54846 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

Dated: August 31, 2012. 

Meredith Fuchs, 

General Counsel, Bureau of Consumer 

Financial Protection. 

[FR Doc. 2012–21998 Filed 9–5–12; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0930; Directorate 

Identifier 2011–NM–251–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 BD–100–1A10 

(Challenger 300) airplanes. This 

proposed AD was prompted by reports 

of failure of a screw cap or end cap of 

the auxiliary hydraulic system 

accumulator while on the ground, 

which resulted in loss of use of that 

hydraulic system and high-energy 

impact damage to adjacent systems and 

structures. This proposed AD would 

require inspecting for the correct serial 

number of a certain hydraulic system 

accumulator, and replacing affected 

hydraulic system accumulators with 

new or serviceable accumulators. We 

are proposing this AD to prevent failure 

of a screw cap or end cap and loss of 

the related hydraulic system, which 

could result in damage to airplane 

structure and consequent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 22, 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, 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; 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 (ACO), 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–2012–0930; Directorate Identifier 

2011–NM–251–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–2011–41, 

dated October 31, 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. To 

date, the lowest number of flight cycles 

accumulated at the time of failure has been 

6991. 

Although there have been no failures to 

date on any BD–100–1A10 aeroplanes, 

accumulators similar to those installed on the 

CL–600–2B19 are installed on them. The 

affected part numbers (P/Ns) of the 

accumulators installed on BD–100–1A10 are 

900095–1 (Auxiliary Hydraulic System 

accumulator), 08–60219–001 (Inboard Brake 

accumulator), and 08–60218–001 (Outboard 

Brake accumulator). 

A detailed analysis of the calculated line 

of trajectory of a failed screw cap/end cap for 

the accumulator has been conducted, 

resulting in the identification of 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 [TCCA] directive provides the initial 

action by mandating the replacement of the 

Auxiliary Hydraulic System accumulators 

that are not identified by the letter ‘‘E’’ after 

the serial number on the identification plate. 

Further corrective actions are anticipated to 

rectify similar safety concerns with the 

Inboard and Outboard Brake accumulators. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 100–29–14, dated December 16, 

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 

We estimate that this proposed AD 

would affect 75 airplanes of U.S. 

registry. We estimate the following costs 

to comply with this proposed AD 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54847 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection to determine part numbers ............ 1 work-hour × $85 per hour = $85 ................. $0 $85 $6,375 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Hydraulic accumulator replacement ............................. 4 work-hours × $85 per hour = $340 ........................... $0 $340 

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– 

0930; Directorate Identifier 2011–NM– 

251–AD. 

(a) Comments Due Date 

We must receive comments by October 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

certificated in any category, having serial 

numbers 20003 through 20335 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Reason 

This AD was prompted by reports of failure 

of a screw-cap or end cap of the auxiliary 

hydraulic system accumulator while on the 

ground, which resulted in loss of use of that 

hydraulic system and high-energy impact 

damage to adjacent systems and structures. 

We are issuing this AD to prevent failure of 

a screw cap or end cap and loss of the related 

hydraulic system, which could result in 

damage to airplane structure and consequent 

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 

At the applicable time specified in 

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

Inspect the identification plate on the 

hydraulic system accumulator having part 

number (P/N) 900095–1 to determine if an 

‘‘E’’ is part of the suffix of the serial number 

stamped on the identification plate, as listed 

in paragraph 2.B. of the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–29–14, dated December 16, 2010. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

suffix of the serial number can be 

conclusively determined from that review. 

(1) For an accumulator that has 

accumulated more than 3,150 total flight 

cycles as of the effective date of this AD, 

inspect that accumulator within 350 flight 

cycles after the effective date of this AD. 

(2) For an accumulator that has 

accumulated 3,150 or fewer total flight cycles 

as of the effective date of this AD, inspect 

that accumulator before it has accumulated 

3,500 total flight cycles. 

(3) For an accumulator on which it is not 

possible to determine the total flight cycles 

accumulated as of the effective date of this 

AD, inspect that accumulator within 350 

flight cycles after the effective date of this 

AD. 

(h) Replacement 

If, during the inspection required by 

paragraph (g) of this AD, any accumulator 

having P/N 900095–1 is found on which the 

letter ‘‘E’’ is not part of the suffix of the serial 

number on the identification plate: Before 

further flight, replace the accumulator with a 

new or serviceable accumulator, in 

accordance with paragraph 2.C. of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–29–14, dated December 

16, 2010. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
54848 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane a 

hydraulic system accumulator having P/N 

900095–1, on which the letter ‘‘E’’ is not part 

of the suffix of the serial number on the 

identification plate. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

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

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to 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) 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 FAAapproved 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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–41, dated October 31, 

2011; and Bombardier Service Bulletin 100– 

29–14, dated December 16, 2010; for related 

information. 

(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 review copies of the referenced 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21946 Filed 9–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0863; Directorate 

Identifier 2012–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 737–300, 

–400, –500, –600, –700, –700C, –800, 

–900, and –900ER series airplanes. This 

proposed AD was prompted by a review 

of the tail strobe light installation, 

which revealed that the tail strobe light 

is not electrically bonded to primary 

structure of the airplane. This proposed 

AD would require installing a new tail 

strobe light housing and a new 

disconnect bracket, and changing the 

wire bundles. We are proposing this AD, 

in case of a direct lightning strike to the 

tail strobe light, to prevent damage to 

the operation of other critical airplane 

systems due to electromagnetic coupling 

and large transient voltages, and damage 

to the control mechanisms or surfaces 

due to a fire, which could result in loss 

of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 22, 2012. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356. 

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 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, 

ANM–130S, Seattle Aircraft 

Certification Office, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

phone: (425) 917–6418; fax: (425) 917– 

6590; email: marie.hogestad@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0863; Directorate Identifier 2012– 

NM–108–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 because of 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 

As a result of a review of the tail 

strobe light installation, located at the 

aft end of section 48, it was determined 

that the tail strobe light is not 

electrically bonded to primary structure 

of the airplane. In case of a direct 

lightning strike to the tail strobe light, 

electromagnetic coupling and large 

transient voltages can be transmitted 

into the pressure vessel and couple to 

wires of the airplane systems that are 

routed with the tail strobe light wires. 

The large transient voltages could cause 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS