### 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 Co ˆ te 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 ultrasonicinspection 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–


### 5021 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations

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 informationdescribes 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.


### 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.


### 5023 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations

(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 Age ˆ ncia 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