Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Proposed Rules 16193 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install a TMU, P/N 4100S018–06, 

on any airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

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

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–34, dated August 16, 

2011; and Bombardier Service Bulletin 84– 

30–14, dated May 20, 2011; for related 

information. 

Issued in Renton, Washington, on March 7, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6626 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0142; Directorate 

Identifier 2010–NM–275–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–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 

and CL–600–2D24 (Regional Jet Series 

900) airplanes. This proposed AD was 

prompted by reports of failures of a 

hydraulic accumulator’s screw-cap/end 

cap while on the ground that resulted in 

loss of use of that hydraulic system and 

in high-energy impact damage to 

adjacent systems and structures. This 

proposed AD would require an 

inspection for part numbers; repetitive 

inspections for any cracking of certain 

hydraulic system accumulators, and 

replacement, if necessary; and revising 

the maintenance program to include a 

life limit for certain hydraulic system 

accumulators. We are proposing this AD 

to prevent loss of use of a hydraulic 

system, which could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• 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 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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; 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 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; 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–2012–0142; Directorate Identifier 

2010–NM–275–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 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–35R1, 

dated June 28, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator screw cap/end cap failure have 

been experienced on CL–600–2B19 

aeroplanes resulting in loss of the associated 

hydraulic system and high-energy impact 

damage to adjacent systems and structure. 

The lowest number of flight cycles 

accumulated at the time of failure, to date, 

has been 6,991 flight cycles. 

Although there have been no failures to 

date on any CL–600–2C10, CL–600–2D15 or 

CL–600–2D24 aeroplanes, similar 

accumulators to those installed on the CL– 

600–2B19, are installed. The part numbers 

(P/Ns) of the accumulators installed on CL– 

600–2C10, CL–600–2D15 and CL–600–2D24 

aeroplanes are 900096–1 (Hydraulic System 

No. 1 and Hydraulic System No. 2 

accumulators), 900097–1 (Hydraulic System 

No. 3 accumulator) and 08–60204–001 

(Inboard Brake and Outboard Brake 

accumulators). 

A detailed analysis of the calculated line 

of trajectory of a failed screw cap/end cap for 

each of the accumulators has been 

conducted, resulting in the identification of 


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several areas where systems and/or structural 

components could potentially be damaged. 

Although all of the failures to date have 

occurred on the ground, an in-flight failure 

affecting such components could potentially 

have an adverse effect on the controllability 

of the aeroplane. 

This [Canadian] directive gives 

instructions to conduct [an inspection to 

determine if certain hydraulic accumulators 

are installed and, if necessary,] repetitive 

ultrasonic inspections [for cracking] of the 

Hydraulic System No. 1, Hydraulic System 

No. 2, Hydraulic System No. 3, Inboard Brake 

and Outboard Brake accumulators, P/Ns 

900096–1, 900097–1, and 08–60204–001, that 

are not identified by the letter ‘‘M’’ or ‘‘T’’ 

after the S/N [serial number] on the 

identification plate. 

* * * * * 

Required actions include revising the 

maintenance program to include a life 

limit for certain accumulators, and for 

airplanes on which cracking is found 

during an ultrasonic inspection, 

replacing the accumulator with a new 

accumulator containing the letter ‘‘M’’ 

or ‘‘T’’, as applicable, after the serial 

number on the identification plate or 

with a new accumulator with a different 

part number, and eventual replacement 

of certain accumulators with new 

accumulators. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bombardier has issued the following 

service information. 

• Bombardier Alert Service Bulletin 

A670BA–29–011, Revision A, dated July 

27, 2010, including Appendix A, 

Revision A, dated July 26, 2010. 

• Bombardier Alert Service Bulletin 

A670BA–29–012, including Appendix 

A, Revision A, dated July 27, 2010. 

• Bombardier Service Bulletin 

A670BA–32–021, Revision C, dated July 

27, 2010, including Appendix A, 

Revision A, dated October 18, 2007. 

• Bombardier Service Bulletin 

670BA–29–013, Revision A, dated July 

27, 2010, including Appendix A, dated 

January 29, 2010. 

• Bombardier Service Bulletin 

670BA–32–026, Revision A, dated July 

27, 2010, including Appendix A, dated 

January 29, 2010. 

• Bombardier Service Bulletin 

670BA–29–014, dated December 22, 

2010. 

• Bombardier Service Bulletin 

670BA–29–015, dated December 22, 

2010. 

• Bombardier Service Bulletin 

670BA–32–028, dated December 22, 

2010. 

• Tasks 29–11–11–000–801 and 29– 

11–11–400–801 of Section 1.3, Safe Life 

Components, of Part 2, Airworthiness 

Limitations, of the Bombardier CL–600– 

2C10, CL–600–2D15, CL–600–2D24, 

CL–600–2E25 Maintenance 

Requirements Manual, CSP B–053, 

Revision 11, dated October 20, 2010. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 389 products of U.S. 

registry. We also estimate that it would 

take up to 21 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $8,988 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be up 

to $4,190,697, or $10,773 per product, 

per inspection cycle. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 7 work-hours and require parts 

costing $8,988, for a cost of $9,583 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Bombardier, Inc.: Docket No. FAA–2012– 

0142; Directorate Identifier 2010–NM– 

275–AD. 


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(a) Comments Due Date 

We must receive comments by May 4, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, with serial number (S/N) 10003 

through 10314 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705) and CL–600–2D24 

(Regional Jet Series 900) airplanes, with S/N 

15001 through 15259 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29: Hydraulic Power, and 32: 

Landing Gear. 

(e) Reason 

This AD was prompted by reports of 

failures of a hydraulic accumulator’s screwcap/end cap while on the ground that 

resulted in loss of use of that hydraulic 

system and in high-energy impact damage to 

adjacent systems and structures. We are 

issuing this AD to prevent loss of use of a 

hydraulic system, which could result in 

reduced controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection for Part Numbers (P/Ns) 

At the applicable time specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

inspect the hydraulic accumulators in the 

hydraulic systems No. 1, No. 2, and No. 3, 

and the inboard and outboard brake systems, 

to determine the part number of the 

accumulator. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the 

accumulator can be conclusively determined 

from that review. 

(1) For an accumulator with more than 

4,500 total flight cycles as of the effective 

date of this AD, inspect that accumulator 

within 500 flight cycles after the effective 

date of this AD. 

(2) For an accumulator with 4,500 or less 

total flight cycles as of the effective date of 

this AD, inspect that accumulator before it 

has accumulated 5,000 total flight cycles. 

(3) If it is not possible to determine the 

total flight cycles accumulated on an 

accumulator, inspect that accumulator within 

500 flight cycles after the effective date of 

this AD. 

(h) Inspection for Letter Designation After 

the Serial Number 

If, during an inspection required by 

paragraph (g) of this AD, an accumulator 

having P/N 900096–1 (for hydraulic systems 

No. 1 and No. 2 accumulators), 900097–1 (for 

hydraulic system No. 3 accumulator), or 08– 

60204–001 (for inboard and outboard brake 

accumulators) is found, at the applicable 

time specified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD, do an inspection of the 

identification plate on the hydraulic 

accumulator to determine if an ‘‘M’’ (for 

hydraulic system accumulators) or a ‘‘T’’ (for 

brake system accumulators) follows the serial 

number on the identification plate. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and the letter of the accumulator can be 

conclusively determined from that review. 

Note 1 to paragraphs (h), (i), (k), (l)(2), and 

(m): The letter ‘‘M’’ after the serial number 

on the identification plate is applicable to 

accumulators, P/Ns 900096–1 and 900097–1, 

on hydraulic systems No. 1, No. 2, and No. 

3. The letter ‘‘T’’ after the serial number on 

the identification plate is applicable to 

accumulators, P/N 08–60204–001, on the 

brake system. 

(i) Initial Ultrasonic Inspections of 

Hydraulic System No. 1, Hydraulic System 

No. 2, Hydraulic System No. 3, Inboard 

Brake, and Outboard Brake Accumulators 

If, during any inspection required by 

paragraph (h) of this AD, any accumulator 

without the letter ‘‘M’’ (for hydraulic system 

accumulators) or a ‘‘T’’ (for brake system 

accumulators) after the serial number is 

found, at the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Do an ultrasonic inspection of the inner 

shoulders of the accumulator screw-cap for 

cracking, in accordance with Part B of the 

Accomplishment Instructions of the 

applicable Bombardier service bulletin 

identified in paragraphs (i)(1), (i)(2), and 

(i)(3) of this AD, and at the internal threads 

of the screw-caps, in accordance with the 

Accomplishment Instructions of the 

applicable Bombardier service bulletin 

identified in paragraphs (i)(4), (i)(5), and 

(i)(6) of this AD. 

(1) For hydraulic system No. 1, and 

hydraulic system No. 2 accumulators: 

Bombardier Alert Service Bulletin A670BA– 

29–011, Revision A, dated July 27, 2010, 

including Appendix A, Revision A, dated 

July 26, 2010. 

(2) For hydraulic system No. 3 

accumulators: Bombardier Alert Service 

Bulletin A670BA–29–012, including 

Appendix A, Revision A, dated July 27, 2010. 

(3) For inboard brake, outboard brake 

accumulators: Bombardier Service Bulletin 

A670BA–32–021, Revision C, dated July 27, 

2010, including Appendix A, Revision A, 

dated October 18, 2007. 

(4) For hydraulic system No. 1 

accumulators: Bombardier Service Bulletin 

670BA–29–013, Revision A, dated July 27, 

2010, including Appendix A, dated January 

29, 2010. 

(5) For hydraulic system No. 2 

accumulators: Bombardier Service Bulletin 

670BA–29–013, Revision A, dated July 27, 

2010, including Appendix A, dated January 

29, 2010. 

(6) For inboard brake, outboard brake 

accumulators: Bombardier Service Bulletin 

670BA–32–026, Revision A, dated July 27, 

2010, including Appendix A, dated January 

29, 2010. 

(j) No Cracking Found During 

Accomplishment of Paragraph (i) of This AD 

If no cracking is found during the 

inspections required by paragraph (i) of this 

AD, do the actions required by paragraph (l) 

of this AD. 

(k) Any Cracking Found During 

Accomplishment of Paragraph (i) of This AD 

If any cracking is found during the 

inspections required by paragraph (i) of this 

AD, before further flight, replace the 

accumulator with a new accumulator 

containing the letter ‘‘M’’ or ‘‘T’’, as 

applicable, after the serial number on the 

identification plate, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (i)(1) through (i)(6) of this AD, or 

replace the accumulator with a new 

accumulator as specified in paragraphs (k)(1) 

through (k)(3) of this AD, as applicable. 

(1) For any cracked hydraulic system No. 

1 or No. 2 accumulator, replace the cracked 

accumulator with a new accumulator, P/N 

900121–1, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–29–014, dated 

December 22, 2010. 

(2) For any cracked hydraulic system No. 

3 accumulator, replace the cracked 

accumulator with a new accumulator, P/N 

900122–1, in accordance with the 

replacement specified in paragraph (o) of this 

AD. 

(3) For any cracked inboard brake or 

outboard brake accumulator replaced the 

cracked accumulator with a new 

accumulator, P/N 90006691, in accordance 

with the replacement specified in paragraph 

(p) of this AD. 

(l) Repetitive Ultrasonic Inspections of 

Hydraulic System No. 1, Hydraulic System 

No. 2, Hydraulic System No. 3, Inboard 

Brake, and Outboard Brake Accumulators 

For each accumulator on which no 

cracking was found during any inspection 

required by paragraph (i) of this AD, within 

500 flight cycles after the previous ultrasonic 

inspection, inspect the accumulator in 

accordance with paragraph (i) of this AD. 

(1) If no cracking is found, do the actions 

required by paragraph (l) of this AD and 

repeat thereafter at intervals not to exceed 

500 flight cycles. 

(2) If any cracking is found, before further 

flight, replace the accumulator with a new 

accumulator containing the letter ‘‘M’’ or 

‘‘T’’, as applicable, after the serial number on 

the identification plate, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (i)(1) through (i)(6) of this AD, or 

replace the accumulator with a new 

accumulator as specified in paragraphs (k)(1), 

(k)(2), and (k)(3) of this AD, as applicable. 

(m) Replacement of Hydraulic System No. 1 

and No. 2 Accumulators 

For airplanes on which a hydraulic system 

No. 1 or No. 2 accumulator having P/N 

900096–1 without the letter ‘‘M’’ after the 

serial number is installed: At the applicable 

time specified in paragraphs (m)(1) and 

(m)(2) of this AD, replace the accumulator 


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with a new one having P/N 900096–1 with 

the letter ‘‘M’’ after the serial number; or 

having P/N 900121–1, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–29–014, dated 

December 22, 2010. 

(1) For an accumulator with more than 

19,500 total flight cycles as of the effective 

date of this AD, replace that accumulator 

within 500 flight cycles after accomplishing 

the most recent inspection required by 

paragraph (i) or (l) of this AD. 

(2) For an accumulator with 19,500 or less 

total flight cycles as of the effective date of 

this AD, replace that accumulator before it 

has accumulated 20,000 total flight cycles. 

(3) If it is not possible to determine the 

total flight cycles accumulated on an 

accumulator, replace that accumulator within 

500 flight cycles after accomplishing the 

most recent ultrasonic inspection required by 

paragraph (i) or (l) of this AD. 

(n) Hydraulic System Safe Life Limit 

Introduction 

Within 60 days after the effective date or 

this AD, revise the maintenance program to 

include a safe life limit for the hydraulic 

system No. 1 and No. 2 accumulators, P/N 

900096–1, by incorporating Tasks 29–11–11– 

000–801 and 29–11–11–400–801 of Section 

1.3, Safe Life Components, of Part 2, 

Airworthiness Limitations, of the Bombardier 

CL–600–2C10, CL–600–2D15, CL–600–2D24, 

CL–600–2E25 Maintenance Requirements 

Manual, CSP B–053, Revision 11, dated 

October 20, 2010. 

(o) Replacement of Hydraulic System No. 3 

Accumulator 

Within 4,000 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first, replace any hydraulic system No. 

3 accumulator having P/N 900097–1 with a 

new accumulator having P/N 900122–1, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–29–015, dated December 22, 2010. 

(p) Replacement of Inboard or Outboard 

Brake System Accumulators 

Within 4,000 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first, replace any inboard or outboard 

brake system accumulator having P/N 08– 

60204–001 with a new accumulator having 

P/N 90006691, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–028, dated 

December 22, 2010. 

(q) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) Actions done before the effective date 

of this AD using Part B of the 

Accomplishment Instructions of the 

Bombardier service bulletin identified in 

paragraph (q)(1)(i), (q)(1)(ii), (q)(1)(iii), 

(q)(1)(iv), or (q)(1)(v) of this AD is acceptable 

for compliance with the corresponding 

requirements of this AD. 

(i) Bombardier Alert Service Bulletin 

A670BA–29–011, dated October 18, 2007. 

(ii) Bombardier Alert Service Bulletin 

A670BA–29–012, dated March 13, 2008. 

(iii) Bombardier Alert Service Bulletin 

A670BA–32–021, dated November 21, 2006. 

(iv) Bombardier Alert Service Bulletin 

A670BA–32–021, Revision A, dated March 7, 

2007. 

(v) Bombardier Alert Service Bulletin 

A670BA–32–021, Revision B, dated October 

18, 2007. 

(2) Actions done before the effective date 

of this AD using the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–29–013, dated January 29, 2010; or 

670BA–32–026, dated January 29, 2010; are 

acceptable for compliance with the 

corresponding requirements of this AD. 

(r) Terminating Actions 

Accomplishing the actions required by 

paragraphs (m), (n), (o), and (p) of this AD 

terminates the requirements of this AD for 

the accumulator at that location only. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, 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 manager of the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(t) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2010–35R1, dated June 28, 

2011, and the service information identified 

in paragraphs (t)(1) through (t)(9) of this AD, 

for related information. 

(1) Bombardier Alert Service Bulletin 

A670BA–29–011, Revision A, dated July 27, 

2010, including Appendix A, Revision A, 

dated July 26, 2010. 

(2) Bombardier Alert Service Bulletin 

A670BA–29–012, including Appendix A, 

Revision A, dated July 27, 2010. 

(3) Bombardier Service Bulletin A670BA– 

32–021, Revision C, dated July 27, 2010, 

including Appendix A, Revision A, dated 

October 18, 2007. 

(4) Bombardier Service Bulletin 670BA– 

29–013, Revision A, dated July 27, 2010, 

including Appendix A, dated January 29, 

2010. 

(5) Bombardier Service Bulletin 670BA– 

32–026, Revision A, dated July 27, 2010, 

including Appendix A, dated January 29, 

2010. 

(6) Bombardier Service Bulletin 670BA– 

29–014, dated December 22, 2010. 

(7) Bombardier Service Bulletin 670BA– 

29–015, dated December 22, 2010. 

(8) Bombardier Service Bulletin 670BA– 

32–028, dated December 22, 2010. 

(9) Tasks 29–11–11–000–801 and 29–11– 

11–400–801 of Section 1.3, Safe Life 

Components, of Part 2, Airworthiness 

Limitations, of the Bombardier CL–600– 

2C10, CL–600–2D15, CL–600–2D24, CL–600– 

2E25 Maintenance Requirements Manual, 

CSP B–053, Revision 11, dated October 20, 

2010. 

Issued in Renton, Washington, on January 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–6622 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

28 CFR Parts 35 and 36 

[CRT Docket No. 123; AG Order No. 3327– 

2012] 

RIN 1190–AA69 

Delaying the Compliance Date for 

Certain Requirements of the 

Regulations Implementing Titles II and 

III of the Americans With Disabilities 

Act 

AGENCY: Civil Rights Division, 

Department of Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: By this rule, the Department 

of Justice is proposing to extend the date 

for compliance with certain 

requirements in the 2010 Americans 

with Disabilities Act (ADA) Standards 

for Accessible Design that relate to 

provision of accessible entry and exit for 

existing swimming pools and spas. 

Concurrently with the publication of 

this Notice of Proposed Rulemaking 

(NPRM), the Department is publishing a 

final rule that extends the compliance 

date with respect to existing swimming 

pools, wading pools, and spas to May 

21, 2012 in order to allow additional 

time to address misunderstandings 

among pool owners and operators 

regarding these ADA requirements. By 

this rule, the Department seeks public 

comment on its proposal to extend the 

compliance date for a longer period of 

six months, until September 17, 2012 in 

the interest of promoting clear and 

consistent application of the ADA’s 

requirements to existing facilities. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS