This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

64960 

Vol. 75, No. 203 

Thursday, October 21, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1039; Directorate 

Identifier 2010–NM–002–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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 that would 

supersede an existing AD. 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: 

There has been numerous reported failures 

of the Regional Jet engine TCGB [throttle 

control gearbox] P/Ns: 2100140–003, 

2100140–005 & 2100140–007. Some of these 

failures have resulted in in-flight engine 

shutdowns. Post incident investigations 

revealed that excessive wear within the 

engine TCGB could alter the rigging position 

or cause the throttle to jam. With the rigging 

position altered, movement of the throttle 

lever towards the idle position can result in 

throttle moving too close to the fuel shut-off 

position, which potentially, can cause the 

engine to flame out. 

* * * * * 

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 December 6, 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 W12–40, 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; 

e-mail 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: 

Rocco Viselli, Senior Aviation Safety 

Engineer, Avionic & Flight Test Branch, 

ANE–172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; 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–2010–1039; Directorate Identifier 

2010–NM–002–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 

On March 8, 2005, we issued AD 

2005–06–04, Amendment 39–14012 (70 

FR 12963, March 17, 2005). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2005–06–04, the 

inspection for the throttle control 

gearbox (TCGB) required by that AD has 

been transcribed in a new certification 

maintenance requirement (CMR) task. 

This NPRM proposes to mandate the 

incorporation of the new CMR task into 

the CL–600–2B19 maintenance 

requirements manual (MRM) as 

introduced by the MRM temporary 

revision 2A–47. Transport Canada Civil 

Aviation, which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2004–01R2, dated September 29, 2009 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

There has been numerous reported failures 

of the Regional Jet engine TCGB P/Ns: 

2100140–003, 2100140–005 & 2100140–007. 

Some of these failures have resulted in inflight engine shutdowns. Post incident 

investigations revealed that excessive wear 

within the engine TCGB could alter the 

rigging position or cause the throttle to jam. 

With the rigging position altered, movement 

of the throttle lever towards the idle position 

can result in throttle moving too close to the 

fuel shut-off position, which potentially, can 

cause the engine to flame out. 

Bombardier issued Service Bulletin (SB) 

601R–76–019 dated 21 August 2003, to 

introduce an inspection of, and if required, 

replacement of the throttle control gearbox 

with a serviceable unit. AD CF–2004–01 was 

originally issued to mandate the subject 

inspection requirement as per SB 601R–76– 

019 and subsequent revisions. 

The subject TCGB inspection requirements 

mandated as per the earlier versions of this 

AD, are now transcribed in a new 

Certification Maintenance Requirement 

(CMR) task. This revision is issued to 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 203 / Thursday, October 21, 2010 / Proposed Rules 64961 

mandate the incorporation of the new CMR 

task into the CL–600–2B19 Maintenance 

Requirements Manual (MRM), as introduced 

by the MRM Temporary Revision (TR) 

2A–47. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 601R–76–019, Revision B, 

dated February 16, 2005; and Service 

Bulletin 601R–76–019, Revision C, 

dated July 5, 2007. Bombardier has also 

issued Temporary Revision 2A–47, 

dated May 27, 2009, to Appendix A— 

Certification Maintenance 

Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 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 638 products of U.S. 

registry. 

The actions that are required by AD 

2005–06–04 and retained in this 

proposed AD take about 7 work-hours 

per product. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

requirements retained in this proposed 

AD on U.S. operators to be $379,610, or 

$595 per product 

We estimate that it would take about 

1 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the new 

basic requirements in this proposed AD 

on U.S. operators to be $54,230, or $85 

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 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 

removing Amendment 39–14012 (70 FR 

12963, March 17, 2005) and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2010– 

1039; Directorate Identifier 2010–NM– 

002–AD. 

Comments Due Date 

(a) We must receive comments by 

December 6, 2010. 

Affected ADs 

(b) The AD supersedes AD 2005–06–04, 

Amendment 39–14012. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

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

& 440) airplanes, certificated in any category, 

having an engine throttle control gearbox 

(TCGB) with part number 2100140–003, 

2100140–005, or 2100140–007 installed. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (m)(1) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 76: Engine Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There has been numerous reported failures 

of the Regional Jet engine TCGB P/Ns: 

2100140–003, 2100140–005 & 2100140–007. 

Some of these failures have resulted in inflight engine shutdowns. Post incident 

investigations revealed that excessive wear 

within the engine TCGB could alter the 

rigging position or cause the throttle to jam. 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
64962 Federal Register / Vol. 75, No. 203 / Thursday, October 21, 2010 / Proposed Rules 

With the rigging position altered, movement 

of the throttle lever towards the idle position 

can result in throttle moving too close to the 

fuel shut-off position, which potentially, can 

cause the engine to flame out. 

Bombardier issued Service Bulletin (SB) 

601R–76–019 dated 21 August 2003, to 

introduce an inspection of, and if required, 

replacement of the throttle control gearbox 

with a serviceable unit. AD CF–2004–01 was 

originally issued to mandate the subject 

inspection requirement as per SB 601R–76– 

019 and subsequent revisions. 

The subject TCGB inspection requirements 

mandated as per the earlier versions of this 

AD, are now transcribed in a new 

Certification Maintenance Requirement 

(CMR) task. This revision is issued to 

mandate the incorporation of the new CMR 

task into the CL–600–2B19 Maintenance 

Requirements Manual (MRM), as introduced 

by the MRM Temporary Revision (TR) 

2A–47. 

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. 

Restatement of Requirements of AD 2005– 

06–04, With New Service Information 

Inspection 

(g) For airplanes having serial numbers 

(S/Ns) 7003 through 7067 inclusive, and 

7069 and subsequent: At the applicable time 

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

AD, do a detailed inspection for wear of the 

left and right engine throttle control 

gearboxes having part number (P/N) 

2100140–005 or 2100140–007 by doing all 

the actions per Part A, paragraphs A., B., and 

C.(1) through C.(4), of the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007. If the wear 

value is the same as that specified in Part A, 

paragraph B.(8), of the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007: Repeat the 

inspection thereafter at intervals not to 

exceed 1,000 flight hours. As of the effective 

date of this AD, only Bombardier Service 

Bulletin 601R–76–019, Revision C, dated July 

5, 2007, may be used. Doing the inspection 

required by paragraph (k) of this AD 

terminates the requirement in this paragraph. 

(1) For airplanes having S/Ns 7003 through 

7067 inclusive and 7069 through 7999 

inclusive: Within 1,000 flight hours or 90 

days after March 25, 2004 (the effective date 

of AD 2004–05–12), whichever is later. 

(2) For airplanes having S/Ns 8000 and 

subsequent: Within 1,000 flight hours or 90 

days after April 1, 2005 (the effective date of 

AD 2005–06–04), whichever is later. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at an intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’ 

Corrective Action 

(h) If the wear value found during any 

inspection required by paragraph (g) of this 

AD is not the same as that specified in Part 

A, paragraph B.(8), of the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007: Do the 

applicable actions required by paragraph 

(h)(1), (h)(2), or (h)(3) of this AD, at the time 

specified, per the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007. Repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 1,000 

flight hours. As the effective date of this AD, 

only Bombardier Service Bulletin 601R–76– 

019, Revision C, dated July 5, 2007, may be 

used. Doing the inspection required by 

paragraph (k) of this AD terminates the 

inspection requirements of this paragraph. 

(1) If the wear value on one or both of the 

gearboxes is the same as that specified in Part 

A, paragraph B.(5), of the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007: Before further 

flight, replace the affected gearbox with a 

new or serviceable gearbox, by doing all the 

actions per Part B, paragraphs D. through 

F.(7) of the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–76–019, 

dated August 21, 2003; Revision ‘A,’ dated 

February 19, 2004; Revision B, dated 

February 16, 2005; or Revision C, dated July 

5, 2007. As the effective date of this AD, only 

Bombardier Service Bulletin 601R–76–019, 

Revision C, dated July 5, 2007, may be used. 

(2) If the wear value on both the left and 

right gearboxes is the same as that specified 

in Part A, paragraph B.(6), of Bombardier 

Service Bulletin 601R–76–019, dated August 

21, 2003; Revision ‘A,’ dated February 19, 

2004; Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007: Before further 

flight, replace the gearbox having the higher 

wear value with a new or serviceable 

gearbox, by doing all the actions per Part B, 

paragraphs D. through F.(7), of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

21, 2003; Revision ‘A,’ dated February 19, 

2004; Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007. Within 1,000 

flight hours after doing the replacement, 

replace the other gearbox. As the effective 

date of this AD, only Bombardier Service 

Bulletin 601R–76–019, Revision C, dated July 

5, 2007, may be used. 

(3) If the wear value on only one gearbox 

is the same as that specified in Part A, 

paragraph B.(7), and the wear value on the 

other gearbox is the same as that specified in 

Part A, paragraph B.(8), of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

21, 2003; Revision ‘A,’ dated February 19, 

2004; Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007: Within 1,000 

flight hours after the inspection, replace the 

gearbox with the wear value that is the same 

as that specified in Part A, paragraph B.(7), 

with a new or serviceable gearbox. Do the 

replacement by doing all the actions per Part 

B, paragraphs D. through F.(7), of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

21, 2003; Revision ‘A,’ dated February 19, 

2004; Revision B, dated February 16, 2005; or 

Revision C, dated July 5, 2007. As the 

effective date of this AD, only Bombardier 

Service Bulletin 601R–76–019, Revision C, 

dated July 5, 2007, may be used. 

Additional Guidance 

Note 3: Bombardier Service Bulletin 601R– 

76–019, dated August 21, 2003; Revision ‘A,’ 

dated February 19, 2004; Revision B, dated 

February 16, 2005; or Revision C, dated July 

5, 2007; reference Trans Digm, Inc., 

AeroControlex Group, Service Bulletin 

2100140–007–76–04, dated July 22, 2003, as 

an additional source of guidance for 

accomplishment of the inspections and 

replacement. 

Reporting Requirement 

(i) At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD, submit 

a report of gearbox wear to Bombardier 

Aerospace, In-Service Engineering (Engine 

Group); fax (514) 855–7708. The report must 

include the airplane serial number, the 

number of flight hours on the airplane, and 

the number of flight hours on each gearbox 

(if different than the number of flight hours 

on the airplane). Under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.), the Office of Management and 

Budget (OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) For Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) airplanes, 

serial numbers 7003 through 7067 inclusive, 

and 7069 through 7999 inclusive: Submit a 

report within 10 days after doing the 

inspection required by paragraph (g) of this 

AD, or within 10 days after March 25, 2004, 

whichever is later. 

(2) For Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) airplanes, 

serial numbers 8000 and subsequent: Submit 

a report within 10 days after doing the 

inspection required by paragraph (g) of this 

AD, or within 10 days after April 1, 2005 (the 

effective date of AD 2005–06–04), whichever 

is later. 

New Requirements of This AD 

Actions 

(j) For all airplanes: Within 30 days as the 

effective date of this AD, revise the 

Airworthiness Limitations (AWL) section of 

the Instructions for Continued Airworthiness 

to include the information in Bombardier 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 203 / Thursday, October 21, 2010 / Proposed Rules 64963 

Temporary Revision 2A–47, dated May 27, 

2009, to Appendix A—Certification 

Maintenance Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

Note 4: The actions required by paragraph 

(j) of this AD may be done by inserting a copy 

of Bombardier Temporary Revision 2A–47, 

dated May 27, 2009, into the AWL section of 

Appendix A—Certification Maintenance 

Requirements, of Part 2 of the Bombardier 

CL–600–2B19 Maintenance Requirements 

Manual. When this temporary revision has 

been included in the limitation section of the 

general revisions of the document, the 

general revisions may be inserted in the 

document, provided the relevant information 

in the general revision is identical to that in 

Bombardier Temporary Revision 2A–47, 

dated May 27, 2009. 

(k) For the task identified in Bombardier 

Temporary Revision 2A–47, dated May 27, 

2009, do the initial inspection within 1,000 

flight hours after the effective date of this AD. 

Doing the initial inspection required by this 

paragraph terminates the requirements of 

paragraph (g) of this AD and the inspection 

requirements of paragraph (h) of this AD. 

(l) Thereafter, except as provided by 

paragraph (m) of this AD, no alternative 

intervals may be approved for the task 

indentified in Bombardier Temporary 

Revision 2A–47, dated May 27, 2009, which 

requires a special detailed inspection of the 

throttle control gearbox for gear and rack 

teeth wear. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) 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 FAAapproved 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 

(n) Refer to MCAI Canadian Airworthiness 

Directive CF–2004–01R2, dated September 

29, 2009; Bombardier Service Bulletin 601R– 

76–019, Revision C, dated July 5, 2007; and 

Bombardier Temporary Revision 2A–47, 

dated May 27, 2009, to Appendix A— 

Certification Maintenance Requirements, of 

Part 2 of the Bombardier CL–600–2B19 

Maintenance Requirements Manual; for 

related information. 

Issued in Renton, Washington, on October 

13, 2010. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–26550 Filed 10–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1038; Directorate 

Identifier 2009–NM–250–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 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: 

During a normal walkaround check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG [main landing gear] piston. The 

affected MLG unit had accumulated 7909 

flight cycles (FC) at the time of detection. 

* * * 

This condition, if not detected and 

corrected, could lead to MLG failure, 

possibly resulting in loss of control of the 

aeroplane during the landing roll-out. 

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 December 6, 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, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@

stork.com; Internet http:// 

www.myfokkerfleet.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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

425–227–1137; fax 425–227–1149. 

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–2010–1038; Directorate Identifier 

2009–NM–250–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1