), (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)(1), (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)(1), (h), 
(i), (j), (k), and (l) of this AD on the affected engine pylon (LH 
or RH).

[[Page 39331]]

    (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)(1), (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) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-71-
1071, dated November 8, 2016, and the actions were not performed on 
4-lugs engines.

(o) 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 (q)(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 SAS' 
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 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.

(p) 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3) and (r)(5) of this AD.

(r) 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 A320-71-1071, Revision 01, dated 
October 17, 2017.
    (ii) Goodrich Aerostructures Service Bulletin RA32071-164, 
Revision 1, dated July 19, 2017.
    (3) For Airbus SAS service information identified in this AD, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 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.
    (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 July 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-16504 Filed 8-8-18; 8:45 am]
 BILLING CODE 4910-13-P


