39326 Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Rules and Regulations 

12 CFR part or section where identified and described OMB 

control No. 

Expiration 

date 

1261.12 .................................................................................................................................................................... 2590–0006 02/28/2021 

1261.14 .................................................................................................................................................................... 2590–0006 02/28/2021 

1263.2 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.4 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.5 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.6 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.7 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.8 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.9 ...................................................................................................................................................................... 2590–0003 03/31/2020 

1263.11 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.12 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.13 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.14 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.15 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.16 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.17 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.18 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.19 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.24 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.26 .................................................................................................................................................................... 2590–0003 03/31/2020 

1263.31 .................................................................................................................................................................... 2590–0003 03/31/2020 

1264.4 ...................................................................................................................................................................... 2590–0001 12/31/2018 

1264.5 ...................................................................................................................................................................... 2590–0001 12/31/2018 

1264.6 ...................................................................................................................................................................... 2590–0001 12/31/2018 

1266.17 .................................................................................................................................................................... 2590–0001 12/31/2018 

1268.7 ...................................................................................................................................................................... 2590–0008 02/29/2016 

1277.22 .................................................................................................................................................................... 2590–0002 04/30/2020 

1277.28 .................................................................................................................................................................... 2590–0002 04/30/2020 

1290.2 ...................................................................................................................................................................... 2590–0005 03/31/2020 

1290.3 ...................................................................................................................................................................... 2590–0005 03/31/2020 

1290.4 ...................................................................................................................................................................... 2590–0005 03/31/2020 

1290.5 ...................................................................................................................................................................... 2590–0005 03/31/2020 

1291.5 ...................................................................................................................................................................... 2590–0007 03/31/2020 

1291.6 ...................................................................................................................................................................... 2590–0007 03/31/2020 

1291.7 ...................................................................................................................................................................... 2590–0007 03/31/2020 

1291.8 ...................................................................................................................................................................... 2590–0007 03/31/2020 

1291.9 ...................................................................................................................................................................... 2590–0007 03/31/2020 

PART 1206—ASSESSMENTS 

■ 6. The authority citation for part 1206 

continues to read as follows: 

Authority: 12 U.S.C. 4516. 

§ 1206.3 [Amended] 

■ 7. Amend § 1206.3(a)(3) by removing 

the reference ‘‘12 U.S.C. 3645’’ and 

adding in its place the reference ‘‘12 

U.S.C. 4635’’. 

SUBCHAPTER B—ENTITY REGULATIONS 

PART 1223—MINORITY AND WOMEN 

INCLUSION 

■ 8. The authority citation for part 1223 

continues to read as follows: 

Authority: 12 U.S.C. 4520 and 4526; 12 

U.S.C. 1833e; E.O. 11478. 

§ 1223.3 [Amended] 

■ 9. Amend § 1223.3(b) by removing the 

reference ‘‘§ 1223.21(b)(6)’’ and adding 

in its place the reference 

‘‘§ 1223.21(b)(9)’’. 

§ 1223.21 [Amended] 

■ 10. Amend § 1223.21(b)(9) by 

removing the reference ‘‘§ 1207.3(b)’’ 

and adding in its place the reference 

‘‘§ 1223.3(b)’’. 

§ 1223.23 [Amended] 

■ 11. Amend § 1223.23(b)(20) by 

removing the reference ‘‘§§ 1207.20 and 

1207.21’’ and adding in its place the 

reference ‘‘§§ 1223.20 and 1223.21’’. 

SUBCHAPTER D—FEDERAL HOME LOAN 

BANKS 

PART 1261—FEDERAL HOME LOAN 

BANK DIRECTORS 

■ 12. The authority citation for part 

1261 continues to read as follows: 

Authority: 12 U.S.C. 1426, 1427, 1432, 

4511 and 4526. 

§ 1261.9 [Amended] 

■ 13. Amend § 1261.9(c) introductory 

text by removing the reference 

‘‘§ 1207.21(b)(5)’’ and adding in its place 

the reference ‘‘§ 1223.21(b)(7)’’. 

Dated: August 2, 2018. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2018–16972 Filed 8–8–18; 8:45 am] 

BILLING CODE 8070–01–P 

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. 

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 


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Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Rules and Regulations 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 

account.airworth-eas@airbus.com; 

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: jan.lewis@goodrich.com; 

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 reidentifying 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 nonconforming 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 


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39328 Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Rules and Regulations 

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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification and re-identification ..... 20 work-hours × $85 per hour = $1,700 ....................... $3,152 $4,852 $2,426,000 

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. 


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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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 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. 

(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. 


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(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 reidentify 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). 


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(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: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(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 account.airworth-eas@

airbus.com; 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: jan.lewis@

goodrich.com; 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/ibrlocations.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 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 301 

[TD 9839] 

RIN 1545–BN41 

Partnership Representative Under the 

Centralized Partnership Audit Regime 

and Election To Apply the Centralized 

Partnership Audit Regime 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Final regulation and removal of 

temporary regulations. 

SUMMARY: This document contains final 

regulations regarding the designation 

and authority of the partnership 

representative under the centralized 

partnership audit regime, which was 

enacted into law on November 2, 2015 

by section 1101 of the Bipartisan Budget 

Act of 2015 (BBA). These final 

regulations affect partnerships for 

taxable years beginning after December 

31, 2017. This document also contains 

final regulations and removes temporary 

regulations regarding the election to 

apply the centralized partnership audit 

regime to partnership taxable years 

beginning after November 2, 2015 and 

before January 1, 2018 under section 

1101(g)(4) of the BBA. These final 

regulations affect partnerships for 

taxable years beginning after November 

2, 2015 and before January 1, 2018. 

DATES: 

Effective date: These regulations are 

effective on August 9, 2018. 

Applicability Date: For dates of 

applicability, see §§ 301.6223–1(h), 

301.6223–2(f), and 301.9100–22(e). 

FOR FURTHER INFORMATION CONTACT: 

Concerning the regulations under 

§§ 301.6223–1 and 301.6223–2, Joy E. 

Gerdy Zogby of the Office of Associate 

Chief Counsel (Procedure and 

Administration), (202) 317–4927; 

concerning § 301.9100–22, Jennifer M. 

Black of the Office of Associate Chief 

Counsel (Procedure and 


sradovich on DSK3GMQ082PROD with RULES