17758 Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 

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 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

(800) 647–5527) is provided 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, 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: 

2011–07–09 Thielert Aircraft Engines 

GmbH: Amendment 39–16646. Docket 

No. FAA–2010–0820; Directorate 

Identifier 2010–NE–31–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 5, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH models TAE 125–01, TAE 

125–02–99, and TAE 125–02–114 

reciprocating engines installed in, but not 

limited to, Cessna 172 and (Reims-built) F172 

series (European Aviation Safety Agency 

(EASA) STC No. EASA.A.S.01527); Piper 

PA–28 series (EASA STC No. EASA.A.S. 

01632); APEX (Robin) DR 400 series (EASA 

STC No. A.S.01380); and Diamond Aircraft 

Industries Models DA 40, DA 42, and DA 

42M NG airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent engine in-flight 

shutdown or power loss, possibly resulting in 

reduced control of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, install 

full-authority digital electronic control 

(FADEC) software version 2.91. 

(2) Guidance on FADEC software 

installation can be found in the following: 

(i) For TAE 125–01 engines, Operation & 

Maintenance Manual OM–02–01, Version 3, 

Revision 15. 

(ii) For TAE 125–02–99 and TAE 125–02– 

114 engines, Operation & Maintenance 

Manual OM–02–02, Version 2, Revision 1. 

Prohibition of FADEC Software Earlier 

Versions 

(f) Once FADEC software version 2.91 is 

installed, do not install any earlier version of 

FADEC software. 

FAA AD Differences 

(g) EASA AD 2010–0137 permits 

installation of earlier FADEC software 

versions, once version 2.91 is installed. This 

AD does not. 

(h) EASA AD 2010–0137 requires 

compliance within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, but no 

later than 6 months after the effective date of 

the AD. This AD requires compliance within 

110 flight hours after the effective date of the 

AD or during next maintenance, whichever 

occurs first. 

Alternative Methods of Compliance 

(AMOCS) 

(i) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Refer to EASA AD 2010–0137, dated 

June 30, 2010, for related information. 

Contact Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, phone: +49–37204–696–0; fax: 

+49–37204–696–2912; e-mail: 

info@centurion-engines.com, for a copy of 

the service information referenced in this 

AD. 

(k) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; phone: 

(781) 238–7143; fax: (781) 238–7199, for 

more information about this AD. 

Material Incorporated by Reference 

(l) None. 

Issued in Burlington, Massachusetts, on 

March 22, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–7293 Filed 3–30–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1200; Directorate 

Identifier 2010–NM–136–AD; Amendment 

39–16647; AD 2011–07–10] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–100–1A10 (Challenger 

300) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 


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Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 17759 

(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: 

Investigation of a recent high altitude loss 

of cabin pressurization on a BD–100–1A10 

aircraft determined that it was caused by a 

partial blockage of a safety valve cabin 

pressure-sensing port, in conjunction with a 

dormant failure/leakage of the safety valve 

manometric capsule. The blockage, caused by 

accumulation of lint/dust on the grid of the 

port plug, did not allow sufficient airflow 

through the cabin pressure-sensing port to 

compensate for the rate of leakage from the 

manometric capsule, resulting in the opening 

of the safety valve. It was also determined 

that failure of the manometric capsule alone 

would not result in the opening of the safety 

valve. 

* * * * * 

The unsafe condition is possible loss 

of cabin pressure caused by the opening 

of the safety valve. We are issuing this 

AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective May 

5, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 1, 2010 (75 FR 27406, May 

17, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; 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 December 21, 2010 

(75 FR 79984), and proposed to 

supersede AD 2010–10–18, Amendment 

39–16297 (75 FR 27406, May 17, 2010). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Investigation of a recent high altitude loss 

of cabin pressurization on a BD–100–1A10 

aircraft determined that it was caused by a 

partial blockage of a safety valve cabin 

pressure-sensing port, in conjunction with a 

dormant failure/leakage of the safety valve 

manometric capsule. The blockage, caused by 

accumulation of lint/dust on the grid of the 

port plug, did not allow sufficient airflow 

through the cabin pressure-sensing port to 

compensate for the rate of leakage from the 

manometric capsule, resulting in the opening 

of the safety valve. It was also determined 

that failure of the manometric capsule alone 

would not result in the opening of the safety 

valve. 

This directive mandates a revision of the 

maintenance schedule, the [repetitive] 

cleaning of the safety valves, the removal of 

material from the area surrounding the safety 

valves and the modification of the safety 

valves with a gridless cabin pressure-sensing 

port plug. 

The unsafe condition is possible loss of 

cabin pressure caused by the opening of 

the safety valve. The required actions 

also include a detailed visual inspection 

of the safety valves and surrounding 

areas for discrepant material (e.g., 

foreign material surrounding the safety 

valves, room temperature vulcanizing 

(RTV) sealant on safety valves, RTV 

excess on the bulkhead, tape near the 

safety valve opening, and, on certain 

airplanes, insulation near the safety 

valve opening, and foam in the area 

surrounding the safety valves), and for 

contamination found in the safety valve 

pressure ports. If contamination is 

found on the safety valve pressure ports, 

a detailed visual inspection for the 

presence of RTV on the outside and 

inside diameter of the pressure sensing 

port conduit is required. If discrepant 

materials are found, removing 

discrepant material, cleaning the 

surfaces of the valves, and securing 

insulation are required, as applicable. If 

the presence of RTV is detected, 

cleaning the surfaces of the valves and 

installing a new safety valve are 

required, as applicable. 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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

about 67 products of U.S. registry. 

The actions that are required by AD 

2010–10–18 and retained in this AD 

take about 9 work-hours per product, at 

an average labor rate of $85 per workhour. Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $765 per product. 

We estimate that it will take about 1 

work-hour per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will 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 

this AD to the U.S. operators to be 

$5,695, 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 AD will not 

have federalism implications under 


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17760 Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 

Executive Order 13132. This AD will 

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 AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

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 

removing Amendment 39–16297 

(75 FR 27406, May 17, 2010) and adding 

the following new AD: 

2011–07–10 Bombardier, Inc.: Amendment 

39–16647. Docket No. FAA–2010–1200; 

Directorate Identifier 2010–NM–136–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 5, 2011. 

Affected ADs 

(b) This AD supersedes AD 2010–10–18, 

Amendment 39–16297. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model BD–100–1A10 (Challenger 300) 

airplanes, having serial numbers (S/Ns) 

20001 through 20274 inclusive, certificated 

in any category. 

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 (l) 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 21: Air conditioning. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Investigation of a recent high altitude loss 

of cabin pressurization on a BD–100–1A10 

aircraft determined that it was caused by a 

partial blockage of a safety valve cabin 

pressure-sensing port, in conjunction with a 

dormant failure/leakage of the safety valve 

manometric capsule. The blockage, caused by 

accumulation of lint/dust on the grid of the 

port plug, did not allow sufficient airflow 

through the cabin pressure-sensing port to 

compensate for the rate of leakage from the 

manometric capsule, resulting in the opening 

of the safety valve. It was also determined 

that failure of the manometric capsule alone 

would not result in the opening of the safety 

valve. 

* * * * * 

The unsafe condition is possible loss of cabin 

pressure caused by the opening of the safety 

valve. 

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 

2010–10–18, With No New Service 

Information 

Actions 

(g) For all airplanes: Within 30 days after 

June 1, 2010 (the effective date of AD 2010– 

10–18, Amendment 39–16297) revise the 

Airworthiness Limitations section of the 

Instructions for Continued Airworthiness by 

incorporating Tasks 21–31–09–101 and 21– 

31–09–102 in the Bombardier Temporary 

Revision (TR) 5–2–53, dated October 1, 2009, 

to Section 5–10–40, ‘‘Certification 

Maintenance Requirements,’’ in Part 2 of 

Chapter 5 of Bombardier Challenger 300 BD– 

100 Time Limits/Maintenance Checks. 

(1) For the new tasks identified in 

Bombardier TR 5–2–53, dated October 1, 

2009: For airplanes identified in the ‘‘Phasein’’ section of Bombardier TR 5–2–53, dated 

October 1, 2009, the initial compliance with 

the new tasks must be carried out in 

accordance with the phase-in schedule 

detailed in Bombardier TR 5–2–53, dated 

October 1, 2009, except where that TR 

specifies a compliance time from the date of 

the TR, this AD requires compliance within 

the specified time after June 1, 2010. 

Thereafter, except as provided by paragraph 

(l)(1) of this AD, no alternative to the task 

intervals may be used. 

(2) When information in Bombardier TR 

5–2–53, dated October 1, 2009, has been 

included in the general revisions of the 

applicable Airworthiness Limitations section, 

that TR may be removed from that 

Airworthiness Limitations section of the 

Instructions for Continued Airworthiness. 

(h) For airplanes having S/Ns 20003 

through 20173 inclusive, 20176, and 20177: 

Within 50 flight hours after June 1, 2010, do 

a detailed visual inspection of the safety 

valves and surrounding areas for discrepant 

material (e.g., foreign material surrounding 

the safety valves, room temperature 

vulcanizing (RTV) sealant on safety valves, 

RTV excess on the bulkhead, tape near the 

safety valve opening, and, on certain 

airplanes, insulation near the safety valve 

opening, and foam in the area surrounding 

the safety valves) and a detailed visual 

inspection for contamination (e.g., RTV, dust, 

or lint) in the safety valve pressure ports, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–25–14, dated June 30, 2008 (for airplanes 

having S/Ns 20124, 20125, 20128, 20134, 

20139, 20143, 20146, 20148 to 20173 

inclusive, 20176, and 20177); or Bombardier 

Service Bulletin 100–25–21, dated June 30, 

2008 (for airplanes having S/Ns 20003 

through 20123 inclusive, 20126, 20127, 

20129 to 20133 inclusive, 20135 to 20138 

inclusive, 20140 to 20142 inclusive, 20144, 

20145, and 20147). 

(1) If any discrepant material is found 

during the detailed visual inspection, before 

further flight, remove the discrepant material, 

clean the surfaces of the valves, and secure 

the insulation, as applicable, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 100–25–14, 

dated June 30, 2008 (for airplanes having 

S/Ns 20124, 20125, 20128, 20134, 20139, 

20143, 20146, 20148 to 20173 inclusive, 

20176, and 20177); or Bombardier Service 

Bulletin 100–25–21, dated June 30, 2008 (for 

airplanes having S/Ns 20003 through 20123 

inclusive, 20126, 20127, 20129 to 20133 

inclusive, 20135 to 20138 inclusive, 20140 to 

20142 inclusive, 20144, 20145, and 20147). 

(2) If contamination (e.g., RTV, dust, or 

lint) is found on the safety valve pressure 

sensing ports, before further flight, do a 

detailed visual inspection of the outside and 

inside diameters of the pressure sensing port 

conduit for the presence of RTV; and do the 

actions specified in paragraph (h)(2)(i) and 

(h)(2)(ii) of this AD, as applicable; in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–25–14, dated June 30, 2008 (for airplanes 

having S/Ns 20124, 20125, 20128, 20134, 

20139, 20143, 20146, 20148 to 20173 


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Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 17761 

inclusive, 20176, and 20177); or Bombardier 

Service Bulletin 100–25–21, dated June 30, 

2008 (for airplanes having S/Ns 20003 

through 20123 inclusive, 20126, 20127, 

20129 to 20133 inclusive, 20135 to 20138 

inclusive, 20140 to 20142 inclusive, 20144, 

20145, and 20147). 

(i) If no RTV is found, clean the plug of the 

sensing port. 

(ii) If any RTV is found, install a new safety 

valve. 

(i) For airplanes having S/Ns 20174, 20175, 

20178 through 20189 inclusive, 20191 

through 20228 inclusive, 20230 through 

20232 inclusive, 20235, 20237, 20238, 20241, 

20244, 20247, 20249 through 20251 

inclusive, 20254, 20256 and 20259: Within 

50 flight hours after June 1, 2010, clean the 

cabin pressure-sensing port plug in both 

safety valves, in accordance with Paragraph 

2.B., ‘‘Part A—Modification—Cleaning,’’ of 

the Accomplishment Instructions of 

Bombardier Service Bulletin A100–21–08, 

dated June 18, 2009. 

(j) For airplanes having S/Ns 20003 

through 20189 inclusive, 20191 through 

20228 inclusive, 20230 through 20232 

inclusive, 20235, 20237, 20238, 20241, 

20244, 20247, 20249 through 20251 

inclusive, 20254, 20256, and 20259: Within 

50 flight hours after June 1, 2010, clean the 

cabin pressure-sensing port plug in both 

safety valves, in accordance with Paragraph 

2.B., ‘‘Part A—Modification—Cleaning,’’ of 

the Accomplishment Instructions of 

Bombardier Service Bulletin A100–21–08, 

dated June 18, 2009. Repeat the cleaning 

thereafter at intervals not to exceed 50 flight 

hours until the actions specified by 

paragraph (k) of this AD are completed. 

New Requirements of This AD 

(k) For airplanes, having S/Ns 20003 

through 20189 inclusive, 20191 through 

20228 inclusive, 20230 through 20232 

inclusive, 20235, 20237, 20238, 20241, 

20244, 20247, 20249 through 20251 

inclusive, 20254, 20256, and 20259: Within 

12 months after the effective date of this AD, 

replace the cabin pressure-sensing port plug 

having part number (P/N) 2844–060 in both 

safety valves with a new gridless plug having 

P/N 2844–19 and re-identify the safety 

valves, in accordance with Paragraph 2.C., 

‘‘Part B—Modification—Replacement,’’ of the 

Accomplishment Instructions of Bombardier 

Service Bulletin A100–21–08, dated June 18, 

2009. Doing the actions in paragraph (k) of 

this AD terminates the repetitive cleanings 

required by paragraph (j) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

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, 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. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–06, dated February 24, 

2010; and the service information specified 

in table 1 of this AD; as applicable; for 

related information. 

TABLE 1—SERVICE INFORMATION

Document Date 

Bombardier Service Bulletin A100–21–08 ...................................................................................................................................... June 18, 2009. 

Bombardier Service Bulletin 100–25–14 ........................................................................................................................................ June 30, 2008. 

Bombardier Service Bulletin 100–25–21 ........................................................................................................................................ June 30, 2008. 

Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘Certification Maintenance Requirements,’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks.October 1, 2009. 

Material Incorporated by Reference 

(n) You must use the applicable service 

information contained 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 Date 

Bombardier Service Bulletin A100–21–08 ...................................................................................................................................... June 18, 2009. 

Bombardier Service Bulletin 100–25–14 ........................................................................................................................................ June 30, 2008. 

Bombardier Service Bulletin 100–25–21 ........................................................................................................................................ June 30, 2008. 

Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘Certification Maintenance Requirements,’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks.October 1, 2009. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of this service information on June 

1, 2010 (75 FR 27406, May 17, 2010). 

(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 March 

21, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–7296 Filed 3–30–11; 8:45 am] 

BILLING CODE 4910–13–P 


jdjones on DSK8KYBLC1PROD with RULES_2