38806 Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules 

(p) New Requirement of This AD: Inspection, 

Corrective Action and Replacement of 

Fittings Replaced in Accordance With 

Paragraph (l) of This AD 

For airplanes on which a new carriage 

attach fitting with the original part number 

on the outboard foreflap was installed in 

accordance with paragraph (l) of this AD: Do 

the actions specified in paragraphs (p)(1) and 

(p)(2) of this AD. 

(1) Within 1,000 flight cycles after the 

effective date of this AD, do a detailed 

inspection for cracks and surface deviation 

on all edges surfaces, and lug attachment 

fastener holes, and a HFEC inspection for 

cracks at the lug attachment fastener holes, 

on the carriage attach fittings for the outboard 

foreflaps, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–57A0135, Revision 4, 

dated September 26, 2012. Repeat the 

inspection at intervals not to exceed 200 

flight cycles. Do all applicable corrective 

actions before further flight. 

(2) Within 3,000 flight cycles or 3 years 

after the effective date of this AD, replace the 

fitting with a new, improved fitting in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

727–57A0135, Revision 4, dated September 

26, 2012. Accomplishing the requirements of 

this paragraph terminates the requirements of 

paragraphs (g), (m), and (p)(1) of this AD for 

that outboard foreflap only. 

(q) New Requirement of This AD: Inspection 

and Corrective Actions on Fittings Replaced 

According to Paragraph (k), (o), or (p) of 

This AD on Outboard Foreflaps 

For airplanes on which a new, improved 

carriage attach fitting on the outboard 

foreflap was replaced in accordance with the 

requirements of paragraph (k), (o), or (p) of 

this AD: Within 20,000 flight cycles after 

installing that fitting, do a detailed 

inspection for cracks and surface deviation 

on all edges surfaces, and lug attachment 

fastener holes, and a HFEC inspection for 

cracks at the lug attachment fastener holes, 

on the carriage attach fittings for the outboard 

foreflaps, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–57A0135, Revision 4, 

dated September 26, 2012. Do all applicable 

corrective actions before further flight. 

Repeat the inspection thereafter at intervals 

not to exceed 1,400 flight cycles. 

Accomplishing the requirements of this 

paragraph terminates the requirements of 

paragraph (g) of this AD for outboard 

foreflaps only. 

(r) Retained Credit for Previously 

Accomplished Service Bulletins 

(1) This paragraph restates the credit 

provided by paragraph (p) of AD 2005–14– 

07, Amendment 39–14184 (70 FR 39647, July 

11, 2005), with no changes. Installations 

accomplished before August 15, 2005 (the 

effective date of AD 2005–14–07), in 

accordance with Boeing 727 Service Bulletin 

57–59, dated September 2, 1965, are 

acceptable for compliance with the 

requirements of paragraph (j)(1) of this AD. 

(2) This paragraph restates the credit 

provided by paragraph (q) of AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, July 11, 

2005), with no changes. Inspections and 

modifications accomplished before August 

15, 2005 (the effective date of AD 2005–14– 

07), in accordance with Boeing Service 

Bulletin 727–27–133, dated October 7, 1971, 

are acceptable for compliance with the 

requirements of paragraph (j)(2) of this AD. 

(s) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (u) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, July 11, 

2005), are approved as AMOCs for the 

corresponding provisions of this AD. 

(t) Related Information 

(1) For more information about this AD, 

contact Chandraduth Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5239; fax: 562–627–5210; email 

chandraduth.ramdoss@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Aircraft 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 June 27, 

2014. 

John P. Piccola, 

Acting Manager, Transport Aircraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15986 Filed 7–8–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0437; Directorate 

Identifier: 2012–CE–036–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Piper Aircraft, 

Inc. Models PA–31P airplanes. AD 76– 

06–09 currently requires repetitive 

inspection of certain exhaust system 

parts with replacement of parts mating 

with the turbocharger, as necessary, and 

allows installation of a certain tailpipe 

v-band coupling as terminating action. 

Since we issued AD 76–06–09, there 

have been reports of exhaust system 

failures, the manufacturer issued new 

service information, and the tailpipe vband coupling used for terminating 

action is obsolete. This proposed AD 

would require the use of the new service 

information and expand the scope of the 

inspections of the turbocharger exhaust 

system. We are proposing this AD to 

correct the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by August 25, 2014. 

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 AD, use the following contact 

information, as applicable, Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/

Publications.cfm; or Lycoming Engines, 

652 Oliver Street, Williamsport, 

Pennsylvania 17701; telephone: (570) 


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323–6181; Internet: http://

www.lycoming.textron.com/support/

publications/index.html. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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–2014– 

0437; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: gary.wechsler@

faa.gov. 

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–2014–0437; Directorate Identifier 

2012–CE–036–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 because of 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 

On October 17, 1978, we issued AD 

76–06–09, Amendment 39–3325 (43 FR 

50417, October 30, 1978), for certain 

Piper Aircraft, Inc. Model PA–31P 

airplanes. AD 76–06–09 requires 

repetitive inspection of certain exhaust 

system parts with replacement of parts 

mating with the turbocharger, as 

necessary, and allows installation of a 

certain tailpipe v-band coupling as 

terminating action. AD 76–06–09 

resulted from reports of exhaust system 

failure. We issued AD 76–06–09 to 

preclude failure of the engine exhaust 

system. 

Actions Since Existing AD Was Issued 

Since we issued AD 76–06–09, 

Amendment 39–3325 (43 FR 50417, 

October 30, 1978), there have been 

exhaust system failures, the 

manufacturer issued new service 

information, and the tailpipe v-band 

coupling used for terminating action is 

obsolete. 

Relevant Service Information 

We reviewed Textron Lycoming 

Mandatory Service Bulletin No. 393C, 

dated November 26, 1976; Piper Aircraft 

Corporation Service Bulletin No. 462A, 

dated November 3, 1975; Piper Aircraft, 

Inc. Service Bulletin No. 492A, dated 

May 29, 2012; Piper Aircraft, Inc. 

Service Bulletin No. 644E, dated May 9, 

2012; Piper Aircraft Corporation kit part 

number (P/N) 760 974, dated February 

19, 1976; Piper Aircraft Corporation kit 

P/N 761 045, dated February 19, 1976; 

and Piper Aircraft Corporation kit P/N 

761 047, dated February 19, 1976. The 

service information describes 

procedures for inspecting and replacing 

parts of the turbocharger exhaust v-band 

couplings, vibration isolators, and 

support brackets. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain 

certain requirements of AD 76–06–09, 

Amendment 39–3325 (43 FR 50417, 

October 30, 1978). This proposed AD 

would require the use of the new service 

information and expand the scope of the 

inspections of the turbocharger exhaust 

system. 

Costs of Compliance 

We estimate that this proposed AD 

affects 85 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. 

operators 

Visual inspection ............................................. 3 work-hours × $85 per hour = $255 ............. Not applicable ....... $255 $21,675 

Review of maintenance records ..................... .5 work-hour × $85 per hour = $42.50 ........... Not applicable ....... 42.50 3,612.50 

We have no way of determining how 

much damage may be found on each 

airplane during the proposed 

inspection. The scope of damage on the 

exhaust system could vary from airplane 

to airplane due to the manner and 

environments the airplane may operate. 

We estimate the following costs to do 

any necessary modification/installation/ 

replacement that would be required 

based on the results of the proposed 

inspection. We have no way of 

determining what damage may be found 

or the number of airplanes that might 

need these modification/installation/

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Modification of the exhaust pipe slip joint .................... 5 work-hours × $85 per hour = $425 ........................... $2,841 $3,266 

Installation of the bracket and clamp assembly ........... 5 work-hours × $85 per hour = $425 ........................... 5,000 5,425 


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38808 Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Replacement of v-band coupling .................................. 2 work-hours × $85 per hour = $170 ........................... 780 950 

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 proposed 

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 have 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 that the 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) 

76–06–09, Amendment 39–3325 (43 FR 

50417, October 30, 1978), and adding 

the following new AD: 

Piper Aircraft, Inc.: Docket No. FAA–2014– 

0437; Directorate Identifier 2012–CE– 

036–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 25, 2014. 

(b) Affected Ads 

This AD supersedes AD 76–06–09, 

Amendment 39–3325 (43 FR 50417, October 

30, 1978). 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Models PA–31P airplanes, serial numbers 

31P–1 through 31P–80 and 31P–7300110 

through 31P–7730012, that are certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of 

exhaust system failures, new service 

information issued by the manufacturer, and 

the tailpipe v-band coupling used for 

terminating action is obsolete. We are issuing 

this AD to prevent the possibility of an inflight powerplant fire due to an exhaust 

system failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Exhaust System 

(1) Within the next 60 hours time-inservice (TIS) after the effective date of this 

AD or within the next 6 months after the 

effective date of this AD, whichever occurs 

first, and repetitively thereafter at intervals 

not to exceed 60 hours TIS or 6 months, 

whichever occurs first, inspect the parts as 

specified in table 1 of paragraph (g)(1) of this 

AD, if installed. 

TABLE 1 OF PARAGRAPH (g)(1) OF THIS AD: INSPECTION FOR PIPER AND LYCOMING EXHAUST SYSTEM PARTS

Product/part nomenclature Make Model/part No. 

With a light and mirror or other method 

capable of achieving an equivalent visual 

resolution, inspect for 

the following conditions 

Airplane ............................................................ Piper ........................... PA–31P ...................... Bulges, cracks, and exhaust leak stains. 

Engine .............................................................. Lycoming .................... TIGO–541–E series ... Bulges, cracks, and exhaust leak stains. 

Pipe, exhaust, right-rear .................................. Lycoming .................... 78012 ......................... Bulges, cracks, and exhaust leak stains. 

Pipe, exhaust, left-rear .................................... Lycoming .................... 78008 ......................... Bulges, cracks, and exhaust leak stains. 

Pipe, rear exhaust adapter .............................. Lycoming .................... LW–13027 .................. Bulges, cracks, and exhaust leak stains. 

Tail pipe assembly, upper ............................... Piper ........................... 46323–05 ................... Bulges, cracks, and exhaust leak stains. 

Tail pipe assembly, lower ................................ Piper ........................... 48788–05 ................... Bulges, cracks, and exhaust leak stains. 

V-band coupling ............................................... Lycoming .................... LW–12093–5 .............. Cracks and exhaust leak stains. 

V-band coupling ............................................... Piper ........................... 555–366 or 557–369 .. Cracks and exhaust leak stains. 

Isolator (CA–3383–1) ....................................... Piper ........................... 467–442 ..................... Cracks, looseness, and distortion. 

Bracket—isolator, upper .................................. Piper ........................... 47014–02 ................... Cracks, looseness, and distortion. 

Bracket—isolator, lower ................................... Piper ........................... 47013–02 ................... Cracks, looseness, and distortion. 


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(2) If any damage is found in any 

inspection required in paragraph (g)(1) of this 

AD, before further fight, do the corrective 

actions, as applicable, in paragraphs (g)(2)(i) 

through (g)(2)(iv). 

(i) Replace Piper v-band couplings 

exhibiting cracks and/or exhaust leak stains 

with airworthy parts following Piper Aircraft, 

Inc. Mandatory Service Bulletin No. 644E, 

dated May 9, 2012. Replace Lycoming v-band 

couplings exhibiting cracks and/or exhaust 

leak stains with airworthy parts following 

Lycoming Service Instruction No. 1238B, 

Revision B, dated January 6, 2010. 

Note to paragraphs (g)(2)(i) and (h)(2)(iii): 

During replacement of v-band couplings, we 

recommend not opening the v-band coupling 

more than the MINIMUM diameter necessary 

to clear coupled flanges. It is recommended 

to replace any locknuts and/or mating 

couplings with airworthy parts when 

locknuts do not exhibit a prevailing torque 

when installed. 

(ii) Replace Lycoming exhaust system parts 

exhibiting bulges, cracks, and/or exhaust leak 

stains with airworthy parts following 

Lycoming Service Instruction No. 1320, 

dated March 7, 1975; or Lycoming Service 

Instruction No. 1391, dated October 5, 1979, 

as applicable. 

(iii) Replace Piper tail pipe assembly parts 

exhibiting bulges, cracks, and/or exhaust leak 

stains with airworthy parts following Piper 

Aircraft, Inc. Mandatory Service Bulletin No. 

644E, dated May 9, 2012. 

(iv) Replace Piper isolators and brackets 

exhibiting cracks, looseness and/or distortion 

following Piper Aircraft, Inc. Service Bulletin 

No. 462A, dated November 3, 1975; and 

Service Bulletin No. 492A, dated May 29, 

2012. 

(h) Exhaust System Modifications 

(1) Within the next 100 hours TIS after the 

effective date of this AD or within the next 

12 months after the effective date of this AD, 

whichever occurs first, review the airplane 

maintenance records to positively identify 

whether the modifications described in 

paragraphs (h)(1)(i) through (h)(1)(iii) of this 

AD have been done. 

(i) Exhaust pipe slip joint modification 

following Piper Aircraft, Inc. Service Bulletin 

No. 492A, dated May 29, 2012; and Lycoming 

Service Bulletin No. 393C, dated November 

26, 1976. 

(ii) Installation of bracket and clamp 

assembly following Piper Kit No. 760–974 as 

specified in Piper Aircraft, Inc. Service 

Bulletin No. 492A, dated May 29, 2012; or 

Piper Aircraft, Inc. Service Bulletin 462A, 

dated November 3, 1975. 

(iii) Replacement of Piper v-band coupling, 

part number 556–053, with Piper v-band 

coupling, part number 557–369, following 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 644E, dated May 9, 2012. 

(2) If you cannot positively identify that 

the modifications described in paragraphs 

(h)(1)(i) through (h)(1)(iii) of this AD have 

been done, before further flight, you must do 

the modifications described in paragraphs 

(h)(2)(i) through (h)(2)(ii), as applicable. 

(i) Exhaust pipe slip joint modification 

following Piper Aircraft, Inc. Service Bulletin 

No. 492A, dated May 29, 2012, and Lycoming 

Service Bulletin SB 393C, dated November 

26, 1976. 

(ii) Installation of bracket and clamp 

assembly following Piper Kit No. 760–974 as 

specified in Piper Aircraft, Inc. Service 

Bulletin No. 492A, dated May 29, 2012; or 

Piper Aircraft, Inc. Service Bulletin 462A, 

dated November 3, 1975. 

(iii) Replacement of Piper v-band coupling, 

part number 556–053, with Piper v-band 

coupling, part number 557–369, following 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 644E, dated May 9, 2012. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Gary Wechsler, Aerospace Engineer, 

Atlanta ACO, FAA, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

(2) For service information identified in 

this AD, contact FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on June 

24, 2014. 

Timothy Smyth, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16003 Filed 7–8–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[REG–150760–13] 

RIN 1545–BM05 

Definition of Real Estate Investment 

True Real Property; Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correction to notice of proposed 

rulemaking. 

SUMMARY: This document contains 

corrections to a notice of proposed 

rulemaking and notice of public hearing 

(REG–150760–13) that was published in 

the Federal Register on Wednesday, 

May 14, 2014 (79 FR 27508), that clarify 

the definition of real property for 

purposes of the real estate investment 

trust provisions of the Internal Revenue 

Code. 

DATES: Written or electronic comments 

and request for a public hearing for the 

notice of proposed rulemaking and 

notice of public hearing published at 79 

FR 27508, May 14, 2014, are still being 

accepted and must be received by 

August 12, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Andrea M. Hoffenson, at (202) 317–7053 

(not a toll-free number). 

SUPPLEMENTARY INFORMATION: 

Background 

The notice of proposed rulemaking 

and notice of public hearing that is the 

subject of this document is under 

section 856 of the Internal Revenue 

Code. 

Need for Correction 

As published, the notice of proposed 

rulemaking and notice of public hearing 

(REG–150760–13) contains errors that 

are misleading and are in need of 

clarification. 

Correction to Publication 

Accordingly, notice of proposed 

rulemaking and notice of public 

hearing, that is the subject of FR Doc. 

2014–11115, is corrected as follows: 

1. On page 27508, in the preamble, 

first column, under the caption FOR

FURTHER INFORMATION CONTACT, second 

line, the language ‘‘Andrea Hoffenson, 

(202) 317–6842, or’’ is corrected to read 

‘‘Andrea M. Hoffenson, (202) 317–7053, 

or’’. 

2. On page 27510, in the preamble, 

second column, sixteenth line of the 

second full paragraph, the language 

‘‘investment credit contexts, this’’ is 

corrected to read ‘‘investment tax credit 

contexts, this’’. 

3. On page 27510, in the preamble, 

third column, eighth and ninth lines of 

the first full paragraph, the language 

‘‘depreciation, (prior) investment tax 

credit, and FIRPTA contexts. In 

drafting’’ is corrected to read 

‘‘depreciation and (prior) investment tax 

credit contexts. In drafting’’. 

§ 1.856–10 [Corrected] 

4. On page 27512, second column, 

fourth line of paragraph (e)(2), the 

language ‘‘is a distinct asset is based on 

all of the’’ is corrected to read ‘‘is a 

distinct asset is based on all the’’. 

5. On page 27512, third column, 

eighth line of paragraph (g) Example 1. 


emcdonald on DSK67QTVN1PROD with PROPOSALS