58226 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 

(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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1112; fax: 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@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. The AMOC 

approval letter must specifically reference 

this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus Defense and Space 

S.A.’s (formerly known as Construcciones 

Aeronauticas, S.A.) EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0040, dated 

March 6, 2015, 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– 

2015–3636. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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 

September 16, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24424 Filed 9–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3635; Directorate 

Identifier 2015–NM–037–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by an evaluation by 

the design approval holder (DAH) 

indicating that the fuselage skin repairs 

are subject to widespread fatigue 

damage (WFD). This proposed AD 

would require an inspection to 

determine whether any fuselage external 

skin (doubler) repairs have been 

accomplished, an inspection for 

cracking of certain repaired external 

fuselage skin areas in the fuselage, and 

repair if necessary. We are proposing 

this AD to detect and correct fatigue 

cracking of the fuselage skin, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2015. 

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: 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 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. 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– 

3635; 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–2015–3635; Directorate Identifier 

2015–NM–037–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 


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Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 58227 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

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 2015–0036R1, dated March 31, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Model A318, 

A319, A320, and A321 series airplanes. 

The MCAI states: 

During A320 family Extended Service Goal 

full scale fatigue tests, it was demonstrated 

that the inspection thresholds defined in the 

current Structural Repair Manual (SRM) for 

the A320 family skin repairs are insufficient 

to detect possible cracks becoming after 

repairs. The findings are limited to 1.2 

[millimeter] (mm) fuselage skin and cover for 

all cut-out external repairs. The internal 

repairs are not affected. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the fuselage at the repaired skin area(s). 

To address this potential unsafe condition, 

Airbus issued Alert Operators Transmission 

(AOT) A53N007–14 to provide inspection 

instructions. 

For the reasons described above, EASA 

issued AD 2015–0036 [http://

www.casa.gov.au/scripts/

nc.dll?WCMS:OLDASSET::svPath=/ADFiles/

over/a320/,svFileName=2015-0036.pdf] to 

require a one-time inspection of the affected 

areas and, depending on findings, 

accomplishment of applicable repair 

instructions. 

Since that AD was issued, operators have 

questioned the inspection threshold for A318 

aeroplanes (not yet in the Airbus AOT), 

which is actually identical to that for A319 

aeroplanes. In addition, an error has been 

detected in paragraph (1), since external 

doublers may have been installed in the 

affected area by a modification that may not 

be recorded as repair. 

Such doubler installations are also subject 

to the inspection requirements of this AD, 

which is therefore revised to provide 

clarifications, correcting paragraph (1) and 

introducing a Note. 

Required actions include an 

inspection to determine whether any 

fuselage external skin (doubler) repairs 

have been accomplished, an external 

ultrasonic inspection or an internal low/ 

high frequency eddy current inspection 

for cracking of certain repaired external 

fuselage skin areas in the fuselage, and 

repair if necessary. The compliance 

times vary depending on airplane 

configuration. The earliest compliance 

time is within 25,200 flight cycles since 

last repair, or within 350 flight cycles 

after the effective date of the AD, 

whichever occurs later. The latest 

compliance time is within 45,000 flight 

cycles since last repair; within 1,500 

flight cycles from the effective date of 

the AD, without exceeding 49,100 flight 

cycles since last repair; or within 350 

flight cycles since the effective date of 

the AD; whichever occurs last. 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– 

3635. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Alert Operators 

Transmission A53N007–14, dated July 

22, 2014. The service information 

describes procedures for an inspection 

to detect cracking on repaired 1.2 

millimeter fuselage skin areas on 

fuselage sections 11, 12, 13, 14, 16, and 

17 at external doubler repairs. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 940 airplanes of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $159,800, or $170 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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: 


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58228 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 

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 

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 adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–3635; 

Directorate Identifier 2015–NM–037–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

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

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the fuselage skin repairs are subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct fatigue cracking 

of the fuselage skin, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine Repair Areas 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do an 

inspection to determine whether any fuselage 

external skin (doubler) repairs have been 

accomplished on fuselage sections 11, 12, 13, 

14, 16, and 17 with a skin thickness of 1.2 

millimeters. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the identification of 

applicable repairs can be conclusively 

determined from that review. 

(1) For Model A319, A320, and A321 series 

airplanes: Except as specified in paragraph 

(h)(1) and (h)(2) of this AD, at the applicable 

time specified in paragraphs 4.1.1.b., and 

4.1.1.c., of ‘‘Accomplishment Timescale,’’ of 

Airbus Alert Operators Transmission (AOT) 

A53N007–14, dated July 22, 2014, or within 

350 flight cycles after the effective date of 

this AD, whichever occurs later. 

(2) For Model A318 series airplanes: 

Except as specified in paragraph (h)(1) and 

(h)(2) of this AD, at the Model A319 airplane 

time specified in paragraphs 4.1.1.b., and 

4.1.1.c., of ‘‘Accomplishment Timescale,’’ of 

Airbus AOT A53N007–14, dated July 22, 

2014, or within 350 flight cycles after the 

effective date of this AD, whichever occurs 

later. 

(h) Exceptions to Service Information 

(1) Where paragraphs 4.1.1.b., and 4.1.1.c., 

of ‘‘Accomplishment Timescale,’’ of Airbus 

AOT A53N007–14, dated July 22, 2014, 

specifies ‘‘FC’’, this AD specifies ‘‘flight 

cycles.’’ 

(2) Where paragraphs 4.1.1.b., and 4.1.1.c., 

of ‘‘Accomplishment Timescale,’’ of Airbus 

AOT A53N007–14, dated July 22, 2014, 

specifies ‘‘from AOT issuance’’, this AD 

specifies ‘‘as of the effective date of this AD.’’ 

(i) Inspection for Cracking 

If, during the inspection required by 

paragraph (g) of this AD, it is determined that 

any fuselage external skin (doubler) repair 

has been accomplished on fuselage section 

11, 12, 13, 14, 16, or 17: At the applicable 

time specified paragraph (g)(1) or (g)(2) of 

this AD, do an external ultrasonic inspection 

(US) or an internal low frequency eddy 

current (LFEC) inspection for cracking of all 

of the repaired 1.2 millimeter (mm) fuselage 

skin areas, in accordance with the 

instructions specified in paragraph 4.2.2 

‘‘Inspection Requirements,’’ of Airbus AOT 

A53N007–14, dated July 22, 2014, except as 

provided by paragraph (j) of this AD. 

(j) Optional Inspection for Cracking 

As an optional method of compliance to 

the US or LFEC inspection required by 

paragraph (i) of this AD: Do a high frequency 

eddy current (HFEC) inspection for cracking 

in the cut-out surrounding the fastener area, 

at and in front (approximately 10–15 

millimeters) of the fastener row, after doubler 

removal and before any new extended 

doubler installation, 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). 

(k) Optional Repetitive Inspections 

In lieu of doing the inspection required by 

paragraph (i) of this AD: Within the 

applicable compliance time specified in 

paragraph 4.1.1 ‘‘Accomplishment 

Timescale,’’ of Airbus AOT A53N007–14, 

dated July 22, 2014, after accomplishing the 

inspections required by paragraph (g) of this 

AD, do a detailed inspection or HFEC 

inspection and repeat the inspection 

thereafter within the applicable compliance 

times specified in paragraph 4.1.1 

‘‘Accomplishment Timescale,’’ of Airbus 

AOT A53N007–14, dated July 22, 2014. The 

inspections must be done in accordance with 

the instructions of paragraph 4.2.2 

‘‘Inspection Requirements,’’ of Airbus AOT 

A53N007–14, dated July 22, 2014. For Model 

A318 series airplanes, use the applicable 

compliance times and instructions specified 

in Airbus AOT A53N007–14, dated July 22, 

2014, that are specified for Model A319 

series airplanes. 

(l) Repair 

If any crack is found during any inspection 

required by paragraph (i), (j), or (k) of this 

AD: Before further flight, repair the cracking, 

in accordance with the instructions of 

paragraph 4.2.3 ‘‘Findings,’’ of Airbus AOT 

A53N007–14, dated July 22, 2014, except 

where Airbus AOT A53N007–14, dated July 

22, 2014, specifies to contact Airbus for a 

repair design approval sheet or for further 

instructions, this AD requires repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(m) FAA-Approved Maintenance or 

Inspection Program Revision 

Concurrently with the accomplishment of 

any repair required by paragraph (l) of this 


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AD, revise the post-repair inspection 

threshold(s) in the applicable FAA-approved 

maintenance program or inspection program, 

as applicable, in accordance with the 

instructions specified in paragraph 4.1.1 

‘‘Accomplishment Timescale,’’ of Airbus 

AOT A53N007–14, dated July 22, 2014; 

except for Model A318 series airplanes use 

the instructions specified for Model A319 

series airplanes. 

(n) 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. 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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0036R1, dated 

March 31, 2015, 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– 

2015–3635. 

(2) For 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. 

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 

September 16, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24423 Filed 9–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[REG–132634–14] 

RIN 1545–BM43 

Qualifying Income From Activities of 

Publicly Traded Partnerships With 

Respect to Minerals or Natural 

Resources; Hearing 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Notice of public hearing on 

proposed rulemaking. 

SUMMARY: This document provides 

notice of public hearing on proposed 

regulations relates to section 

7704(d)(1)(E) of the Internal Revenue 

Code relating to qualifying income from 

exploration, development, mining or 

production, processing, refining, 

transportation, and marketing of 

minerals or production, processing, 

refining, transportation, and marketing 

of minerals or natural resources. 

DATES: The public hearing is being held 

on Tuesday, October 27, 2015, at 10 a.m. 

The IRS must receive outlines of the 

topics to be discussed at the public 

hearing by Wednesday, October 7, 2015. 

ADDRESSES: The public hearing is being 

held in the IRS Auditorium, Internal 

Revenue Service Building, 1111 

Constitution Avenue NW., Washington, 

DC 20224. Send Submissions to 

CC:PA:LPD:PR (REG–132634–14), Room 

5205, Internal Revenue Service, P.O. 

Box 7604, Ben Franklin Station, 

Washington, DC 20044. Submissions 

may be hand-delivered Monday through 

Friday to CC:PA:LPD:PR (REG–132634– 

14), Couriers Desk, Internal Revenue 

Service, 1111 Constitution Avenue NW., 

Washington, DC or sent electronically 

via the Federal eRulemaking Portal at 

www.regulations.gov (IRS–2015–0021). 

FOR FURTHER INFORMATION CONTACT: 

Concerning the regulations, Caroline E. 

Hay (202) 317–5279; concerning 

submissions of comments, the hearing 

and/or to be placed on the building 

access list to attend the hearing, Regina 

Johnson at (202) 317–6901 (not toll-free 

numbers). 

SUPPLEMENTARY INFORMATION: The 

subject of the public hearing is the 

notice of proposed rulemaking (REG– 

132634–14) that was published in the 

Federal Register on Wednesday, May 6, 

2015 (73 FR 25970). The rules of 26 CFR 

601.601(a)(3) apply to the hearing. 

Persons who wish to present oral 

comments at the hearing that submitted 

written comments by August 4, 2015 

must submit an outline of the topics to 

be addressed and the amount of time to 

be devoted to each topic by Wednesday, 

October 7, 2015. 

A period of 10 minutes is allotted to 

each person for presenting oral 

comments. After the deadline for 

receiving outlines has passed, the IRS 

will prepare an agenda containing the 

schedule of speakers. Copies of the 

agenda will be made available, free of 

charge, at the hearing or in the Freedom 

of Information Reading Room (FOIA RR) 

(Room 1621) which is located at the 

11th and Pennsylvania Avenue, 

entrance, of 1111 Constitution Avenue 

NW., Washington, DC. 

Because of access restrictions, the IRS 

will not admit visitors beyond the 

immediate entrance area more than 30 

minutes before the hearing starts. For 

information about having your name 

placed on the building access list to 

attend the hearing, see the FOR FURTHER

INFORMATION CONTACT section of this 

document. 

Martin V. Franks, 

Chief, Publications and Regulations Branch, 

Associate Chief Counsel (Procedure and 

Administration). 

[FR Doc. 2015–24568 Filed 9–25–15; 8:45 am] 

BILLING CODE 4830–01–P 

DEPARTMENT OF LABOR 

Mine Safety and Health Administration 

30 CFR Part 75 

RIN 1219–AB78 

Proximity Detection Systems for 

Mobile Machines in Underground Coal 

Mines 

AGENCY: Mine Safety and Health 

Administration, Labor. 

ACTION: Proposed rule; scheduling of 

public hearing. 

SUMMARY: The Mine Safety and Health 

Administration (MSHA) is announcing 

the date and location of public hearings 

on the Agency’s proposed rule 

addressing Proximity Detection Systems 

for Mobile Machines in Underground 

Coal Mines, published on September 2, 

2015. 

DATES: The public hearing dates and 

locations are listed in the 

SUPPLEMENTARY INFORMATION section of 

this document. Comments must be 

received by midnight Eastern Standard 

Time on December 1, 2015. 

ADDRESSES: Comments, requests to 

speak, and informational materials for 


rmajette on DSK7SPTVN1PROD with PROPOSALS