27318 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200, –200PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fractured rudder pedal pushrod connecting 

bolts in the rudder pedal assembly. We are 

issuing this AD to prevent fracture of the 

rudder pedal pushrod connecting bolts 

during pedal use, which could result in a 

large involuntary input to the rudder, nosewheel steering, and braking systems, leading 

to a runway excursion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 60 months after the effective date 

of this AD, do a detailed inspection of the 

rudder pedal assembly bolt holes to 

determine the diameter, in each of the 

captain and the first officer rudder pedal 

assemblies, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–27A0153, dated May 9, 

2012, as revised by Boeing Alert Service 

Bulletin 757–27A0153, Revision 1, dated 

October 29, 2012. Repeat this inspection 

thereafter at intervals not to exceed 15,000 

flight cycles. 

(h) Installation 

Do the applicable actions specified in 

paragraph (h)(1), (h)(2), or (h)(3) of this AD 

for each of the captain and first officer rudder 

pedal assemblies, based on the results of any 

inspection required by paragraph (g) of this 

AD. Accomplishment of paragraph (h)(1), 

(h)(2), or (h)(3) of this AD terminates the 

requirements of AD 2001–22–13, 

Amendment 39–12492 (66 FR 55075, 

November 1, 2001), for that Model 757 

airplane only. 

(1) If the diameters of both holes are within 

0.3120 and 0.3140 inch on the assembly, 

before further flight, install new rudder pedal 

pushrod connect bolt, washer, nut, and cotter 

pin, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(2) If the diameter of only one hole is 

greater than 0.3140 inch on the assembly, 

before further flight, do the actions specified 

in paragraphs (h)(2)(i) and (h)(2)(ii) of this 

AD. 

(i) Install a new rudder pedal assembly, or 

install a bushing in the worn hole, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(ii) Install new rudder pedal pushrod 

connecting bolt, washer, nut, and cotter pin, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(3) If the diameters of both holes are greater 

than 0.3140 inch on the assembly, before 

further flight, do the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. 

(i) Install a new rudder pedal assembly, or 

install two bushings in the two worn holes, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(ii) Install new rudder pedal pushrod 

connecting bolt, washer, nut, and cotter pin, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install, in a rudder pedal 

assembly of any Boeing 757 airplane, a bolt 

having part number (P/N) 

BACB30NM5DK47. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if operators installed washers having 

part number NAS1149D0516J, 

NAS1149D0532J, and NAS1149D0563J, and 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 757–27A0153, dated May 9, 

2012, which is not incorporated by reference 

in this AD, as unmodified by Boeing Alert 

Service Bulletin 757–27A0153, Revision 1, 

dated October 29, 2012. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-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 Authorization (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. 

(l) Related Information 

(1) For more information about this AD, 

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. 

(2) For service information identified in 

this 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. 

Issued in Renton, Washington, on May 2, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11168 Filed 5–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0367; Directorate 

Identifier 2012–NM–177–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 a report of corrosion 

of the components of the main landing 

gear (MLG) retraction actuator found in 

service; the corrosion was found at the 

interface of the rod end and the piston, 

and at the bracket and related pins. This 

proposed AD would require inspection 

of the MLG retraction actuator 

components; corrective actions if 

necessary; and, for certain retraction 

actuators, installation of a new jam nut. 

We are proposing this AD to prevent 

disconnection of the MLG retraction 

actuator, which could result in 

extension of the MLG without damping, 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 27319 

and consequent structural damage and 

collapse of the MLG during landing. 

DATES: We must receive comments on 

this proposed AD by June 24, 2013. 

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 Bombardier 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. For 

Goodrich service information identified 

in this proposed AD, contact Goodrich 

Corporation, Landing Gear, 1400 South 

Service Road, West Oakville L6L 5Y7, 

Ontario, Canada; telephone 905–825– 

1568; email jean.breed@goodrich.com; 

Internet http://www.goodrich.com/ 

TechPubs. 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–2013–0367; Directorate Identifier 

2012–NM–177–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–2011–36R1, 

dated October 3, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Corrosion of the main landing gear (MLG) 

retraction actuator components was found inservice, either at the interface of the rod end 

and the piston or at the bracket and its 

related pins. This can cause the MLG 

retraction actuator to disconnect, leading to 

an MLG extension without damping, and a 

potential for MLG structural damage and 

possible collapse during landing. 

This [Canadian] AD mandates the inspection 

and rectification [corrective action] of the 

MLG retraction actuator components. 

This revision is to mandate [, for certain MLG 

retraction actuators,] the installation of the 

new retraction actuator jam nut. This 

revision also corrects the background 

information and updates Service Bulletin 

(SB) references. 

The required inspection includes, for 

certain MLG retraction actuator 

assemblies, a detailed inspection of the 

retraction actuator assembly for 

evidence of corrosion, and security of 

the jam nut; and, for certain MLG 

dressed shock struts, a detailed 

inspection for evidence of corrosion of 

the retract actuator bracket assembly, 

associated pins, and mating lugs on the 

outer cylinder and a detailed inspection 

of the associated pins for chrome 

damage. The corrective actions include 

replacing pins that have chrome damage 

or evidence of corrosion, replacing 

retraction actuator bracket assemblies 

and mating lugs that have evidence of 

corrosion. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued the 

following service bulletins. 

• Bombardier Service Bulletin 

670BA–32–031, Revision C, dated April 

17, 2012. 

• Bombardier Service Bulletin 

670BA–32–033, Revision B, dated Jun 

26, 2012. 

Goodrich Corporation has issued the 

following service bulletins. 

• Goodrich Service Bulletin 49000– 

32–46, Revision 2, dated November 11, 

2011. 

• Goodrich Service Bulletin 49600– 

32–63, Revision 1, dated May 17, 2011. 

• Goodrich Service Bulletin 49600– 

32–64, Revision 3, dated December 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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies using ‘‘later 

approved revisions’’ of the service 

information when accomplishing the 

requirements. However, ‘‘later approved 

revisions’’ must not be used in an AD 

when referring to the service document 

because doing so violates Office of the 

Federal Register (OFR) regulations for 

approval of materials ‘‘incorporated by 

reference’’ in rules. Therefore, we have 

not included ‘‘later approved revisions’’ 

in this proposed AD. If additional parts 

are identified in later revisions of the 

service information, we might consider 

further rulemaking then. 

Goodrich Service Bulletin 49600–32– 

63, Revision 1, dated May 17, 2011, 

specifies to return retract actuators to 

Goodrich if corrosion is found or if a 

jam nut is not secured. However, this 

proposed AD would require replacing 

the retract actuators with new or 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
27320 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 

serviceable retract actuators if those 

conditions are found. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 391 products of U.S. 

registry. We also estimate that it would 

take up to 16 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 $1,018 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 $929,798, or up to $2,378 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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–2013– 

0367; Directorate Identifier 2012–NM– 

177–AD. 

(a) Comments Due Date 

We must receive comments by June 24, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

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, serial numbers 10002 and 

subsequent. 

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

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

(Regional Jet Series 900) airplanes, serial 

numbers 15001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by a report of 

corrosion of the components of the main 

landing gear (MLG) retraction actuator found 

in service; the corrosion was found at the 

interface of the rod end and the piston, and 

at the bracket and related pins. We are 

issuing this AD to prevent disconnection of 

the MLG retraction actuator, which could 

result in extension of the MLG without 

damping, and consequent structural damage 

and collapse of the MLG during landing. 

(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 of the MLG Retraction 

Actuator and Corrective Actions 

For any airplane with a MLG retraction 

actuator assembly having any part number 

and serial number identified in paragraph 

1.A., Effectivity, of Bombardier Service 

Bulletin 670BA–32–031, Revision C, dated 

April 17, 2012, except airplanes on which 

modification status ‘‘32–64’’ is marked on the 

identification plate: At the applicable time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, perform a detailed inspection of the 

retraction actuator assembly for evidence of 

corrosion and security of the jam nut, as 

applicable, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012; and Goodrich Service 

Bulletin 49600–32–63, Revision 1, dated May 

17, 2011. If any corrosion or unsecured jam 

nut is found, before further flight, replace the 

retract actuator with a new or serviceable 

retract actuator; install the retract actuator in 

accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012. Repeat the inspection 

at intervals not to exceed 1,200 flight hours 

or 12 months, whichever occurs first. 

(1) For MLG retraction actuator assemblies 

on which, as of the effective date of this AD, 

8,000 or more total flight hours have 

accumulated since new or since overhaul, or 

have been in service for more than 4 years 

since new or since overhaul: Inspect within 

1,200 flight hours or 12 months after the 

effective date of this AD, whichever occurs 

first. 

(2) For MLG retraction actuator assemblies 

on which, as of the effective date of this AD, 

less than 8,000 total flight hours have 

accumulated since new or since overhaul, 

and have been in service for 4 years or less 

since new or since overhaul: Inspect before 

the accumulation of 9,200 total flight hours 

on the MLG retraction actuator assembly 

since new or since overhaul or within 5 years 

in service since new or since overhaul, 

whichever occurs first. 

(h) Inspection of MLG Retraction Actuator 

Bracket and Related Pins, and Corrective 

Actions 

For any airplane with a MLG dressed shock 

strut having any part number and serial 

number identified in paragraph 1.A., 

Effectivity, of Bombardier Service Bulletin 

670BA–32–033, Revision B, dated June 26, 

2012: Within 4,400 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first, perform a detailed inspection of 

the retract actuator bracket assembly, 

associated pins, and the mating lugs on the 

outer cylinder for evidence of corrosion, in 

accordance with Bombardier Service Bulletin 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 27321 

670BA–32–033, Revision B, dated June 26, 

2012; and Goodrich Service Bulletin 49000– 

32–46, Revision 2, dated November 11, 2011. 

Do all applicable corrective actions before 

further flight (i.e., replace retract actuator 

bracket assembly and pins, or outer cylinder 

lugs, as applicable). 

(i) Installation of New Jam Nut 

For any airplane with a MLG retraction 

actuator assembly having any part number 

and serial number identified in paragraph 

1.A., Effectivity, of Bombardier Service 

Bulletin 670BA–32–031, Revision C, dated 

April 17, 2012, except airplanes on which 

modification status ‘‘32–64’’ is marked on the 

identification plate: Within 20,000 flight 

hours or 10 years after the effective date of 

this AD, whichever occurs first, install a new 

jam nut having part number 49606–5, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012; and Goodrich Service 

Bulletin 49600–32–64, Revision 3, dated 

December 15, 2011. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (g) and (i) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Bombardier Service Bulletin 670BA–32–031, 

dated March 14, 2011; Revision A, dated June 

9, 2011; or Revision B, dated July 29, 2011; 

which are not incorporated by reference in 

this AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 670BA–32–033, dated March 

14, 2011; or Revision A, dated July 29, 2011; 

which are not incorporated by reference in 

this AD. 

(k) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install on any airplane a MLG 

retraction actuator assembly having any part 

number and serial number identified in 

paragraph 1.A., Effectivity, of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012, unless that retraction 

actuator assembly has been inspected as 

specified in paragraph (g) of this AD, and all 

applicable corrective actions (i.e., 

replacement of the retract actuator) specified 

in paragraph (g) of this AD have been done. 

Repeat the inspection specified in paragraph 

(g) of this AD thereafter at the intervals 

specified in paragraph (g) of this AD. 

(2) As of the effective date of this AD, no 

person may install on any airplane a MLG 

retraction actuator assembly having any part 

number and serial number identified in 

paragraph 1.A., Effectivity, of Bombardier 

Service Bulletin 670BA–32–033, Revision B, 

dated June 26, 2012, unless that retraction 

actuator assembly has been inspected and all 

applicable corrective actions have been done, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–033, Revision B, dated June 26, 

2012. 

(l) 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. 

(m) Related Information 

(1) Refer to mandatory continued 

airworthiness information (MCAI) Canadian 

Airworthiness Directive CF–2011–36R1, 

dated October 3, 2012, and the service 

bulletins specified in paragraphs (m)(1)(i) 

through (m)(1)(v) of this AD, for related 

information. 

(i) Bombardier Service Bulletin 670BA–32– 

031, Revision C, dated April 17, 2012. 

(ii) Bombardier Service Bulletin 670BA– 

32–033, Revision B, dated June 26, 2012. 

(iii) Goodrich Service Bulletin 49000–32– 

46, Revision 2, dated November 11, 2011. 

(iv) Goodrich Service Bulletin 49600–32– 

63, Revision 1, dated May 17, 2011. 

(v) Goodrich Service Bulletin 49600–32– 

64, Revision 3, dated December 15, 2011. 

(2) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 514– 

855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. For Goodrich service 

information identified in this AD, contact 

Goodrich Corporation, Landing Gear, 1400 

South Service Road, West Oakville L6L 5Y7, 

Ontario, Canada; telephone 905–825–1568; 

email jean.breed@goodrich.com; Internet 

http://www.goodrich.com/TechPubs. 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. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11067 Filed 5–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 5 

[Docket No. USCG–1999–6712] 

RIN 1625–AB66 

Revision of Auxiliary Regulations 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes to 

revise and reorganize the regulations 

that govern the operation and 

administration of the Coast Guard 

Auxiliary, a uniformed, volunteer, nonmilitary organization chartered by 

Congress. The proposed changes would 

conform the regulatory language to 

changes in the laws governing the Coast 

Guard Auxiliary, clarify the Auxiliary’s 

organization, status, and role in Coast 

Guard operations, and update 

provisions on liability protection for 

Auxiliary members assigned to Coast 

Guard duty. 

DATES: Comments and related material 

must either be submitted to our online 

docket via http://www.regulations.gov 

on or before August 8, 2013 or reach the 

Docket Management facility by that 

date. 

ADDRESSES: You may submit comments 

identified by docket number USCG– 

1999–6712 using any one of the 

following methods: 

(1) Federal eRulemaking Portal: 

http://www.regulations.gov. 

(2) Fax: 202–493–2251. 

(3) Mail: Docket Management Facility 

(M–30), U.S. Department of 

Transportation, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590– 

0001. 

(4) Hand delivery: Same as mail 

address above, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The telephone number 

is 202–366–9329. 

To avoid duplication, please use only 

one of these four methods. See the 

‘‘Public Participation and Request for 

Comments’’ portion of the 

SUPPLEMENTARY INFORMATION section 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1