Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64375 

(1) A high-pressure compressor (HPC) rotor 

stage 2 to 5 spool, part number (P/N) 382– 

104–807–0, with a serial number (S/N) listed 

in EA Service Bulletin (SB) No. EAGP7–72– 

327, dated July 21, 2015; or 

(2) an HPC rotor stage 7 to 9 spool, P/N 

2031M90G04, 2031M90G05, or 2031M90G07, 

with an S/N listed in EA SB No. EAGP7–72– 

328, dated July 21, 2015. 

(d) Unsafe Condition 

This AD was prompted by reports of the 

installation of non-conforming honeycomb 

seals in the HPC adjacent to the HPC rotor 

stage 2 to 5 spool and stage 7 to 9 spool. We 

are issuing this AD to prevent failure of the 

HPC rotor stage 2 to 5 spools and stage 7 to 

9 spools, which could lead to uncontained 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. Within 30 days after the effective date 

of this AD or before accumulating 2,100 

engine cycles since the last disassembly of 

the compressor module of the engine, 

whichever occurs later: 

(1) For engines with an HPC rotor stage 2 

to 5 spool, P/N 382–104–807–0, installed 

with a S/N listed in EA SB No. EAGP7–72– 

327, dated July 21, 2015, do the following: 

(i) Remove the HPC rotor stage 2 to 5 spool 

from service and replace with a part eligible 

for installation. 

(ii) Remove and replace the honeycomb 

seals on the HPC stage 5 vanes. 

(2) For engines with an HPC rotor stage 7 

to 9 spool, P/N 2031M90G04, 2031M90G05, 

or 2031M90G07 installed with an S/N listed 

in EA SB No. EAGP7–72–328, dated July 21, 

2015, do the following: 

(i) Remove the HPC rotor stage 7 to 9 spool 

from service and replace with a part eligible 

for installation. 

(ii) Remove and replace the honeycomb 

seals on the HPC stage 6, stage 7, and stage 

8 vanes. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. You may email your request to: 

ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Martin Adler, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7157; fax: 781–238– 

7199; email: martin.adler@faa.gov. 

(2) EA SBs No. EAGP7–72–327, dated July 

21, 2015; and No. EAGP7–72–328, dated July 

21, 2015 can be obtained from EA using the 

contact information in paragraph (g)(3) of this 

proposed AD. 

(3) For service information identified in 

this AD, contact Engine Alliance, 400 Main 

St., East Hartford, CT 06108, M/S 169–10, 

phone: 800–565–0140; email: help24@

pw.utc.com; Web site: 

www.engineallianceportal.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

October 16, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–26755 Filed 10–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4202; Directorate 

Identifier 2014–NM–016–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2012–18– 

12, for certain Airbus Model A318, 

A319, and A320 series airplanes. AD 

2012–18–12 currently requires 

modifying the off-wing escape slide 

(OWS) enclosures on the left-hand (LH) 

side and right-hand (RH) side of the 

fuselage. Since we issued AD 2012–18– 

12, we have received reports that 

additional OWS part numbers have been 

affected. This proposed AD would 

retain the requirements of AD 2012–18– 

12 and expand the applicability to all 

Airbus Model A318, A319, and A320 

series airplanes. We are proposing this 

AD to prevent off-wing exits on the LH 

and RH sides of the fuselage from 

becoming inoperative, which, during an 

emergency, could impair the safe 

evacuation of occupants, possibly 

resulting in personal injuries. 

DATES: We must receive comments on 

this proposed AD by December 7, 2015. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For Air 

Cruisers service information identified 

in this proposed AD, contact Air 

Cruisers Company, Cage Code 70167, 

1747 State Route 34, Wall Township, NJ 

07727–3935; telephone 732–681–3527; 

fax 732–681–9163; Internet http://www.

zodiacaerospace.com/en/our-activities/

aerosafety/zodiac-evacuation-systems. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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–2015– 

4202; 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 proposed AD, 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 Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–4202; Directorate Identifier 

2014–NM–016–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://

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64376 Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 

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 

On August 31, 2012, we issued AD 

2012–18–12, Amendment 39–17189 (77 

FR 57003, September 17, 2012). AD 

2012–18–12 requires actions intended to 

address an unsafe condition on certain 

Airbus Model A318, A319, and A320 

series airplanes. 

Since we issued AD 2012–18–12, 

Amendment 39–17189 (77 FR 57003, 

September 17, 2012), we received 

reports that additional OWS part 

numbers have been affected which 

requires expanding the applicability to 

all Airbus Model A318, A319, and A320 

series airplanes. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0025R1, dated May 26, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Airbus Model 

A318, A319, and A320 series airplanes. 

The MCAI states: 

One operator reported a torn out aspirator 

during scheduled deployment (for on ground 

testing purposes) of the Left Hand (LH) offwing [escape] slide (OWS). Investigation 

results revealed that the aspirator of the OWS 

system interfered with the extrusion lip of 

the OWS enclosure during the initial stage of 

the deployment sequence. 

This condition, if not corrected, could lead 

to an off-wing exit, either LH or Right Hand 

(RH), becoming unserviceable, which, during 

an emergency situation, could impair the safe 

evacuation of occupants, possibly resulting 

in personal injuries. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

25–1649 containing modification instructions 

for certain part number (P/N) OWS 

enclosures. Consequently, EASA issued 

[EASA] AD 2010–0210 [(http://ad.easa.

europa.eu/ad/2010-0210)] which 

corresponds to FAA AD 2012–18–12, 

Amendment 39–17189 (77 FR 57003, 

September 17, 2012)] to require modification 

of the affected OWS enclosures. 

Since that [EASA] AD was issued, several 

other OWS P/N[s] have been identified as 

potentially impacted. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2010–0210, which is superseded, 

expands the Applicability to all A318, A319 

and A320 aeroplanes, and expands the batch 

of affected P/N[s] prohibited to be installed 

on an aeroplane. 

For the reason described above, EASA 

issued AD 2014–0025, retaining the 

requirements of EASA AD 2010–0210, which 

was superseded, expanding the Applicability 

to all A318, A319 and A320 aeroplanes, and 

expanding the batch of affected P/N[s] 

prohibited to be installed on an aeroplane. 

That [EASA] AD also retained the 

requirements of * * * [an AD, which was 

superseded], which required modification of 

the OWS and its aspirator. 

This [EASA] AD is revised to amend 

paragraphs (1) and (3) to restore the original 

applicability of DGAC France AD 2001–380 

and EASA AD 2010–0210, respectively, and 

to correct paragraph (2) to give credit for 

certain production modifications that were 

equivalent for the in-service actions 

previously required by DGAC France AD 

2001–380. 

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–2015– 

4202. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A320–25– 

1156, Revision 03, dated December 5, 

2001. This service information describes 

procedures for modifying OWS 

enclosures having part numbers (P/N) 

D31865–101, D31865–102, D31865–103, 

D31865–104, D31865–105, D31865–106, 

D31865–107, or D31865–108 of certain 

Airbus Model A319 and A320 series 

airplanes. 

• Airbus Service Bulletin A320–25– 

1265, Revision 01, dated December 5, 

2001. This service information describes 

procedures for modifying and installing 

the OWS enclosure on the LH and RH 

sides of the fuselage on certain Airbus 

Model A319 and A320 series airplanes. 

• Airbus Service Bulletin A320–25– 

1649, dated February 16, 2010. This 

service information describes 

procedures for modifying and installing 

OWS enclosures having part numbers 

(P/N) D31865–109, D31865–110, 

D31865–209, or D31865–210, on the LH 

and RH sides of the fuselage on certain 

Airbus Model A318, A319, and A320 

series airplanes. 

Air Cruisers has issued Service 

Bulletin A320 004–25–84, Revision 4, 

dated November 9, 2012. This service 

information describes procedures for 

modifying LH and RH OWS. 

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 of 

this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

The actions required by AD 2012–18– 

12, Amendment 39–17189 (77 FR 

57003, September 17, 2012), and 

retained in this proposed AD take about 

14 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost $0 per product. 

Based on these figures, the estimated 

cost of the actions that are required by 

AD 2012–18–12 is $1,190 per product. 

We also estimate that it would take 

about 48 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost $0 per product. Based 

on these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $3,472,080, or $4,080 per product. 

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. 

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 

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Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64377 

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) 

2012–18–12, Amendment 39–17189 (77 

FR 57003, September 17, 2012), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–4202; 

Directorate Identifier 2014–NM–016–AD. 

(a) Comments Due Date 

We must receive comments by December 7, 

2015. 

(b) Affected ADs 

This AD replaces (AD) 2012–18–12, 

Amendment 39–17189 (77 FR 57003, 

September 17, 2012). 

(c) Applicability 

This AD applies to the Airbus airplanes 

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

(c)(3) of this AD, certificated in any category, 

all manufacturer serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model 320–211, –212, –214, –231, –232, 

and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Reason 

This AD was prompted by a report of a torn 

out aspirator due to the aspirator interfering 

with the extrusion lip of the off-wing escape 

slide (OWS) enclosure during the initial stage 

of the deployment sequence. This AD was 

also prompted by reports that additional 

OWS part numbers have been affected which 

requires expanding the applicability to all 

Airbus Model A318, A319, and A320 series 

airplanes. We are issuing this AD to prevent 

off-wing exits on the left-hand (LH) and righthand (RH) sides of the fuselage from 

becoming inoperative, which, during an 

emergency, could impair the safe evacuation 

of occupants, possibly resulting in personal 

injuries. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–18–12, 

Amendment 39–17189 (77 FR 57003, 

September 17, 2012) with no changes. For 

airplanes equipped with OWS enclosures 

having part number (P/N) D31865–109, 

D31865–110, D31865–209, or D31865–210, 

except as provided by paragraph (i)(1) of this 

AD: Within 36 months after October 22, 

2012, (the effective date of AD 2012–18–12), 

modify the OWS enclosures and install an 

OWS enclosure having P/N D31865–309, 

D31865–311, D31865–310, or D31865–312 on 

the LH side and RH side of the fuselage, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

25–1649, dated February 16, 2010. 

(h) New Modification of Affected OWS 

Enclosures and Aspirators 

For airplanes equipped with an OWS 

enclosure having P/N D31865–101, D31865– 

102, D31865–103, D31865–104, D31865–105, 

D31865–106, D31865–107, or D31865–108, 

except as provided by paragraph (i)(2) of this 

AD: Within 36 months after the effective date 

of this AD, do the actions specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Modify the OWS enclosures and their 

aspirators in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1156, Revision 03, 

dated December 5, 2001. 

(2) Install off-wing escape slides having P/ 

N D31865–109, D31865–110, D31865–209, or 

D31865–210 on the LH side and RH side of 

the fuselage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1265, Revision 01, 

dated December 5, 2001; and accomplish the 

modification required by paragraph (g) of this 

AD. 

(i) Exceptions to the Requirements of 

Paragraphs (g) and (h) of This AD 

(1) Airplanes having Airbus modification 

30088 embodied in production using an 

OWS enclosure having P/N D31865–111 or 

D31865–112 are not affected by the 

requirements of paragraph (g) of this AD, 

unless a replacement OWS enclosure, having 

a part number listed in paragraphs (k)(9) 

through (k)(12) of this AD, has been installed 

on that airplane since first flight. 

(2) Airplanes on which Airbus 

modifications 24850, 25844, and 27275 have 

been embodied in production, or on which 

modifications of the LH and RH OWS 

enclosures and their aspirators have been 

accomplished using Airbus Service Bulletin 

A320–25–1156, Revision 01, dated February 

2, 1999, or Revision 2, dated October 26, 

1999, and Airbus Service Bulletin A320–25– 

1265, dated June 6, 2001, are compliant with 

the modification requirement of paragraph 

(h) of this AD. 

(j) Optional Method of Compliance for 

Paragraph (g) of This AD 

Installing both LH and RH OWS that have 

been modified in accordance with the 

Accomplishment Instructions of Air Cruisers 

Service Bulletin A320 004–25–84, Revision 

4, dated November 9, 2012, is an acceptable 

method of compliance with the modification 

required by paragraph (g) of this AD. 

(k) Part Installation Prohibition 

As of the effective date of this AD, do not 

install on any airplane an OWS enclosure 

having a part number listed in paragraphs 

(k)(1) through (k)(12) of this AD, except as 

required by paragraph (h)(2) of this AD for 

the OWS enclosures identified in paragraph 

(h) of this AD. 

(1) D31865–101 

(2) D31865–102 

(3) D31865–103 

(4) D31865–104 

(5) D31865–105 

(6) D31865–106 

(7) D31865–107 

(8) D31865–108 

(9) D31865–109 

(10) D31865–110 

(11) D31865–209 

(12) D31865–210 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information identified in paragraph (l)(1)(i) 

or (l)(1)(ii) of this AD, which is not 

incorporated by reference. 

(i) Airbus Service Bulletin A320–25–1156, 

Revision 01, dated February 2, 1999. 

(ii) Airbus Service Bulletin A320–25–1156, 

Revision 02, dated October 26, 1999. 

(2) This paragraph provides credit for the 

actions specified in paragraph (h)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–25–1265, dated June 

6, 2001, which is not incorporated by 

reference. 

(3) This paragraph provides credit for the 

actions specified in paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (l)(3)(i), 

(l)(3)(ii), (l)(3)(iii), or (l)(3)(iv) of this AD, 

which is not incorporated by reference. 

(i) Air Cruisers Service Bulletin A320 004– 

25–84, dated February 5, 2010. 

(ii) Air Cruisers Service Bulletin A320 

004–25–84, Revision 1, dated April 9, 2010. 

(iii) Air Cruisers Service Bulletin A320 

004–25–84, Revision 2, dated February 11, 

2011. 

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64378 Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 

(iv) Air Cruisers Service Bulletin A320 

004–25–84, Revision 3, dated October 28, 

2011. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2012–18–12, Amendment 39–17189 (77 FR 

57003, September 17, 2012), are approved as 

AMOCs for the corresponding provisions of 

paragraph (g) 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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0025R1, dated 

May 26, 2014, 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– 

2015–4202. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

For Air Cruisers service information 

identified in this AD, contact Air Cruisers 

Company, Cage Code 70167, 1747 State 

Route 34, Wall Township, NJ 07727–3935; 

telephone 732–681–3527; fax 732–681–9163; 

Internet http://www.zodiacaerospace.com/

en/our-activities/aerosafety/zodiacevacuation-systems. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26611 Filed 10–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Parts 1, 20, 25, 26, 31, and 301 

[REG–148998–13] 

RIN 1545–BM10 

Definition of Terms Relating to Marital 

Status 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This document contains 

proposed regulations that reflect the 

holdings of Obergefell v. Hodges, 576 

U.S. __, 135 S. Ct. 2584 (2015), Windsor 

v. United States, 570 U.S. __, 133 S. Ct. 

2675 (2013), and Revenue Ruling 2013– 

17 (2013–38 IRB 201), and that define 

terms in the Internal Revenue Code 

(Code) describing the marital status of 

taxpayers. The proposed regulations 

primarily affect married couples, 

employers, sponsors and administrators 

of employee benefit plans, and 

executors. This document invites 

comments from the public regarding 

these proposed regulations. 

DATES: Written or electronic comments 

and requests for a public hearing must 

be received by December 7, 2015. 

ADDRESSES: Send submissions to: 

CC:PA:LPD:PR (REG–148998–13), Room 

5205, Internal Revenue Service, P.O. 

Box 7604, Ben Franklin Station, 

Washington, DC 20044. Submissions 

may be hand-delivered Monday through 

Friday between the hours of 8 a.m. and 

4 p.m. to CC:PA:LPD:PR (REG–148998– 

13), Courier’s Desk, Internal Revenue 

Service, 1111 Constitution Avenue NW., 

Washington, DC; or sent electronically 

via the Federal eRulemaking Portal at 

www.regulations.gov (IRS REG–148998– 

13). 

FOR FURTHER INFORMATION CONTACT: 

Concerning the proposed amendments 

to the regulations, Mark Shurtliff at 

(202) 317–3400; concerning submissions 

of comments and requests for a hearing, 

Regina Johnson at (202) 317–6901 (not 

toll-free numbers). 

SUPPLEMENTARY INFORMATION: 

Background and Explanation of 

Provisions 

This document contains proposed 

amendments to the Income Tax 

Regulations (26 CFR part 1), the Estate 

Tax Regulations (26 CFR part 20), the 

Gift Tax Regulations (26 CFR part 25), 

the Generation-Skipping Transfer Tax 

Regulations (26 CFR part 26), the 

Employment Tax and Collection of 

Income Tax at Source Regulations (26 

CFR part 31), and the Regulations on 

Procedure and Administration (26 CFR 

part 301). 

Amendments to Regulations 

Incorporating Holdings of Windsor, 

Obergefell, and Revenue Ruling 2013–17 

On June 26, 2013, the Supreme Court 

in United States v. Windsor, 570 U.S. 

__, 133 S. Ct. 2675 (2013), held that 

Section 3 of the Defense of Marriage 

Act, which generally prohibited the 

federal government from recognizing the 

marriages of same-sex couples, is 

unconstitutional because it violates the 

principles of equal protection and due 

process. Revenue Ruling 2013–17 

provides guidance on the Windsor 

decision’s effect on the IRS’s 

interpretation of Code sections that refer 

to taxpayers’ marital status. Cf. Notice 

2014–19 (2014–47 IRB 979), amplified 

by Notice 2014–37 (2014–24 IRB 1100) 

(regarding the application of the 

Windsor decision to qualified retirement 

plans); Notice 2014–1 (2014–02 IRB 

270) (regarding elections and 

reimbursements for same-sex spouses 

under cafeteria plans, flexible spending 

arrangements, and health savings 

accounts following the Windsor 

decision); Notice 2013–61 (2013–44 IRB 

432) (regarding the application of the 

Windsor decision and Rev. Rul. 2013–17 

to employment taxes and special 

administrative procedures for employers 

to make adjustments or claims for 

refund or credit); and Revenue 

Procedure 2014–18 (2014–7 IRB 513) 

(regarding extensions of time for estates 

to make a portability election). On June 

26, 2015, the Supreme Court in 

Obergefell v. Hodges, 576 U.S. __ (2015), 

held that state laws are ‘‘invalid to the 

extent they exclude same-sex couples 

from civil marriage on the same terms 

and conditions as opposite-sex couples’’ 

and ‘‘that there is no lawful basis for a 

State to refuse to recognize a lawful 

same-sex marriage performed in another 

State on the ground of its same-sex 

character.’’ Obergefell, 576 U.S. at 23, 

28. 

In light of the holdings of Windsor 

and Obergefell, the Treasury Department 

and the IRS have determined that, for 

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