45140 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0140, dated July 12, 2013, 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–2014–0492. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18373 Filed 8–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0491; Directorate 

Identifier 2014–NM–023–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–1A11 

(CL–600), CL–600–2A12 (CL–601), and 

CL–600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604 Variants) airplanes. This 

proposed AD was prompted by a 

determination that the forward lugs of 

the flap hinge box might not conform to 

engineering drawings, which could 

result in premature fatigue cracking. 

This proposed AD would require 

revising the maintenance or inspection 

program to include new airworthiness 

limitations tasks; and measuring the 

forward lug edge distance of each flap 

hinge box, and inspecting for cracking 

and damage (i.e., deformation or bearing 

failure) of the forward lug edge of each 

flap hinge box, and repair if necessary. 

We are proposing this AD to detect and 

correct non-conforming flap hinge box 

forward lugs, which could result in 

failure of the lugs and detachment of the 

flap hinge box and consequent 

detachment of the flap surface. 

DATES: We must receive comments on 

this proposed AD by September 18, 

2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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. 

• 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– 

0491; 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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; 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–2014–0491; Directorate Identifier 

2014–NM–023–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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–01, 

dated January 3, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The aeroplane manufacturer has 

determined that the flap hinge box forward 

lugs edge distance may not conform to the 

engineering drawings. Non-conforming flap 

hinge box forward lugs may result in 

premature fatigue cracking. 

Failure of the lugs could lead to the 

detachment of the flap hinge box and 

consequently the detachment of the flap 

surface. The loss of a flap surface could 

adversely affect the continued safe operation 

of the aeroplane. 

This [Canadian] AD mandates the 

incorporation of new Time Limits/

Maintenance Checks (TLMC) Airworthiness 

Limitations (AWL) tasks, and the 

measurement [and inspection for cracking 

and damage] of the forward lug edge distance 

of each flap hinge-box and rectification as 

required. 

Corrective actions include repairing 

damage and cracking. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0491. 

Relevant Service Information 

Bombardier has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Bombardier Service Bulletin 600– 

0762, dated September 26, 2013 (for 

Model CL–600–1A11 airplanes). 

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Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 45141 

• Bombardier Service Bulletin 601– 

0631, dated September 26, 2013 (for 

Models CL–600–2A12 and CL–600– 

2B16 airplanes). 

• Bombardier Service Bulletin 604– 

57–007, dated September 26, 2013 (for 

Model CL–600–2B16 airplanes). 

• Bombardier Service Bulletin 605– 

57–005, dated September 26, 2013 (for 

Model CL–600–2B16 airplanes). 

• Canadair Challenger Temporary 

Revision 5–157, dated July 8, 2013, to 

Canadair Challenger Time Limits/

Maintenance Checks Manual, PSP 605. 

• Canadair Challenger Temporary 

Revision 5–158, dated July 8, 2013, to 

Canadair Challenger Time Limits/

Maintenance Checks Manual, PSP 605. 

• Canadair Challenger Temporary 

Revision 5–262, dated July 8, 2013, to 

Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601. 

• Canadair Challenger Temporary 

Revision 5–275, dated July 8, 2013, to 

Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601A. 

• Canadair Challenger Temporary 

Revision 5–276, dated July 8, 2013, to 

Canadian Challenger Time Limits/

Maintenance Checks Manual PSP 601A. 

• Tasks 57–50–00–121 and 57–52– 

01–102 of Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 

Bombardier CL–605 Time Limits/

Maintenance Checks Manual, Revision 

8, dated July 8, 2013. 

• Tasks 57–50–00–121 and 57–52– 

01–102 of Section 5–10–30 of Part 2, 

‘‘Airworthiness Limitations,’’ of 

Bombardier CL–604 Time Limits/

Maintenance Checks Manual, Revision 

20, dated July 8, 2013. 

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 designs. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections). 

Compliance with these actions is 

required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this AD, the operator 

may not be able to accomplish the 

actions described in the revisions. In 

this situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (k) 

of this AD. The request should include 

a description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

‘‘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 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 

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. 

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45142 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 

Costs of Compliance 

We estimate that this proposed AD 

affects 105 airplanes of U.S. registry. 

We also estimate that it would take 

about 45 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $401,625, or $3,825 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the cost of parts or oncondition actions specified in this 

proposed 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 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 adding 

the following new airworthiness 

directive (AD): 

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

0491; Directorate Identifier 2014–NM– 

023–AD. 

(a) Comments Due Date 

We must receive comments by September 

18, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category. 

(1) Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes, serial numbers 1004 

through 1085 inclusive. 

(2) Bombardier, Inc. Model CL–600–2A12 

(CL–601) airplanes, serial numbers 3001 

through 3066 inclusive. 

(3) Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes, serial numbers 5001 through 5194 

inclusive. 

(4) Bombardier, Inc. Model CL–600–2B16 

(CL–604 Variants) airplanes; serial numbers 

5301 through 5665 inclusive, and 5701 

through 5953 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that the flap hinge box forward lugs edge 

distance might not conform to engineering 

drawings, which could result in premature 

fatigue cracking. We are issuing this AD to 

detect and correct non-conforming flap hinge 

box forward lugs, which could result in 

failure of the lugs and detachment of the flap 

hinge box and consequent detachment of the 

flap surface. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, by incorporating the 

applicable airworthiness limitation (AWL) 

tasks as specified in table 1 to paragraph (g) 

of this AD. The initial compliance time for 

doing the task is at the applicable times 

specified in table 1 to paragraph (g) of this 

AD. 

Note 1 to paragraph (g) of this AD: For the 

incorporation of tasks specified in the 

temporary revisions (TRs) specified in table 

1 to paragraph (g) of this AD that are a part 

of the maintenance or inspection program 

revision required by paragraph (g) of this AD, 

such incorporation may be done by inserting 

a copy of the applicable TRs specified in 

table 1 to paragraph (g) of this AD into the 

applicable ‘‘time limits/maintenance checks’’ 

(TLMC) manuals specified in table 1 to 

paragraph (g) of this AD. When the 

applicable TRs specified in table 1 to 

paragraph (g) of this AD have been included 

in general revisions of the applicable TLMC 

manual specified in table 1 to paragraph (g) 

of this AD, the general revisions may be 

inserted in the applicable TLMC manual 

specified in table 1 to paragraph (g) of this 

AD. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS

Affected airplanes Task No. Canadair service information Initial compliance time 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

greater than 7,400 total flight cycles 

but equal to or less than 14,850 total 

flight cycles as of the effective date of 

this AD.

57–40–00–186 Canadair Challenger Temporary Revision (TR) 5–158, dated July 8, 2013, 

of the Canadair Challenger Time Limits/Maintenance Checks (TLMC) Manual, PSP 605.

Within 500 flight cycles after the effective date of this AD, but not later than 

15,100 total flight cycles. 

Model CL600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

greater than 14,850 total flight cycles 

as of the effective date of this AD.

57–40–00–186 Canadair Challenger TR 5–158, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605.

Within 250 flight cycles after the effective date of this AD. 

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TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued 

Affected airplanes Task No. Canadair service information Initial compliance time 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with inboard flaps having 

equal to or less than 7,400 total flight 

cycles.

57–40–00–186 Canadair Challenger TR 5–158, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605.

Before the accumulation of 7,900 total 

flight cycles. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

greater than 7,500 total flight cycles, 

but equal to or less than 11,350 total 

flight cycles as of the effective date of 

this AD.

57–40–00–160 Canadair Challenger TR 5–157, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605.

Within 500 flight cycles after the effective date of this AD, but no later than 

11,600 total flight cycles. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

greater than 11,350 total flight cycles 

as of the effective date of this AD.

57–40–00–160 Canadair Challenger TR 5–157, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–1A11 (CL–600 Variant) 

airplanes with outboard flaps having 

equal to or less than 7,500 total flight 

cycles.

57–40–00–160 Canadair Challenger TR 5–157, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps having 

greater than 7,400 total flight cycles, 

but equal to or less than 14,850 total 

flight cycles, as of the effective date 

of this AD.

57–40–01–101 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Within 500 flight cycles after the effective date of this AD, but no later than 

15,100 total flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps with 

greater than 14,850 total flight cycles 

as of the effective date of this AD.

57–40–01–101 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with inboard flaps with 

equal to or less than 7,400 total flight 

cycles as of the effective date of this 

AD.

57–40–01–101 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Before the accumulation of 7,900 total 

flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps with 

greater than 7,500 total flight cycles 

but equal to or less than 11,350 total 

flight cycles as of the effective date of 

this AD.

57–40–00–175 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Within 500 flight cycles after the effective date of this AD, but not later than 

11,600 total flight cycles. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps having 

greater than 11,350 total flight cycles 

as of the effective date of this AD.

57–40–00–175 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–2A12 (CL–601 Variant) 

airplanes with outboard flaps having 

equal to or less than 7,500 total flight 

cycles as of the effective date of this 

AD.

57–40–00–175 Canadair Challenger TR 5–262, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive with inboard flaps having greater than 7,400 

total flight cycles but equal to or less 

than 14,850 total flight cycles as of 

the effective date of this AD.

57–40–00–101 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Within 500 flight cycles after the effective date of this AD, but not later than 

15,100 total flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with inboard flaps having greater than 

14,850 total flight cycles as of the effective date of this AD.

57–40–00–101 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Within 250 flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with inboard flaps having equal to or less 

than 7,400 total flight cycles as of the 

effective date of this AD.

57–40–00–101 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Before the accumulation of 7,900 total 

flight cycles. 

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45144 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued 

Affected airplanes Task No. Canadair service information Initial compliance time 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with outboard flaps having greater than 7,500 

total flight cycles but equal to or less 

than 11,350 total flight cycles as of 

the effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Within 500 flight cycles after the effective date of this AD, but no later than 

11,600 total flight cycles. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with outboard flaps having greater than 

11,350 total flight cycles as of the effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Within 250 flight cycles after the effective date of this AD. 

Model CL–600–2B16 (CL–601–3A and 

–3R Variant) airplanes having S/Ns 

5001 through 5194 inclusive, with outboard flaps having equal to or less 

than 7,500 total flight cycles as of the 

effective date of this AD.

57–40–00–174 Canadair Challenger TR 5–276, dated 

July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5.

Before the accumulation of 8,000 total 

flight cycles. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes with inboard and outboard 

flaps.

57–50–00–121 Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 

604 TLMC Manual, Revision 8, dated 

July 8, 2013.

Before the accumulation of 7,800 total 

flight cycles, or within 500 flight cycles after the effective date of this 

AD, whichever occurs later. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes, S/Ns 5301 through 5665 inclusive.

57–52–01–102 Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 

604 TLMC Manual, Revision 8, dated 

July 8, 2013.

At the time specified in the task. 

Model CL–600–2B16 (CL–604 Variant) 

airplanes, S/Ns 5701 through 5953 inclusive.

57–50–00–121 

and 57–52–01– 

102 

Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 

605 TLMC Manual, Revision 8, dated 

July 8, 2013.

At the applicable time specified in the 

tasks. 

(h) Lug Edge Measurement and Inspection 

At the applicable times specified in table 

2 to paragraphs (h) and (i)(1) of this AD, 

measure the forward lug edge distance of all 

flap hinge boxes, in accordance with the 

applicable service bulletin specified in 

paragraphs (h) and (i)(1) of this AD; and do 

a general visual inspection for cracking and 

damage (i.e., deformation or bearing failure) 

of the forward lug edge of all flap hinge 

boxes. 

TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND

INSPECTION

Airplane models Affected flaps Compliance time Service information 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having less than or 

equal to 7,400 total flight cycles 

as of the effective date of this 

AD.

Before the accumulation of 7,900 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having greater than 

7,400 total flight cycles, but 

equal to or less than 14,850 

total flight cycles as of the effective date of this AD.

Before the accumulation of 

15,100 total flight cycles, or 

within 500 flight cycles or 48 

months after the effective date 

of this AD; whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Inboard flaps having greater than 

14,850 total flight cycles as of 

the effective date of this AD.

Within 250 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having equal to or 

less than 7,500 total flight cycles as of the effective date of 

this AD.

Before the accumulation of 8,000 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having greater 

than 7,500 total flight cycles but 

less than or equal to 11,350 

total flight cycles as of the effective date of this AD.

Within 500 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first; but not exceeding 11,600 

total flight cycles.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

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Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 45145 

TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND

INSPECTION—Continued 

Airplane models Affected flaps Compliance time Service information 

Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 

1085 inclusive.

Outboard flaps having greater 

than 11,350 total flight cycles 

as of the effective date of this 

AD.

Within 250 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first.

Bombardier Service Bulletin 600– 

0762, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variants) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having less than or 

equal to 7,400 total flight cycles 

as of the effective date of this 

AD.

Before the accumulation of 7,900 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having greater than 

7,400 total flight cycles, but 

equal to or less than 14,850 

total flight cycles, as of the effective date of this AD.

Within 500 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first; but not exceeding 

15,100 total flight cycles.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Inboard flaps having greater than 

14,850 total flight cycles as of 

the effective date of this AD.

Within 250 flight cycles or within 

48 months after the effective 

date of this AD, whichever occurs first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having less than 

or equal to 7,500 total flight cycles as of the effective date of 

this AD.

Before the accumulation of 8,000 

total flight cycles, or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having greater 

than 7,500 total flight cycles, 

but equal to or less than 11,350 

total flight cycles, as of the effective date of this AD.

Within 500 flight cycles or within 

48 months after the effective 

date of this AD; but not exceeding 11,600 total flight cycles.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2A12 (CL–601 

Variant) and CL–600–2B16 (CL– 

601–3A and –3R Variant) airplanes having S/N 3001 through 

3066 inclusive, and 5001 

through 5194 inclusive.

Outboard flaps having greater 

than 11,350 total flight cycles 

as of the effective date of this 

AD.

Within 250 flight cycles or 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 601– 

0631, dated September 26, 

2013. 

Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 

5301 through 5665 inclusive.

Outboard and inboard flaps .......... Before the accumulation of 7,800 

total flight cycles or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 604– 

57–007, dated October 2, 2013. 

Model CL–600–2B16 (CL–604 

Variant) airplanes having S/Ns 

5701 through 5953 inclusive.

Outboard and inboard flaps .......... Before the accumulation of 7,800 

total flight cycles or within 48 

months after the effective date 

of this AD, whichever occurs 

first.

Bombardier Service Bulletin 605– 

57–005, dated November 15, 

2013. 

(i) Corrective Actions 

(1) If, during the measurement required by 

paragraph (h) of this AD, the lug edge 

distance is equal to or greater than the limit 

specified in the applicable service bulletin 

specified in table 2 to paragraphs (h) and 

(i)(1) of this AD, no further action is required 

by this paragraph. 

(2) If, during the measurement required by 

paragraph (h) of this AD, the lug edge 

distance is below the limit specified in the 

applicable service bulletin specified in table 

3 to paragraphs (h) and (i)(1) 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. 

(3) If, during the inspection required by 

paragraph (h) of this AD, any cracking or 

damage is found, before further flight, repair 

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 DAOauthorized signature. 

(j) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(k) 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 

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45146 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 

1The EPA has set both an annual and a 24-hour 

NAAQS for PM2.5 (40 CFR 50.7). 

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 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–01, dated 

January 3, 2014, 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– 

2014–0491. 

(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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18401 Filed 8–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Highway Administration 

23 CFR Part 790 

[FHWA Docket No. FHWA–2013–0018] 

RIN 2125–AF63 

Congestion Mitigation and Air Quality 

Improvement (CMAQ) Program 

AGENCY: Federal Highway 

Administration (FHWA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The CMAQ program provides 

funding to State and local governments 

for transportation projects and programs 

to help meet the requirements of the 

Clean Air Act (CAA). Funding is 

available to reduce congestion and 

improve air quality for areas that do not 

meet the National Ambient Air Quality 

Standards (NAAQS) for ozone, carbon 

monoxide (CO), or particulate matter 

(nonattainment areas) and for areas that 

were out of compliance but have now 

met the standards (maintenance areas). 

The Moving Ahead for Progress in the 

21st Century Act (MAP–21) requires 

priority use of CMAQ funds in areas 

that are designated nonattainment or 

maintenance for fine particulate matter 

(PM2.5) NAAQS under the CAA. 

Specifically, an amount equal to 25 

percent of the CMAQ funds apportioned 

to each State for a nonattainment or 

maintenance area that is based all or in 

part on the weighted population of the 

PM2.5 nonattainment area shall be 

obligated to projects that reduce PM2.5

emissions in such area. These projects 

include diesel retrofits for on-road and 

some off-road applications, as well as 

for diesel equipment operated on a 

highway construction project within 

PM2.5 nonattainment and maintenance 

areas. 

Although the MAP–21 language for 

the CMAQ funds that must be obligated 

for PM2.5 projects (referred to in this 

NPRM as a ‘‘set-aside’’) instructs that 

the set-aside be calculated based on 

‘‘weighted population’’ for PM2.5, the 

statute does not specify the values to be 

applied to determine the weighted 

population. In this proposed rule, 

FHWA is requesting comments on a 

proposed weighting factor of 5, to be 

used in determining the weighted 

population of a PM2.5 nonattainment 

area. 

DATES: Comments must be received on 

or before October 3, 2014. Late-filed 

comments will be considered to the 

extent practicable. 

ADDRESSES: Mail or hand deliver 

comments to the U.S. Department of 

Transportation, Dockets Management 

Facility, 1200 New Jersey Avenue SE., 

Washington, DC 20590, or submit 

electronically at www.regulations.gov or 

fax comments to 202–493–2251. All 

comments should include the docket 

number that appears in the heading of 

this document. All comments received 

will be available for examination and 

copying at the above address from 9 

a.m. to 5 p.m., e.t., Monday through 

Friday, except Federal holidays. Those 

desiring notification of receipt of 

comments must include a selfaddressed, stamped postcard or you 

may print the acknowledgment page 

that appears after submitting comments 

electronically. Anyone is able to search 

the electronic form of all comments in 

any one of our dockets by the name of 

the individual submitting the comment 

(or signing the comment, if submitted 

on behalf of an association, business, or 

labor union). You may review DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (Volume 65, Number 70, Pages 

19477–78). 

FOR FURTHER INFORMATION CONTACT: Ms. 

Cecilia Ho, Office of Natural 

Environment, HEPN, 202–366–9862, or 

Ms. Janet Myers, Office of the Chief 

Counsel, 202–366–2019, Federal 

Highway Administration, 1200 New 

Jersey Avenue SE., Washington, DC 

20590–0001. Office hours are from 8:00 

a.m. to 4:30 p.m., e.t., Monday through 

Friday, except Federal holidays. 

SUPPLEMENTARY INFORMATION: 

Electronic Access and Filing 

You may submit or retrieve comments 

online through the Document 

Management System at: http://

www.regulations.gov. Electronic 

submission and retrieval help and 

guidelines are available under the help 

section of the Web site. It is available 24 

hours each day, 365 days each year. 

Please follow the instructions. An 

electronic copy of this document may 

also be downloaded by accessing the 

Federal Register’s home page at: http:// 

www.federalregister.gov. 

Executive Summary 

I. Purpose of the Regulatory Action 

This regulation seeks to establish a 

proposed weighting factor of 5, to be 

used in determining the weighted 

population of a PM2.5 nonattainment 

area. Although the MAP–21 language for 

the CMAQ funds that must be obligated 

for PM2.5 projects instructs that the setaside be calculated based on ‘‘weighted 

population’’ for PM2.5, the statute does 

not specify the values to be applied to 

determine the weighted population. 

Section 1113(b)(6) of MAP–21 amends 

23 U.S.C. 149 by adding subsection 

(k)(1) that requires priority use of 

CMAQ funds in areas that are 

designated nonattainment or 

maintenance for the PM2.5 NAAQS.1

Specifically, 23 U.S.C. 149(k)(1) states 

that an amount equal to 25 percent of 

the funds attributed to PM2.5

nonattainment in each of the affected 

States must be used for projects that 

reduced PM2.5 emissions in those 

nonattainment and maintenance areas. 

Although this MAP–21 language 

states that the PM2.5 set-aside must be 

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