17884 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009. 

(1) Within 30 days after August 5, 2008. 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle. 

Note 1: Boeing Alert Service Bulletin 737– 

57A1304, dated June 2, 2008; and Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009; reference Boeing 

Alert Service Bulletin 737–57A1277, 

Revision 1, dated November 25, 2003; for 

further guidance on accomplishing the 

related investigative actions. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2009–23–10, AMENDMENT 39–16084: 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Action for Certain 

Airplanes 

(i) For airplanes on which a carriage 

spindle having a serial number identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009, is installed: At the latest of 

the times specified in paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD, as applicable, do a 

detailed inspection (or, as an option for the 

forward end of the spindle only, a borescope 

inspection technique may be used) of the 

spindle for corrosion and potential 

indications of corrosion of the carriage 

spindle, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

57A1304, Revision 1, dated August 11, 2009. 

Do all applicable related investigative and 

corrective actions before further flight. 

Repeat the detailed inspection (or, as an 

option for the forward end of the spindle 

only, the borescope inspection) and related 

investigative actions (i.e., the gap-check or 

optional NDT ultrasonic inspection) at the 

applicable compliance times specified in 

paragraph 1.E. of Boeing Service Bulletin 

737–57A1304, Revision 1, dated August 11, 

2009. 

(1) Within 30 days after November 24, 2009 

(the effective date of AD 2009–23–10). 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009. 

(3) Within 90 days after doing an 

inspection in accordance with Boeing Alert 

Service Bulletin 737–57A1304, dated June 2, 

2008. 

Parts Installation 

(j) As of August 5, 2008, an HVOF-coated 

spindle without an ‘R’ suffix on the serial 

number may be installed on an airplane 

provided the actions required by paragraph 

(h) or (i) of this AD, as applicable, are done 

on that spindle. 

NEW REQUIREMENTS OF THIS AD: 

Terminating Action 

(k) Within 48 months after the effective 

date of this AD: Replace any HVOF-coated 

carriage spindle having a serial number 

identified in Table 2 or 3 of Appendix A of 

Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009, with a 

non-HVOF coated carriage spindle, or with a 

serviceable HVOF-coated carriage spindle 

with an ‘R’ suffix on the serial number, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008; or Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009. Replacing all affected 

carriage spindles terminates the repetitive 

inspections required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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. Send information to ATTN: 

Nancy Marsh, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6440; fax 

(425) 917–6590. Or, e-mail information to 

9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 

Delegation 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. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7944 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0375; Directorate 

Identifier 2010–NM–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes; Model 

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

701, & 702) Airplanes; Model CL–600– 

2D15 (Regional Jet Series 705) and 

Model CL–600–2D24 (Regional Jet 

Series 900) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Following five reported 

cases of balance washer screw failure on 

similar ADGs [air-driven generators]/ 

ram air turbines installed on other 

aircraft types, investigation by Hamilton 

Sundstrand determined that a specific 

batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Failure of a balance washer 

screw can result in loss of the related 

balance washer, with consequent 

turbine imbalance. Such imbalance 

could potentially result in ADG 

structural failure (including blade 

failure), loss of ADG electrical power 

and structural damage to the aircraft 

and, if deployment was activated by a 

dual engine shutdown, could also result 

in loss of hydraulic power for the flight 

controls [and consequent reduced 

ability of the flightcrew to maintain the 

safe flight and landing of the airplane]. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

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– 


sroberts on DSKD5P82C1PROD with PROPOSALS
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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: 

Christopher Alfano, 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– 

7340; 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–2010–0375; Directorate Identifier 

2010–NM–014–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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–2009–48, 

dated December 14, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Following five reported cases of balance 

washer screw failure on similar ADGs [airdriven generators]/ram air turbines installed 

on other aircraft types, investigation by 

Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 152 ‘‘dry’’ ADGs [Hamilton Sundstrand 

Part Numbers (P/Ns) in the 761339 series and 

1711405; see Note] either had nonconforming screws installed during 

production or may possibly have had nonconforming screws installed during 

maintenance or repair at Hamilton 

Sundstrand repair stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in ADG 

structural failure (including blade failure), 

loss of ADG electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking the ADG and replacing the balance 

washer screws, if required. It also prohibits 

future installation of unmodified ADGs. 

Note: ADGs with Hamilton Sundstrand P/ 

Ns in the 761339 series and 1711405 are 

installed on the aircraft models listed in the 

Applicability section above in addition to 

Bombardier Inc. Model CL–600–2B16. The 

latter model is covered in a separate 

directive. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletins 601R–24–127, Revision A, 

dated February 25, 2010; and 670BA– 

24–026, dated October 23, 2009. 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 AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 1,008 products of U.S. 

registry. We also estimate that it would 

take about 10 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 $0 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 costs. 

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 $856,800, or $850 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 


sroberts on DSKD5P82C1PROD with PROPOSALS
17886 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

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); and 

3. 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–2010– 

0375; Directorate Identifier 2010–NM– 

014–AD. 

Comments Due Date 

(a) We must receive comments by May 24, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet Series 100 

& 440) airplanes, serial numbers 7305 

through 7990 inclusive and 8000 and 

subsequent; Model CL–600–2C10 (Regional 

Jet Series 700, 701, & 702) airplanes, serial 

numbers 10003 and subsequent; Model CL– 

600–2D15 (Regional Jet Series 705) and 

Model CL–600–2D24 (Regional Jet Series 

900) airplanes, serial numbers 15001 and 

subsequent; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Following five reported cases of balance 

washer screw failure on similar ADGs [airdriven generators]/ram air turbines installed 

on other aircraft types, investigation by 

Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 152 ‘‘dry’’ ADGs [Hamilton Sundstrand 

Part Numbers (P/Ns) in the 761339 series and 

1711405; see Note] either had nonconforming screws installed during 

production or may possibly have had nonconforming screws installed during 

maintenance or repair at Hamilton 

Sundstrand repair stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in ADG 

structural failure (including blade failure), 

loss of ADG electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking the ADG and replacing the balance 

washer screws, if required. It also prohibits 

future installation of unmodified ADGs. 

Note: ADGs with Hamilton Sundstrand P/ 

Ns in the 761339 series and 1711405 are 

installed on the aircraft models listed in the 

Applicability section above in addition to 

Bombardier Inc. Model CL–600–2B16. The 

latter model is covered in a separate 

directive. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) For Model CL–600–2C10, CL–600–2D15 

and CL–600–2D24 airplanes: At the earliest 

of the times identified in paragraphs (g)(1), 

(g)(2), (g)(3), or (g)(4) of this AD, do an 

inspection to determine the serial number of 

the installed air-driven generator (ADG), in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the serial number of 

the ADG can be conclusively identified from 

that review. 

(1) Within 4,000 flight hours or 18 months 

after the effective date of this AD, whichever 

occurs first; or. 

(2) Prior to the next in-flight or on-ground 

functional check of the ADG, whichever 

occurs first after the effective date of this AD; 

or 

(3) Prior to the next in-flight or on-ground 

operational check of the ADG, whichever 

occurs first after the effective date of this AD; 

or 

(4) Before the next scheduled ADG in-flight 

deployment. 

(h) For Model CL–600–2B19 airplanes: At 

the earliest of the times identified in 

paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of 

this AD, do an inspection to determine the 

serial number of the installed ADG, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

the ADG can be conclusively identified from 

that review. 

(1) Within 4,000 flight hours after the 

effective date of this AD; or 

(2) Prior to the next in-flight or on-ground 

functional check of the ADG, whichever 

occurs first after the effective date of this AD; 

or 

(3) Prior to the next in-flight or on-ground 

operational check of the ADG, whichever 

occurs first after the effective date of this AD; 

or 

(4) Before the next scheduled ADG in-flight 

deployment. 

TABLE 1—SERVICE BULLETINS

Model— Bombardier Service 

Bulletin— Revision— Dated— 

CL–600–2B19 airplanes ...................................................... 601R–24–127 ...................... A .......................................... February 25, 2010. 


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Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 17887 

TABLE 1—SERVICE BULLETINS—Continued 

Model— Bombardier Service 

Bulletin— Revision— Dated— 

CL–600–2C10, CL–600–2D15, CL–600–2D24 airplanes ... 670BA–24–026 .................... Original ................................ October 23, 2009. 

(i) If the ADG serial number determined in 

paragraph (g) or (h) of this AD is identified 

in paragraph 1.A. of the applicable service 

bulletin listed in Table 1 of this AD, before 

further flight do an inspection to determine 

if the symbol ‘‘24–5’’ is marked on the ADG 

identification plate. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the symbol ‘‘24–5’’ mark can 

be conclusively identified from that review. 

(1) If the symbol ‘‘24–5’’ is marked on the 

ADG identification plate, the balance washer 

screws have already been replaced, and no 

further action is required by this paragraph. 

(2) If the symbol ‘‘24–5’’ is not marked on 

the ADG identification plate, before further 

flight replace all balance washer screws with 

new balance washer screws, part number 

MS24667–14, and mark the ADG 

identification plate with symbol ‘‘24–5,’’ in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. 

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

person may install on any airplane, a 

replacement or spare ADG, Hamilton 

Sundstrand part number in the 761339 or 

1711405 series, having one of the serial 

numbers identified in paragraph 1.A. of the 

applicable service bulletin identified in Table 

1 of this AD, unless the ADG is identified 

with the symbol ‘‘24–5’’ on the identification 

plate. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(k) Inspections accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 601R–24–127, 

dated October 23, 2009, are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI specifies to inspect only airplanes 

having certain serial numbers that are part of 

the MCAI applicability. Because the affected 

part could be rotated onto any of the 

airplanes listed in the applicability, this AD 

requires the inspection be done on all 

airplanes. We have coordinated this with the 

TCCA. 

Other FAA AD Provisions 

(l) 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. Send information 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 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–48, dated December 14, 

2009; and Bombardier Service Bulletins 

601R–24–127, Revision A, dated February 25, 

2010, and 670BA–24–026, dated October 23, 

2009; for related information. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7947 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0377; Directorate 

Identifier 2009–NM–246–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 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 

Model 767 airplanes. This proposed AD 

would require doing a detailed 

inspection for correct main track 

downstop assembly, thread protrusion, 

and damaged and missing parts of the 

main track downstop assemblies of the 

outboard slats, and related investigative 

and corrective actions if necessary. This 

proposed AD would also require doing 

a detailed inspection for foreign objects 

debris and damage to the wall of the 

track housing of the outboard slats, and 

corrective actions if necessary. This 

proposed AD results from reports of 

broken bolts in the outboard slat main 

track downstop assembly. We are 

proposing this AD to detect and correct 

incorrectly installed main track 

downstop assemblies, which can allow 

the main track downstop hardware to 

fall into the track housing and cause a 

puncture in the track housing when the 

slat is retracted. This condition, if not 

corrected, could result in a fuel leak and 

an increased risk of fire. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

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 20590, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; 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. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 


sroberts on DSKD5P82C1PROD with PROPOSALS