27416 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

TABLE 1—CREDIT SERVICE INFORMATION

Airbus Service Bulletin— Revision— Dated— 

A320–24–1120 ..................................................................................................................................... Original .................... May 31, 2007. 

A320–24–1120 ..................................................................................................................................... 01 ............................ December 19, 2007. 

A320–24–1120 ..................................................................................................................................... 02 ............................ July 8, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

No differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. 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 

(j) Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2009–0235, dated October 29, 2009; and 

Airbus Service Bulletin A320–24–1120, 

Revision 03, dated July 10, 2009; for related 

information. 

Material Incorporated by Reference 

(k) You must use Airbus Service Bulletin 

A320–24–1120, Revision 03, dated July 10, 

2009, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 27, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–10722 Filed 5–14–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0792; Directorate 

Identifier 2009–NM–057–AD; Amendment 

39–16300; AD 2010–10–21] 

RIN 2120–AA64 

Airworthiness Directives; 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 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2C10/ 

CL600–2D15/CL–600–2D24 aircraft fuel 

system against the new fuel tank safety 

standards, introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043. The 

identified non-compliances were assessed 

using Transport Canada Policy Letter No. 

525–001 to determine if mandatory corrective 

action was required. 

The assessment showed that certain 

hydraulic system failure scenarios could lead 

to a rapid overheat in the hydraulic lines 

without giving flight crew sufficient time to 

react before the No. 1 and No. 2 hydraulic 

system tubing inside the fuel tank reaches the 

fuel auto ignition temperature. This could 

result in a fuel tank explosion. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

21, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 21, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Alfano, Aerospace 

Engineer, Airframe and Propulsion 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 28, 2009 (74 FR 

49346). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2C10/ 

CL600–2D15/CL–600–2D24 aircraft fuel 

system against the new fuel tank safety 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27417 

standards, introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043. The 

identified non-compliances were assessed 

using Transport Canada Policy Letter No. 

525–001 to determine if mandatory corrective 

action was required. 

The assessment showed that certain 

hydraulic system failure scenarios could lead 

to a rapid overheat in the hydraulic lines 

without giving flight crew sufficient time to 

react before the No. 1 and No. 2 hydraulic 

system tubing inside the fuel tank reaches the 

fuel auto ignition temperature. This could 

result in a fuel tank explosion. 

To correct the unsafe condition, this 

[Canadian airworthiness] directive mandates 

the installation of thermal fuses in the No. 1 

and No. 2 hydraulic systems and the 

introduction of Fuel System Limitations 

(FSL) and Critical Design Configuration 

Control Limitations (CDCCL) associated with 

this design change. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM 

The Air Line Pilots Association 

(ALPA) supports the proposed AD. 

Request To Delay Rule Until Updated 

Service Information Is Released 

American Eagle Airlines (American 

Eagle) requests that we incorporate 

updated service information into the 

NPRM. American Eagle states that 

during the accomplishment of 

Bombardier Service Bulletin 670BA–29– 

005, Revision A, dated January 29, 2009 

(which specifies the accomplishment of 

Mitsubishi Service Bulletin 670MM–29– 

006, Revision A, dated February 12, 

2009) (which was referred to in the 

NPRM as the appropriate source of 

service information for the proposed 

actions), several issues were found, 

including part numbers called out in 

these service bulletins that have been 

superseded by new part numbers 

included in a kit, an incorrect location 

specified for bracket installation, and 

the need for alternate fasteners. 

American Eagle requests that a revised 

service bulletin correcting these issues 

be released and incorporated into the 

NPRM with credit given for actions 

accomplished in accordance with earlier 

versions of the service bulletins. 

American Eagle states that this will 

greatly reduce the number of requests 

for alternative methods of compliance 

(AMOCs) and possible instances of noncompliance. 

We find that clarification is necessary. 

We contacted Bombardier to inquire as 

to the status of updating the service 

information. However, no estimated 

date for releasing updated service 

information could be provided at this 

time. We do not agree that it is 

necessary to wait to issue this final rule 

until the manufacturer updates 

Bombardier Service Bulletin 670BA–29– 

005. To further delay the issuance of 

this AD would be inappropriate, since 

we have determined that an unsafe 

condition exists and that the required 

actions must be done to ensure 

continued safety. 

We note that Bombardier has issued 

Service Non-Incorporated Engineering 

Order (SNIEO) KMM670–75007, 

Identifier S01, dated September 3, 2009, 

which permits installation of certain 

fasteners, and SNIEO KMM670–75007, 

Identifier S02, dated September 11, 

2009, which permits installation of the 

left-side bracket on the right (and vice 

versa). For clarification purposes, we 

added a new Note 2 to this final rule to 

specify that guidance for accomplishing 

the modification required by paragraph 

(f)(1) of this AD can be found in the 

SNIEOs. 

In addition, paragraph (f)(5) of this 

AD gives credit for actions 

accomplished in accordance with 

Bombardier Service Bulletin 670BA–29– 

005, dated December 18, 2008. 

Explanation of Change Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Explanation of Change to Costs of 

Compliance 

After the NPRM was issued, we 

reviewed the figures we have used over 

the past several years to calculate AD 

costs to operators. To account for 

various inflationary costs in the airline 

industry, we find it necessary to 

increase the labor rate used in these 

calculations from $80 per work hour to 

$85 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Costs of Compliance 

We estimate that this AD will affect 

334 products of U.S. registry. We also 

estimate that it will take about 45 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $6,765 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$3,537,060, or $10,590 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 


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27418 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

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 AD: 

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 AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–10–21 Bombardier, Inc.: Amendment 

39–16300. Docket No. FAA–2009–0792; 

Directorate Identifier 2009–NM–057–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 21, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

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

701, & 702) airplanes, certificated in any 

category, having serial numbers 10003 

through 10267 inclusive; and Bombardier 

Model CL–600–2D15 (Regional Jet Series 

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

900) airplanes, certificated in any category, 

having serial numbers 15001 through 15199 

inclusive, 15202, and 15204. 

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 (g) 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 29: Hydraulic power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2C10/ 

CL600–2D15/CL–600–2D24 aircraft fuel 

system against the new fuel tank safety 

standards, introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043. The 

identified non-compliances were assessed 

using Transport Canada Policy Letter No. 

525–001 to determine if mandatory corrective 

action was required. 

The assessment showed that certain 

hydraulic system failure scenarios could lead 

to a rapid overheat in the hydraulic lines 

without giving flight crew sufficient time to 

react before the No. 1 and No. 2 hydraulic 

system tubing inside the fuel tank reaches the 

fuel auto ignition temperature. This could 

result in a fuel tank explosion. 

To correct the unsafe condition, this 

[Canadian airworthiness] directive mandates 

the installation of thermal fuses in the No. 1 

and No. 2 hydraulic systems and the 

introduction of Fuel System Limitations 

(FSL) and Critical Design Configuration 

Control Limitations (CDCCL) associated with 

this design change. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 6,000 flight hours after the 

effective date of this AD, modify the aircraft 

hydraulic system by installing thermal fuses 

according to the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–29–005, Revision A, dated January 

29, 2009. 

Note 2: Guidance for accomplishing the 

modification required by paragraph (f)(1) of 

this AD can be found in Bombardier Service 

Non-Incorporated Engineering Order (SNIEO) 

KMM670–75007, Identifier S01, dated 

September 3, 2009, and SNIEO KMM670– 

75007, Identifier S02, dated September 11, 

2009. 

(2) Before or concurrently with the actions 

required by paragraph (f)(1) of this AD, revise 

the Airworthiness Limitations Section (ALS) 

of the Instructions for Continued 

Airworthiness to incorporate the tasks 

identified in Table 1 of this AD as specified 

in Bombardier Temporary Revision (TR) 2– 

269, dated December 18, 2008, to Section 3, 

‘‘Fuel Systems Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15, 

and CL–600–2D24 Maintenance 

Requirements Manual. The initial 

compliance time for the task is within 10,000 

flight hours after doing the action required by 

paragraph (f)(1) of this AD, or within 60 days 

after the effective date of this AD, whichever 

occurs later, and the limitation task must be 

accomplished thereafter at the ‘‘limiting 

interval’’ specified in Bombardier TR 2–269, 

dated December 18, 2008, except as provided 

by paragraphs (f)(4) and (g)(1) of this AD. 

TABLE 1—FUEL SYSTEM LIMITATION

TASK

Task No. Task description 

29–30–00– 

603.

Hydraulic System No. 1 and 

No. 2 Thermal Fuse: Discard the system No. 1 and 

No. 2 thermal fuse (Post 

Modsum 670T112042 or 

SB 670BA–29–005). 

(3) Before or concurrently with the actions 

required by paragraph (f)(1) of this AD, revise 

the ALS of the Instructions for Continued 

Airworthiness to incorporate the CDCCL data 

specified in Bombardier TR 2–268, dated 

December 18, 2008, to Section 3, ‘‘Fuel 

System Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15 

and CL–600–2D24 Maintenance 

Requirements Manual. 

Note 3: The actions required by paragraphs 

(f)(2) and (f)(3) of this AD may be done by 

inserting a copy of the TR into the 

maintenance requirements manual. When the 

TR has been included in the general revision 

of the maintenance program, the general 

revision may be inserted into the 

maintenance requirements manual, provided 

the relevant information in the general 

revision is identical to that in the TR, and the 

TR may be removed. 

(4) After accomplishing the actions 

specified in paragraphs (f)(2) and (f)(3) of this 

AD, no alternative limitation tasks, limitation 

task intervals, or CDCCLs may be used unless 

the limitation task, limitation task interval, or 

CDCCL is approved as an alternative method 

of compliance (AMOC) in accordance with 

the procedures specified in paragraph (g)(1) 

of this AD. 

(5) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 670BA–29–005, 

dated December 18, 2008, are considered 

acceptable for compliance with the 

corresponding action specified in paragraph 

(f)(1) of this AD. 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27419 

Note 4: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the ALS, as 

required by paragraphs (f)(2) and (f)(3) of this 

AD, do not need to be reworked in 

accordance with the CDCCLs. However, once 

the ALS has been revised, future 

maintenance actions on these components 

must be done in accordance with the 

CDCCLs. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–09, dated March 9, 2009; 

Bombardier Service Bulletin 670BA–29–005, 

Revision A, dated January 29, 2009; and 

Bombardier TR 2–268 and Bombardier TR 2– 

269, both dated December 18, 2008, both to 

Section 3, ‘‘Fuel System Limitations,’’ of Part 

2 of the Bombardier CL–600–2C10, CL–600– 

2D15, and CL–600–2D24 Maintenance 

Requirements Manual; for related 

information. 

Material Incorporated by Reference 

(i) You must use the applicable service 

information specified in Table 2 of this AD, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Bombardier Service Bulletin 670BA–29–005 ...................................................................................... A .............................. January 29, 2009. 

Bombardier Temporary Revision 2–268 to Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15, and CL–600–2D24 Maintenance Requirements 

Manual.

Original .................... December 18, 2008. 

Bombardier Temporary Revision 2–269 to Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15, and CL–600–2D24 Maintenance Requirements 

Manual.

Original .................... December 18, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington on May 3, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11183 Filed 5–14–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1254; Directorate 

Identifier 2009–NM–040–AD; Amendment 

39–16292; AD 2010–10–13] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ70A, 146– 

RJ85A, and 146–RJ100A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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 the removal of the wing removable 

leading edge on a BAe 146 aircraft for a 

repair (not related to the subject addressed by 

this AD), corrosion was found on the wing 

fixed leading edge structure. The 

investigation determined that the existing 

scheduled environmental and fatigue 

inspections would not have detected the 

corrosion or fatigue damage. 

Corrosion or fatigue damage in this area, if 

not detected and corrected, could lead to 

degradation of the structural integrity of the 

wing. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

21, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 21, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 


srobinson on DSKHWCL6B1PROD with RULES