60604 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 5, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) McDonnell Douglas Corporation Model 

DC–10–10, DC–10–10F, DC–10–15, DC–10– 

30, DC–10–30F (KC–10A and KDC–10), DC– 

10–40, DC–10–40F, MD–10–10F, and MD– 

10–30F airplanes; certificated in any 

category; as identified in Boeing Service 

Bulletin DC10–28–252, Revision 1, dated 

January 6, 2010. 

(2) McDonnell Douglas Corporation Model 

MD–11 and MD–11F airplanes; certificated in 

any category; as identified in Boeing Service 

Bulletin MD11–28–132, Revision 1, dated 

July 6, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent fuel tank explosions and 

consequent loss of the airplane. 

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. 

Installation 

(g) Within 60 months after the effective 

date of this AD do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For Model DC–10–10, DC–10–10F, DC– 

10–15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, DC–10–40F, MD–10– 

10F, and MD–10–30F airplanes: Install an inline fuse in each float level switch and 

pressure switch, including sleeving the wires 

between the fuel tank and the in-line fuse, in 

fuel tanks 1, 2, and 3; upper and lower 

auxiliary fuel tanks; forward and aft auxiliary 

fuel tanks; and center wing fuel tanks; as 

applicable; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–252, Revision 1, 

dated January 6, 2010. 

(2) For Model MD–11 and MD–11F 

airplanes: Install an in-line fuse in each float 

level switch, including sleeving the wires 

between the fuel tank and the in-line fuse, in 

fuel tanks 1, 2, and 3; upper and lower 

auxiliary fuel tanks; forward auxiliary fuel 

tank; center wing fuel tanks; and tail fuel 

tank; as applicable; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin MD11–28–132, Revision 1, 

dated July 6, 2010. 

Installation According to Previous Issues of 

Service Bulletins 

(h) Installing an in-line fuse in each float 

level switch and pressure switch, including 

sleeving the wires between the fuel tank and 

the in-line fuse, in fuel tanks 1, 2, and 3; 

upper and lower auxiliary fuel tanks; forward 

and aft auxiliary fuel tanks; and center wing 

fuel tanks; as applicable; is also acceptable 

for compliance with the corresponding 

requirements of paragraph (g)(1) of this AD, 

if done before the effective date of this AD, 

in accordance with Boeing Service Bulletin 

DC10–28–252, dated November 25, 2008. 

(i) Installing an in-line fuse in each float 

level switch, including sleeving the wires 

between the fuel tank and the in-line fuse, in 

fuel tanks 1, 2, and 3; upper and lower 

auxiliary fuel tanks; forward auxiliary fuel 

tank; center wing fuel tanks; and tail fuel 

tank; as applicable; is also acceptable for 

compliance with the corresponding 

requirements of paragraph (g)(2) of this AD 

if done before the effective date of this AD, 

in accordance with Boeing Service Bulletin 

MD11–28–132, dated November 25, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Philip Kush, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5263; fax (562) 

627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

DC10–28–252, Revision 1, dated January 6, 

2010; or Boeing Service Bulletin MD11–28– 

132, Revision 1, dated July 6, 2010; 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.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 

September 16, 2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–24172 Filed 9–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0550; Directorate 

Identifier 2009–NM–124–AD; Amendment 

39–16454; AD 2010–20–19] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes; Model 

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

701, & 702) Airplanes; Model CL–600– 

2D15 (Regional Jet Series 705) 

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: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part is also installed on CL–600– 

2C10, –2D15 and –2D24 aircraft. 

Investigation determined that the crack was 

in an area of the strut where the wall 

thickness of the casting was below 

specification, due to a manufacturing 

anomaly in a specific batch of ADGs. 

Structural failure and departure of the ADG 

during deployment could possibly result in 

damage to the aircraft structure. If 

deployment was activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

* * * * * 

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Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations 60605 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 5, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 5, 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: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; 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 June 18, 2010 (75 FR 34657). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part is also installed on CL–600– 

2C10, –2D15 and –2D24 aircraft. 

Investigation determined that the crack was 

in an area of the strut where the wall 

thickness of the casting was below 

specification, due to a manufacturing 

anomaly in a specific batch of ADGs. 

Structural failure and departure of the ADG 

during deployment could possibly result in 

damage to the aircraft structure. If 

deployment was activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

This [Transport Canada Civil Aviation 

(TCCA)] directive gives instructions to check 

the part number of the installed ADG and, for 

ADGs with a part number in the 761339 

series, the serial numbers of the ADG and 

strut and generator housing assembly are also 

to be checked. If these serial numbers are 

within specified ranges * * *, a one-time 

fluorescent penetrant inspection of the ADG 

strut is required [and replacement of the ADG 

if necessary]. 

Note: For ADGs with serial numbers in the 

* * * specified ranges, subsequent 

fluorescent penetrant inspections are 

required after each scheduled in-flight or onground functional check of the ADG and also 

after each unscheduled in-flight ADG 

deployment. These inspection requirements 

are not mandated in this [TCCA] directive 

but are specified in the approved 

maintenance program. 

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 comment received. Air 

Line Pilots Association, International 

supports the NPRM. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 

1,073 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $91,205, 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 

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 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. 

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60606 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–20–19 Bombardier, Inc.: Amendment 

39–16454. Docket No. FAA–2010–0550; 

Directorate Identifier 2009–NM–124–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 5, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

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

& 440) airplanes, serial numbers 7305 

through 8051 inclusive; Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10003 through 

10260 inclusive; and Model CL–600–2D15 

(Regional Jet Series 705) airplanes and Model 

CL–600–2D24 (Regional Jet Series 900) 

airplanes, serial numbers 15001 through 

15106 inclusive; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Two cases of a crack on a ‘‘dry’’ ADG [air 

driven generator] (Hamilton Sundstrand part 

number in the 761339 series), in the aft area 

of the strut and generator housing assembly, 

have been reported on CL–600–2B19 aircraft. 

The same part is also installed on CL–600– 

2C10, –2D15 and–2D24 aircraft. Investigation 

determined that the crack was in an area of 

the strut where the wall thickness of the 

casting was below specification, due to a 

manufacturing anomaly in a specific batch of 

ADGs. Structural failure and departure of the 

ADG during deployment could possibly 

result in damage to the aircraft structure. If 

deployment was activated by a dual engine 

shutdown, ADG structural failure would also 

result in loss of hydraulics for the flight 

controls. 

This [Transport Canada Civil Aviation 

(TCCA)] directive gives instructions to check 

the part number of the installed ADG and, for 

ADGs with a part number in the 761339 

series, the serial numbers of the ADG and 

strut and generator housing assembly are also 

to be checked. If these serial numbers are 

within specified ranges * * *, a one-time 

fluorescent penetrant inspection of the ADG 

strut is required [and replacement of the ADG 

if necessary]. 

Note: For ADGs with serial numbers in the 

* * * specified ranges, subsequent 

fluorescent penetrant inspections are 

required after each scheduled in-flight or onground functional check of the ADG and also 

after each unscheduled in-flight ADG 

deployment. These inspection requirements 

are not mandated in this [TCCA] directive 

but are specified in the approved 

maintenance program. 

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) Do the following actions. 

(1) Within 1,000 flight hours after the 

effective date of this AD or before the first 

scheduled ADG functional test after the 

effective date of this AD, whichever occurs 

first, inspect to determine the part number of 

the installed ADG. A review of the airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number can be 

conclusively determined from that review. 

(i) If a Hamilton Sundstrand ADG having 

part number 1711405 is installed, the strut 

thickness is within specification and no 

further action is required by this AD. 

(ii) If a Hamilton Sundstrand ADG having 

a part number in the 761339 series is 

installed, within 1,000 flight hours after the 

effective date of this AD or before the first 

scheduled ADG functional test after the 

effective date of this AD, whichever occurs 

first, inspect to determine the serial number 

of the ADG. A review of the airplane 

maintenance records is acceptable in lieu of 

this inspection if the serial number can be 

conclusively determined from that review. 

(A) If the serial number of the ADG is 2000 

or higher, the strut wall thickness is within 

specification and no further action is 

required by this AD. 

(B) If the serial number of the ADG is in 

the range 0101 through 1999 and symbol 

‘‘24–3’’ is marked in the serial number block 

of the identification plate, the strut wall 

thickness is within specification, no further 

action is required by this AD. 

(C) If the serial number of the ADG is in 

the range 0101 through 1999 and the symbol 

‘‘24–3’’ is not marked in the serial block of the 

identification plate, within 1,000 flight hours 

after the effective date of this AD or before 

the first scheduled ADG functional test after 

the effective date of this AD, whichever 

occurs first, inspect to determine the serial 

number of the strut and generator housing 

assembly. A review of the airplane 

maintenance records is acceptable in lieu of 

this inspection if the serial number can be 

conclusively determined from that review. 

(1) If the serial number of the strut and 

generator housing assembly is in the range 

0001 through 2503, do a fluorescent 

penetrant inspection in accordance with 

paragraph (g)(2) of this AD at the times 

specified in paragraph (g)(2) of this AD. 

(2) If the serial number of the strut and 

generator housing assembly is 2504 or higher, 

the strut wall thickness is within 

specification and no further action is 

required by this AD. 

(3) If the serial number of the strut and 

generator housing assembly is not inspected 

or it is not possible to determine the serial 

number, do a fluorescent penetrant 

inspection in accordance with paragraph 

(g)(2) of this AD at the times specified in 

paragraph (g)(2) of this AD. 

(2) For ADGs having a strut and generator 

assembly identified in paragraph 

(g)(1)(ii)(C)(1) or (g)(1)(ii)(C)(3) of this AD: 

Within 1,000 flight hours after the effective 

date of this AD or before the first scheduled 

ADG functional test after the effective date of 

this AD, whichever occurs first, do a 

fluorescent penetrant inspection for cracking 

of the ADG strut, and if any crack is found, 

before further flight, replace the ADG with a 

serviceable ADG, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A601R–24–120, 

Revision C, dated April 20, 2009 (for Model 

CL–600–2B19 airplanes); or Bombardier Alert 

Service Bulletin A670BA–24–020, Revision 

C, dated April 20, 2009 (for Model CL–600– 

2C10, CL–600–2D15, and CL–600–2D24 

airplanes). 

(3) Fluorescent penetrant inspections 

accomplished before the effective date of this 

AD in accordance with any applicable 

service bulletin specified in Table 1 of this 

AD are considered acceptable for compliance 

with the corresponding fluorescent penetrant 

inspection specified in this AD. 

TABLE 1—CREDIT SERVICE BULLETINS

Bombardier, Inc. model— Service Bulletin— Revision— Date— 

CL–600–2B19 airplanes .................................... Bombardier Alert Service Bulletin A601R–24– 

120.

Original ....................... April 20, 2005. 

CL–600–2B19 airplanes .................................... Bombardier Alert Service Bulletin A601R–24– 

120.

A ................................. December 1, 2005. 

CL–600–2B19 airplanes .................................... Bombardier Alert Service Bulletin A601R–24– 

120.

B ................................. December 7, 2006. 

CL–600–2C10 airplanes and CL–600–2D24 

airplanes.

Bombardier Alert Service Bulletin A670BA– 

24–020.

Original ....................... April 20, 2005. 

CL–600–2C10 airplanes; and CL–600–2D15 

and CL–600–2D24 airplanes.

Bombardier Alert Service Bulletin A670BA– 

24–020.

A ................................. May 17, 2005. 

CL–600–2C10 airplanes; and CL–600–2D15 

and CL–600–2D24 airplanes.

Bombardier Alert Service Bulletin A670BA– 

24–020.

B ................................. December 7, 2006. 

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Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations 60607 

TABLE 1—CREDIT SERVICE BULLETINS—Continued 

Bombardier, Inc. model— Service Bulletin— Revision— Date— 

CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600– 

2D24 airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–3.

Original ....................... April 14, 2005. 

CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600– 

2D24 airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–3.

1 ................................. April 19, 2005. 

CL–600–2B19 airplanes; CL–600–2C10 airplanes; and CL–600–2D15 and CL–600– 

2D24 airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–3.

2 ................................. November 14, 2006. 

Bombardier, Inc. CL–600–2B19 airplanes; CL– 

600–2C10 airplanes; and CL–600–2D15 and 

CL–600–2D24 airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–3.

3 ................................. March 12, 2009. 

Note 1: Additional guidance on the ADGs 

specified in paragraphs (g)(1)(ii)(C)(1)and 

(g)(1)(ii)(C)(3) of this AD and the repetitive 

fluorescent penetrant inspections specified as 

part of the periodic ADG functional check 

procedure may be found in the applicable 

tasks identified in Table 2 of this AD. These 

tasks can be found in Part 2—Airworthiness 

Limitations, Appendix A—Certification 

Maintenance Requirements (CMR), of the 

Bombardier CL–600–2C10, CL–600–2D15, 

and CL–600–2D24 Maintenance 

Requirements Manual; and the Canadair CRJ 

Series Regional Jet Aircraft Maintenance 

Manual (AMM); as applicable. 

TABLE 2—GUIDANCE FOR THE PERIODIC ADG FUNCTIONAL CHECK PROCEDURE

Bombardier, Inc. Model— Task number— 

CL–600–2B19 airplanes ........................................................................... CMR Task C24–20–129–01 and AMM Task 24–23–01–720–803 

CL–600–2C10 airplanes ........................................................................... CMR Task 24–23–00–102 and AMM Task 24–23–01–720–802 

CL–600–2D15 and CL–600–2D24 airplanes ........................................... CMR Task 24–23–00–102 and AMM Task 24–23–01–720–802 

Note 2: Additional guidance on the ADGs 

specified in paragraph (g)(1)(ii)(C)(1), and the 

fluorescent penetrant inspection necessary 

following each future unscheduled in-flight 

ADG deployment can be found in the tasks 

specified in Table 3 of this AD. 

TABLE 3—GUIDANCE FOR INSPECTION FOLLOWING UNSCHEDULED IN-FLIGHT ADG DEPLOYMENT

Bombardier, Inc. Model— AMM task— 

CL-600–2B19 airplanes, serial numbers 7305 through 8051 inclusive ................................................................................ 05–51–19–210–801 

CL–600–2C10 airplanes, serial numbers 10003 through 10260 inclusive ........................................................................... 05–51–19–210–801 

CL-600-2D15 and CL–600–2D24 airplanes, serial numbers 15001 through 15106 inclusive ............................................. 05–51–19–210–801 

Note 3: In Hamilton Sundstrand Service 

Bulletin ERPS10AG–24–3, the fluorescent 

penetrant inspection is referred to as a 

‘‘Penetrant Check.’’. 

FAA AD Differences 

Note 4: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) 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. 

(4) Special Flight Permits: Special flight 

permits, as described in section 21.197 and 

section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed. 

Related Information 

(i) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–27, dated June 8, 2009; 

Bombardier Alert Service Bulletin A601R– 

24–120, Revision C, dated April 20, 2009; 

and Bombardier Alert Service Bulletin 

A670BA–24–020, Revision C, dated April 20, 

2009; for related information. 

Material Incorporated by Reference 

(j) You must use Bombardier Alert Service 

Bulletin A601R–24–120, Revision C, dated 

April 20, 2009; or Bombardier Alert Service 

Bulletin A670BA–24–020, Revision C, dated 

April 20, 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 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. 

(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 

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60608 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Rules and Regulations 

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 

September 21, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24482 Filed 9–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0438; Directorate 

Identifier 2009–NM–265–AD; Amendment 

39–16450; AD 2010–20–15] 

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 superseding an 

existing 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: 

The heating capability of several AOA 

[angle of attack] transducer heating elements 

removed from in-service aircraft has been 

found to be below the minimum requirement. 

Also, it was discovered that a large number 

of AOA transducers repaired in an approved 

maintenance facility were not calibrated 

accurately. 

Inaccurate calibration of the AOA 

transducer and/or degraded AOA transducer 

heating elements can result in early or late 

activation of the stall warning, stick shaker 

and stick pusher by the Stall Protection 

Computer (SPC). 

* * * * * 

Inaccurate calibration of the AOA 

transducers and/or degraded AOA 

transducer heating elements could 

result in an ineffective response to an 

aerodynamic stall and reduced 

controllability of the airplane. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

November 5, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 5, 2010. 

On November 13, 2009 (74 FR 55767, 

October 29, 2009), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in this AD. 

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: 

Wing Chan, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7311; 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 May 10, 2010 (75 FR 25791), 

and proposed to supersede AD 2009– 

22–12, Amendment 39–16065 (74 FR 

55767, October 29, 2009). That NPRM 

proposed to correct an unsafe condition 

for the specified products. 

When we issued AD 2009–22–12, we 

stated that we did not include certain 

actions (the inspection to determine if 

certain transducers are installed and 

replaced if necessary in paragraph (h) of 

this AD) because the planned 

compliance time was not enough to give 

notice as AD 2009–22–12 was issued as 

an immediately adopted rule. We now 

have determined that further 

rulemaking is indeed necessary, and 

this AD follows from that 

determination. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Since we issued the NPRM we have 

reviewed Bombardier Service Bulletin 

670BA–27–053, Revision B, dated 

January 12, 2010. We referred to 

Bombardier Service Bulletin 670BA–27– 

053, Revision A, dated July 7, 2009, as 

the appropriate source of service 

information for doing certain actions 

specified in the NPRM. Bombardier 

Service Bulletin 670BA–27–053, 

Revision B, dated January 12, 2010, 

contains minor editorial changes that do 

not have an effect on the technical 

content in this AD. We have revised 

paragraphs (h) and (i) of this AD to refer 

to Bombardier Service Bulletin 670BA– 

27–053, Revision B, dated January 12, 

2010. We have also added Bombardier 

Service Bulletin 670BA–27–053, 

Revision A, dated July 7, 2009, to 

paragraph (j) of this AD for credit for 

inspections and replacements 

accomplished before the effective date 

of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. One 

commenter, Air Line Pilots Association, 

International, supports the NPRM. 

Request to Reference the Correct 

Service Bulletin 

Comair, Inc. states that the intended 

reference for paragraph (j) of the NPRM 

should be Bombardier Service Bulletin 

670BA–27–053, dated May 14, 2009, for 

inspections and replacements 

accomplished before the effective date 

of this AD. 

We agree with Comair, Inc. that 

Bombardier Service Bulletin 670BA–27– 

053, dated May 14, 2009, is considered 

acceptable for compliance with the 

corresponding actions specified in this 

AD. We have added this service bulletin 

to paragraph (j) of this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We 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 

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