16488 Federal Register / Vol. 77, No. 55 / Wednesday, March 21, 2012 / Proposed Rules 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(i) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0083, dated May 12, 2011, 

and the service information specified in 

paragraphs (i)(1) and (i)(2) of this AD, for 

related information. 

(1) Fokker Service Bulletin SBF50–24–032, 

including Fokker Manual Change 

Notification—Maintenance Documentation 

MCNM–F50–072, dated February 10, 2011. 

(2) Fokker Service Bulletin SBF100–24– 

043, including Fokker Manual Change 

Notification—Maintenance Documentation 

MCNM–F100–141, dated February 10, 2011. 

Issued in Renton, Washington, on March 9, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6804 Filed 3–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0271; Directorate 

Identifier 2011–NM–196–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 DHC–8–100, 

DHC–8–200, and DHC–8–300 series 

airplanes. This proposed AD was 

prompted by reports of hydraulic 

accumulator screw cap or end cap 

failure. This proposed AD would 

require replacing the affected parking 

brake accumulator. We are proposing 

this AD to prevent failure of the parking 

brake accumulator screw caps or end 

caps, which could result in loss of the 

number 2 hydraulic system and damage 

to airplane structures, and could 

potentially have an adverse effect on the 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 7, 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., Q–Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@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–2012–0271; Directorate Identifier 

2011–NM–196–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–2011–29, 

dated August 2, 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 or end cap failure 

have been experienced on CL–600–2B19 

(CRJ) 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 DHC–8 aeroplanes, similar 

accumulators to those installed on the CL– 

600–2B19, Part Numbers (P/N)0860162001 

and 0860162002 (Parking Brake 

Accumulator), are installed on the aeroplanes 

listed in the Applicability section of this 

[TCCA] directive. 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for the 

accumulator has been conducted. It has 

identified that the worst-case scenarios 

would be the loss of number 2 hydraulic 

system, and damage to aeroplane structures. 

This [TCCA] directive gives instructions to 

determine the part number and serial number 

of the existing parking brake accumulator, 

and where applicable, replace the 

accumulator. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 55 / Wednesday, March 21, 2012 / Proposed Rules 16489 

Failure of the parking brake 

accumulator screw caps and/or end caps 

could result in loss of the number 2 

hydraulic system, and damage to 

airplane structures, and could 

potentially have an adverse effect on the 

controllability of the airplane. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 8–32–170, dated February 25, 

2011; and Service Bulletin 8–32–172, 

dated March 15, 2011. 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 129 products of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$21,930, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $1,625, for a cost of $1,880 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– 

0271; Directorate Identifier 2011–NM– 

196–AD. 

(a) Comments Due Date 

We must receive comments by May 7, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–101, –102, –103, –106, –201, –202, 

–301, –311 and, –315 airplanes, certificated 

in any category, serial numbers 003 and 

subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of 

hydraulic accumulator screw cap or end cap 

failure. We are issuing this AD to prevent 

failure of the parking brake accumulator 

screw caps or end caps, which could result 

in loss of the number 2 hydraulic system and 

damage to airplane structures, and could 

potentially have an adverse effect on the 

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 and Replacement 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

comes first: Inspect to determine the part 

number (P/N) and serial number of the 

parking brake hydraulic accumulator, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–170, dated February 25, 2011. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and serial number of the parking brake 

hydraulic accumulator can be conclusively 

determined from that review. 

(1) For accumulators not having P/N 

0860162001 or 0860162002: No further 

action is required by this paragraph. 

(2) For accumulators having P/N 

0860162001 or 0860162002: Before further 

flight, do the applicable actions specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) If the serial number is listed in the table 

in paragraph 3.B.(2) of Bombardier Service 

Bulletin 8–32–170, dated February 25, 2011: 

No further action is required by this 

paragraph. 

(ii) If the serial number is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011: Within 2,000 flight hours or 12 

months after the effective date of this AD, 

whichever comes first, replace the 

accumulator with a new non-suspect 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–172, dated March 15, 

2011. 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install a parking brake 

accumulator, P/N 0860162001 or 0860162002 

with a serial number that is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011, on any airplane. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
16490 Federal Register / Vol. 77, No. 55 / Wednesday, March 21, 2012 / Proposed Rules 

(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–2011–29, dated August 2, 2011; 

and the service information identified in 

paragraphs (j)(1) and (j)(2) of this AD; for 

related information. 

(1) Bombardier Service Bulletin 8–32–170, 

dated February 25, 2011. 

(2) Bombardier Service Bulletin 8–32–172, 

dated March 15, 2011. 

Issued in Renton, Washington, on March 9, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6805 Filed 3–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0293; Directorate 

Identifier 2012–NM–034–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) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, and 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes. This proposed AD 

was prompted by reports of a bleed air 

leak from the high pressure ducts which 

was not immediately detected by the 

bleed leak detection system. This 

proposed AD would require installing 

new sensing elements in the main 

landing gear wheel well and the 

overwing area, protective blankets on 

the upper surface of the wing box and 

fuel tubes, and protective shields on the 

rudder quadrant support-beam in the aft 

equipment compartment. We are 

proposing this AD to prevent an 

undetected bleed air leak which can 

cause loss of rudder control, can lead to 

degradation of structural integrity, and 

could be a potential heat source that can 

lead to fuel being ignited. 

DATES: We must receive comments on 

this proposed AD by May 7, 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–2012–0293; Directorate Identifier 

2012–NM–034–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–2012–06, 

dated January 26, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

There have been multiple events reported 

where a bleed air leak from the high pressure 

ducts was not immediately detected by the 

Bleed Leak Detection System (BLDS). 

An investigation revealed that if a bleed air 

leak develops due to a cracked or ruptured 

duct, the duct shroud may not channel 

sufficient bleed air to the sensing loop 

elements to enable an automatic shutdown of 

the bleed air system. The inability to detect 

a bleed air leak could result in the rudder 

quadrant bracket, pressure floor, pressure 

floor beam, fuel vent boot or fuel tubes being 

exposed to high temperatures. This could 

potentially lead to the loss of rudder control, 

degrade the structural integrity of primary 

structure or fuel ignition. 

This [Canadian] Airworthiness Directive 

(AD) mandates the installation of newly 

designed sensing elements in the main 

landing gear wheel well and the overwing 

area, protective blankets on the upper surface 

of the wing box and fuel tubes, as well as 


srobinson on DSK4SPTVN1PROD with PROPOSALS