41114 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD, do a detailed inspection 

to determine the presence of panel thickness 

reduction of the lower panel joint with the 

side panels at stringer (STR) 24 left-hand and 

STR24 right-hand, in accordance with Airbus 

Military All Operator Letter (AOL) 235–024, 

Revision 01, dated March 1, 2013. 

(1) For airplane versions CG01, CL04, 

ED01, GC01, MM01, and SM01: Inspect at the 

later of the times specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD. 

(i) Before the accumulation of 1,900 total 

flight cycles. 

(ii) Within 10 flight cycles or 30 days after 

the effective date of this AD, whichever 

occurs first. 

(2) For any airplane version not identified 

in paragraph (g)(1) of this AD: Inspect at the 

later of the times specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Before the accumulation of 3,800 total 

flight cycles. 

(ii) Within 10 flight cycles or 30 days after 

the effective date of this AD, whichever 

occurs first. 

(h) Repetitive Nondestructive Testing (NDT) 

Inspections 

(1) For airplanes having MSNs C–196 

through C–200 inclusive and C–203 through 

C–208 inclusive, and for airplanes with a 

reduced panel thickness identified during the 

inspection required by paragraph (g) of this 

AD: At the applicable time specified in 

paragraph (g)(1)(i) of this AD (for airplanes 

identified in paragraph (g)(1) of this AD), or 

paragraph (g)(2)(i) of this AD (for airplanes 

identified in paragraph (g)(2) of this AD), or 

within 50 flight cycles after the effective date 

of this AD, whichever occurs later, do an 

NDT inspection for cracking, in accordance 

with Airbus Military AOL 235–024, Revision 

01, dated March 1, 2013. Repeat the 

inspection thereafter at the applicable time 

specified in paragraph (h)(1)(i) or (h)(1)(ii) of 

this AD. 

(i) For airplane versions CG01, CL04, ED01, 

GC01, MM01, and SM01: Inspect at intervals 

not to exceed 1,000 flight cycles. 

(ii) For airplane versions other than those 

identified in paragraph (h)(1)(i) of this AD: 

Inspect at intervals not to exceed 2,000 flight 

cycles. 

(2) If any cracking is detected during the 

inspection required by paragraph (h)(1) of 

this AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (j)(2) of 

this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

inspections required by paragraphs (g) and 

(h)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Military AOL 235–024, dated 

February 12, 2013. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1112; 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 European Aviation Safety Agency 

(EASA); or EADS CASA’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0131, dated 

June 25, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0980-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(l) 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 Military All Operator Letter 235– 

024, Revision 01, dated March 1, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(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/

ibr-locations.html. 

Issued in Renton, Washington, on June 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15804 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1025; Directorate 

Identifier 2013–NM–096–AD; Amendment 

39–17894; AD 2014–13–18] 

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 

Bombardier, Inc., Model DHC–8–102, 

–103, and –106 airplanes; and DHC–8– 

200 and DHC–8–300 series airplanes. 

This AD was prompted by a report of a 

beta warning horn (BWH) system failing 

to activate when the beta mode was 

triggered. This AD requires modifying 

the BWH microswitch installation. We 

are issuing this AD to prevent the 

inadvertent activation of ground beta 

mode during flight, which could lead to 

engine overspeed, engine damage or 

failure, and consequent reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

August 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 19, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1025 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., QSeries Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41115 

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. 

FOR FURTHER INFORMATION CONTACT: Kent 

Fredrickson, Aerospace Engineer, 

Propulsion and Flight Test Branch, 

ANE–173, FAA; NY Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7364; 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 

DHC–8–102, –103, and –106 airplanes; 

and DHC–8–200 and DHC–8–300 series 

airplanes. The NPRM published in the 

Federal Register on December 11, 2013 

(78 FR 75291). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–01R1, 

dated March 6, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

certain Bombardier, Inc., Model DHC– 

8–102, –103, and –106 airplanes; and 

DHC–8–200 and DHC–8–300 series 

airplanes. The MCAI states: 

* * * * * 

During an on-ground Beta Warning Horn 

(BWH) system check conducted in the wake 

of an in-flight Beta range operation incident 

on a DHC–8 Series 200 aeroplane, it was 

discovered that the BWH system failed to 

activate when the Beta mode was triggered. 

An investigation by Bombardier had 

determined that the deformation of the 

flexible center console cover could cause the 

BWH system triggering microswitch to 

malfunction, resulting in dormant failure of 

the BWH system. To mitigate the safety risk 

by minimizing the risk exposure period, 

[TCCA] * * * mandate[d] a 50 hours 

periodic operational test of the BWH system 

functionality. 

To address the root cause of the subject 

problem, Bombardier has issued Service 

Bulletin (SB) 8–76–33 that modifies the BWH 

microswitch installation by replacing the 

BWH microswitch attachment bracket with a 

new, more robust bracket that is not affected 

by deformation of the center console cover. 

[Canadian] AD CF–2012–01 is therefore 

revised to mandate compliance with SB 8– 

76–33 as terminating action for the 50 hours 

periodic operational test requirement. 

The unsafe condition is the inadvertent 

activation of ground beta mode during 

flight, which could lead to engine 

overspeed, engine damage or failure, 

and consequent reduced controllability 

of the airplane. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-1025- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 75291, December 11, 2013) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in this AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all Mandatory Continuing 

Airworthiness Information (MCAI) ADs 

in which the FAA develops an AD 

based on a foreign authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (78 FR 75291, December 

11, 2013), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (78 FR 75291, December 11, 2013 

about these proposed changes. However, 

a comment was provided for another 

NPRM, Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the action must be accomplished using 

a method approved by the FAA, 

Transport Canada Civil Aviation 

(TCCA), or Bombardier’s TCCA Design 

Approval Organization (DAO). Where 

necessary throughout this AD, we also 

replaced any reference to approvals of 

corrective actions with a reference to the 

Contacting the Manufacturer paragraph. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

are TCCA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not DAO-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 


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41116 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

discussed previously, Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), pointed out 

that in many cases the foreign 

manufacturer’s service bulletin and the 

foreign authority’s MCAI might have 

been issued some time before the FAA 

AD. Therefore, the DOA might have 

provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘DAH with State of Design Authority 

design organization approval,’’ but 

instead we have provided the specific 

delegation approval granted by the State 

of Design Authority for the DAH in the 

Contacting the Manufacturer paragraph. 

Conclusion 

We reviewed the relevant data 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 (78 FR 

75291, December 11, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 75291, 

December 11, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 94 

airplanes of U.S. registry. 

We also estimate that it will take 

about 7 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $117 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $66,928, or $712 

per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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-2013-1025; 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): 

2014–13–18 Bombardier, Inc.: Amendment 

39–17894. Docket No. FAA–2013–1025; 

Directorate Identifier 2013–NM–096–AD. 

(a) Effective Date 

This AD becomes effective August 19, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc., 

Model DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes; certificated 

in any category; serial numbers 003 through 

672 inclusive with a beta warning horn 

(BWH) (Mod 8/2852) incorporated; except for 

airplanes that have incorporated Bombardier 

option CR873CH00003, CR873CH00005, 

CR873SOO8112, or MS8Q902206. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 31, Instruments; Code 76, 

Engine Controls. 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41117 

(e) Reason 

This AD was prompted by a report of a 

BWH system failing to activate when the beta 

mode was triggered. We are issuing this AD 

to prevent the inadvertent activation of 

ground beta mode during flight, which could 

lead to engine overspeed, engine damage or 

failure, and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Terminating Modification 

Within 6,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD: Modify the BWH microswitch 

installation by replacing the existing BWH 

microswitch installation bracket with a new 

bracket having part number 87610164–003, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–76–33, dated December 13, 2012. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) 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 

Transport Canada Civil Aviation (TCCA); or 

Bombardier’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–01R1, 

dated March 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1025-0002. 

(j) 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 8–76–33, 

dated December 13, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@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 June 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15952 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0395; Directorate 

Identifier 2014–SW–016–AD; Amendment 

39–17876; AD 2014–06–51] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Airbus Helicopters) (Type Certificate 

Previously Held by Eurocopter 

Deutschland GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Airbus 

Helicopters Model MBB–BK 117 A–3, 

MBB–BK 117 A–4, MBB–BK 117 B–1, 

and MBB–BK 117 C–2 helicopters with 

a certain Metro Aviation, Inc. (Metro), 

vapor-cycle air conditioning kit pulley 

(pulley) installed, which was sent 

previously to all known U.S. owners 

and operators of these helicopters. This 

AD supersedes AD 2013–12–06, which 

required inspecting the pulley for 

looseness and properly installed 

lockwire and re-installing the pulley. 

Since we issued AD 2013–12–06, we 

received a report of a possible design 

and manufacturing deficiency in some 

pulleys wherein they did not have 

sufficient thread depth, allowing the 

pulley to detach from the rotor brake 

disc. This AD requires inspecting each 

pulley attaching bolt hole to determine 

if there is sufficient depth of the threads 

and either removing the pulley if the 

depth is insufficient or installing dual 

locking tabs under each pulley attaching 

bolt if the depth is sufficient. These 

actions are intended to prevent the 

pulley from detaching, resulting in 

damage to the tail rotor (T/R) driveshaft, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

30, 2014 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

(EAD) 2014–06–51, issued on March 24, 

2014, which contains the requirements 

of this AD. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 30, 2014. 

We must receive comments on this 

AD by September 15, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov 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 economic 

evaluation, any incorporated by 

reference service information, 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 service information identified in 

this AD, contact Metro Aviation, Inc., 


wreier-aviles on DSK5TPTVN1PROD with RULES