5670 Federal Register / Vol. 80, No. 22 / Tuesday, February 3, 2015 / Rules and Regulations 

additional data from advanced 

approaches HCs. 

Pursuant to the PRA’s emergency 

review process, 44 U.S.C. 3507(j), the 

Board is filing an emergency clearance 

review to eliminate Schedule SC–R, 

Regulatory Capital, Part I, on the Parent 

Company Only Financial Statements for 

Small Holding Companies (FR Y–9SP) 

to reduce burden on small SLHCs 

immediately. In the emergency 

submission, the burden for the FR Y– 

9SP related to the elimination of 

Schedule SC–R, Regulatory Capital, Part 

I, would decrease by 156,935 hours. The 

change implemented through the 

emergency clearance process would be 

effective for six months. The Board is 

now proposing to make the change 

permanent and welcomes public 

comment on any aspect of this 

information collection. The burden 

estimates below reflect the updated 

number from the total emergency 

clearance review. 

Estimated Paperwork Burden 

Estimated Burden per Response: 

FR Y–9C (non Advanced Approaches 

bank holding companies)—48.84 

hours; 

FR Y–9C (Advanced Approaches bank 

holding companies)—50.09 hours; 

FR Y–9LP—5.25 hours; 

FR Y–9SP—5.40 hours; 

FR Y–9ES—0.5 hours; and 

FR Y–9CS—0.5 hours. 

Number of respondents: 

FR Y–9C (non Advanced Approaches 

bank holding companies)—644; 

FR Y–9C (Advanced Approaches bank 

holding companies)—12; 

FR Y–9LP—818; 

FR Y–9SP—4,390; 

FR Y–9ES—86; and 

FR Y–9CS—236. 

Total estimated annual burden: 

FR Y–9C (non Advanced Approaches 

bank holding companies)—125,812 

hours; 

FR Y–9C (Advanced Approaches bank 

holding companies)—2,404 hours; 

FR Y–9LP—17,178 hours; 

FR Y–9SP—47,412 hours; 

FR Y–9ES—43 hours; and 

FR Y–9CS—472 hours. (Total burden 

193,321 hours) 

C. Plain Language 

Section 722 of the Gramm-LeachBliley Act requires the Federal banking 

agencies to use ‘‘plain language’’ in all 

proposed and final rules published after 

January 1, 2000. In light of this 

requirement, the Board has sought to 

present the interim final rule in a simple 

and straightforward manner. The Board 

invites comments on whether there are 

additional steps it could take to make 

the rule easier to understand. 

List of Subjects in 12 CFR Part 217 

Administrative practice and 

procedure, Banks, banking, Capital, 

Federal Reserve System, Holding 

companies, Reporting and 

recordkeeping requirements, Securities. 

Board of Governors of the Federal 

Reserve System 

12 CFR CHAPTER II 

Authority and Issuance 

For the reasons set forth in the 

supplementary information, the Board 

amends 12 CFR Chapter II part 217 to 

read as follows: 

PART 217—CAPITAL ADEQUACY OF 

BANK HOLDING COMPANIES, 

SAVINGS AND LOAN HOLDING 

COMPANIES, AND STATE MEMBER 

BANKS (REGULATION Q) 

■ 1. The authority citation for part 217 

continues to read as follows: 

Authority: 12 U.S.C. 248(a), 321–338a, 

481–486, 1462a, 1467a, 1818, 1828, 1831n, 

1831o, 1831p–l, 1831w, 1835, 1844(b), 1851, 

3904, 3906–3909, 4808, 5365, 5368, 5371. 

■ 2. In § 217.1, amend paragraph 

(c)(1)(iii) to read as follows: 

§ 217.1 Purpose, applicability, 

reservations of authority, and timing. 

* * * * * 

(c) * * * 

(1) * * * 

(iii) A covered savings and loan 

holding company domiciled in the 

United States, other than a savings and 

loan holding company that has total 

consolidated assets of less than $500 

million and meets the requirements of 

12 CFR part 225, Appendix C, as if the 

savings and loan holding company were 

a bank holding company and the 

savings association were a bank. For 

purposes of compliance with the capital 

adequacy requirements and calculations 

in this part, savings and loan holding 

companies that do not file the FR Y–9C 

should follow the instructions to the FR 

Y–9C. 

* * * * * 

By order of the Board of Governors of the 

Federal Reserve System, January 29, 2015. 

Michael Lewandowski, 

Associate Secretary of the Board. 

[FR Doc. 2015–02038 Filed 1–30–15; 11:15 am] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0082; Directorate 

Identifier 2014–NM–233–AD; Amendment 

39–18092; AD 2015–02–23] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting 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, and CL– 

601–3R Variants) airplanes. This AD 

requires repetitive inspections for 

fractured or incorrectly oriented 

fasteners on the inboard flap hinge-box 

forward fittings on both wings, and 

replacement of all fasteners, if 

necessary. This AD was prompted by 

several reports of incorrectly oriented 

and fractured fasteners found on the 

inboard flap hinge-box forward fitting at 

wing station (WS) 76.50. We are issuing 

this AD to detect and correct incorrectly 

oriented or fractured fasteners, which 

could result in detachment of the flap 

hinge-box and the flap surface, and 

consequent reduced controllability of 

the airplane. 

DATES: This AD becomes effective 

February 18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 18, 2015. 

We must receive comments on this 

AD by March 20, 2015. 

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. 


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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–2015– 

0082. 

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–2015– 

0082; or in person at the Docket 

Operations office 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. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7329; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Emergency Airworthiness Directive CF– 

2013–39R2, dated December 12, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition on certain Bombardier, Inc. 

Model CL–600–1A11 (CL–600), CL– 

600–2A12 (CL–601), and CL–600–2B16 

(CL–601–3A, and CL–601–3R Variants) 

airplanes. The MCAI states: 

There have been three in-service reports on 

604 Variant aeroplanes of a fractured fastener 

head on the inboard flap hinge-box forward 

fitting at Wing Station (WS) 76.50, found 

during a routine maintenance inspection. 

Investigation revealed that the installation of 

these fasteners on the inboard flap hinge-box 

forward fittings at WS 76.50 and WS 127.25, 

on both wings, does not conform to the 

engineering drawings. Incorrect installation 

may result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting. Failure of the fasteners 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 

* * * [result in reduced controllability of the 

airplane]. 

The original issue of this [Canadian] AD 

[dated December 6, 2013] [http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0054-0002] 

[which corresponds to FAA AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014)] mandated a detailed visual 

inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and 

rectification as required. Incorrectly oriented 

fasteners require repetitive inspections until 

the terminating action is accomplished. 

Although there have been no reported 

fractured fastener heads found to date on any 

model CL–600–1A11, –2A12 or –2B16 (601– 

3A–3R Variant) aeroplanes, incorrectly 

oriented fasteners may also be installed. 

After the issuance of the original 

[Canadian] AD [dated August 15, 2014], there 

has been one reported incident on a 604 

Variant aeroplane where four fasteners were 

found fractured on the same flap hinge-box 

forward fitting. The investigation determined 

that the fasteners were incorrectly installed. 

Revision 1 of this [Canadian] AD was 

issued to remove the 604 Variant aeroplanes 

from the Applicability section since they 

were addressed in [Canadian] AD CF–2014– 

27 [dated August 15, 2014] [which 

corresponds to FAA AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, October 

28, 2014)] and to clarify paragraphs A.2. and 

C of this [Canadian] AD so that it matched 

the Bombardier Alert Service Bulletins. 

After the issuance of Revision 1 of this 

[Canadian] AD, there have been several 

reports of incorrectly oriented fasteners 

found on CL–600–1A11, and –2B16 (601–3A 

Variant) aeroplanes. Although there have 

been no reports of fractured fasteners found 

to date, incorrectly oriented fasteners could 

result in the premature failure of the forward 

flap hinge-box fitting. 

Revision 2 of this [Canadian] AD is issued 

to reduce the initial and repetitive inspection 

intervals and to impose replacement of the 

incorrectly oriented fasteners * * *. This 

[Canadian] AD also corrects various 

terminology errors which were found in 

previous French versions of this [Canadian] 

AD. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0082. 

Related Rulemaking 

On February 3, 2014, we issued AD 

2014–03–17, Amendment 39–17754 (79 

FR 9389, February 19, 2014) for 

Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes, having serial 

numbers (S/Ns) 1004 through 1085 

inclusive; Model CL–600–2A12 (CL– 

601) airplanes, having S/Ns 3001 

through 3066 inclusive; and Model CL– 

600–2B16 (CL–601–3A, CL–601–3R, & 

CL–604 Variants) airplanes, having S/Ns 

5001 through 5194 inclusive, 5301 

through 5665 inclusive, and 5701 

through 5920 inclusive. AD 2014–03–17 

requires repetitive inspections for 

fractured or incorrectly oriented 

fasteners on the inboard flap hinge-box 

forward fittings on both wings, and 

fastener replacement if necessary, and 

was prompted by two reports of 

fractured fastener heads found on the 

inboard flap hinge-box forward fitting. 

AD 2014–03–17 was issued to detect 

and correct incorrectly oriented or 

fractured fasteners, which could result 

in detachment of the flap hinge-box and 

the flap surface, and consequent 

reduced controllability of the airplane. 

After we issued AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, 

February 19, 2014), we received a report 

of an additional incident of fractured 

fasteners on a Model CL–600–2B16 (CL– 

604 Variant) airplane. We then issued 

AD 2014–17–51, Amendment 39–17999 

(79 FR 64088, October 28, 2014), as a 

‘‘stand-alone’’ AD to reduce compliance 

times for the initial and repetitive 

inspections only for Model CL–600– 

2B16 airplanes having S/Ns 5301 

through 5665 inclusive, and 5701 

through 5920 inclusive. Issuing AD 

2014–17–51 as a ‘‘stand-alone’’ AD 

instead of superseding AD 2014–03–17 

was determined to be clearer and less 

burdensome for operators with airplanes 

unaffected by the reduced compliance 

times required by AD 2014–17–51. 

Since we issued AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, 

October 28, 2014), we received a report 

of incorrectly oriented fasteners on a 

Model CL–600–1A11 airplane and on a 

Model CL–600–2B16 (601–3A Variant) 

airplane. Consequently, we determined 

it was necessary to issue this AD to 

reduce compliance times for the other 

airplane models not affected by AD 

2014–17–51. Doing so reduces the 

potential complexity for two groups of 

airplanes (those that are and are not 

affected by AD 2014–17–51). 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Alert Service 

Bulletins A600–0763, Revision 02, 

dated December 9, 2014, including 

Appendices 1 and 2, dated September 

26, 2013; and A601–0627, Revision 02, 

dated December 9, 2014, including 

Appendices 1 and 2, dated September 

26, 2013. The service information 

describes procedures for repetitive 

inspections of the fasteners on the 

inboard flap hinge-box forward fittings 

on both wings, and replacement of all 

fasteners, if necessary. The actions 

described in this service information are 


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intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available; see 

ADDRESSES for ways to access this 

service information. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because we have received several 

reports of incorrectly oriented and 

fractured fasteners found on the inboard 

flap hinge-box forward fitting at WS 

76.50. Incorrectly oriented or fractured 

fasteners could result in detachment of 

the flap hinge-box and the flap surface, 

and consequent reduced controllability 

of the airplane. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

replacement of incorrectly oriented 

fasteners, which will constitute 

terminating action for the repetitive 

inspections required by this AD action. 

However, the planned compliance time 

for the replacement would allow enough 

time to provide notice and opportunity 

for prior public comment on the merits 

of the modification. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0082; 

Directorate Identifier 2014–NM–233– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 120 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $10,200, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 58 work-hours and require parts 

costing $753, for a cost of $5,683 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

According to the manufacturer, some 

of the costs of this 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 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–02–23 Bombardier, Inc.: Amendment 

39–18092. Docket No. FAA–2015–0082; 

Directorate Identifier 2014–NM–233–AD. 

(a) Effective Date 

This AD becomes effective February 18, 

2015. 

(b) Affected ADs 

This AD affects AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014). 

(c) Applicability 

This AD applies to the Bombardier, Inc. 

airplanes identified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD, certificated in 

any category. 

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

(CL–600) airplanes, having serial numbers (S/ 

Ns) 1004 through 1085 inclusive. 

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

(CL–601) airplanes, having S/Ns 3001 

through 3066 inclusive. 


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

(CL–601–3A and CL–601–3R Variants) 

airplanes, having S/Ns 5001 through 5194 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by several reports 

of incorrectly oriented and fractured 

fasteners found on the inboard flap hinge-box 

forward fitting at wing station (WS) 76.50. 

We are issuing this AD to detect and correct 

incorrectly oriented or fractured fasteners, 

which could result in detachment of the flap 

hinge-box and the flap surface, and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection on Airplanes Not Previously 

Inspected 

For airplanes that have not been inspected 

as required by paragraph (g) of AD 2014–03– 

17, Amendment 39–17754 (79 FR 9389, 

February 19, 2014), as of the effective date of 

this AD: Within 10 flight cycles after the 

effective date of this AD or 100 flight cycles 

after March 6, 2014 (the effective date of AD 

2014–03–17), whichever occurs first, do a 

detailed visual inspection for incorrect 

orientation and any fractured or missing 

fastener heads of each inboard flap fastener 

of the hinge-box forward fitting at WS 76.50 

and WS 127.25, on both wings, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

Accomplishing the inspection required by 

this paragraph terminates the requirements of 

paragraph (g) of AD 2014–03–17 for the 

inspected airplane only. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(2) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, Revision 02, dated December 9, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013. 

(h) Corrective Actions for Paragraph (g) of 

This AD 

(1) If, during any inspection required by 

paragraph (g) of this AD, all fasteners are 

found correctly oriented and not fractured, 

and no fastener heads are missing (fasteners 

found intact): No further action is required by 

this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, any fastener is 

found incorrectly oriented but no fasteners 

are fractured or are missing a fastener head 

(fasteners found intact), repeat the inspection 

required by paragraph (g) of this AD 

thereafter at intervals not to exceed 10 flight 

cycles until the replacement specified in 

paragraph (h)(3) or (k) of this AD is 

accomplished. 

(3) If, during any inspection required by 

paragraph (g) of this AD, any fastener is 

found fractured or has a missing fastener 

head: Before further flight, remove and 

replace all forward and aft fasteners 

(regardless of orientation or condition) at WS 

76.50 and WS 127.25, on both wings, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (h)(3)(i) 

and (h)(3)(ii) of this AD, except as required 

by paragraph (m) of this AD. After 

accomplishing the replacement required by 

this paragraph, no further action is required 

by this AD. 

(i) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, Revision 02, dated December 9, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013. 

(i) Inspection for Airplanes Previously 

Inspected and Found To Have Incorrectly 

Oriented Fastener(s) 

For airplanes on which an inspection 

required by paragraph (g) or (j) of AD 2014– 

03–17, Amendment 39–17754 (79 FR 9389, 

February 19, 2014), has been done as of the 

effective date of this AD, and on which any 

incorrectly oriented fastener was found but 

no fasteners were fractured (fasteners found 

intact): Except as provided by paragraph (l) 

of this AD, within 10 flight cycles after the 

effective date of this AD, or within 100 flight 

cycles after accomplishing the most recent 

inspection required by AD 2014–03–17, 

whichever occurs first, do a detailed visual 

inspection for any fractured or missing 

fastener heads of each inboard flap fastener 

of the hinge-box forward fitting at WS 76.50 

and WS 127.25, on both wings. Do the 

inspection in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (i)(1) and (i)(2) of this AD. 

Accomplishing the inspection required by 

this paragraph terminates the requirements of 

paragraphs (g) and (j) of AD 2014–03–17 for 

the inspected airplane only. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(2) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, Revision 02, dated December 9, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013. 

(j) Corrective Actions for Paragraph (i) of 

This AD 

(1) If, during any inspection required by 

paragraph (i) of this AD, no fasteners are 

found fractured or have missing fastener 

heads (fasteners are intact), repeat the 

inspection required by paragraph (i) of this 

AD thereafter at intervals not to exceed 10 

flight cycles until the replacement specified 

in paragraph (j)(2) or (k) of this AD is 

accomplished. 

(2) If, during any inspection required by 

paragraph (i) of this AD, any fastener is found 

fractured or has a missing fastener head: 

Before further flight, remove and replace all 

forward and aft fasteners (regardless of 

orientation or condition) at WS 76.50 and WS 

127.25, on both wings, in accordance with 

the Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, 

except as required by paragraph (m) of this 

AD. After accomplishing the replacement 

required by this paragraph, no further action 

is required by this AD. 

(i) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, Revision 02, dated December 9, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013. 

(k) Optional Terminating Action for 

Incorrectly Oriented Fasteners 

Replacement of all forward and aft 

fasteners (regardless of orientation or 

condition) at WS 76.50 and WS 127.25, on 

both wings, terminates the requirements of 

this AD. The replacement must be done in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (k)(1) 

and (k)(2) of this AD, except as provided by 

paragraph (m) of this AD. Doing the 

replacement specified in this paragraph 

terminates the requirements of paragraphs (g) 

and (j) of AD 2014–03–17, Amendment 39– 

17754 (79 FR 9389, February 19, 2014), only 

for the airplane on which the replacement 

was done. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes having S/Ns 1004 through 1085 

inclusive: Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(2) For Model CL–600–2A12 (CL–601) 

airplanes having S/Ns 3001 through 3066 

inclusive, and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes 

having S/Ns 5001 through 5194 inclusive: 

Bombardier Alert Service Bulletin A601– 

0627, Revision 02, dated December 9, 2014, 


tkelley on DSK3SPTVN1PROD with RULES
5674 Federal Register / Vol. 80, No. 22 / Tuesday, February 3, 2015 / Rules and Regulations 

including Appendices 1 and 2, dated 

September 26, 2013. 

(l) Exception for Previously Replaced 

Fasteners 

Replacement of all fractured and 

incorrectly oriented forward and aft 

fasteners, as specified in paragraph (i) or (k) 

of AD 2014–03–17, Amendment 39–17754 

(79 FR 9389, February 19, 2014), if done 

before the effective date of this AD, is 

considered acceptable for compliance with 

the requirements of this AD. 

(m) Exception to the Service Information 

Where Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013; and Bombardier Alert 

Service Bulletin A601–0627, Revision 02, 

dated December 9, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; specify to contact Bombardier for 

repair instructions, before further flight, 

repair using a method approved by the 

Manager, New York Aircraft Certification 

Office (ACO), FAA; or Transport Canada 

Civil Aviation (TCCA); or Bombardier’s 

TCCA Design Approval Organization (DAO). 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

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

AD, if those actions were performed before 

the effective date of this AD using the 

applicable service information identified in 

paragraphs (n)(1) through (n)(4) of this AD. 

(1) Bombardier Alert Service Bulletin 

A600–0763, including Appendices 1 and 2, 

dated September 26, 2013, which was 

previously incorporated by reference on 

March 6, 2014 (79 FR 9389, February 19, 

2014). 

(2) Bombardier Alert Service Bulletin 

A600–0763, Revision 01, dated February 26, 

2014, including Appendices 1 and 2, dated 

September 26, 2013, which is not 

incorporated by reference in this AD. 

(3) Bombardier Alert Service Bulletin 

A601–0627, including Appendices 1 and 2, 

dated September 26, 2013, which was 

previously incorporated by reference on 

March 6, 2014 (79 FR 9389, February 19, 

2014). 

(4) Bombardier Alert Service Bulletin 

A601–0627, Revision 01, dated February 26, 

2014, including Appendices 1 and 2, dated 

September 26, 2013, which is not 

incorporated by reference in this AD. 

(o) 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, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(p) Special Flight Permits 

Special flight permits to operate the 

airplane to a location where the airplane can 

be repaired in accordance with sections 

21.197 and 31.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199) are 

not allowed. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2013–39R2, dated December 12, 2014, for 

related information. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–0082. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (r)(3) and (r)(4) of this AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A601–0627, Revision 02, dated December 9, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(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 January 

20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01661 Filed 2–2–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 870 

[Docket No. FDA–2013–N–0234] 

Effective Date of Requirement for 

Premarket Approval for Automated 

External Defibrillator Systems; 

Republication 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final order; republication. 

SUMMARY: The Food and Drug 

Administration (FDA or the Agency) is 

republishing in its entirety a final order 

entitled ‘‘Effective Date of Requirement 

for Premarket Approval for Automated 

External Defibrillator’’ that published in 

the Federal Register on January 29, 

2015 (80 FR 4783). FDA is republishing 

to correct an inadvertent omission of a 

comment regarding adverse tissue 

reaction as a risk to health and the 

Agency’s response to that comment. The 

final order requires the filing of 

premarket approval applications (PMA) 

for automated external defibrillator 

(AED) systems, which consist of an AED 

and those AED accessories necessary for 

the AED to detect and interpret an 

electrocardiogram and deliver an 

electrical shock (e.g., pad electrodes, 

batteries, adapters, and hardware keys 

for pediatric use). 

DATES: This order is effective on 

February 3, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Linda Ricci, Center for Devices and 

Radiological Health, 10903 New 

Hampshire Ave., Bldg. 66, rm. 1314, 

Silver Spring, MD 20993, 301–796– 

6325, linda.ricci@fda.hhs.gov. 

SUPPLEMENTARY INFORMATION: 

I. Background—Regulatory Authorities 

The Federal Food, Drug, and Cosmetic 

Act (the FD&C Act), as amended by the 

Medical Device Amendments of 1976 

(the 1976 amendments) (Pub. L. 94– 

295), the Safe Medical Devices Act of 

1990 (Pub. L. 101–629), the Food and 

Drug Administration Modernization Act 

of 1997 (Pub. L. 105–115), the Medical 

Device User Fee and Modernization Act 


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