56264 Federal Register / Vol. 79, No. 182 / Friday, September 19, 2014 / Rules and Regulations 

• Federal Rulemaking Web site: Go to 

http://www.regulations.gov and search 

for Docket ID NRC–2012–0246. Address 

questions about NRC dockets to Carol 

Gallagher; telephone: 301–287–3422; 

email: Carol.Gallagher@nrc.gov. For 

technical questions, contact the 

individual listed in the FOR FURTHER

INFORMATION CONTACT section of this 

document. 

• NRC’s Agencywide Documents 

Access and Management System 

(ADAMS): You may access publicly 

available documents online in the 

ADAMS Public Documents collection at 

http://www.nrc.gov/reading-rm/

adams.html. To begin the search, select 

‘‘ADAMS Public Documents’’ and then 

select ‘‘Begin Web-based ADAMS 

Search.’’ For problems with ADAMS, 

please contact the NRC’s Public 

Document Room (PDR) reference staff at 

1–800–397–4209, 301–415–4737, or by 

email to pdr.resource@nrc.gov. The 

ADAMS accession number for each 

document referenced in this document 

(if that document is available in 

ADAMS) is provided the first time that 

a document is referenced. The two 

volumes of the final GEIS are available 

electronically in ADAMS under 

Accession Nos. ML14196A105 and 

ML14196A107. 

• NRC’s PDR: You may examine and 

purchase copies of public documents at 

the NRC’s PDR, Room O1–F21, One 

White Flint North, 11555 Rockville 

Pike, Rockville, Maryland 20852. 

In addition, the final GEIS may be 

accessed online at the NRC’s Web page 

at: http://www.nrc.gov/reading-rm/doccollections/nuregs/staff/. 

FOR FURTHER INFORMATION CONTACT: 

Sarah Lopas, Office of Nuclear Material 

Safety and Safeguards, U.S. Nuclear 

Regulatory Commission, Washington, 

DC 20555–0001; telephone: 301–287– 

0675, email: Sarah.Lopas@nrc.gov. 

SUPPLEMENTARY INFORMATION: In 

response to a ruling by the Court of 

Appeals for the District of Columbia 

Circuit (New York v. NRC, 681 F.3d 471) 

that vacated the NRC’s former Waste 

Confidence rule (§ 51.23 of Title 10 of 

the Code of Federal Regulations (10 

CFR)), the NRC developed a revised rule 

supported by a GEIS. NUREG–2157, 

‘‘Generic Environmental Impact 

Statement for Continued Storage of 

Spent Nuclear Fuel’’ provides a 

regulatory basis for the final rule and 

generically determines the 

environmental impacts of continued 

storage of spent fuel beyond the 

licensed life for operation of a reactor 

(continued storage). Concurrently with 

this document, the NRC is publishing 

the final rule, ‘‘Continued Storage of 

Spent Nuclear Fuel’’ (RIN 3150–AJ20; 

NRC–2012–0246), in the Rules section 

of this issue of the Federal Register. The 

final rule codifies the results of the 

analyses in NUREG–2157 in 10 CFR 

51.23 and makes other conforming 

changes to 10 CFR part 51. 

The NRC prepared the GEIS to satisfy 

its National Environmental Policy Act 

obligations regarding the environmental 

impacts of continued storage. A notice 

of intent to prepare a draft 

environmental impact statement and 

conduct scoping was published in the 

Federal Register on October 25, 2012 

(77 FR 65137). The draft GEIS notice of 

availability and public meetings, and 

request for comment, was published on 

September 13, 2013 (78 FR 56621). 

Additional draft GEIS public meeting 

notices were published on September 

19, 2013 (78 FR 57538); October 29, 

2013 (78 FR 64412; 78 FR 64413); and 

November 4, 2013 (78 FR 65903). An 

extension to the comment period was 

published on November 7, 2013 (78 FR 

66858). The purpose of this notice is to 

inform the public that the final GEIS is 

available for public inspection. 

Dated at Rockville, Maryland, this 10th day 

of September, 2014. 

For the Nuclear Regulatory Commission. 

Paul Michalak, 

Acting Director, Waste Confidence 

Directorate, Office of Nuclear Material Safety 

and Safeguards. 

[FR Doc. 2014–22250 Filed 9–18–14; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0144; Directorate 

Identifier 2013–NM–232–AD; Amendment 

39–17970; AD 2014–19–02] 

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–8–400, 

–401, and –402 airplanes. This AD was 

prompted by reports of rudder bearings 

falling out of the fore rudder hinge 

bracket during assembly. This AD 

requires a proof load test and detailed 

inspections; and installation of a new 

bearing, reaming, or repair of the 

bearing if necessary. We are issuing this 

AD to detect and correct improper 

bearing installation, which could result 

in abnormal wear and potential 

increased freeplay in the rudder system, 

and resultant airframe vibration, leading 

to compromise of the flutter margins of 

the airplane. 

DATES: This AD becomes effective 

October 24, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 24, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0144 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., 

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. 

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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; 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 Model 

DHC–8–400, –401, and –402 airplanes. 

The NPRM published in the Federal 

Register on March 25, 2014 (79 FR 

16245). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–34, 

dated November 1, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier Model DHC–8– 

400, –401, and –402 airplanes. The 

MCAI states: 


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It was reported that rudder bearings were 

falling out of the fore rudder hinge bracket 

during assembly. Investigation revealed the 

root cause as improper application of the 

adhesive compound and the lack of 

application of sealant during the installation 

of the rudder bearings into the fore rudder 

hinge bracket. The improper bearing 

installation, if not corrected, could result in 

abnormal wear and could potentially 

increase the freeplay in the rudder system. 

This may result in airframe vibration, 

eventually compromising the flutter-margins 

of the aeroplane. 

This [Canadian] AD mandates the 

inspection, and rectification as required, of 

the fore rudder bearings in the hinge bracket 

assembly. 

Required actions include a proof load 

test for slippage and freeplay. Related 

investigative actions include a detailed 

inspection of a certain bearing for 

damage, corrosion, and dimension 

conformity; and a detailed inspection of 

the fitting bore of the fore rudder hinge 

bracket for wear, damage, corrosion, and 

dimension conformity. Corrective 

actions include installation of a new 

bearing, reaming, or repair of the 

bearing. You may examine the MCAI in 

the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0144- 

0002. 

Revised Service Information 

Since the NPRM (79 FR 16245, March 

25, 2014) was issued, Bombardier has 

issued Service Bulletin 84–27–44, 

Revision ‘B’, dated February 11, 2014. 

Among other things, Bombardier 

Service Bulletin 84–27–44, Revision ‘B’, 

dated February 11, 2014, clarifies a note, 

and corrects a task number for the 

operational check of the rudder control 

system. 

We have revised this AD to include 

Bombardier Service Bulletin 84–27–44, 

Revision ‘B’, dated February 11, 2014, as 

an additional source of appropriate 

service information. We also have 

revised paragraph (i) of this AD to 

include Bombardier Service Bulletin 

84–27–44, Revision ‘A,’ dated June 10, 

2009, as service information that can be 

used for credit for previous 

accomplishment of certain actions 

required by this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 16245, 

March 25, 2014) and the FAA’s response 

to each comment. 

Request To Change Airworthy Product 

Paragraph 

Horizon Air requested that we revise 

the Airworthy Product paragraph, i.e., 

paragraph (j)(2) of the NPRM (79 FR 

16245, March 25, 2014), to either 

remove or change the sentence that 

states, in part, that ‘‘repair approvals 

must specifically refer to this AD.’’ 

Horizon Air reasoned that the 

sentence in question places an 

unnecessary regulatory burden on 

operators with airplanes that are built in 

Canada. Horizon Air explained that 

since TCCA is the State holding Design 

Authority for Bombardier, Inc. Model 

DHC–8–400 series airplanes, any repairs 

created by Bombardier would have to be 

in compliance with the TCCA AD, and 

the repair would specifically refer to the 

TCCA AD. 

The commenter added that the 

bilateral agreement between Canada and 

the United States accepts documents 

approved by TCCA as meeting the 

requirements for FAA-approval. The 

commenter questioned whether the U.S. 

AD number is necessary when the repair 

is approved by TCCA and the repair 

specifically refers to the Canadian AD, 

and asked what value is added by 

specifically referring to the U.S. AD if 

the repair meets the approval 

requirements of the State holding the 

Design Authority. Horizon Air noted 

that the language in paragraph (j)(2) of 

the NPRM (79 FR 16245, March 25, 

2014) would force operators that 

incorporated a repair method prior to 

the effective date of the AD to go back 

to the manufacturer and request a 

revision to the repair method to add the 

U.S. AD number, even if the repair 

method referenced the TCCA AD. 

Horizon Air also explained that it 

discussed the statement concerning 

repair approvals with Bombardier 

Aerospace, Toronto. The Engineering 

Department management of Bombardier 

Aerospace, Toronto, stated they are 

under the TCCA umbrella, and they can 

refer only to a TCCA AD on their repair 

drawings. If this requirement is retained 

in the U.S. AD as written, it would 

require an operator to somehow have a 

repair drawing revised to include the 

U.S. AD number. This is a difficult task, 

considering the manufacturer’s stated 

position that they currently do not 

include the U.S. AD number, and they 

have no internal processes to add it. The 

statement in the U.S. AD should allow 

the TCCA AD number as an equivalent 

to the U.S. AD number. 

Horizon Air also noted that an 

operator could pursue an alternative 

method of compliance (AMOC) but that 

would add additional time and cost to 

compliance. The additional time 

required for an AMOC will most likely 

delay returning the airplanes to service, 

and if the AMOC is needed on a 

weekend or federal holiday, the return 

to service would take even longer. 

We concur with the commenter’s 

request to remove from this AD the 

requirement that repair approvals must 

specifically refer to 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 16245, March 25, 

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. 

A related comment was provided for 

an NPRM having Directorate Identifier 

2012–NM–101–AD (78 FR 78285, 

December 26, 2013), which applies to 

certain Airbus airplane models. 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 


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56266 Federal Register / Vol. 79, No. 182 / Friday, September 19, 2014 / Rules and Regulations 

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 actions 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 

not TCCA-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility afforded previously 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 

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 may have been issued some time 

before the FAA AD. Therefore, the DOA 

may 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 from this AD the requirement 

that the DAH-provided repair 

specifically refer to this AD. Before 

adopting such a requirement in the 

future, 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 an AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We have also decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or the ‘‘DAH with 

State of Design Authority design 

organization approval,’’ but instead we 

will provide the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

16245, March 25, 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 16245, 

March 25, 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 78 

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 $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $46,410, or $595 

per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 8 work-hours and require parts 

costing $155, for a cost of $835 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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-2014-0144; 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 


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Federal Register / Vol. 79, No. 182 / Friday, September 19, 2014 / Rules and Regulations 56267 

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): 

2014–19–02 Bombardier, Inc.: Amendment 

39–17970. Docket No. FAA–2014–0144; 

Directorate Identifier 2013–NM–232–AD. 

(a) Effective Date 

This AD becomes effective October 24, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4166 through 4175, inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

rudder bearings falling out of the fore rudder 

hinge bracket during assembly. We are 

issuing this AD to detect and correct 

improper bearing installation, which could 

result in abnormal wear and potential 

increased freeplay in the rudder system, and 

resultant airframe vibration, leading to 

compromise of the flutter margins of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Proof Load Test 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first, do a proof load test for slippage 

and freeplay (relative movement between the 

bearing and fitting), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–44, Revision ‘B,’ 

dated February 11, 2014. If no slippage or 

freeplay is detected during the proof load test 

required by this paragraph, before further 

flight, identify the area with a marker and 

apply sealant if missing, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘B,’ dated February 11, 2014; and 

after identifying the area with a marker and 

applying sealant, no further action is 

required by this AD. 

(h) Rectification 

If any slippage or freeplay (relative 

movement between the bearing and fitting) is 

detected during the test required by 

paragraph (g) of this AD, before further flight, 

do the actions specified in paragraphs (h)(1) 

and (h)(2) of this AD. 

(1) Do a detailed inspection of bearing 

DSC8–6 for damage, corrosion, and 

dimension conformity, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘B,’ dated February 11, 2014. If 

damage, corrosion, or dimension nonconformity is found, before further flight, 

install new bearing DSC8–6, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘B,’ dated February 11, 2014. 

(2) Do a detailed inspection of the fitting 

bore of the fore rudder hinge bracket 

assembly for wear, damage, corrosion, and 

dimension conformity, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘B,’ dated February 11, 2014. 

(i) If damage, corrosion, or dimension nonconformity is found during the inspection 

required by paragraph (h)(2) of this AD, 

before further flight, ream the inside 

diameter, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–44, Revision ‘B,’ 

dated February 11, 2014. 

(ii) If bore wear or damage beyond 0.8140- 

inch diameter is found during the inspection 

required by paragraph (h)(2) of this AD, 

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 

DAO-authorized signature. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 84–27–44, dated April 13, 

2009; or Bombardier Service Bulletin 84–27– 

44, Revision ‘A,’ dated June 10, 2009; which 

are not incorporated by reference in 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 ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the New York ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

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

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 DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–34, dated 

November 1, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0144-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available 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) Bombardier Service Bulletin 84–27–44, 

Revision ‘B,’ dated February 11, 2014. (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 

September 8, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22153 Filed 9–18–14; 8:45 am] 

BILLING CODE 4910–13–P 


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