10216 Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 

(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. 

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 airworthiness 

directive (AD): 

2011–04–08 Learjet Inc.: Amendment 39– 

16608; Docket No. FAA–2010–0951; 

Directorate Identifier 2010–NM–107–AD. 

Effective Date 

(a) This AD is effective March 31, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Learjet Inc. Model 

45 airplanes, certificated in any category; 

having serial numbers identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Serial numbers 45–2001 through 45– 

2114 inclusive, 45–2116 through 45–2120 

inclusive, 45–2122, 45–2125, and 45–2126. 

(2) Serial numbers 45–005 through 45–380 

inclusive, 45–382 through 45–391 inclusive, 

45–393 through 45–396 inclusive, 45–398, 

45–400, 45–401, and 45–403. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Unsafe Condition 

(e) This AD results from reports of wire 

damage on the pilot and copilot circuit 

breaker panels caused by a short circuit 

between chafed wiring and the circuit 

breaker panel forward mounting bracket. The 

Federal Aviation Administration is issuing 

this AD to detect and correct damaged or 

misrouted wires, which could result in a 

short circuit and the loss of systems 

associated with the wiring (including fire 

suppression function for one engine and 

essential avionics systems). 

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. 

Inspection and Corrective Action 

(g) Within 50 flight hours after the effective 

date of this AD: Do a general visual 

inspection for damage of wiring and correct 

routing of wires in the left and right circuit 

breaker panels, and all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A40–24–11, dated November 16, 

2009; or Bombardier Alert Service Bulletin 

A45–24–16, dated November 16, 2009; as 

applicable; except if arcing damage is found 

on the forward mounting bracket of the 

circuit breaker panel, before further flight, 

repair in accordance with a method approved 

by the Manager, Wichita Aircraft 

Certification Office, FAA. Do all applicable 

related investigative and corrective actions 

before further flight. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Wichita 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: Jose 

Flores, Aerospace Engineer, Electrical 

Systems and Avionics, ACE–119W, FAA, 

Wichita Aircraft Certification Office (ACO), 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

316–946–4133; fax 316–946–4107. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

Related Information 

(i) For more information about this AD, 

contact Jose Flores, Aerospace Engineer, 

Electrical Systems and Avionics, ACE–119W, 

FAA, Wichita Aircraft Certification Office 

(ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; 

telephone 316–946–4133; fax 316–946–4107. 

Material Incorporated by Reference 

(j) You must use Bombardier Alert Service 

Bulletin A40–24–11, dated November 16, 

2009; or Bombardier Alert Service Bulletin 

A45–24–16, dated November 16, 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 

Bombardier Alert Service Bulletin A40–24– 

11, dated November 16, 2009; and 

Bombardier Alert Service Bulletin A45–24– 

16, dated November 16, 2009; under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Learjet, Inc., One Learjet 

Way, Wichita, Kansas 67209–2942; telephone 

316–946–2000; fax 316–946–2220; e-mail 

ac.ict@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 an NARA facility, 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 February 

7, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–3534 Filed 2–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1039; Directorate 

Identifier 2010–NM–002–AD; Amendment 

39–16612; AD 2011–05–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

There has been numerous reported failures 

of the Regional Jet engine TCGB [throttle 

control gearbox] P/Ns: 2100140–003, 

2100140–005 & 2100140–007. Some of these 

failures have resulted in in-flight engine 

shutdowns. Post incident investigations 

revealed that excessive wear within the 


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Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 10217 

engine TCGB could alter the rigging position 

or cause the throttle to jam. With the rigging 

position altered, movement of the throttle 

lever towards the idle position can result in 

throttle moving too close to the fuel shut-off 

position, which potentially, can cause the 

engine to flame out. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 31, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 31, 2011. 

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: 

Rocco Viselli, Senior Aviation Safety 

Engineer, Avionic & Flight Test Branch, 

ANE–172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531; e-mail 

Rocco.Viselli@faa.gov. 

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 October 21, 2010 (75 FR 

64960), and proposed to supersede AD 

2005–06–04, Amendment 39–14012 (70 

FR 12963, March 17, 2005). That NPRM 

proposed to correct an unsafe condition 

for the specified products. 

Since we issued AD 2005–06–04, the 

inspection for the throttle control 

gearbox (TCGB) required by that AD has 

been transcribed in a new certification 

maintenance requirement (CMR) task. 

This AD mandates the incorporation of 

new CMR Task C76–11–127–01 into the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual (MRM) as 

introduced by Bombardier Temporary 

Revision 2A–47. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2004–01R2, dated September 29, 2009 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

There has been numerous reported failures 

of the Regional Jet engine TCGB [throttle 

control gearbox] P/Ns: 2100140–003, 

2100140–005 & 2100140–007. Some of these 

failures have resulted in in-flight engine 

shutdowns. Post incident investigations 

revealed that excessive wear within the 

engine TCGB could alter the rigging position 

or cause the throttle to jam. With the rigging 

position altered, movement of the throttle 

lever towards the idle position can result in 

throttle moving too close to the fuel shut-off 

position, which potentially, can cause the 

engine to flame out. 

Bombardier issued Service Bulletin (SB) 

601R–76–019 dated 21 August 2003, to 

introduce an inspection of, and if required, 

replacement of the throttle control gearbox 

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

originally issued to mandate the subject 

inspection requirement as per SB 601R–76– 

019 and subsequent revisions. 

The subject TCGB inspection requirements 

mandated as per the earlier versions of this 

[Canadian] AD, are now transcribed in a new 

Certification Maintenance Requirement 

(CMR) task. This revision is issued to 

mandate the incorporation of the new CMR 

task [Task C76–11–127–01] into the CL–600– 

2B19 Maintenance Requirements Manual 

(MRM), as introduced by the MRM 

Temporary Revision (TR) 2A–47. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

The NPRM referred to Bombardier 

Service Bulletin 601R–76–019, Revision 

C, dated July 5, 2007, as the appropriate 

source of service information for 

accomplishing certain proposed actions. 

Bombardier Inc. has issued Service 

Bulletin 601R–76–019, Revision D, 

dated September 23, 2010. This service 

bulletin does not add any work for the 

affected airplanes. We have revised this 

final rule to refer to Bombardier Service 

Bulletin 601R–76–019, Revision D, 

dated September 23, 2010, as the 

appropriate source of service 

information for accomplishing the 

applicable actions. 

We have added new paragraph (m) to 

this final rule to give credit to operators 

for accomplishing the applicable actions 

before the effective date of this AD in 

accordance with Bombardier Service 

Bulletin 601R–76–019, Revision C, 

dated July 5, 2007. We have reidentified subsequent paragraphs 

accordingly. 

The NPRM also referred to 

Bombardier Temporary Revision 2A–47, 

dated May 27, 2009, to Appendix A— 

Certification Maintenance 

Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual for incorporating 

new CMR Task C76–11–127–01 into the 

maintenance program. Bombardier Inc. 

has issued Temporary Revision 2A–53, 

dated December 15, 2010, to Appendix 

A—Certification Maintenance 

Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. Bombardier 

Temporary Revision 2A–53, dated 

December 15, 2010, was issued to revise 

the task description of CMR Task C76– 

11–127–01. We have revised this final 

rule to allow operators to use either 

Bombardier Temporary Revision 2A–47, 

dated May 27, 2009; or Bombardier 

Temporary Revision 2A–53, dated 

December 15, 2010; for revising the 

maintenance program to include CMR 

Task C76–11–127–01. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 638 products of U.S. registry. 

The actions that are required by AD 

2005–06–04 and retained in this AD 

take about 7 work-hours per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $595 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 workVerDate Mar<15>2010 16:10 Feb 23, 2011 Jkt 223001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\24FER1.SGM 24FER1

jlentini on DSKJ8SOYB1PROD with RULES
10218 Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 

hour. Based on these figures, we 

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

operators to be $54,230, or $85 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–14012 (70 FR 

12963, March 17, 2005) and adding the 

following new AD: 

2011–05–03 Bombardier, Inc.: Amendment 

39–16612. Docket No. FAA–2010–1039; 

Directorate Identifier 2010–NM–002–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 31, 2011. 

Affected ADs 

(b) The AD supersedes AD 2005–06–04, 

Amendment 39–14012. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

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

& 440) airplanes, certificated in any category, 

having an engine throttle control gearbox 

(TCGB) with part number 2100140–003, 

2100140–005, or 2100140–007 installed. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

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

the operator must request approval for an 

alternative method of compliance according 

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

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 76: Engine Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There has been numerous reported failures 

of the Regional Jet engine TCGB P/Ns: 

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

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

investigations revealed that excessive wear 

within the engine TCGB could alter the 

rigging position or cause the throttle to jam. 

With the rigging position altered, movement 

of the throttle lever towards the idle position 

can result in throttle moving too close to the 

fuel shut-off position, which potentially, can 

cause the engine to flame out. 

Bombardier issued Service Bulletin (SB) 

601R–76–019 dated 21 August 2003, to 

introduce an inspection of, and if required, 

replacement of the throttle control gearbox 

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

originally issued to mandate the subject 

inspection requirement as per SB 601R–76– 

019 and subsequent revisions. 

The subject TCGB inspection requirements 

mandated as per the earlier versions of this 

[Canadian] AD, are now transcribed in a new 

Certification Maintenance Requirement 

(CMR) task. This revision is issued to 

mandate the incorporation of the new CMR 

task [Task C76–11–127–01] into the CL–600– 

2B19 Maintenance Requirements Manual 

(MRM), as introduced by the MRM 

Temporary Revision (TR) 2A–47. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2005– 

06–04, With New Service Information 

Inspection 

(g) For airplanes having serial numbers 

(S/Ns) 7003 through 7067 inclusive, and 

7069 and subsequent: At the applicable time 

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

AD, do a detailed inspection for wear of the 

left and right engine throttle control 

gearboxes having part number (P/N) 

2100140–005 or 2100140–007 by doing all 

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

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

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010. If the wear 

value is the same as that specified in Part A, 

paragraph B.(8), of the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010; repeat the 

inspection thereafter at intervals not to 

exceed 1,000 flight hours. As of the effective 

date of this AD, only Bombardier Service 

Bulletin 601R–76–019, Revision D, dated 

September 23, 2010, may be used. Doing the 

inspection required by paragraph (k) of this 

AD terminates the requirement in this 

paragraph. 

(1) For airplanes having S/Ns 7003 through 

7067 inclusive and 7069 through 7999 

inclusive: Within 1,000 flight hours or 90 

days after March 25, 2004 (the effective date 

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

(2) For airplanes having S/Ns 8000 and 

subsequent: Within 1,000 flight hours or 90 


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days after April 1, 2005 (the effective date of 

AD 2005–06–04), whichever is later. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at an intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’ 

Corrective Action 

(h) If the wear value found during any 

inspection required by paragraph (g) of this 

AD is not the same as that specified in Part 

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

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010: Do the 

applicable actions required by paragraph 

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

specified, per the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010. Repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 1,000 

flight hours. As of the effective date of this 

AD, only Bombardier Service Bulletin 601R– 

76–019, Revision D, dated September 23, 

2010, may be used. Doing the inspection 

required by paragraph (k) of this AD 

terminates the inspection requirements of 

this paragraph. 

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

gearboxes is the same as that specified in Part 

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

Instructions of Bombardier Service Bulletin 

601R–76–019, dated August 21, 2003; 

Revision ‘A,’ dated February 19, 2004; 

Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010: Before further 

flight, replace the affected gearbox with a 

new or serviceable gearbox, by doing all the 

actions per Part B, paragraphs D. through 

F.(7), of the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–76–019, 

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

February 19, 2004; Revision B, dated 

February 16, 2005; Revision C, dated July 5, 

2007; or Revision D, dated September 23, 

2010. As of the effective date of this AD, only 

Bombardier Service Bulletin 601R–76–019, 

Revision D, dated September 23, 2010, may 

be used. 

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

right gearboxes is the same as that specified 

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

Service Bulletin 601R–76–019, dated August 

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

2004; Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010: Before further 

flight, replace the gearbox having the higher 

wear value with a new or serviceable 

gearbox, by doing all the actions per Part B, 

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

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

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

2004; Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010. Within 1,000 

flight hours after doing the replacement, 

replace the other gearbox. As of the effective 

date of this AD, only Bombardier Service 

Bulletin 601R–76–019, Revision D, dated 

September 23, 2010, may be used. 

(3) If the wear value on only one gearbox 

is the same as that specified in Part A, 

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

other gearbox is the same as that specified in 

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

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

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

2004; Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010: Within 1,000 

flight hours after the inspection, replace the 

gearbox with the wear value that is the same 

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

with a new or serviceable gearbox. Do the 

replacement by doing all the actions per Part 

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

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–76–019, dated August 

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

2004; Revision B, dated February 16, 2005; 

Revision C, dated July 5, 2007; or Revision 

D, dated September 23, 2010. As of the 

effective date of this AD, only Bombardier 

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

dated September 23, 2010, may be used. 

Additional Guidance 

Note 3: Bombardier Service Bulletin 601R– 

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

dated February 19, 2004; Revision B, dated 

February 16, 2005; Revision C, dated July 5, 

2007; and Revision D, dated September 23, 

2010; reference Trans Digm, Inc., 

AeroControlex Group Service Bulletin 

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

an additional source of guidance for 

accomplishment of the inspections and 

replacement. 

Reporting Requirement 

(i) At the applicable time specified in 

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

a report of gearbox wear to Bombardier 

Aerospace, In-Service Engineering (Engine 

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

include the airplane serial number, the 

number of flight hours on the airplane, and 

the number of flight hours on each gearbox 

(if different than the number of flight hours 

on the airplane). 

(1) For Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) airplanes, 

serial numbers 7003 through 7067 inclusive, 

and 7069 through 7999 inclusive: Submit a 

report within 10 days after doing the 

inspection required by paragraph (g) of this 

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

whichever is later. 

(2) For Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) airplanes, 

serial numbers 8000 and subsequent: Submit 

a report within 10 days after doing the 

inspection required by paragraph (g) of this 

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

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

is later. 

New Requirements of This AD 

Actions 

(j) For all airplanes: Within 30 days after 

the effective date of this AD, revise the 

maintenance program to include new CMR 

Task C76–11–127–01 specified in 

Bombardier Temporary Revision 2A–47, 

dated May 27, 2009; or Bombardier 

Temporary Revision 2A–53, dated December 

15, 2010; to Appendix A—Certification 

Maintenance Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

Note 4: The actions required by paragraph 

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

of Bombardier Temporary Revision 2A–47, 

dated May 27, 2009; or Bombardier 

Temporary Revision 2A–53, dated December 

15, 2010; into the AWL section of Appendix 

A—Certification Maintenance Requirements, 

of Part 2 of the Bombardier CL–600–2B19 

Maintenance Requirements Manual. When 

this temporary revision has been included in 

the limitation section of the general revisions 

of the document, the general revisions may 

be inserted in the document, provided the 

relevant information (CMR Task C76–11– 

127–01) in the general revision is identical to 

that in Bombardier Temporary Revision 2A– 

47, dated May 27, 2009; or Bombardier 

Temporary Revision 2A–53, dated December 

15, 2010. 

(k) For CMR Task C76–11–127–01 

identified in Bombardier Temporary Revision 

2A–47, dated May 27, 2009; or Bombardier 

Temporary Revision 2A–53, dated December 

15, 2010; do the initial inspection within 

1,000 flight hours after the effective date of 

this AD. Doing the initial inspection required 

by this paragraph terminates the 

requirements of paragraph (g) of this AD and 

the inspection requirements of paragraph (h) 

of this AD. 

(l) Thereafter, except as provided by 

paragraph (n) of this AD, no alternative 

intervals may be approved for CMR Task 

C76–11–127–01 identified in Bombardier 

Temporary Revision 2A–47, dated May 27, 

2009; or Bombardier Temporary Revision 

2A–53, dated December 15, 2010; which 

require a special detailed inspection of the 

throttle control gearbox for gear and rack 

teeth wear. 

(m) Accomplishment of the actions 

specified in paragraphs (g) and (h) of this AD 

before the effective date of this AD according 

to Bombardier Service Bulletin 601R–76–019, 

Revision C, dated July 5, 2007, is acceptable 

for compliance with the corresponding 

requirements of this AD. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(n) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 


jlentini on DSKJ8SOYB1PROD with RULES
10220 Federal Register / Vol. 76, No. 37 / Thursday, February 24, 2011 / Rules and Regulations 

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. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it 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, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding 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: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(o) Refer to MCAI Canadian Airworthiness 

Directive CF–2004–01R2, dated September 

29, 2009; Bombardier Service Bulletin 601R– 

76–019, Revision D, dated September 23, 

2010; and Bombardier Temporary Revision 

2A–47, dated May 27, 2009, or Bombardier 

Temporary Revision 2A–53, dated December 

15, 2010, to Appendix A—Certification 

Maintenance Requirements, of Part 2 of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual; for related 

information. 

Material Incorporated by Reference 

(p) You must use Bombardier Service 

Bulletin 601R–76–019, Revision D, dated 

September 23, 2010; and Bombardier 

Temporary Revision 2A–47, dated May 27, 

2009, or Bombardier Temporary Revision 

2A–53, dated December 15, 2010, to 

Appendix A—Certification Maintenance 

Requirements, of Part 2 of the Bombardier 

CL–600–2B19 Maintenance Requirements 

Manual; 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 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 February 

14, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–4012 Filed 2–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1192; Directorate 

Identifier 2010–CE–020–AD; Amendment 

39–16611; AD 2011–05–02] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate No. A–815 

Formerly Held by Bombardier Inc. and 

de Havilland, Inc.) Model DHC–3 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitively inspecting the elevator 

control tabs for discrepancies and, if any 

discrepancies are found, taking 

necessary corrective actions to bring all 

discrepancies within acceptable 

tolerances. This AD also requires 

reporting certain inspection results to 

the FAA. This AD was prompted by an 

evaluation of revisions to the 

manufacturer’s maintenance manual 

that adds new repetitive inspections of 

the elevator control tabs. To require 

compliance with these inspections for 

U.S. owners and operators we are 

mandating the inspections through the 

rulemaking process. We are issuing this 

AD to add new repetitive inspections of 

the elevator control tabs. If these 

inspections are not done, excessive freeplay in the elevator control tabs could 

develop. This condition could lead to 

loss of tab control linkage and severe 

elevator flutter. Such elevator flutter 

could lead to possible loss of control. 

DATES: This AD is effective March 31, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 31, 2011. 

ADDRESSES: For information about the 

revisions to the FAA-approved 

maintenance/inspection program 

identified in this AD, contact Viking Air 

Ltd., 9574 Hampden Road, Sidney, BC 

Canada V8L 5V5; telephone: (800) 663– 

8444; Internet: http:// 

www.vikingair.com. You may review 

copies of the referenced revisions at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

George Duckett, Aerospace Engineer, 

New York Aircraft Certification Office, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone: 

(516) 228–7325; fax: (516) 794–5531; 

e-mail: george.duckett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 


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