50880 Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(ii) For airplanes on which hydraulic fluid 

coking or heat discoloration is found but no 

cracking, etching, or pitting is found during 

the inspection required by paragraph (g)(2) of 

this AD (Condition 2B): Do the actions 

required by paragraph (g)(2)(ii)(A) and 

(g)(2)(ii)(B) of this AD. 

(A) Within 300 flight cycles after doing the 

inspection required by paragraph (g)(2) of 

this AD: Do a detailed inspection of the 

exterior of the strut disconnect assembly for 

cracks, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; and repeat the detailed 

inspection thereafter at intervals not to 

exceed 300 flight cycles. As of the effective 

date of this AD, use only Boeing Service 

Bulletin 777–54A0024, Revision 2, dated 

January 23, 2014, for accomplishing the 

actions in this paragraph. 

(B) Within 6,000 flight cycles or 750 days 

after hydraulic fluid coking and/or heat 

discoloration was found during the 

inspection required by paragraph (g)(2) of 

this AD, whichever occurs first: Replace the 

titanium system disconnect assembly with an 

Inconel system, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(h) Retained Corrective Action With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011), with revised service information. For 

airplanes on which any crack, etching, or 

pitting is found during any inspection 

required by paragraph (g)(2) or (g)(2)(ii)(A) of 

this AD (Condition 3): Before further flight, 

replace the titanium system disconnect 

assembly with an Inconel system, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(i) Retained Optional Terminating Action 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–09–11, Amendment 

39–16673 (76 FR 24354, May 2, 2011), with 

revised service information. Replacing the 

titanium system disconnect assembly with an 

Inconel system disconnect assembly in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; terminates the actions 

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

As of the effective date of this AD, use only 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014, for 

accomplishing the actions in this paragraph. 

(j) New Inspection and Corrective Action 

For airplanes on which the system 

disconnect assembly has been replaced in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, dated April 1, 

2010; or Revision 1, dated November 4, 2010: 

Within 1,125 days after the effective date of 

this AD, do a detailed inspection of the cover 

plate fasteners to determine if all cover plate 

attach fasteners are installed, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

54A0024, Revision 2, dated January 23, 2014. 

If any fastener is missing, before further 

flight, install fasteners (including doing a 

detailed inspection for damage of the 

electrical components and repairing any 

damaged components), in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(k) Credit for Previous Actions 

This paragraph restates the credit provided 

by paragraph (j) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011). This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g), (h), and (i) of this AD, if those 

actions were performed before June 6, 2011 

(the effective date of AD 2011–09–11) using 

Boeing Service Bulletin 777–54A0024, dated 

April 1, 2010, which is not incorporated by 

reference in this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 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. 

Issued in Renton, Washington, on August 

15, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–20221 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0582; Directorate 

Identifier 2014–NM–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–03– 

05, for certain Bombardier, Inc. Model 

BD–700–1A10 airplanes. AD 2014–03– 

05 currently requires modification of the 

air data probes and sensors. Since we 

issued AD 2014–03–05, we have 

determined that additional airplanes are 

affected by the unsafe condition. This 

proposed AD would add airplanes to the 

applicability. We are proposing this AD 

to detect and correct an unannunciated 

failure of two pitot static probe heaters, 

which could affect controllability of the 

airplane in icing conditions. 

DATES: We must receive comments on 

this proposed AD by October 10, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50881 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0582; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7301; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0582; Directorate Identifier 

2014–NM–065–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On January 22, 2014, we issued AD 

2014–03–05, Amendment 39–17742 (79 

FR 10331, February 25, 2014). AD 2014– 

03–05 requires actions intended to 

address an unsafe condition on certain 

Bombardier, Inc. Model BD–700–1A10 

airplanes. 

Since we issued AD 2014–03–05, 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014), we have determined 

that airplanes have been inadvertently 

omitted from the applicability; there are 

additional airplanes that are on the FAA 

supplemental type certificate, but not 

the Canadian supplemental type 

certificate, that are subject to the unsafe 

condition. For airplanes equipped with 

any electrical wiring heater current/

brake temperature monitor unit (HBMU) 

installed in accordance with any FAA 

supplemental type certificate specified 

in table 2 of paragraph 1.A., 

‘‘Effectivity,’’ of Bombardier Service 

Bulletin 700–30–021, Revision 01, dated 

November 21, 2012, the modification of 

the air data probes and sensors must be 

done to address the unsafe condition. 

We have coordinated this issue with 

Transport Canada Civil Aviation. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed 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 an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the 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. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) 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 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 


tkelley on DSK3SPTVN1PROD with PROPOSALS
50882 Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 

approved by the FAA, Transport Canada 

Civil Aviation (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 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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 79 airplanes of U.S. registry. 

The actions that are required by AD 

2014–03–05, Amendment 39–17742 (79 

FR 10331, February 25, 2014), and 

retained in this proposed AD take about 

35 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2014–03–05 is $2,975 

per product. 

We also estimate that it would take 

about 35 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $235,025, or $2,975 per 

product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This proposed 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Airworthiness Directive (AD) 

AD 2014–03–05, Amendment 39–17742 

(79 FR 10331, February 25, 2014), and 

adding the following new AD: 

Bombardier, Inc.: Docket No. FAA–2014– 

0582; Directorate Identifier 2014–NM– 

065–AD. 

(a) Comments Due Date 

We must receive comments by October 10, 

2014. 

(b) Affected ADs 

This AD replaces AD 2014–03–05, 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014). 

(c) Applicability 

(1) This AD applies to Bombardier, Inc. 

Model BD–700–1A10 airplanes, certificated 

in any category, equipped with any electrical 

wiring heater current/brake temperature 

monitor unit (HBMU) installed in accordance 

with any FAA supplemental type certificate 

specified in table 1 and table 2 of paragraph 

1.A., ‘‘Effectivity,’’ of Bombardier Service 

Bulletin 700–30–021, Revision 01, dated 

November 21, 2012. 

(2) For airplanes on which the applicable 

service request for product support action 

(SRPSA) specified in table 3 and table 4 of 

paragraph 1.A., ‘‘Effectivity,’’ of Bombardier 

Service Bulletin 700–30–021, Revision 01, 

dated November 21, 2012, has been 

incorporated, the requirements of this AD 

have been met. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 30, Ice and Rain Protection. 

(e) Reason 

This AD was prompted by a report that the 

manufacturer has determined that some 

completion centers used the HBMU logic 

circuit to control the line voltage of the drain 

mast heaters. This same logic circuit is also 

used to control the line voltage of the number 

2 pitot static (PS) probe heater. Since the 

drain mast heaters are connected in parallel 

with the number 2 PS probe heater circuit, 

a number 2 PS probe heater failure may not 

be detected by the fault monitoring 

capabilities of the HBMU. We are issuing this 

AD to detect and correct an unannunciated 

failure of two PS probe heaters, which could 

affect controllability of the airplane in icing 

conditions. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–03–05, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50883 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014). For airplanes equipped 

with any electrical wiring HBMU installed in 

accordance with any FAA supplemental type 

certificate specified in table 1 of paragraph 

1.A., ‘‘Effectivity,’’ of Bombardier Service 

Bulletin 700–30–021, Revision 01, dated 

November 21, 2012: Within 800 flight hours 

or 15 months after April 1, 2014 (the effective 

date of AD 2014–03–05), whichever occurs 

first, modify the air data probes and sensors, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

700–30–021, Revision 01, dated November 

21, 2012. 

(h) New Modification 

For airplanes equipped with any electrical 

wiring HBMU installed in accordance with 

any FAA supplemental type certificate 

specified in table 2 of paragraph 1.A., 

‘‘Effectivity,’’ of Bombardier Service Bulletin 

700–30–021, Revision 01, dated November 

21, 2012: Within 800 flight hours or 15 

months after the effective date of this AD, 

whichever occurs first, modify the air data 

probes and sensors, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 700–30–021, Revision 01, 

dated November 21, 2012. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) or (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 700–30–021, dated August 

28, 2012, which is 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 Aircraft 

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

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–32, dated 

December 13, 2012, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0582. 

(2) 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. 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. 

Issued in Renton, Washington, on August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20223 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R08–OAR–2013–0006; FRL–9915–74– 

Region 8] 

Approval and Promulgation of Air 

Quality Implementation Plans; 

Wyoming; Revisions to the Wyoming 

Air Quality Standards and Regulations; 

Ambient Standards for Particulate 

Matter and for Lead 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is proposing to approve a 

State Implementation Plan (SIP) 

revision submitted by the State of 

Wyoming. The revision affects 

Wyoming’s Air Quality Standards and 

Regulations (WAQSR) regarding 

ambient standards for particulate matter 

and for lead (Pb). This action is being 

taken under section 110 of the Clean Air 

Act (CAA). 

DATES: Written comments must be 

received on or before September 25, 

2014. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R08– 

OAR–2013–0006, by one of the 

following methods: 

• http://www.regulations.gov. Follow 

the on-line instructions for submitting 

comments. 

• Email: pratt.steven@epa.gov. 

• Fax: (303) 312–6064 (please alert 

the individual listed in the FOR FURTHER

INFORMATION CONTACT if you are faxing 

comments). 

• Mail: Director, Air Program, EPA, 

Region 8, Mailcode 8P–AR, 1595 

Wynkoop Street, Denver, Colorado 

80202–1129. 

• Hand Delivery: Director, Air 

Program, EPA, Region 8, Mailcode 8P– 

AR, 1595 Wynkoop, Denver, Colorado 

80202–1129. Such deliveries are only 

accepted Monday through Friday, 8:00 

a.m. to 4:30 p.m., excluding Federal 

holidays. Special arrangements should 

be made for deliveries of boxed 

information. 

Please see the direct final rule which is 

located in the Rules Section of this 

Federal Register for detailed instruction 

on how to submit comments. 

FOR FURTHER INFORMATION CONTACT: 

Steven Pratt, Air Program, EPA, Region 

8, Mailcode 8P–AR, 1595 Wynkoop, 

Denver, Colorado 80202–1129, (303) 

312–6575, pratt.steven@epa.gov. 

SUPPLEMENTARY INFORMATION: In the 

‘‘Rules and Regulations’’ section of this 

Federal Register, EPA is approving 

Wyoming’s SIP revision as a direct final 

rule without prior proposal because the 

Agency views this as a noncontroversial 

SIP revision and anticipates no adverse 

comments. A detailed rationale for the 

approval is set forth in the preamble to 

the direct final rule. If EPA receives no 

adverse comments, EPA will not take 

further action on this proposed rule. If 

EPA receives adverse comments, EPA 

will withdraw the direct final rule and 

it will not take effect. EPA will address 

all public comments in a subsequent 

final rule based on this proposed rule. 

EPA will not institute a second 

comment period on this action. Any 

parties interested in commenting must 

do so at this time. Please note that if 

EPA receives adverse comment on an 

amendment, paragraph, or section of 

this rule and if that provision may be 

severed from the remainder of the rule, 

EPA may adopt as final those provisions 

of the rule that are not the subject of an 

adverse comment. See the information 

provided in the Direct Final action of 

the same title which is located in the 

Rules and Regulations Section of this 

Federal Register. 

Authority: 42 U.S.C. 7401 et seq. 

Dated: August 5, 2014. 

Shaun L. McGrath, 

Regional Administrator, Region 8. 

[FR Doc. 2014–20224 Filed 8–25–14; 8:45 am] 

BILLING CODE 6560–50–P 


tkelley on DSK3SPTVN1PROD with PROPOSALS