44516 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Proposed Rules 

(g) Definitions for This AD 

(1) An affected part is a RAT hydraulic 

pump having part number (P/N) 5916430 and 

a serial number identified in UTC Aerospace 

Systems Service Bulletin ERPS06M–29–22, 

dated March 17, 2017, or Revision 1, dated 

June 27, 2017. 

(2) A serviceable part is a RAT hydraulic 

pump identified as acceptable in Airbus 

Service Bulletin A330–29–3130 or A340–29– 

4098, both dated May 3, 2017, as applicable. 

(3) Group 1 airplanes are airplanes on 

which an affected part is installed. 

(4) Group 2 airplanes are airplanes on 

which no affected part is installed. A Model 

A330 airplane on which Airbus SAS 

Modification 206604 has been embodied in 

production is a Group 2 airplane, provided 

that the airplane remains in that 

configuration. 

(h) Replacement and Re-identification for 

Group 1 Airplanes 

(1) Within 18 months after the effective 

date of this AD; replace any affected RAT 

hydraulic pump with a serviceable part, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3130 or A340–29–4098, both dated May 

3, 2017, as applicable. 

(2) Concurrently with the replacement 

required by paragraph (h)(1) of this AD, reidentify the part number of the serviceable 

RAT module, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–29–3130 or A340–29– 

4098, both dated May 3, 2017, as applicable. 

Note 1 to paragraph (h)(2) of this AD: 

Airbus Service Bulletins A330–29–3130 and 

A340–29–4098, both dated May 3, 2017, 

provide guidance for re-identification of the 

part numbers of the RAT hydraulic pumps 

that are not affected, and the part numbers 

of the RAT modules that are not equipped 

with an affected hydraulic pump. 

(i) Compliance With AD 2016–14–01 

After re-identification of a RAT module on 

an airplane, as required by paragraph (h)(2) 

of this AD, the airplane remains compliant 

with the RAT module re-identification 

requirements of AD 2016–14–01 for that 

airplane. 

(j) Parts Installation Prohibition 

(1) For Group 1 airplanes: After 

replacement of any affected RAT hydraulic 

pump as required by paragraph (h)(1) of this 

AD, do not install any affected RAT 

hydraulic pump. 

(2) For Group 2 airplanes: As of the 

effective date of this AD, do not install any 

affected RAT hydraulic pump. 

(k) 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 Branch, send it 

to the attention of the person identified in 

paragraph (l)(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 The 

European Aviation Safety Agency (EASA); or 

Airbus SAS’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0062, dated March 20, 2018, 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–2018–0764. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax: 206–231–3229. 

(3) For 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. 

You may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on 

August 16, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18811 Filed 8–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0762; Product 

Identifier 2018–NM–033–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2016–07– 

23, which applies to all Airbus SAS 

Model A318, A319, A320, and A321 

series airplanes. AD 2016–07–23 

requires, for certain airplanes, repetitive 

replacements of the fixed fairing upper 

and lower attachment studs of both the 

left-hand (LH) and right-hand (RH) main 

landing gear (MLG); and repetitive 

inspections for corrosion, wear, fatigue 

cracking, and loose studs of each 

forward stud assembly of the fixed 

fairing door upper and lower forward 

attachments of both the LH and RH 

MLG; and replacement if necessary. AD 

2016–07–23 also provides an optional 

terminating modification for the 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. Since we issued AD 2016–07–23, 

we have determined that for some 

airplane configurations, associated fixed 

fairing assembly part numbers 

susceptible to fatigue cracking were not 

listed in certain service information 

required by AD 2016–07–23. In 

addition, we have determined that 

additional work is necessary to reidentify the fixed fairing assembly part 

number on certain airplanes. This 

proposed AD would retain the 

requirements of AD 2016–07–23 and, for 

certain airplanes, require reidentification of the LH and RH fixed 

fairing assemblies’ part numbers. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 15, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint 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. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 


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Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Proposed Rules 44517 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0762; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0762; Product Identifier 2018– 

NM–033–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued AD 2016–07–23, 

Amendment 39–18468 (81 FR 26115, 

May 2, 2016) (‘‘AD 2016–07–23’’), for all 

Airbus SAS Model A318, A319, A320, 

and A321 series airplanes. AD 2016–07– 

23 requires, for certain airplanes, 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs of both the LH and RH MLG; and 

repetitive inspections for corrosion, 

wear, fatigue cracking, and loose studs 

of each forward stud assembly of the 

fixed fairing door upper and lower 

forward attachment of both the LH and 

RH MLG; and replacement if necessary. 

AD 2016–07–23 also provides an 

optional terminating modification for 

the repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. AD 2016–07–23 resulted from 

reports of in-flight loss of fixed and 

hinged MLG fairings, and reports of 

post-modification MLG fixed fairing 

assemblies that have wear and 

corrosion. We issued AD 2016–07–23 to 

address in-flight detachment of an MLG 

fixed fairing and consequent damage to 

the airplane. 

Actions Since AD 2016–07–23 Was 

Issued 

Since we issued AD 2016–07–23, we 

have determined that for some airplane 

configurations, associated fixed fairing 

assembly part numbers susceptible to 

fatigue cracking were not listed in 

certain service information required by 

AD 2016–07–23. In addition, we have 

determined that additional work is 

necessary to re-identify the fixed fairing 

assembly part number after completion 

of the optional terminating 

modification. This proposed AD would 

retain the requirements of AD 2016–07– 

23 and require re-identification of the 

part number of the LH and RH fixed 

fairing assemblies after completion of 

the optional terminating modification. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0023, 

dated January 26, 2018; corrected 

February 5, 2018 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A318 and 

A319 series airplanes; all Airbus SAS 

Model A320–211, A320–212, A320–214, 

A320–216, A320–231, A320–232, and 

A320–233 airplanes; and all Airbus SAS 

Model A321–111, A321–112, A321–131, 

A321–211, A321–212, A321–213, A321– 

231 and A321–232 airplanes. The MCAI 

states: 

Several occurrences were reported of inflight loss of main landing gear (MLG) fixed 

and hinged fairings. The majority of reported 

events occurred following scheduled 

maintenance activities. One result of the 

investigation was that a discrepancy between 

the drawing and the maintenance manuals 

was discovered. The maintenance documents 

were corrected to prevent mis-rigging of the 

MLG fixed and hinged fairings, which could 

induce fatigue cracking. 

Prompted by these findings, Airbus issued 

Service Bulletin (SB) A320–52–1083, 

providing instructions for a one-time 

inspection of the MLG fixed fairing 

composite insert and the surrounding area, 

replacement of the adjustment studs at the 

lower forward position and adjustment to the 

new clearance tolerances. That SB was 

replaced by Airbus SB A320–52–1100 

(modification (mod) 27716) introducing a redesigned location stud, rod end and location 

plate at the forward upper and lower leg 

fixed-fairing positions. Subsequently, reports 

were received of post-mod 27716/post-SB 

A320–52–1100 MLG fixed fairing assemblies 

with corrosion, which could also induce 

cracking. 

This condition, if not detected and 

corrected, could lead to further cases of inflight detachment of a MLG fixed fairing, 

possibly resulting in injury to persons on the 

ground and/or damage to the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2014–0096 to require 

repetitive detailed inspections (DET) of the 

MLG fixed fairings, and, depending on 

findings, accomplishment of applicable 

corrective actions. That [EASA] AD also 

prohibited installation of certain MLG fixed 

fairing rod end assemblies and studs as 

replacement parts on aeroplanes 

incorporating Airbus mod 27716 in 

production, or modified in accordance with 

Airbus SB A320–52–1100 (any revision) in 

service. 

Since EASA AD 2014–0096 was issued, 

Airbus developed an alternative inspection 

programme to meet the [EASA] AD 

requirements. In addition, a terminating 

action (mod 155648) was developed, which 

was made available for in-service aeroplanes 

through Airbus SB A320–52–1165. 

Consequently, EASA issued AD 2015–0001 

(later revised), retaining the requirements of 

EASA AD 2014–0096, which was 

superseded, and adding an optional 

terminating action for the repetitive 

inspections. For post-mod aeroplanes, i.e. 

incorporating Airbus mod 155648 in 

production, or modified by Airbus SB A320– 

52–1165 in service, the only remaining 

requirement was to ensure that pre-mod 

components are no longer installed. 

Since EASA AD 2015–0001R1 [which 

corresponds to FAA AD 2016–07–23] was 

issued, Airbus revised SB A320–52–1165 to 

include additional work, to re-identify the 

fairing assembly part number (P/N). During 

the preparation of this additional work, it 

was noted that several configurations and 

associated P/N were not listed in the original 

SB, which may have an impact on aeroplanes 

on which SB A320–52–1165 original issue or 

Revision (rev.) 01 was already accomplished. 

It has also been noticed that the instructions 

for reidentification of two P/N were not 

correct in revision 02 of this SB. 

For the reasons described above, this 

[EASA] AD retains the requirement of EASA 

AD 2015–0001R1, which is superseded, but 

requires using the SB at rev. 03. 

This [EASA] AD also requires 

accomplishment of additional work [reidentification of the part number for the LH 

and RH fixed fairing assemblies] for those 

aeroplanes on which parts were replaced in 

accordance with the instructions of Airbus 

SB A320–52–1165 at original issue, rev. 01 or 

rev. 02 and correct (re)identification as 

applicable. 

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– 

0762. 


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Related Service Information Under 1 

CFR Part 51 

Airbus SAS has issued the following 

service information. 

• Airbus Service Bulletin A320–52– 

1100, Revision 01, dated March 12, 

1999. This service information describes 

procedures for modification of the 

airplane to post-Airbus Modification 

27716 configuration (by replacing the 

location stud, rod end, and location 

plate at the forward upper and lower leg 

fixed-fairing positions of the MLG door 

assemblies). The modification includes 

a resonance frequency inspection for 

debonding of the composite insert and 

delamination of the honeycomb area 

around the insert, and applicable 

corrective actions. Corrective actions 

include repairing the insert. The actions 

in this service information are an 

optional terminating modification. 

• Airbus Service Bulletin A320–52– 

1163, Revision 01, including Appendix 

01, dated June 22, 2015. This service 

information describes procedures for 

inspection of the fixed fairing door 

upper and lower forward attachments of 

the LH and RH MLG, and replacement 

of the fixed fairing upper and lower 

attachment studs of the LH and RH 

MLG. 

• Airbus Service Bulletin A320–52– 

1165, Revision 03, excluding Appendix 

01 and including Appendix 02, dated 

November 9, 2017. The service 

information describes procedures for 

replacing the fixed fairing attachment 

stud assemblies of the MLG door 

assembly with new assemblies, and reidentifying the part number of the LH 

and RH MLG fixed fairing assemblies. 

The actions in this service information 

are an optional terminating 

modification. 

The service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Proposed Requirements of This NPRM 

This proposed AD would retain all of 

the requirements of AD 2016–07–23. 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 901 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

18 work-hours × $85 per hour = $1,530 ..................................................................................... $4,110 $5,640 $5,081,640 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per product 

Up to 18 work-hours × $85 per hour = $1,530 ....................................... Up to $4,110 .................................. Up to $5,640 

We estimate the following costs to do 

any necessary replacements or reidentifications that would be required 

based on the results of the inspection. 

We have no way of determining the 

number of aircraft that might need these 

replacements or re-identifications: 

ON-CONDITION COSTS

Labor cost Parts cost Cost per product 

Up to 20 work-hours × $85 per hour = $1,700 ....................................... Up to $4,110 .................................. Up to $5,810 

According to the manufacturer, some 

or all of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 


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Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

3. Will not affect intrastate aviation in 

Alaska, and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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 

removing Airworthiness Directive (AD) 

2016–07–23, Amendment 39–18468 (81 

FR 26115, May 2, 2016), and adding the 

following new AD: 

Airbus SAS: Docket No. FAA–2018–0762; 

Product Identifier 2018–NM–033–AD. 

(a) Comments Due Date 

We must receive comments by October 15, 

2018. 

(b) Affected ADs 

This AD replaces AD 2016–07–23, 

Amendment 39–18468 (81 FR 26115, May 2, 

2016) (‘‘AD 2016–07–23’’). 

(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, A318–112, A318– 

121, and A318–122 airplanes. 

(2) Model A319–111, A319–112, A319– 

113, A319–114, A319–115, A319–131, A319– 

132, and A319–133 airplanes. 

(3) Model A320–211, A320–212, A320– 

214, A320–216, A320–231, A320–232, and 

A320–233 airplanes. 

(4) Model A321–111, A321–112, A321– 

131, A321–211, A321–212, A321–213, A321– 

231 and A321–232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by reports of inflight loss of fixed and hinged main landing 

gear (MLG) fairings, and reports of postmodification MLG fixed fairing assemblies 

that have wear and corrosion. This AD was 

also prompted by a determination that for 

some airplane configurations, associated 

fixed fairing assembly part numbers 

susceptible to fatigue cracking were not listed 

in certain service information required by AD 

2016–07–23. In addition, we have 

determined that additional work is necessary 

to re-identify the fixed fairing assembly part 

number on certain airplanes. We are issuing 

this AD to prevent in-flight detachment of an 

MLG fixed fairing and consequent damage to 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Replacements, With 

No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2016–07–23, with no 

changes. For airplanes in pre-Airbus 

Modification 27716 and pre-Airbus Service 

Bulletin A320–52–1100 configuration, with 

any of the components installed that are 

identified in paragraphs (g)(1) through (g)(5) 

of this AD: At the applicable compliance 

time specified in paragraph (h) of this AD, 

replace fixed fairing upper and lower 

attachment studs of both left-hand (LH) and 

right-hand (RH) MLG, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015. 

Repeat the replacements thereafter at 

intervals not to exceed 6,500 flight cycles. 

(1) Plate—support having part number (P/ 

N) D5284024820000. 

(2) Plate—support having P/N 

D5284024820200. 

(3) Stud—adjustment having P/N 

D5284024420000. 

(4) Rod end assembly (lower) having P/N 

D5284000500000. 

(5) Rod end assembly (upper) having P/N 

D5284000600000. 

(h) Retained Compliance Times for the 

Requirements of Paragraph (g) of This AD, 

With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2016–07–23, with no 

changes. For airplanes identified in 

paragraph (g) of this AD, except as provided 

by paragraph (o) of this AD: Do the initial 

replacement required by paragraph (g) of this 

AD at the latest of the times specified in 

paragraphs (h)(1) through (h)(4) of this AD. 

(1) Before the accumulation of 6,500 total 

flight cycles since the airplane’s first flight. 

(2) Within 6,500 flight cycles since the last 

installation of a pre-Airbus Modification 

27716 stud on the airplane. 

(3) Within 1,500 flight cycles after June 6, 

2016 (the effective date of AD 2016–07–23). 

(4) Within 8 months after June 6, 2016 (the 

effective date of AD 2016–07–23). 

(i) Retained Repetitive Inspections, With No 

Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2016–07–23, with no 

changes. For airplanes in post-Airbus 

Modification 27716 or post-Airbus Service 

Bulletin A320–52–1100 configuration, with 

any of the components installed that are 

identified in paragraphs (i)(1), (i)(2), and 

(i)(3) of this AD: At the applicable 

compliance time specified in paragraph (j) of 

this AD, do a detailed inspection of the LH 

and RH MLG forward stud assemblies of the 

fixed fairing door upper and lower forward 

attachments of both LH and RH MLG for 

indications of corrosion, wear, fatigue 

cracking, and loose studs, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015. 

Repeat the detailed inspection thereafter at 

intervals not to exceed 12 months. 

Replacement of both LH and RH MLG 

forward stud assemblies on an airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015, extends the interval 

for the next detailed inspection to 72 months; 

and the inspection must be repeated 

thereafter at intervals not to exceed 12 

months. 

(1) Stud—adjustment having P/N 

D5285600720000. 

(2) Rod end assembly (lower) having P/N 

D5285600400000. 

(3) Rod end assembly (upper) having P/N 

D5285600500000. 

(j) Retained Compliance Times for the 

Requirements of Paragraph (i) of This AD, 

With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2016–07–23, with no 

changes. For airplanes identified in 

paragraph (i) of this AD, except as provided 

by paragraph (o) of this AD: Do the initial 

inspection required by paragraph (i) of this 

AD at the latest of the times specified in 

paragraphs (j)(1) through (j)(4) of this AD. 

(1) Before the accumulation of 72 months 

since the airplane’s first flight. 

(2) Within 72 months since the last 

installation of a post-Airbus Modification 

27716 assembly or since accomplishment of 

the actions specified in Airbus Service 

Bulletin A320–52–1100. 

(3) Within 1,500 flight cycles after June 6, 

2016 (the effective date of AD 2016–07–23). 

(4) Within 8 months after June 6, 2016 (the 

effective date of AD 2016–07–23). 


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(k) Retained Corrective Action, With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (k) of AD 2016–07–23, with 

revised service information. If any 

discrepancy (including any indication of 

corrosion, wear, fatigue cracking, or loose 

studs) of any MLG forward stud assembly is 

found during any inspection required by 

paragraph (i) of this AD, except as specified 

in paragraph (l) of this AD: Before further 

flight, replace the discrepant upper and 

lower fixed fairing forward stud assemblies 

of the LH and RH MLG, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015; 

or Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015; or Airbus Service Bulletin 

A320–52–1165, Revision 03, excluding 

Appendix 01 and including Appendix 02, 

dated November 9, 2017. As of the effective 

date of this AD only Airbus Service Bulletin 

A320–52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015; or Airbus 

Service Bulletin A320–52–1165, Revision 03, 

excluding Appendix 01 and including 

Appendix 02, dated November 9, 2017, may 

be used. 

(l) Retained Corrective Action or Repetitive 

Inspections for Certain Corrosion Findings, 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (l) of AD 2016–07–23, with revised 

service information. If any corrosion is found 

during any inspection required by paragraph 

(i) of this AD on any MLG fixed fairing 

forward stud assembly (upper, lower, LH or 

RH), but the corroded stud is not loose: Do 

the action specified in paragraph (l)(1) or 

(l)(2) of this AD. 

(1) Before further flight, replace the 

affected assembly, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015; 

or Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015; or Airbus Service Bulletin 

A320–52–1165, Revision 03, excluding 

Appendix 01 and including Appendix 02, 

dated November 9, 2017. As of the effective 

date of this AD only Airbus Service Bulletin 

A320–52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015; or Airbus 

Service Bulletin A320–52–1165, Revision 03, 

excluding Appendix 01 and including 

Appendix 02, dated November 9, 2017, may 

be used. 

(2) Within 4 months after finding 

corrosion, and thereafter at intervals not to 

exceed 4 months, do a detailed inspection for 

indications of corrosion, wear, fatigue 

cracking, and loose studs of the forward stud 

assembly of the affected (LH or RH) MLG, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1163, Revision 01, including Appendix 

01, dated June 22, 2015. 

(m) Retained Corrective Action for 

Inspections Specified in Paragraph (l)(2) of 

This AD, With Revised Service Information 

This paragraph restates the requirements of 

paragraph (m) of AD 2016–07–23, with 

revised service information. If any indication 

of wear, fatigue cracking, or loose studs of 

any forward stud assembly is found during 

any inspection required by paragraph (l)(2) of 

this AD: Before further flight, replace the 

affected (LH or RH) MLG fixed fairing 

forward stud assembly, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1163, Revision 01, 

including Appendix 01, dated June 22, 2015; 

or Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015; or Airbus Service Bulletin 

A320–52–1165, Revision 03, excluding 

Appendix 01 and including Appendix 02, 

dated November 9, 2017. As of the effective 

date of this AD only Airbus Service Bulletin 

A320–52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015; or Airbus 

Service Bulletin A320–52–1165, Revision 03, 

excluding Appendix 01 and including 

Appendix 02, dated November 9, 2017, may 

be used. 

(n) Retained Terminating Action, With 

Revised Service Information 

This paragraph restates the requirements of 

paragraph (n) of AD 2016–07–23, with 

revised service information. 

(1) Replacement of parts on an airplane, as 

required by paragraph (g), (k), (l)(1), or (m) 

of this AD, does not constitute terminating 

action for the repetitive inspections required 

by paragraph (i) of this AD, except as 

specified in paragraph (n)(3) of this AD. 

(2) The repetitive replacements required by 

paragraph (g) of this AD may be terminated 

by modification of the airplane to postAirbus Modification 27716 configuration, 

including a resonance frequency inspection 

for debonding of the composite insert and 

delamination of the honeycomb area around 

the insert, and all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1100, Revision 01, 

dated March 12, 1999, provided all 

applicable corrective actions are done before 

further flight. Thereafter, refer to paragraph 

(i) of this AD to determine the compliance 

time for the next detailed inspection required 

by this AD. 

(3) Modification of an airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

52–1165, Revision 01, dated October 23, 

2015, excluding Appendix 01, dated 

November 3, 2014, and including Appendix 

02, dated October 23, 2015; or Airbus Service 

Bulletin A320–52–1165, Revision 03, 

excluding Appendix 01 and including 

Appendix 02, dated November 9, 2017, 

constitutes terminating action for actions 

required by paragraphs (g) through (m) of this 

AD for the airplane on which the 

modification is done. As of the effective date 

of this AD only Airbus Service Bulletin 

A320–52–1165, Revision 03, excluding 

Appendix 01 and including Appendix 02, 

dated November 9, 2017, may be used. 

(o) Retained Exceptions to Certain AD 

Actions, With No Changes 

This paragraph restates the requirements of 

paragraph (o) of AD 2016–07–23, with no 

changes. An airplane on which Airbus 

Modification 155648 has been embodied in 

production is not affected by the 

requirements of paragraphs (g) and (i) of this 

AD, provided that no affected component, 

identified by part number as specified in 

paragraphs (g)(1) through (g)(5) and (i)(1) 

through (i)(3) of this AD, has been installed 

on that airplane since first flight of the 

airplane. 

(p) Retained Parts Installation Prohibition, 

With No Changes 

This paragraph restates the requirements of 

paragraph (p) of AD 2016–07–23, with no 

changes. 

(1) For airplanes in pre-Airbus 

Modification 27716 or pre-Airbus Service 

Bulletin A320–52–1100 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) of this AD on 

any airplane after doing the actions provided 

in paragraph (n)(2) of this AD. 

(2) For airplanes in post-Airbus 

Modification 27716 or post Airbus Service 

Bulletin A320–52–1100 configuration: As of 

the effective date of this AD, no person may 

install a component identified in paragraphs 

(g)(1) through (g)(5) of this AD on any 

airplane. 

(3) For airplanes in pre-Airbus 

Modification 155648 or pre-Airbus Service 

Bulletin A320–52–1165 configuration: No 

person may install a component identified in 

paragraphs (g)(1) through (g)(5) and (i)(1) 

through (i)(3) of this AD on any airplane after 

doing the actions provided in paragraph 

(n)(3) of this AD. 

(4) For airplanes in post-Airbus 

Modification 155648 or post-Airbus Service 

Bulletin A320–52–1165 configuration: As of 

the effective date of this AD, no person may 

install a component identified in (g)(1) 

through (g)(5) and (i)(1) through (i)(3) of this 

AD on any airplane. 

(q) Retained No Reporting Requirement, 

With No Changes 

This paragraph restates the requirements of 

paragraph (q) of AD 2016–07–23, with no 

changes. Although Airbus Service Bulletin 

A320–52–1163, Revision 01, including 

Appendix 01, dated June 22, 2015, specifies 

to submit certain information to the 

manufacturer, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

does not include that requirement. 

(r) New Requirement of This AD: Additional 

Work 

For any airplane on which, before the 

effective date of this AD, any part was 

installed or replaced, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–52–1165, dated 

November 3, 2014; Revision 01, dated 

October 13, 2015; or Revision 02, dated 

February 12, 2016: Within 12 months after 

the effective date of this AD, accomplish the 

instructions identified as ‘‘additional work’’ 

in the Accomplishment Instructions of 

Airbus Service Bulletin A320–52–1165, 


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Revision 03, excluding Appendix 01 and 

including Appendix 02, dated November 9, 

2017, as applicable to the airplane 

configuration. 

(s) New Terminating Action 

Modification of an airplane in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–52–1165, 

Revision 03, excluding Appendix 01 and 

including Appendix 02, dated November 9, 

2017, or as specified in paragraph (r) of this 

AD constitutes terminating action for the 

requirements of paragraphs (g), (i), (k), (l), 

and (m) of this AD for that airplane. 

(t) New Parts Installation Prohibition 

(1) Do not install on any airplane a 

component specified in paragraphs (g)(1) 

through (g)(5) of this AD, as required by 

paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as 

applicable. 

(i) For airplanes in pre-Airbus Modification 

27716 or pre-Airbus Service Bulletin A320– 

52–1100 configuration: After completing the 

optional modification specified in paragraph 

(n)(2) of this AD. 

(ii) For airplanes in post-Airbus 

Modification 27716 or post Airbus Service 

Bulletin A320–52–1100 configuration: As of 

the effective date of this AD. 

(2) Do not install on any airplane a 

component specified in paragraphs (g)(1) 

through (g)(5) of this AD or paragraphs (i)(1) 

through (i)(3) of this AD, as required by 

paragraph (t)(2)(i) or (t)(2)(ii) of this AD, as 

applicable. 

(i) For airplanes in pre-Airbus Modification 

155648 or pre-Airbus Service Bulletin A320– 

52–1165, Revision 03, excluding Appendix 

01 and including Appendix 02, dated 

November 9, 2017, configuration: After 

completion of the additional work required 

by paragraph (r) of this AD. 

(ii) For airplanes in post-Airbus 

Modification 155648 or post-Airbus Service 

Bulletin A320–52–1165, Revision 03, 

excluding Appendix 01 and including 

Appendix 02, dated November 9, 2017, 

configuration: As of the effective date of this 

AD. 

(u) Credit for Previous Actions 

(1) This paragraph provides credit for 

optional actions provided by paragraph (n)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–52–1100, 

dated December 7, 1998. 

(2) This paragraph provides credit for the 

actions required by paragraphs (g), (i), (k), (l), 

and (m) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–52–1163, 

dated February 4, 2014. 

(3) This paragraph provides credit for the 

actions required by paragraphs (k), (l)(1), (m), 

and (n)(3) of this AD if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–52–1165, 

Revision 01, dated October 23, 2015, 

excluding Appendix 01, dated November 3, 

2014, and including Appendix 02, dated 

October 23, 2015. 

(v) Other FAA AD Provisions 

(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 (w)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2016–07–23 are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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 the European 

Aviation Safety Agency (EASA); or Airbus 

SAS’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as specified by paragraph (q) 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. 

(w) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0023, dated January 26, 2018; corrected 

February 5, 2018; 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–2018–0762. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3223. 

(3) For 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. 

You may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on 

August 17, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18813 Filed 8–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 284 

[Docket No. RM96–1–041] 

Standards for Business Practices of 

Interstate Natural Gas Pipelines 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) is 

proposing to amend its regulations to 

incorporate by reference, with certain 

enumerated exceptions, the latest 

version (Version 3.1) of business 

practice standards adopted by the 

Wholesale Gas Quadrant of the North 

American Energy Standards Board 

(NAESB) applicable to natural gas 

pipelines in place of the currently 

incorporated version (Version 3.0) of 

those business practice standards. 

DATES: Comments are due October 1, 

2018. 

ADDRESSES: Comments, identified by the 

docket number of this proceeding, may 

be filed electronically at http://

www.ferc.gov in acceptable native 

applications and print-to-PDF, but not 

in scanned or picture format. For those 

unable to file electronically, comments 

may be filed by mail or hand-delivery 

to: Federal Energy Regulatory 

Commission, Secretary of the 

Commission, 888 First Street NE, 

Washington, DC 20426. The Comment 

Procedures Section of this document 

contains more detailed filing 

procedures. 

FOR FURTHER INFORMATION CONTACT: 

Stanley Wolf (technical issues), Office of 

Energy Policy and Innovation, Federal 

Energy Regulatory Commission, 888 

First Street NE, Washington, DC 

20426, Telephone: (202) 502–6841, Email: stanley.wolf@ferc.gov. 

Oscar F. Santillana (technical issues), 

Office of Energy Market Regulation, 

Federal Energy Regulatory 


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