Federal Register / Vol. 77, No. 44 / Tuesday, March 6, 2012 / Rules and Regulations 13191 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in Table 1 of this AD, 

except as required by paragraph (k) of this 

AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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. Information may be mailed to 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authority (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6432; fax: 425–917– 

6590; email: bill.ashforth@faa.gov. 

(o) Material Incorporated by Reference 

You must use Boeing Service Bulletin 747– 

53A2563, Revision 4, dated May 6, 2010, to 

do the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on February 

17, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–4520 Filed 3–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0992; Directorate 

Identifier 2011–NM–126–AD; Amendment 

39–16968; AD 2012–04–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B16 

(CL–604 Variant) airplanes. This AD 

was prompted by reports of the airdriven generator (ADG) failing to 

provide power during operational/ 

function checks due to wires in the ADG 

power feeder cables being damaged. The 

damage was due to galvanic corrosion 

and inadequate silver-plating. This AD 

requires replacing ADG power feeder 

cables. We are issuing this AD to 

prevent galvanic corrosion on ADG 

power feeder cables, which could result 

in damage to the cable and consequently 

the cable may not be able to provide 

emergency electrical power to the 

airplane. 

DATES: This AD becomes effective April 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 10, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 23, 2011 (76 FR 

59067). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Three (3) events have occurred where the 

Air-Driven Generator (ADG) failed to provide 

power on CL–600–2B19 (CRJ) aeroplanes 

during their regularly scheduled operational/ 

functional checks. An investigation revealed 

that in all cases, the silver-plated copper 

wires within the ADG power feeder cables 

were damaged due to galvanic corrosion. It 

was subsequently determined that the silverplating is inadequate for this application. 

In the event of damage to the power feeder 

cable wires, the ADG may not be able to 

provide emergency electrical power to the 

aeroplane. 

Although there have been no reported 

failures to date on any CL–600–2B16 (604 

Variant) aeroplanes, a sampling program 

carried out on these aeroplanes showed signs 

of microscopic galvanic corrosion on the 

ADG power feeder cable wires. 

This [Transport Canada] directive is issued 

to correct this potentially unsafe condition by 

mandating the replacement of all ADG power 

feeder cables * * * with an ADG power 

feeder cable that contains tin-plated copper 

wires. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Revise Applicability 

Bombardier Aerospace (Bombardier) 

commented that the aircraft 

applicability needs to be revised to 

remove two of the three model 

designations (Model CL–601–3A and 

–3R) specified in the NPRM (76 FR 

59067, September 23, 2011), because 

only airplanes of the Model CL–604 

Variant are affected by the proposed 

actions of the NPRM. 

We agree to revise the applicability of 

this AD as requested. The airplane serial 

numbers specified in Transport Canada 

Civil Aviation (TCCA) Airworthiness 

Directive CF–2011–08, dated April 28, 

2011 (cited in the NPRM (76 FR 59067, 

September 23, 2011) as the Canadian 

mandatory continuing airworthiness 

information (MCAI)), and Bombardier 

Service Bulletin 604–24–024, dated 

January 31, 2011 (cited as the 

appropriate service information for 

accomplishing the actions proposed by 

the NPRM) are all of the Model CL–604 


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13192 Federal Register / Vol. 77, No. 44 / Tuesday, March 6, 2012 / Rules and Regulations 

Variant. We have changed the affected 

airplanes specified in the applicability 

in the Summary and in paragraph (c) of 

this AD accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 72 products of U.S. registry. We 

also estimate that it will take about 24 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $1,897 

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 

this AD to the U.S. operators to be 

$283,464, or $3,937 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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 AD and placed it in the AD docket. 

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 the NPRM (76 FR 59067, 

September 23, 2011), 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. 

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 AD: 

2012–04–12 Bombardier, Inc.: Amendment 

39–16968. Docket No. FAA–2011–0992; 

Directorate Identifier 2011–NM–126–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 10, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 (CL –604 Variant) airplanes, 

certificated in any category, serial numbers 

5301, 5302, 5305 through 5318 inclusive, 

5320 through 5328 inclusive, 5331 through 

5349 inclusive, 5351 through 5367 inclusive, 

5369 through 5408 inclusive, 5410, 5412 

through 5426 inclusive, 5428 through 5438 

inclusive, 5440 through 5489 inclusive, 5491 

through 5498 inclusive, 5500 through 5517 

inclusive, 5519 through 5522 inclusive, and 

5524 through 5665 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24: Electrical power. 

(e) Reason 

This AD was prompted by reports of the 

air-driven generator (ADG) failing to provide 

power during operational/function checks 

due to wires in the ADG power feeder cables 

being damaged. The damage was due to 

galvanic corrosion and inadequate silverplating. We are issuing this AD to prevent 

galvanic corrosion on ADG power feeder 

cables, which could result in damage to the 

cable and consequently the cable may not be 

able to provide emergency electrical power to 

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) Actions 

Within 72 months after the effective date 

of this AD, replace the ADG power feeder 

cable, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 604–24–024, dated January 

31, 2011. 

(h) 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. 


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Federal Register / Vol. 77, No. 44 / Tuesday, March 6, 2012 / Rules and Regulations 13193 

(i) Related Information 

Refer to MCAI Transport Canada Civil 

Aviation (TCCA) Airworthiness Directive 

CF–2011–08, dated April 28, 2011; and 

Bombardier Service Bulletin 604–24–024, 

dated January 31, 2011; for related 

information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information. 

(i) Bombardier Service Bulletin 604–24– 

024, dated January 31, 2011, approved for 

IBR April 10, 2012. 

(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. 

(3) You may review copies of the service 

information at the FAA, 1601 Lind Avenue 

SW., Renton, Washington. For information 

on the availability of this material at the 

FAA, call (425) 227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on February 

22, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4805 Filed 3–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1230; Directorate 

Identifier 2011–NM–141–AD; Amendment 

39–16964; AD 2012–04–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model DHC–8–102, –103, and –106 

airplanes and Model DHC–8–200, –300, 

and –400 series airplanes. This AD was 

prompted by reports of cracking of the 

DHC–8 Series 100 rudder actuator 

mounting bracket. This AD requires 

modifying the mounting adapters of the 

power control unit (PCU). We are 

issuing this AD to prevent loss of both 

rudder PCU actuators which could 

result in free play of the rudder control 

surface and loss of controllability of the 

airplane. 

DATES: This AD becomes effective April 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 10, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 18, 2011 (76 FR 

71470). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received 

regarding cracking of the DHC–8 Series 100 

rudder actuator mounting bracket. An 

investigation revealed that the mounting 

bracket has been under-designed based on 

the static and endurance loading conditions. 

The failure of the mounting brackets that 

attach the power control unit (PCU) to the 

airframe could result in a loss of the rudder 

actuating system. The loss of both rudder 

PCU actuators could result in free play of the 

rudder control surface and potentially induce 

a flutter condition. 

This [TCCA] directive mandates the 

installation of a new design of rudder 

actuator mounting bracket [adapter]. 

The unsafe condition is loss of 

controllability of the airplane. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM (76 FR 

71470, November 18, 2011). 

Explanation of Change Made to This 

AD 

We have revised the heading for and 

the wording in paragraph (h) of this AD; 

this change has not changed the intent 

of that paragraph. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

71470, November 18, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 71470, 

November 18, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 171 products of U.S. registry. We 

also estimate that it will take up to 10 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost up to $2,856 

per product. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be up to $633,726, or 

$3,706 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 


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