13758 Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Rules and Regulations 

benefits of available regulatory 

alternatives and, if regulation is 

necessary, to select regulatory 

approaches that maximize net benefits 

(including potential economic, 

environmental, public health and safety 

effects, distributive impacts, and 

equity). Executive Order 13563 

emphasizes the importance of 

quantifying both costs and benefits, 

reducing costs, harmonizing rules, and 

promoting flexibility. This rule has not 

been designated a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. 

Notwithstanding any other provision 

of law, no person is required to respond 

to, nor shall any person be subject to a 

penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act of 1995 (44 U.S.C. 3501– 

3521), unless that collection of 

information displays a currently valid 

Office of Management and Budget 

Control Number. This rule does not 

involve any collection of information 

subject to the Paperwork Reduction Act. 

This rule does not contain ‘‘policies 

that have federalism implications’’ as 

that term is defined under Executive 

Order 13132. 

List of Subjects 

3 CFR Part 101 

Freedom of information. 

5 CFR Part 2500 

Classified information. 

5 CFR Part 2502 

Courts, Freedom of information. 

5 CFR Part 2504 

Privacy. 

Accordingly, under the authority of 5 

U.S.C. 553 and as discussed in the 

preamble, amend 3 CFR part 101 and 

chapter XV of title 5 of the Code of 

Federal Regulations as follows. 

Title 3—The President 

CHAPTER I—EXECUTIVE OFFICE OF THE 

PRESIDENT 

PART 101—PUBLIC INFORMATION 

PROVISIONS OF THE 

ADMINISTRATIVE PROCEDURES ACT 

■ 1. The authority citation for part 101 

continues to read as follows: 

Authority: 5 U.S.C. 552. 

§ 101.3 [REMOVED] 

■ 2. Remove § 101.3. 

Title 5—Administrative Personnel 

CHAPTER XV—[REMOVED] 

■ 3. Remove chapter XV, consisting of 

parts 2500 through 2599. 

Dated: February 23, 2015. 

Beth A. Jones, 

Deputy Assistant to the President, Director, 

Office of Administration. 

[FR Doc. 2015–05899 Filed 3–16–15; 8:45 am] 

BILLING CODE 3215–F5–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0653; Directorate 

Identifier 2014–NM–057–AD; Amendment 

39–18113; AD 2015–05–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

reports of cracking on the skin panels 

and skin splice joints and angles at 

certain stringers at various locations 

between certain fuselage stations. This 

AD requires revising the maintenance or 

inspection program, as applicable, to 

incorporate new or revised maintenance 

requirements and airworthiness 

limitations, and incorporating structural 

repairs and modifications to preclude 

widespread fatigue damage (WFD). We 

are issuing this AD to detect and correct 

WFD, which could adversely affect the 

structural integrity of the airplane. 

DATES: This AD becomes effective April 

21, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 21, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/ 

#!docketDetail;D=FAA-2014-0653 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0653. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, 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: 516–228–7329; fax: 

516–794–5531; email: 

aziz.ahmed@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes. The NPRM published in 

the Federal Register on October 1, 2014 

(79 FR 59157). The NPRM was 

prompted by reports of cracking on the 

skin panels and skin splice joints and 

angles at certain stringers at various 

locations between certain fuselage 

stations. The NPRM proposed to require 

revising the maintenance or inspection 

program, as applicable, to incorporate 

new or revised maintenance 

requirements and airworthiness 

limitations, and incorporating structural 

repairs and modifications to preclude 

WFD. We are issuing this AD to detect 

and correct WFD, which could 

adversely affect the structural integrity 

of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–07, 

dated January 31, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. The MCAI states: 

Complete aeroplane fatigue testing on a 

CL–600–2B19 aeroplane by the aeroplane 

manufacturer revealed the onset of 

simultaneous cracking on the skin panels and 

skin splice joints and angles at stringers 

number 6 and 20 at various locations 


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Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Rules and Regulations 13759 

between fuselage stations (FS) 409.00 to FS 

589.00. 

Cracks at multiple locations may reduce 

the residual strength of the joint below the 

required levels if the cracks are not 

detectable under the existing maintenance 

program established at the time of 

certification. This multiple site damage 

(MSD) behavior, if not corrected, could lead 

to widespread fatigue damage (WFD) and 

adversely affect the structural integrity of the 

aeroplane and/or could result in rapid 

decompression of the aeroplane. 

A Temporary Revision (TR) has been made 

to the Maintenance Requirements Manual 

(MRM) to revise existing Airworthiness 

Limitations (AWL) tasks and introduce new 

inspection tasks for the detection of MSD. 

The aeroplane manufacturer is also 

developing a structural modification to 

preclude WFD from occurring in the fleet at 

these locations. 

This [Canadian] AD mandates the 

incorporation of the new and revised AWL 

tasks [into the maintenance program], and a 

structural modification to preclude WFD. 

You may examine the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2014-0653- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no valid comments on the 

NPRM (79 FR 59157, October 1, 2014) 

or on the determination of the cost to 

the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

59157, October 1, 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 59157, 

October 1, 2014). 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Airworthiness Limitations (AWL) 

Task 53–41–109, Longitudinal Str. 6 

splice at STR 6 and 20, of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 

9, dated June 10, 2013, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual, CSP A–053. This 

service information describes 

procedures for inspecting the 

longitudinal stringer 6 splice at stringers 

6 and 20. 

• AWL Task 53–41–110, Longitudinal 

Str. 6 splice butt strap at Str. 6, FS409.0 

to FS617.0, of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 

9, dated June 10, 2013, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual, CSP A–053. This 

service information describes 

procedures for inspecting the 

longitudinal stringer 6 splice butt at 

stringer 6 at fuselage station 409.0 to 

fuselage station 617.0. 

• AWL Task 53–41–204, Frame splice 

angles at STR 6 and 20, of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 

9, dated June 10, 2013, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual, CSP A–053. This 

service information describes 

procedures for inspecting the frame 

splice angles at stringers 6 and 20. 

• AWL Task 53–41–205, Longitudinal 

skin splice at STR 6 and 20, of 

Appendix B, Airworthiness Limitations, 

of Part 2, Airworthiness Requirements, 

Revision 9, dated June 10, 2013, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual, CSP A–053. This 

service information describes 

procedures for inspecting the 

longitudinal skin splice at stringers 6 

and 20. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 526 

airplanes of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. We have received no definitive 

data that would enable us to provide 

cost estimates for the repairs and 

modifications specified in this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$44,710, or $85 per product. 

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-2014-0653; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 


rljohnson on DSK3VPTVN1PROD with RULES
13760 Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–05–03 Bombardier, Inc.: Amendment 

39–18113. Docket No. FAA–2014–0653; 

Directorate Identifier 2014–NM–057–AD. 

(a) Effective Date 

This AD becomes effective April 21, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by reports of 

cracking on the skin panels and skin splice 

joints and angles at certain stringers at 

various locations between certain fuselage 

stations. We are issuing this AD to detect and 

correct widespread fatigue damage, which 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 60 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the airworthiness limitations 

(AWL) tasks specified in paragraphs (g)(1) 

through (g)(4) of this AD. The initial 

compliance times for the tasks start from the 

applicable threshold times specified in Part 

2 Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of Appendix B, 

Airworthiness Limitations, of Bombardier 

CL–600–2B19, Maintenance Requirements 

Manual, CSP A–053; except that, for 

airplanes that have accumulated more than 

38,000 total flight cycles as of the effective 

date of this AD, the initial compliance time 

for the AWL tasks is before the accumulation 

of 2,000 flight cycles after the effective date 

of this AD. 

(1) AWL Task 53–41–109, Longitudinal Str. 

6 splice at STR 6 and 20, of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of the Bombardier CL– 

600–2B19, Maintenance Requirements 

Manual, CSP A–053. 

(2) AWL Task 53–41–110, Longitudinal Str. 

6 splice butt strap at Str. 6, FS409.0 to 

FS617.0, of Appendix B, Airworthiness 

Limitations, of Part 2, Airworthiness 

Requirements, Revision 9, dated June 10, 

2013, of the Bombardier CL–600–2B19, 

Maintenance Requirements Manual, CSP A– 

053. 

(3) AWL Task 53–41–204, Frame splice 

angles at STR 6 and 20, of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of the Bombardier CL– 

600–2B19, Maintenance Requirements 

Manual, CSP A–053. 

(4) AWL Task 53–41–205, Longitudinal 

skin splice at STR 6 and 20., of Appendix B, 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of the Bombardier CL– 

600–2B19, Maintenance Requirements 

Manual, CSP A–053. 

(h) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as 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 (j)(1) of 

this AD. 

(i) Repairs and Modifications 

Before the accumulation of 60,000 total 

flight cycles: Install repairs and 

modifications to preclude widespread fatigue 

damage at locations specified in the tasks 

identified in paragraphs (g)(1) through (g)(4) 

of this AD, using a method approved by the 

Manager, New York ACO, ANE–170, 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. 

(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 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, 

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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–07, dated 

January 31, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2014-0653-0003. 

(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) Appendix B, Airworthiness Limitations, 

of Part 2, Airworthiness Requirements, 

Revision 9, dated June 10, 2013, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual, CSP A–053: 

(A) Airworthiness Limitations (AWL) Task 

53–41–109, Longitudinal Str. 6 splice at STR 

6 and 20; 

(B) AWL Task 53–41–110, Longitudinal 

Str. 6 splice butt strap at Str. 6, FS409.0 to 

FS617.0; 

(C) AWL Task 53–41–204, Frame splice 

angles at STR 6 and 20; and 

(D) AWL Task 53–41–205, Longitudinal 

skin splice at STR 6 and 20. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05717 Filed 3–16–15; 8:45 am] 

BILLING CODE 4910–13–P 


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