Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44663 

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 Airbus’s EASA Design 

Organization Approval (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. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0146, dated 

June 11, 2014, for related information. You 

may examine the MCAI on the Internet at 

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

and locating Docket No. FAA–2014–0486. 

(m) 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 

A53N006–14, dated May 13, 2014. 

(ii) Airbus Service Bulletin A320–53–1285, 

dated January 29, 2014. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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 July 12, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17782 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0228; Directorate 

Identifier 2013–NM–216–AD; Amendment 

39–17911; AD 2014–15–09] 

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 all 

Airbus Model A330–200 Freighter, 

A330–200 and –300, and A340–200, 

–300, –500, and –600 series airplanes. 

This AD was prompted by reassessment 

of an unsafe condition related to MZtype spoiler servo-controls (SSCs) that 

did not remain locked in the retracted 

position (hydraulic locking function) 

after manual depressurization of the 

corresponding hydraulic circuit. This 

reassessment resulted in the 

determination that performing repetitive 

operational tests of all SSC types is 

necessary. This AD requires repetitive 

operational tests of the hydraulic 

locking function on each SSC installed 

on the blue or yellow hydraulic circuits, 

and replacing any affected SSC with a 

serviceable SSC. We are issuing this AD 

to detect and correct loss of the 

hydraulic locking function during takeoff, which, in combination with one 

inoperative engine, could result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 5, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0228 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 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. 

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 all Airbus Model A330–200 

Freighter, A330–200 and –300, and 

A340–200, –300, –500, and –600 series 

airplanes. The NPRM published in the 

Federal Register on April 14, 2014 (79 

FR 20839). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0251 

dated October 15, 2013; Correction 

dated October 16, 2013 (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: 

During post-flight maintenance checks 

accomplished on an A330 and on an A340 

airplane, it was identified that seven spoiler 

servo-controls MZ series had lost their 

hydraulic locking function. The results of the 

subsequent technical investigation 

accomplished in-shop by the part supplier 

confirmed the system failure was due to a 

sheared seal on the blocking valve, ensuring 

the blocking function of the spoiler. It is 

suspected that the seal damage may have 

occurred during accomplishment of a 

modification to fit a new design of 

maintenance cover on wing, required by 

EASA AD 2008–0160 [http://

ad.easa.europa.eu/blob/easa_ad_2008_

0160.pdf/AD_2008–0160], [which 

corresponds to FAA AD 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009)]. 


emcdonald on DSK67QTVN1PROD with RULES
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This condition, if not detected and 

corrected, in combination with one engine 

inoperative at take-off, could result in 

reduced control of the aeroplane. 

Prompted by these findings, Airbus issued 

All Operators Telex (AOT) A330–27A3185 

and AOT A340–27A4181 to request a onetime operational test of the Hydraulic 

Locking Function for aeroplanes on which 

MZ type Spoiler Servo Control (SSC) Part 

Number (P/N) MZ4339390–12 or P/N 

MZ4306000–12 are fitted, and EASA issued 

AD 2012–0009 [http://ad.easa.europa.eu/

blob/easa_ad_2012_0009.pdf/AD_2012–0009, 

which corresponds to FAA AD 2012–25–10, 

Amendment 39–17291 (77 FR 76228, 

December 27, 2012)] to require 

accomplishment of this test. 

Since that [EASA] AD was issued, Airbus 

re-assessed the situation and determined that 

it is necessary to introduce repetitive 

inspections [operational tests] of the SSC, 

irrespective of SSC type. Airbus issued three 

SBs for those repetitive inspections 

[operational tests] on all A330, A340, and 

A340–500/600 aeroplanes. 

For the reason described above, this 

[EASA] AD requires repetitive operational 

tests of the hydraulic locking function of the 

SSC installed on the Blue and Yellow 

hydraulic circuits, irrespective of the SSC 

type, and, depending on test results, 

replacement of the SSC. 

This [EASA] AD has been republished to 

correct the date of publication. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA–2014–0228– 

0002. 

Revised Service Information 

Since the NPRM (79 FR 20839, April 

14, 2014) was published, we have 

received the following revised service 

information: 

• Airbus Service Bulletin A330–27– 

3195, Revision 01, dated February 6, 

2014. 

• Airbus Service Bulletin A340–27– 

4188, Revision 01, dated February 6, 

2014. 

• Airbus Service Bulletin A340–27– 

5059, Revision 01, dated February 6, 

2014. 

We have determined that this service 

information does not add any additional 

actions to those proposed in the NPRM 

(79 FR 20839, April 14, 2014); therefore, 

we have revised paragraph (g) of this AD 

to refer to that service information. We 

have also added a new paragraph (h) to 

this AD (and redesignated subsequent 

paragraphs accordingly) to provide 

credit for actions performed before the 

effective date of this AD using the 

following service information: 

• Airbus Service Bulletin A330–27– 

3195, dated December 7, 2012. 

• Airbus Service Bulletin A340–27– 

4188, dated December 7, 2012. 

• Airbus Service Bulletin A340–27– 

5059, dated April 10, 2013. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 20839, April 14, 2014) 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 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 (79 FR 20839, April 14, 

2014), 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 (79 FR 20839, April 14, 2014) 

about these proposed changes. However, 

a comment was provided for an NPRM 

having 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 the 

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 actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

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

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

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 

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. 


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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44665 

Other commenters to the NPRM 

having 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 throughout this 

AD. 

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 (79 FR 

20839, April 14, 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 20839, 

April 14, 2014). 

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 77 

airplanes of U.S. registry. 

We also estimate that it takes about 6 

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 the AD on U.S. operators to be 

$39,270, or $510 per product. 

We estimate that it takes about 3 

work-hours per product to do any 

necessary SSC replacement that would 

be required based on the results of the 

operational test. Required parts cost 

about $35,000 per SSC. We have no way 

of determining the number of aircraft 

that might need these replacements. 

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-2013-0597; 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): 

2014–15–09 Airbus: Amendment 39– 

17911. Docket No. FAA–2014–0228; 

Directorate Identifier 2013–NM–216–AD. 

(a) Effective Date 

This AD becomes effective September 5, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; Model A340–211, 

–212, –213, –311, –312, and –313 airplanes; 

and Model A340–541 and –642 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reassessment of 

an unsafe condition related to MZ-type 

spoiler servo-controls (SSCs) that did not 

remain locked in the retracted position 

(hydraulic locking function) after manual 

depressurization of the corresponding 

hydraulic circuit. This reassessment resulted 

in the determination that performing 

repetitive operational tests of all SSC types 

is necessary. We are issuing this AD to detect 

and correct loss of the hydraulic locking 

function during take-off, which, in 

combination with one inoperative engine, 

could result in reduced controllability of the 

airplane. 


emcdonald on DSK67QTVN1PROD with RULES
44666 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Operational Tests 

(1) At the time specified in paragraph (g)(2) 

of this AD: Accomplish an operational test of 

the hydraulic locking function on each SSC 

(any type), when fitted on the Blue or Yellow 

hydraulic circuits, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. Repeat the operational test thereafter 

at intervals not to exceed 48 months. 

(i) Airbus Service Bulletin A330–27–3195, 

Revision 01, dated February 6, 2014 (for 

Model A330–200 Freighter, A330–200 and 

–300 series airplanes). 

(ii) Airbus Service Bulletin A340–27–4188, 

Revision 01, dated February 6, 2014 (for 

Model A340–200, and –300 series airplanes). 

(iii) Airbus Service Bulletin A340–27– 

5059, Revision 01, dated February 6, 2014 

(for Model A340–500 and –600 series 

airplanes). 

(2) At the latest of the times specified in 

paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of 

this AD, do the operational test specified in 

paragraph (g)(1) of this AD. 

(i) Within 48 months since first flight of the 

airplane. 

(ii) Within 48 months since accomplishing 

the most recent operational test, as specified 

in the applicable Airbus All Operators Telex 

(AOT) A330–27A3185; or AOT A340– 

27A4181; both dated January 4, 2012. These 

AOTs were incorporated by reference in AD 

2012–25–10, Amendment 39–17291 (77 FR 

76228, December 27, 2012). 

(iii) Within 24 months after the effective 

date of this AD. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information identified in paragraph 

(h)(1), (h)(2), or (h)(3) of this AD, which is 

not incorporated by reference in this AD. 

(i) Airbus Service Bulletin A330–27–3195, 

dated December 7, 2012. 

(ii) Airbus Service Bulletin A340–27–4188, 

dated December 7, 2012. 

(iii) Airbus Service Bulletin A340–27– 

5059, dated April 10, 2013. 

(i) Replacement of Affected SSCs 

If, during any operational test required by 

paragraph (g)(1) of this AD, the hydraulic 

locking function of an SSC fails the test, 

before further flight, replace the affected SSC 

with a serviceable part, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. 

(j) No Terminating Action 

Doing the replacement required by 

paragraph (i) of this AD is not terminating 

action for the repetitive operational tests 

required by paragraph (g)(1) of this AD. 

(k) 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, WA 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0251 dated October 15, 2013; 

Correction dated October 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-2014-0228-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(m) 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 Service Bulletin A330–27–3195, 

Revision 01, dated February 6, 2014. 

(ii) Airbus Service Bulletin A340–27–4188, 

Revision 01, dated February 6, 2014. 

(iii) Airbus Service Bulletin A340–27– 

5059, Revision 01, dated February 6, 2014. 

(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 July 17, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17468 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0196; Directorate 

Identifier 2014–NM–015–AD; Amendment 

39–17913; AD 2014–15–11] 

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 CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This AD was prompted by 

two in-service reports of fracture of the 

rudder pedal tubes installed on the 

pilot-side rudder bar assembly. This AD 

requires repetitive inspections for 

cracking and damage of the pilot-side 

rudder pedal tubes, and corrective 

action if necessary. This AD also 

provides optional terminating action for 

the repetitive inspections. We are 

issuing this AD to detect and correct 

cracked and damaged pilot-side rudder 

pedal tubes, which could result in loss 

of function of the pilot’s rudder pedal 

during flight, takeoff, or landing, and 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

September 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 


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