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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of a certain publication 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–2014–0196 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 514–855– 

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. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; 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–600–2C10 (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. The NPRM published in the 

Federal Register on April 14, 2014 (79 

FR 20829). 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2014–02, dated January 8, 2014 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’). The MCAI states: 

There have been two in-service reports of 

fracture of the rudder pedal tubes installed 

on the pilot-side rudder bar assembly on CL– 

600–2B19 model aeroplanes. 

Laboratory examination of the fractured 

rudder pedal tubes found that in both cases, 

the fatigue cracks initiated at the aft taper pin 

holes where the connecting rod fitting is 

attached. Fatigue testing of the rudder pedal 

tubes confirmed that the fatigue cracking is 

due to loads induced during parking brake 

application. Therefore, only the rudder pedal 

tubes on the pilot’s side are vulnerable to 

fatigue cracking as the parking brake is 

primarily applied by the pilot. 

Loss of pilot rudder pedal input during 

flight would result in reduced yaw 

controllability of the aeroplane. Loss of pilot 

rudder pedal input during takeoff or landing 

may lead to a runway excursion. 

Although there have been no reported 

failures to date on any CL–600–2C10, –2D15, 

–2D24, and –2D25 model aeroplanes, the 

same torque tubes part number (P/N) 600– 

90204–3 are installed, which may be prone 

to premature fatigue cracking. 

This [Canadian] AD mandates initial and 

repetitive [detailed and eddy current] 

inspections [for cracking and damage] of the 

pilot-side rudder pedal tubes, P/N 600– 

90204–3, until the terminating action 

[replacement of both pilot-side rudder bar 

assemblies] is accomplished [and corrective 

actions if necessary]. 

Corrective actions include replacement 

of the rudder bar assembly and repair. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0196- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 20829, 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 20829, 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 20829, April 14, 2014) 

about these proposed changes. However, 

a comment was provided for a similar 

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, TCCA, 

or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). 

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 


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44668 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

not TCCA-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 

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 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 

20829, 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 20829, 

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 400 

airplanes of U.S. registry. 

We also estimate that it takes about 3 

work-hours per product to comply with 

the basic inspection 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 $102,000, or $255 per 

airplane, per inspection cycle. 

In addition, we estimate that any 

necessary replacement of the rudder 

pedal tubes takes about 6 work-hours 

and require parts costing $2,850, for a 

cost of $3,360 per product. We have no 

way of determining the number of 

aircraft that might need this action. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs 

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-2014-0196; 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): 

2014–15–11 Bombardier, Inc.: Amendment 

39–17913. Docket No. FAA–2014–0196; 

Directorate Identifier 2014–NM–015–AD. 

(a) Effective Date 

This AD becomes effective September 5, 

2014. 


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(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10002 through 

10342 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705), and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15001 through 15337 

inclusive. 

(3) Bombardier, Inc. Model CL–600–2E25 

(Regional Jet Series 1000) airplanes, serial 

numbers 19001 through 19040 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by two in-service 

reports of fracture of the rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before the accumulation of 26,000 total 

flight cycles or within 3 months after the 

effective date of this AD, whichever occurs 

later: Perform a detailed or eddy current 

inspection for cracking around the aft tapered 

holes of both pilot-side rudder pedal tubes, 

and for damage of the rudder pedal tubes in 

locations other than around the aft tapered 

holes, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013. 

Repeat the inspection thereafter at the 

applicable intervals specified in paragraph 

(g)(1) or (g)(2) of this AD, until the 

terminating action specified in paragraph (i) 

of this AD is done. 

(1) If the most recent inspection was a 

detailed inspection: Within 750 flight cycles 

after doing the detailed inspection. 

(2) If the most recent inspection was an 

eddy current inspection: Within 1,250 flight 

cycles after doing the eddy current 

inspection. 

(h) Corrective Actions 

(1) If any crack is found around the aft 

tapered holes during any inspection required 

by paragraph (g) of this AD, before further 

flight, replace the rudder bar assembly, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013. 

(2) If any damage is found during any 

inspection required by paragraph (g) of this 

AD in a location other than around the aft 

tapered holes: Before further flight, repair 

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. 

(i) Optional Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) 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. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–02, dated 

January 8, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0196-0002. 

(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) Bombardier Service Bulletin 670BA–27– 

065, including Appendix A, dated November 

15, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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 July 17, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17467 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–2014–0254; Directorate 

Identifier 2013–NM–047–AD; Amendment 

39–17910; AD 2014–15–08] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP, 

850XP, and 900XP airplanes. This AD 

was prompted by a design review that 

revealed there were no instructions to 

apply sealant to structural components 

in the fuel tank during the winglet 

installation process. This AD requires 

an inspection for the presence of sealant 

on doubler plate edges, doubler plate 

rivets, and adjacent skin in the fuel vent 

surge tanks; and corrective actions if 

necessary. We are issuing this AD to 

detect and correct missing sealant, 

which, during a lightning strike, could 

result in a potential source of ignition in 

a fuel tank and consequent explosion or 


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