5020 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

ANE–170, FAA; or Transport Canada Civil 

Aviation (TCCA); or Bombardier, Inc.’s TCCA 

Design Approval Organization (DAO). The 

initial compliance time for the operational 

test is within 100 flight hours after the 

effective date of this AD. 

Note 1 to paragraph (h) of this AD: 

Bombardier Task 27–41–00–101, Operational 

Test (BITE) of the Horizontal Stabilizer Trim 

Controls System (HSTCS), provides guidance 

for the operational test specified in paragraph 

(h) of this AD. Bombardier Task 27–41–00– 

101 is included in the Bombardier Challenger 

604 Time Limits/Maintenance Checks 

(TLMC) Manual; and in the Bombardier 

Challenger 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 (m)(1) of 

this AD. 

(j) HSTA Replacement 

For airplanes equipped with a HSTA 

having P/N 604–92305–3 (vendor P/N 

845401) 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 

845401) or P/N 604–92305–5 (vendor P/N 

8454–2) with a 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, 

Revision 02, dated April 22, 2014; or 

Bombardier Service Bulletin 605–27–002, 

Revision 02, dated April 22, 2014; as 

applicable. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (j) of this AD 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraphs (k)(1) 

through (k)(4) of this AD, as applicable. This 

service information is not incorporated by 

reference in this AD. 

(1) Bombardier Service Bulletin 604–27– 

032, dated September 10, 2012. 

(2) Bombardier Service Bulletin 604–27– 

032, Revision 01, dated April 29, 2013. 

(3) Bombardier Service Bulletin 605–27– 

002, dated September 10, 2012. 

(4) Bombardier Service Bulletin 605–27– 

002, Revision 01, April 29, 2013. 

(l) 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 604– 

92305–5 (vendor P/N 8454–2) on any 

airplane. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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) 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, New York ACO, ANE–170; 

or TCCA; or Bombardier, Inc.’s TCCA Design 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(n) 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/

#!documentDetail;D=FAA-2014-0231-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 604–27– 

032, Revision 02, dated April 22, 2014. 

(ii) Bombardier Service Bulletin 605–27– 

002, Revision 02, dated April 22, 2014. 

(iii) Bombardier Temporary Revision 604/ 

37, dated May 21, 2013, to the Bombardier 

Challenger CL–604 Airplane Flight Manual, 

PSP 604–1. 

(iv) Bombardier Temporary Revision 605/ 

18, dated May 21, 2013, to the Bombardier 

Challenger CL–605 Airplane Flight Manual, 

PSP 605–1. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01171 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0079; Directorate 

Identifier 2013–NM–091–AD; Amendment 

39–18085; AD 2015–02–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–201, –202, –203, 

–301, –302, and –303 airplanes. This AD 

requires a one-time ultrasonic 

inspection for fractures of all aft mountpylon bolts of each engine. This AD was 

prompted by a report of one bolt on the 

aft engine mount upper beam found 

totally broken. We are issuing this AD 

to detect and correct fracture of the aft 

mount-pylon bolts, which could result 

in failure of the engine mount and 

consequent detachment of the engine. 

DATES: This AD becomes effective 

February 17, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 17, 2015. 

We must receive comments on this 

AD by March 16, 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– 


rljohnson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5021 

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 AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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– 

0079; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1138; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0094, dated April 15, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–201, –202, –203, –301, 

–302, and –303 airplanes. The MCAI 

states: 

During a scheduled replacement of a CF6– 

80E1 engine #1 on an A330 aeroplane, one 

bolt on the aft engine mount upper beam was 

found totally broken. That bolt is one of the 

four bolts that attach the upper beam to the 

pylon. 

The subsequent analyses of the broken bolt 

and the upper beam identified the following: 

—a fatigue origin area with crack propagation 

from the boundary of the bolt, 

—a spiral groove with cold work and 

microstructural distortion underlying that 

extended axially along the shank, and 

—a score mark on counter-bore edge of the 

upper beam. 

The preliminary root-cause investigation 

shows that an unusual contact with the 

counter-bore edge of the beam induced a 

significant groove on the bolt during its 

installation in production. It is suspected that 

this groove led to a fatigue crack initiation 

and subsequent quick propagation leading to 

the complete fracture of the bolt. 

As the root-cause is still under 

investigation, including the installation 

sequence specific to this aeroplane—engine 

model, the other A330 propulsion systems 

are not affected. 

This condition, if not detected and 

corrected, could lead, in conjunction with a 

second fractured bolt, to the loss of engine 

mount structural integrity and potential 

engine detachment in flight as the remaining 

bolts would not be able to sustain the 

residual fatigue and limit loads. 

For the reasons described above, this 

[EASA] AD requires a one-time ultrasonic 

inspection of the four aft mount-pylon bolts 

of both engines for detection of completely 

sheared [fractured] bolts through the bolt 

section and, depending on finding, 

accomplishment of applicable corrective 

actions [repair]. 

This [EASA] AD is considered as an 

interim action, pending the results of the 

ongoing investigations, and further AD action 

may follow. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0079. 

Related Service Information 

Airbus has issued Alert Operators 

Transmission (AOT) A71L002–13, dated 

April 8, 2013. The service information 

describes procedures to perform a onetime ultrasonic inspection for fractures 

of all aft mount-pylon bolts of each 

engine. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0079; 

Directorate Identifier 2013–NM–091– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 0 

airplanes of U.S. registry. 

We also estimate that it will take 

about 3 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $255 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition action 

specified in this AD. We have no way 

of determining the number of aircraft 

that might need this action. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 


rljohnson on DSK4SPTVN1PROD with RULES
5022 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2015–02–18 Airbus: Amendment 39–18085. 

Docket No. FAA–2015–0079; Directorate 

Identifier 2013–NM–091–AD. 

(a) Effective Date 

This AD becomes effective February 17, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –301, –302, and –303 

airplanes, certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a report of one 

bolt on the aft engine mount upper beam 

found totally broken. We are issuing this AD 

to detect and correct fracture of the aft 

mount-pylon bolts, which could result in 

failure of the engine mount and consequent 

detachment of the engine. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Bolt Inspection 

Within 1,000 flight hours after the effective 

date of this AD, do a one-time ultrasonic 

inspection for fractures of all aft mount-pylon 

bolts of each engine, in accordance with 

Airbus Alert Operators Transmission (AOT) 

A71L002–13, dated April 8, 2013. If any 

fracture is detected, repair before further 

flight 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). 

(h) Reporting 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Airbus, at the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD. Send the 

report to the contact for inspection results 

specified in paragraph 7, ‘‘REPORTING,’’ of 

Airbus AOT A71L002–13, dated April 8, 

2013. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1138; 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’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0094, dated 

April 15, 2013, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–0079. 


rljohnson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5023 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A71L002–13, dated April 8, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

15, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01174 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0622; Directorate 

Identifier 2014–NM–009–AD; Amendment 

39–18080; AD 2015–02–13] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(Embraer) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Empresa Brasileira de Aeronautica S.A. 

(Embraer) Model EMB–135ER, –135KE, 

–135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP airplanes. This AD was 

prompted by a determination of the 

need to revise the airplane 

airworthiness limitations related to the 

pylon yokes I and II, and the skin panel 

of the windshield pillar. This AD 

requires revising the maintenance or 

inspection program, as applicable. We 

are issuing this AD to prevent fatigue 

cracking of various structural elements, 

which could affect the structural 

integrity of the airplane. 

DATES: This AD becomes effective 

March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 6, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0622; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

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 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. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Embraer Model EMB 

–135ER, –135KE, –135KL, –135LR, 

–145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP 

airplanes. The NPRM published in the 

Federal Register on September 4, 2014 

(79 FR 52588). 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Airworthiness Directive 2014–01–01, 

dated January 20, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Embraer Model EMB –135ER, 

–135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, 

–145MP, and –145EP airplanes. The 

MCAI states: 

This [Brazilian] AD was prompted by a 

new revision to the airworthiness limitations 

requirements [related to the pylon yokes I 

and II, and the skin panel of the windshield 

pillar] of the Maintenance Review Board 

Report. We are issuing this [Brazilian] AD to 

ensure that fatigue cracking of various 

structural elements is detected and corrected. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0622- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 52588, September 4, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

52588, September 4, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 52588, 

September 4, 2014). 

Related Service Information 

We reviewed EMBRAER EMB145 

Temporary Revision 15–3, dated August 

26, 2013, to the Airworthiness 

Limitation Requirements of the 

EMBRAER EMB145 Maintenance 

Review Board Report MRB 145/1150; 

and EMBRAER EMB145 Temporary 

Revision 15–4, dated August 26, 2013, 

to the Airworthiness Limitation 

Requirements of the EMBRAER EMB145 

Maintenance Review Board Report 

MRB–145/1150. The service information 

describes airworthiness limitations 

related to inspections of certain fuselage 

or pylon components. You can find this 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0622. 

Costs of Compliance 

We estimate that this AD affects 688 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 


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