Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 27315 

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– 

0370; Directorate Identifier 2013–NM– 

034–AD. 

(a) Comments Due Date 

We must receive comments by June 24, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 701, 

& 702) airplanes, serial numbers 10002 

through 10265 inclusive; and Model CL–600– 

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

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15002 through 15153 

inclusive, 15156 and 15157; certificated in 

any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 35, Oxygen. 

(e) Reason 

This AD was prompted by a report that 

traces of oil could be found in the crew 

oxygen system due to the use of incorrect 

pressure testing procedures during 

manufacturing. We are issuing this AD to 

detect and correct oil contaminants, which 

could cause an ignition and result in a fire 

in the oxygen system. 

(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 6,600 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first: Clean the crew oxygen system, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–35–012, Revision A, dated November 

26, 2012. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 670BA–35–012, dated August 3, 

2012, which is not incorporated by reference. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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, send it to ATTN: 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 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 Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–01, dated 

January 22, 2013, and Bombardier Service 

Bulletin 670BA–35–012, Revision A, dated 

November 26, 2012, for related information. 

Issued in Renton, Washington, on May 2, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11169 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–2013–0369; Directorate 

Identifier 2012–NM–128–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 all The 

Boeing Company Model 757 airplanes. 

This proposed AD was prompted by 

reports of fractured rudder pedal 

pushrod connecting bolts in a rudder 

pedal assembly. This proposed AD 

would require repetitive replacements 

of the rudder pedal pushrod connecting 

bolts and repetitive inspections of the 

rudder pedal assembly bolt holes in 

each of the captain and the first officer 

rudder pedal assemblies, and if 

necessary, repair or replacement of 

worn rudder pedal assemblies. We are 

proposing 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, nose-wheel steering, and 

braking systems, leading to a runway 

excursion. 

DATES: We must receive comments on 

this proposed AD by June 24, 2013. 

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. 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
27316 Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 

• 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– 

2013–0369; Directorate Identifier 2012– 

NM–128–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 

We received reports of fractured 

rudder pedal pushrod connecting bolts 

on Boeing Model 757 airplanes. One 

operator discovered a bolt was fractured 

during an inspection, following a report 

that the captain’s right pedal was loose. 

Another operator reported a fractured 

bolt during the airplane pushback. 

When the captain applied the brakes, 

the right hand rudder pedal collapsed 

and both pedals fell forward. An 

inspection revealed that a rudder pedal 

pushrod bolt was fractured, resulting in 

a full left rudder input. Also, in a 

separate incident, during routine 

maintenance, while the brakes were 

released, a loud crack was heard and the 

right hand rudder pedal went all the 

way forward. During investigation, it 

was determined that the captain’s right 

hand rudder pedal pushrod bolt had 

fractured. The rudder pedal pushrod 

connecting bolt secures the rudder 

pedal arm to the rudder pushrod. The 

bolt is cantilevered in a single shear 

arrangement that is not capable of 

carrying its design load if there is 

looseness in the installation (bolt 

bending is introduced). The bolts can 

also rotate, due to lack of bolt clamp-up, 

causing additional wear. This condition, 

if not corrected, could result in a 

fracture of the rudder pedal pushrod 

connecting bolts during pedal use, 

which could result in large involuntary 

input to the rudder, nose-wheel 

steering, and braking systems, leading to 

a runway excursion. 

Related Rulemaking 

We issued AD 2001–22–13, 

Amendment 39–12492 (66 FR 55075, 

November 1, 2001), for certain Model 

737, 747, 757, 767, and 777 series 

airplanes. That AD requires replacing 

the rudder pedal pushrod fasteners 

(bolts) for the captain’s and first officer’s 

pedal assemblies with titanium 

fasteners (bolts). 

We have determined that titanium 

bolts are under-strength on Model 757 

airplanes and must be replaced with 

Inconel bolts. Titanum bolts do, 

however, meet the static and fatigue 

requirements for the other airplane 

models affected by AD 2001–22–13, 

Amendment 39–12492 (66 FR 55075, 

November 1, 2001). 

Relevant Service Information 

We reviewed 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. For information 

on the procedures and compliance 

times, see this service information at 

http://www.regulations.gov by searching 

for Docket No. FAA–2013–0369. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. Replacements of the rudder 

pedal pushrod connecting bolts are 

done after each inspection specified in 

paragraph (g) of this AD, regardless of 

the inspection results. Some actions 

would terminate the requirements of AD 

2001–22–13, Amendment 39–12492 (66 

FR 55075, November 1, 2001), for Model 

757 airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

affects 685 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 91 / Friday, May 10, 2013 / Proposed Rules 27317 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspect/replace bolts (Condition 1 in 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).

5 work-hours × $85 per 

hour = $425 per inspection cycle.

$217 $642 per inspection cycle $439,770 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs/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 repairs/ 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replace rudder pedal assembly (Condition 2 in 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 work-hours × $85 

per hour = $170.

Unknown ..... $170 

Repair rudder pedal assembly (Condition 3 in 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 work-hours × $85 

per hour = $255.

Unknown ..... 255 

Repair rudder pedal assembly (Condition 4 in 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).

4 work-hours × $85 

per hour = $340.

Unknown ..... 340 

The on-condition costs in the table 

above are per rudder pedal assembly. 

Depending on the diamater of the holes 

found during the inspection, it may be 

necessary to replace or repair the rudder 

pedal assemblies. The parts cost to 

replace or repair the rudder pedal 

assemblies are not included in the 

estimate. It is considered ‘‘Parts & 

Materials Supplied by the Operator’’, 

which is referenced in 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. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 

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 airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2013–0369; Directorate Identifier 2012– 

NM–128–AD. 

(a) Comments Due Date 

We must receive comments by June 24, 

2013. 

(b) Affected ADs 

Certain requirements of this AD terminate 

the requirements of AD 2001–22–13, 

Amendment 39–12492 (66 FR 55075, 

November 1, 2001), for Model 757 airplanes. 


rmajette on DSK2TPTVN1PROD with PROPOSALS-1
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