### 80236 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

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):
2015–25–08 The Boeing Company: Amendment 39–18346; Docket No. FAA–2015–1281; Directorate Identifier 2014–NM–241–AD.
(a) Effective Date

This AD is effective January 28, 2016.

(b) Affected ADs

None. (c) Applicability

This AD applies to all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certificated in any category.
(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by an evaluation by the design approval holder indicating that the lap splices of the aft pressure bulkhead webs are subject to widespread fatigue damage on aging Model 777 airplanes that have accumulated at least 38,000 total flight cycles. We are issuing this AD to detect and correct fatigue cracking in the aft webs of the radial lap splices of the aft pressure bulkhead; such cracking could result in reduced structural integrity of the airplane, decompression of the cabin, and collapse of the floor structure.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspection of Lap Splice in the Web of the Aft Pressure Bulkhead

Except as required by paragraph (h) of this AD: At the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0078, dated December 5, 2014, do a medium frequency eddy current inspection for any cracking in the aft webs of the radial lap splices of the aft pressure bulkhead, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0078, dated December 5, 2014. Repeat the inspection thereafter at intervals not to exceed 8,400 flight cycles from the previous inspection. If any crack is found during any inspection required by this AD, do the applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0078, dated December 5, 2014. If a corrective action described in Boeing Alert Service Bulletin 777–53A0078, dated December 5, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (h) Exception to Service Information Specifications

Where Boeing Alert Service Bulletin 777– 53A0078, dated December 5, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.
(i) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle 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 (j) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD.

(4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (1)(4)(ii) of this AD apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.
(j) Related Information

For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6412; fax: 425– 917–6590; email: Eric.Lin@faa.gov.
(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 the AD specifies otherwise.

(i) Boeing Alert Service Bulletin 777– 53A0078, dated December 5, 2014.

(ii) Reserved. (3) 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.

(4) You may view this service information at 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 December 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–31715 Filed 12–23–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0625; Directorate Identifier 2014–NM–044–AD; Amendment**  **39–18343; AD 2015–25–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain


### 80237 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

Bombardier, Inc. Model CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601– 3A, CL–601–3R, and CL–604 Variants) airplanes. This AD was prompted by a report of an aft equipment bay fire due to chafing and subsequent arcing of the integrated drive generator (IDG) power cables. Additionally, we have received several reports of broken support brackets of the hydraulic line. This AD requires a one-time inspection of the IDG power cables for chafing, and for any cracked or broken support bracket of the hydraulic line; and corrective actions if necessary. We are issuing this AD to detect and correct broken support brackets of the hydraulic lines, which could result in inadequate clearance between the IDG power cables and hydraulic lines and chafing of the IDG power cables, and consequent high energy arcing and an uncontrolled fire in the aft equipment bay.

**DATES :**  This AD becomes effective January 28, 2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 28, 2016.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0625 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 Bombardier, Inc., 400 Co

ˆ te Vertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–85– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014–
0625.

**FOR FURTHER INFORMATION CONTACT :**  Assata Dessaline, Aerospace Engineer, Avionics and Service Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7301; fax (516) 794–5531.

**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 certain Bombardier, Inc. Model CL–600–2A12 (CL–601) and CL–600– 2B16 (CL–601–3A, CL–601–3R, and CL– 604 Variants) airplanes. The NPRM published in the Federal Register on September 17, 2014 (79 FR 55673).

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–05, dated January 20, 2014 (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:

There has been one reported case on the CL–600–2B19 aeroplane of an aft equipment bay fire occurring due to arcing of chafed integrated drive generator (IDG) power cables. Additionally, the hydraulic line support brackets located at the fuselage station (FS) 672 and FS 682 on a CL–600– 2B19 aeroplane could result in inadequate clearance between the IDG power cables and hydraulic lines, potentially resulting in chafing of the IDG power cables. Chafed IDG power cables can generate high energy arcing, which can result in an uncontrolled fire in the aft equipment bay.

It was found that a similar configuration exists on models CL–600–2A12 and CL–600– 2B16 aeroplanes. Therefore, a similar unsafe condition exists.

This [Canadian] AD mandates the detailed visual inspection and, if required, rectification of the IDG power cables and hydraulic line support bracket.

Required corrective actions include repair or replacement of the IDG power cable if any chafing is found, and replacement of any cracked or broken support bracket. You may examine the MCAI in the AD docket on the Internet
at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0625-
0003

. Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 55673, September 17, 2014) and the FAA’s response to each comment. Request To Correct Typographical Error

Bombardier asked that one of the service bulletin references identified in the ‘‘Relevant Service Information’’ section of the NPRM (79 FR 55673, September 17, 2014) be changed to correct a typographical error. Bombardier Service Bulletin ‘‘604– 0625,’’ as identified in the ‘‘Relevant Service Information’’ section, should be identified as Bombardier Service Bulletin ‘‘601–0625.’’ We agree with the commenter for the reason provided, and we have changed this reference to correctly specify Bombardier Service Bulletin 601–0625 throughout this final rule. Request To Clarify Credit Provisions

Bombardier asked that we clarify the language in paragraph (h) of the proposed AD, ‘‘Credit for Previous Actions.’’ Bombardier stated that the current language may cause some confusion because the content is not clear.

We acknowledge the commenter’s concern, and we provide the following clarification for the credit language used in paragraph (h) of this AD. Paragraph (h) of this AD matches the intent of the last two paragraphs in the ‘‘Corrective Actions’’ section of Canadian AD CF– 2014–05, dated January 20, 2014. Both this FAA AD and the Canadian AD give credit for accomplishing Bombardier Service Bulletins 605–24–007, 604–24– 026, and 601–0625, all dated September 18, 2012, but only if Service Request for Product Support Action (SRPSA) 27512, SRPSA 30806, SRPSA 32727, SRPSA 32864, or SRPSA 33161 has not been done. Clarification of Airplane Models

We have included the airplane models identified in the service information in the ‘‘Related Service Information under 1 CFR part 51’’ section, and paragraphs (g)(1), (g)(2), and (g)(3) of this AD (79 FR 55673, September 17, 2014), for clarification.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 55673, September 17, 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 55673, September 17, 2014).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

Bombardier has issued the following service information:

• Bombardier Service Bulletin 605– 24–007, Revision 01, dated January 13,


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2014 (for Model CL–600–2B16 airplanes (CL–604 Variant));

• Bombardier Service Bulletin 604– 24–026, Revision 01, dated January 13, 2014 (for Model CL–600–2B16 airplanes (CL–604 Variant)); and

• Bombardier Service Bulletin 601– 0625, Revision 01, dated January 13, 2014 (for Model CL–600–2A12 (CL–601) and CL–600–2B16 airplanes (CL–601– 3A and CL–601–3R Variants)).

This service information describes procedures for a one-time inspection of the IDG power cables for chafing, and for any cracked or broken support bracket of the hydraulic line; and corrective actions if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section. Costs of Compliance

We estimate that this AD affects 95 airplanes of U.S. registry.

We also estimate that it takes about 1 work-hour 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 $8,075, or $85 per product.

We have received no definitive data that would enable us to provide cost estimates for the on-condition repair of chafed power cables or cracked or broken support brackets, as specified in this 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 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. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA–2014–0625; 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 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. 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):
2015–25–05 Bombardier, Inc.: Amendment 39–18343; Docket No. FAA–2014–0625; Directorate Identifier 2014–NM–044–AD.

(a) Effective Date

This AD becomes effective January 28,
2016.
(b) Affected ADs

None. (c) Applicability This AD applies to Bombardier, Inc. airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.

(1) Model CL–600–2A12 (CL–601) airplanes, serial numbers 3001 through 3066 inclusive.

(2) Model CL–600–2B16 (CL–601–3A, CL– 601–3R Variants) airplanes, serial numbers 5001 through 5194 inclusive.

(3) Model CL–600–2B16 (CL–604 Variant) airplanes, serial numbers 5301 through 5665 inclusive, and 5701 through 5934 inclusive.
(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical Power.
(e) Reason

This AD was prompted by a report of an aft equipment bay fire due to chafing and subsequent arcing of the integrated drive generator (IDG) power cables. Additionally, we have received several reports of broken support brackets of the hydraulic lines. We are issuing this AD to detect and correct broken support brackets of the hydraulic lines, which could result in inadequate clearance between the IDG power cables and hydraulic lines and chafing of the IDG power cables, and consequent high energy arcing and an uncontrolled fire in the aft equipment bay.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) One-Time Inspection and Corrective Actions

Within 400 flight hours or 18 months after the effective date of this AD, whichever occurs first: Perform a one-time detailed inspection of the IDG power cables for chafing between the cables and the adjacent hydraulic and pneumatic lines, and for any cracked or broken support bracket of the hydraulic lines, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. If any chafing of the power cables or any cracked or broken support bracket is found, before further flight, repair or replace, as applicable, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.

(1) Bombardier Service Bulletin 605–24– 007, Revision 01, dated January 13, 2014 (for Model CL–600–2B16 airplanes (CL–604 Variant)).

(2) Bombardier Service Bulletin 604–24– 026, Revision 01, dated January 13, 2014 (for Model CL–600–2B16 airplanes (CL–604 Variant)).

(3) Bombardier Service Bulletin 601–0625, Revision 01, dated January 13, 2014 (for Model Cl-600–2A12 (CL–601) and CL–600– 2B16 airplanes (CL–601–3A and CL–601–3R Variants)).
(h) Credit for Previous Actions

This paragraph provides credit for action required by paragraph (g) of this AD, if the


### 80239 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

conditions specified in both paragraphs (h)(1) and (h)(2) of this AD are met.

(1) The action was performed before the effective date of this AD using Bombardier Service Bulletin 605–24–007, Bombardier Service Bulletin 604–24–026, or Bombardier Service Bulletin 601–0625, all dated September 18, 2012. This service information is not incorporated by reference in this AD.

(2) The action specified in Service Request for Product Support Action (SRPSA) 27512, SRPSA 30806, SRPSA 32727, SRPSA 32864, or SRPSA 33161 has not been done.
(i) 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 New York 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 516–794–553. 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, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO,the approval must include the DAOauthorized signature.
(j) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–05, dated January 20, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/#!documentDetail;D= FAA-2014-0625-0003.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD.
(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) Bombardier Service Bulletin 605–24– 007, Revision 01, dated January 13, 2014.

(ii) Bombardier Service Bulletin 604–24– 026, Revision 01, dated January 13, 2014. (iii) Bombardier Service Bulletin 601–0625, Revision 01, dated January 13, 2014.

(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 December 8, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–31604 Filed 12–23–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0083; Directorate Identifier 2014–NM–131–AD; Amendment**  **39–18347; AD 2015–25–09]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and all Model A340–200 and A340–300 series airplanes. This AD was prompted by reports that a bracket that attaches the cockpit instrument panel to the airplane structure does not sustain the fatigue loads of the design service goal. This AD requires repetitive inspections of that bracket for cracking and to determine if both lugs are fully broken, an inspection for cracking of an adjacent bracket if necessary, and corrective actions if necessary. This AD also provides an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct cracking on a bracket of the cockpit instrument panel, which, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, and reduced controllability of the airplane.

**DATES :**  This AD becomes effective January 28, 2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 28, 2016.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0083; 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 final rule, 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
0083.

**FOR FURTHER INFORMATION CONTACT :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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 certain Airbus Model A330– 200, A330–200 Freighter, and A330–300 series airplanes; and all Model A340– 200 and A340–300 series airplanes. The NPRM published in the Federal Register on February 13, 2015 (80 FR 7989).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0127, dated May 15, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200, A330–200 Freighter,