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 


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

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 

Coˆte 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, 


tkelley on DSK3SPTVN1PROD with RULES
80238 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 

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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 80239 

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 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 

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, 


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