21160 Federal Register / Vol. 79, No. 72 / Tuesday, April 15, 2014 / Proposed Rules 

Bombardier, Inc.: Docket No. FAA–2014– 

0231; Directorate Identifier 2013–NM– 

163–AD. 

(a) Comments Due Date 

We must receive comments by May 30, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 (CL–604 Variant) airplanes, 

certificated in any category, serial numbers 

5301 and subsequent, equipped with 

horizontal stabilizer trim actuator (HSTA) 

part number (P/N) 604–92305–3 (vendor P/N 

8454–1) or P/N 604–92305–5 (vendor P/N 

8454–2). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of loose, 

broken, or backed out spur gear bolts on the 

HSTA. We are issuing this AD to detect and 

correct loose spur gear bolts on the HSTA, 

which, if combined with the failure of the 

primary load path, could lead to failure of the 

HSTA and subsequent loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Airplane Flight Manual (AFM) Revision 

Within 30 days after the effective date of 

this AD, revise the Normal Procedures 

section of the applicable Bombardier AFM to 

include the information in the applicable 

temporary revision (TR) specified in 

paragraph (g)(1) or (g)(2) of this AD. The TRs 

introduce revised procedures for the 

stabilizer trim system check. Operate the 

airplane according to the limitations and 

procedures in the applicable TR. The 

revision may be done by inserting copies of 

the applicable TR specified in paragraph 

(g)(1) or (g)(2) of this AD in the AFM. When 

the TR has been included in the general 

revisions of the AFM, the general revisions 

may be inserted in the AFM, provided the 

relevant information in the general revision 

is identical to that in the applicable TR and 

the TR may be removed. 

(1) Bombardier TR 604/37, dated May 21, 

2013, to the Bombardier CL–604 AFM, PSP 

604–1. 

(2) Bombardier TR 605/18, dated May 21, 

2013, to the Bombardier CL–605 AFM, PSP 

605–1. 

(h) Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating Task 27–41–00–101, 

Operational Test (BITE) of the HorizontalStabilizer Trim-control System (HSTCS), 

specified in the applicable revision 

submission (RS) specified in paragraph (h)(1) 

or (h)(2) of this AD. The initial compliance 

time for the operational test is within 100 

flight hours after the effective date of this AD. 

The maintenance or inspection program 

revision may be done by inserting a copy of 

the applicable RS specified in paragraph 

(h)(1) or (h)(2) of this AD into the applicable 

time limits/maintenance checks (TLMC) 

manual. When the RS has been included in 

the general revisions of the TLMC manual, 

the general revisions may be inserted in the 

TLMC manual, provided the relevant 

information in the general revision is 

identical to that in the applicable RS, and the 

RS may be removed. 

(1) Task 27–41–00–101, Operational Test 

(BITE) of the Horizontal-Stabilizer Trimcontrol System (HSTCS), specified in 

Bombardier Revision Submission RS–CL604– 

055, dated April 27, 2012, to Section 5–10– 

40, Certification Maintenance Requirements, 

of Chapter 5 of the Bombardier CL–604 Time 

Limits/Maintenance Checks (TLMC) Manual. 

(2) Task 27–41–00–101, Operational Test 

(BITE) of the Horizontal-Stabilizer Trimcontrol System (HSTCS), specified in 

Bombardier Revision Submission RS–CL605– 

030, dated April 27, 2012, to Section 5–10– 

40, Certification Maintenance Requirements, 

of Chapter 5 of the Bombardier CL–605 

TLMC Manual. 

(i) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised, as required by 

paragraph (h) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l)(1) of 

this AD. 

(j) HSTA Replacement 

For airplanes equipped with an HSTA 

having P/N 604–92305–3 (vendor P/N 8454– 

1) or P/N 604–92305–5 (vendor P/N 8454–2): 

Within 3,000 flight hours or 26 months after 

the effective date of this AD, whichever 

occurs first, replace any HSTA having P/N 

604–92305–3 (vendor P/N 8454–1) or P/N 

604–92305–5 (vendor P/N 8454–2) with an 

HSTA having P/N 604–92305–7 (vendor P/N 

8454–3), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 604–27–032, dated 

September 10, 2012; or 605–27–002, dated 

September 10, 2012; as applicable. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any HSTA having P/N 

604–92305–3 (vendor P/N 8454–1) or P/N 

604–92305–5 (vendor P/N 8454–2) on any 

airplane. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval, as 

applicable). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–18, dated 

July 16, 2013, 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– 

2014–0231. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. 

Issued in Renton, Washington, on April 1, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–08463 Filed 4–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0234; Directorate 

Identifier 2013–NM–220–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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Federal Register / Vol. 79, No. 72 / Tuesday, April 15, 2014 / Proposed Rules 21161 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135BJ 

airplanes. This proposed AD was 

prompted by reports of failure of the 

bolts that connect the cockpit 

windshield center-post to the forward 

fuselage. This proposed AD would 

require repetitive detailed inspections to 

detect discrepancies on the attaching 

parts of the cockpit windshield centerpost; checking whether the bolts are 

tightened, if applicable; and modifying 

parts, including inspecting for and 

repairing damage. The modification 

would terminate the repetitive 

inspections. We are proposing this AD 

to prevent failed bolts and failed 

attaching parts of the cockpit 

windshield center-post, which could 

lead to loss of structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 30, 2014. 

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 service information identified in 

this proposed AD, contact Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER), Technical Publications 

Section (PC 060), Av. Brigadeiro Faria 

Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; 

telephone +55 12 3927–5852 or +55 12 

3309–0732; fax +55 12 3927–7546; 

email distrib@embraer.com.br; Internet 

http://www.flyembraer.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–2014– 

0234; 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1175; 

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–2014–0234; Directorate Identifier 

2013–NM–220–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 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil, which is the aviation authority for 

Brazil, has issued Brazilian 

Airworthiness Directive 2013–10–02, 

dated October 23, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

This [Brazilian] AD was prompted by 

reports of failure of the bolts that connect the 

lower eyelet fitting of the cockpit windshield 

center-post to the forward fuselage. We are 

issuing this [Brazilian] AD to detect failed 

bolts and correct the attaching parts of the 

lower eyelet fitting of the cockpit windshield 

center-post, which could lead to loss of 

structural integrity of the airplane. 

Required actions include repetitive 

detailed inspections for discrepancies 

on the attaching parts of the lower 

eyelet fitting of the cockpit windshield 

center-post; a bolt check, if applicable; 

and modification of the attaching parts 

of the lower eyelet fitting of the cockpit 

windshield center-post, including a 

general visual inspection for damage of 

the specified lower eyelet fitting and 

repair of the damage. The modification 

would terminate the repetitive detailed 

inspections. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov by 

searching for and locating it in Docket 

No. FAA–2014–0234. 

Relevant Service Information 

EMBRAER has issued Service Bulletin 

145LEG–53–A032, Revision 1, dated 

September 24, 2013. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 


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21162 Federal Register / Vol. 79, No. 72 / Tuesday, April 15, 2014 / Proposed Rules 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, this 

proposed AD would require that the 

repair approval specifically refer to the 

FAA AD. This change is intended to 

clarify the method of compliance and to 

provide operators with better visibility 

of repairs that are specifically developed 

and approved to correct the unsafe 

condition. In addition, we use the 

phrase ‘‘its delegated agent, or the DAH 

with State of Design Authority design 

organization approval, as applicable’’ in 

this proposed AD to refer to a DAH 

authorized to approve required repairs 

for this proposed AD. 

Clarification of Requirements 

Brazilian Airworthiness Directive 

2013–10–02, dated October 23, 2013, 

specifies that for those airplanes 

identified in Group 1 of EMBRAER 

Service Bulletin 145LEG–53–A032, 

Revision 01, dated September 24, 2013, 

that have done certain actions specified 

in EMBRAER Service Bulletin 145LEG– 

53–0021, dated June 8, 2005, and 

EMBRAER Service Bulletin 145LEG– 

53–0021, Revision 01, dated July 13, 

2007, to do those actions at certain 

compliance times. For those actions, 

this AD specifies the affected airplanes 

as airplanes identified in Group 1 of 

EMBRAER Service Bulletin 145LEG– 

53–A032, Revision 01, dated September 

24, 2013, that have done the actions 

specified in any revision of EMBRAER 

Service Bulletin 145LEG–53–0021. This 

difference has been coordinated with 

the Ageˆncia Nacional de Aviac ̧a ̃o Civil. 

Costs of Compliance 

We estimate that this proposed AD 

affects 56 airplanes of U.S. registry. 

We also estimate that it would take 

about 35 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 about $386 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $188,216, or $3,361 

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: 

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): 

Empresa Brasileira de Aeronautica S.A. 

(Embraer): Docket No. FAA–2014–0234; 

Directorate Identifier 2013–NM–220–AD. 

(a) Comments Due Date 

We must receive comments by May 30, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Empresa Brasileira de 

Aeronautica S.A. (EMBRAER) Model EMB– 

135BJ airplanes, certificated in any category, 

as identified in EMBRAER Service Bulletin 

145LEG–53–A032, Revision 01, dated 

September 24, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of failure 

of the bolts that connect the cockpit 

windshield center-post to the forward 

fuselage. We are issuing this AD to prevent 

failed bolts and failed attaching parts of the 

cockpit windshield center-post, which could 

lead to loss of structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, do a 

detailed inspection to detect discrepancies 

on the attaching parts of the lower eyelet 

fitting of the cockpit windshield center-post 

and, if applicable, check whether the bolts 

are tightened, in accordance with Part I of the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145LEG–53–A032, Revision 

01, dated September 24, 2013. If any 

discrepancy is found or if any bolt is not 

tightened, do the actions specified in 

paragraph (h) of this AD before further flight. 

Repeat the detailed inspection thereafter at 

intervals not to exceed 50 flight cycles until 

the modification required by paragraph (h) of 

this AD is done. 

(1) For airplanes identified as Group 1 in 

EMBRAER Service Bulletin 145LEG–53– 

A032, Revision 01, dated September 24, 

2013, on which the actions of EMBRAER 

Service Bulletin 145LEG–53–0021, has been 

done: Do the detailed inspection within 

3,000 flight cycles after accomplishment of 

the actions of EMBRAER Service Bulletin 

145LEG–53–0021, or within 50 flight cycles 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes identified as Group 2 

airplanes in EMBRAER Service Bulletin 

145LEG–53–A032, Revision 01, dated 

September 24, 2013: Do the detailed 

inspection before the accumulation of 3,000 

total flight cycles, or within 50 flight cycles 

after the effective date of this AD, whichever 

occurs later. 

(h) Modification 

Except as required by paragraph (g) of this 

AD, at the applicable time specified in 

paragraphs (h)(1) or (h)(2) of this AD, modify 

the attaching parts of the lower eyelet fitting 


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Federal Register / Vol. 79, No. 72 / Tuesday, April 15, 2014 / Proposed Rules 21163 

of the cockpit windshield center-post, 

including a general visual inspection for any 

damage (cracks, dents, scratches) of the 

specified lower eyelet fitting, in accordance 

with Part II of the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145LEG–53–A032, Revision 01, dated 

September 24, 2013. If any damage is found 

during the general visual inspection, before 

further flight repair using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

The Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC) (or its delegated agent, or the Design 

Approval Holder (DAH) with ANAC design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. The 

modification terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(1) For airplanes identified as Group 1 in 

EMBRAER Service Bulletin 145LEG–53– 

A032, Revision 01, dated September 24, 

2013, on which the actions specified in 

EMBRAER Service Bulletin 145LEG–53– 

0021, has been done: Do the modification 

before the accumulation of 3,000 flight cycles 

after doing the actions specified in 

EMBRAER Service Bulletin 145LEG–53– 

0021, or within 300 flight cycles after the 

effective date of this AD, whichever occurs 

later. 

(2) For airplanes identified as Group 2 in 

EMBRAER Service Bulletin 145LEG–53– 

A032, Revision 01, dated September 24, 

2013: Do the modification before the 

accumulation of 3,000 total flight cycles, or 

within 300 flight cycles after the effective 

date of this AD, whichever occurs later. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using EMBRAER 

Service Bulletin 145LEG–53–A032, dated 

September 20, 2013, which is not 

incorporated by reference in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directive 2013–10–02, dated 

October 23, 2013, 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 it in Docket No. 

FAA–2014–0234. 

(2) For service information identified in 

this AD, contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.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 April 1, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–08460 Filed 4–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[REG–144468–05] 

RIN 1545–BE98 

Disallowance of Partnership Loss 

Transfers, Mandatory Basis 

Adjustments, Basis Reduction in Stock 

of a Corporate Partner, Modification of 

Basis Allocation Rules for Substituted 

Basis Transactions, Miscellaneous 

Provisions; Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correction to a notice of 

proposed rulemaking and notice of 

public hearing. 

SUMMARY: This document contains 

corrections to a notice of proposed 

rulemaking and notice of public hearing 

(REG–144468–05) that was published in 

the Federal Register on Thursday, 

January 16, 2014. The proposed rules 

provide guidance on certain provisions 

of the American Jobs Creation Act of 

2004 and conform the regulations to 

statutory changes in the Taxpayer Relief 

Act of 1997. 

DATES: Written or electronic comments 

and requests for a public hearing for the 

notice of proposed rulemaking 

published at 79 FR 3042, January 16, 

2014, are still being accepted and must 

be received by April 16, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Benjamin Weaver or Wendy Kribell at 

(202) 317–6850 (not a toll free number). 

SUPPLEMENTARY INFORMATION: 

Background 

The notice of proposed rulemaking 

and notice of public hearing (REG– 

144468–05) that is the subject of these 

corrections is under sections 704, 732, 

734, 743, 755, and 1502 of the Internal 

Revenue Code. 

Need for Correction 

As published, the notice of proposed 

rulemaking and notice of public hearing 

(REG–144468–05) contains errors that 

may prove to be misleading and are in 

need of clarification. 

Correction of Publication 

Accordingly, the notice of proposed 

rulemaking and notice of public hearing 

(REG–144468–05), that was the subject 

of FR Doc. 2014–00649, is corrected as 

follows: 

1. On page 3042, in the preamble, 

third column, thirty-third line from the 

top of the page, the language ‘‘3,600.’’ is 

corrected to read ‘‘3,600 hours.’’. 

2. On page 3042, in the preamble, 

third column, fortieth line from the top 

of the page, the language ‘‘burden: 

2,700.’’ is corrected to read ‘‘burden: 

2,700 hours.’’. 

3. On page 3046, in the preamble, 

second column, twenty-fifth line of the 

first full paragraph, the language 

‘‘1(b)(2)(iv)(f) (‘‘reverse section 704(c)’’ 

is corrected to read ‘‘1(b)(2)(iv)(f) or 

§ 1.704–1(b)(2)(iv)(s) (‘‘reverse section 

704(c)’’. 

4. On page 3052, in the preamble, 

second column, tenth line from the 

bottom of the page, the language 

‘‘Questions have been raised whether 

the’’ is corrected to read ‘‘Questions 

have been raised regarding whether 

the’’. 

5. On page 3054, in the preamble, 

second column, seventh line from the 

top of the page, the language ‘‘by 

differences in the property’s adjusted’’ 

is corrected to read ‘‘by decreases in the 


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