27406 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

Related Information 

(i) Refer to MCAI Brazilian Airworthiness 

Directive 2009–01–01, effective January 8, 

2009, as corrected by Brazilian Airworthiness 

Directive Errata, effective January 20, 2009; 

EMBRAER Service Bulletin 145–32–0120, 

Revision 02, dated February 17, 2009; and 

EMBRAER Service Bulletin 145LEG–32– 

0032, Revision 02, dated February 17, 2009; 

for related information. 

Material Incorporated by Reference 

(j) You must use EMBRAER Service 

Bulletin 145–32–0120, Revision 02, dated 

February 17, 2009; and EMBRAER Service 

Bulletin 145LEG–32–0032, Revision 02, 

dated February 17, 2009; as applicable; 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 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone: 

+55 12 3927–5852 or +55 12 3309–0732; fax: 

+55 12 3927–7546; e-mail: 

distrib@embraer.com.br; Internet: http:// 

www.flyembraer.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 29, 

2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–10872 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–2010–0475; Directorate 

Identifier 2010–NM–083–AD; Amendment 

39–16297; AD 2010–10–18] 

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; request for 

comments. 

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: 

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. This AD requires 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: This AD becomes effective June 

1, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 1, 2010. 

We must receive comments on this 

AD by July 1, 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. 

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 (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 

Transport Canada Civil Aviation, 

which is the aviation authority for 

Canada, has issued Canadian 

Airworthiness Directive CF–2010–06, 

dated February 24, 2010 (referred to 

after this as ‘‘the MCAI’’), 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 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27407 

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. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin A100–21–08, dated June 18, 

2009; Service Bulletin 100–25–14, dated 

June 30, 2008; Service Bulletin 100–25– 

21, dated June 30, 2008; and 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. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because if the safety valve cabin 

pressure-sensing ports are partially 

blocked in conjunction with a dormant 

failure or leakage of the safety valve 

manometric capsule could result in a 

loss of cabin pressurization. Therefore, 

we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in fewer than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0475; 

Directorate Identifier 2010–NM–083– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 

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. 

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: 

2010–10–18 Bombardier, Inc.: Amendment 

39–16297. Docket No. FAA–2010–0475; 

Directorate Identifier 2010–NM–083–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 1, 2010. 


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27408 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

Affected ADs 

(b) None. 

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 and 25: Air conditioning 

and Equipment/Furnishings, respectively. 

Reason 

(e) The mandatory continued 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. 

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. 

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 all airplanes: Within 30 days after 

the effective date of this AD, 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 the effective date of 

this AD. 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 the effective date 

of this AD, 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 

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 the effective date of this 

AD, 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 the effective date of this 

AD, 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. 

(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: 

Replacing the cabin pressure-sensing port 

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

both safety valves with a new gridless plug 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27409 

having P/N 2844–19 and re-identifying 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, 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: This 

AD does not require the replacement of the 

safety valve cabin pressure-sensing port 

plugs and the re-identification of the safety 

valves required in Part V of MCAI Canadian 

Airworthiness Directive CF–2010–06, dated 

February 24, 2010. The planned compliance 

times for these actions would not allow 

enough time to provide notice and 

opportunity for prior public comment on the 

merits of those actions. Therefore, we are 

considering further rulemaking to address 

these issues. 

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 ensure 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–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 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 

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. 2010–11074 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–2010–0060; Directorate 

Identifier 2010–SW–06–AD; Amendment 39– 

16282; AD 2010–10–03] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–92A Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Sikorsky Model S–92A helicopters. The 


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