20498 Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 

NLG door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

Repair 

(j) If an additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD, before further flight, 

replace both forward and aft fittings with 

new fittings on the aft hinge of the affected 

NLG aft door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

(k) If no additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD: Repeat the HFEC 

inspection specified in paragraph (i) of this 

AD thereafter at intervals not to exceed 10 

flight cycles; or perform a fluorescent 

penetrant inspection for cracking thereafter at 

intervals not to exceed 3 flight cycles, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–52–5016, Revision 02, dated 

August 25, 2010, until the replacement 

required by paragraph (k)(1) or (k)(2) of this 

AD is done. 

(1) If an additional crack is found during 

any inspection required by paragraph (k) of 

this AD, before further flight, replace both 

forward and aft fittings with new fittings on 

the aft hinge of the affected NLG aft door, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–52–5016, Revision 02, dated 

August 25, 2010. 

(2) If no additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD, or repetitive HFEC 

inspection or fluorescent penetrant 

inspection required by paragraph (k) of this 

AD: Within 20 flight cycles after finding a 

crack during the most recent inspection 

required by paragraph (g) or (h) of this AD, 

replace both forward and aft fittings with 

new fittings on the aft hinge of the affected 

NLG aft door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

(l) For airplanes on which the forward 

fitting of the aft hinge of the NLG aft door is 

replaced in accordance with paragraph (j) or 

(k) of this AD: Prior to the accumulation of 

1,000 flight cycles on the forward fitting, 

perform the detailed inspection required in 

paragraph (g) of this AD, and thereafter the 

applicable repetitive inspection required in 

paragraph (h) of this AD, and apply the 

applicable actions required in paragraphs (i), 

(j), and (k) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Inspections accomplished before the 

effective date of this AD according to Airbus 

Mandatory Service Bulletin A340–52–5016, 

dated February 1, 2010; or Airbus Mandatory 

Service Bulletin A340–52–5016, Revision 01, 

dated March 30, 2010; are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI does not specify corrective action if 

cracking is found during a fluorescent 

penetrant inspection. This AD specifies 

replacing both forward and aft fittings with 

new fittings on the aft hinge of the affected 

nose landing gear aft door, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–52– 

5016, Revision 02, dated August 25, 2010. 

Other FAA AD Provisions 

(n) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone: 425–227–1138; fax: 425– 

227–1149. Information may be e-mailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2010–0028, dated February 23, 

2010; and Airbus Mandatory Service Bulletin 

A340–52–5016, Revision 02, dated August 

25, 2010; for related information. 

Material Incorporated by Reference 

(p) You must use Airbus Mandatory 

Service Bulletin A340–52–5016, excluding 

Appendix 01 and including Appendix 02, 

Revision 02, dated August 25, 2010, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone: +33 

5 61 93 36 96; fax: +33 5 61 93 45 80; e-mail: 

airworthiness.A330-A340@airbus.com; 

Internet: http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

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

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

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8278 Filed 4–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0703; Directorate 

Identifier 2009–NM–093–AD; Amendment 

39–16654; AD 2011–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) Airplanes, 

Model CL–600–2D15 (Regional Jet 

Series 705) Airplanes, and Model CL– 

600–2D24 (Regional Jet Series 900) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 


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Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 20499 

DATES: This AD becomes effective May 

18, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 18, 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: 

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; phone: 516–228–7355; 

fax: 516–794–5531; e-mail: 

Craig.Yates@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

January 11, 2011 (76 FR 1556). That 

supplemental NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

Investigation has determined that incorrect 

stack-up tolerances of the apex joint or 

improper installation of the locking plate and 

apex nut could result in torque link apex pin 

disengagement. This directive mandates [a 

one-time detailed] inspection of the torque 

link apex joint [for correct installation and 

damage, and corrective actions if necessary] 

and replacement of the torque link apex nut. 

The corrective actions include reinstalling parts that are not correctly 

installed and replacing damaged parts. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the 

supplemental NPRM or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed in the supplemental NPRM. 

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 

Based on the service information, we 

estimate that this AD will affect about 

361 products of U.S. registry. We also 

estimate that it will take about 5 workhours 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 the AD on U.S. operators to be 

$153,425, or $425 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 adding 

the following new AD: 

2011–08–04 Bombardier, Inc.: Amendment 

39–16654. Docket No. FAA–2009–0703; 

Directorate Identifier 2009–NM–093–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 18, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) airplanes, serial 

numbers (S/Ns) 10003 and subsequent. 


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20500 Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 

(2) Model CL–600–2D15 (Regional Jet 

Series 705) airplanes and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, S/ 

Ns 15001 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

Investigation has determined that incorrect 

stack-up tolerances of the apex joint or 

improper installation of the locking plate and 

apex nut could result in torque link apex pin 

disengagement. This directive mandates [a 

one-time detailed] inspection of the torque 

link apex joint [for correct installation and 

damage, and corrective actions if necessary] 

and replacement of the torque link apex nut. 

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 for Part Number (P/N) and Serial 

Number (S/N) 

(g) For all airplanes identified in 

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

Within 900 flight hours after the effective 

date of this AD, inspect the main landing 

gear (MLG) shock strut assemblies to 

determine whether an MLG shock strut 

assembly having P/Ns 49000–11 through 

49000–22 inclusive and a S/N 0001 through 

0284 inclusive is installed. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part and serial 

numbers of the MLG shock strut assembly 

can be conclusively determined from that 

review. 

Inspection of the Torque Link Apex Joint 

(h) For any MLG shock strut assembly 

having P/Ns 49000–11 through 49000–22 

inclusive and a S/N 0001 through 0284 

inclusive found installed during the 

inspection or records check required by 

paragraph (g) of this AD: Within 900 flight 

hours after the effective date of this AD, 

perform a one-time detailed inspection and 

all applicable corrective actions on the torque 

link apex joint, in accordance with Part A of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–019, 

Revision A, dated September 18, 2008, 

except as provided by paragraph (l) of this 

AD. Do all applicable corrective actions 

before further flight. 

Replacement or Rework of the Apex Nut 

(i) For any MLG shock strut assembly 

identified during the inspection or records 

check required by paragraph (g) of this AD: 

Within 4,500 flight hours after the effective 

date of this AD, replace or rework the apex 

nut, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008. 

Parts Installation 

(j) As of the effective date of this AD, no 

person may install, on any airplane, a 

replacement MLG shock strut assembly 

identified in paragraph (j)(1) or (j)(2) of this 

AD, unless it has been reworked in 

accordance with paragraph B. of Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008. 

(1) Part numbers 49000–11 through 49000– 

22 inclusive, and with a serial number in the 

range of S/Ns 0001 through 0284 inclusive 

(the serial number can start with ‘‘MA,’’ 

‘‘MAL,’’ or ‘‘MA–’’). 

(2) Part numbers 49050–5 through 49050– 

10 inclusive, and with a serial number in the 

range of S/Ns 1001 through 1114 inclusive 

(the serial number can start with ‘‘MA,’’ 

‘‘MAL,’’ or ‘‘MA-’’). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(k) Inspections, corrective actions, 

replacements, and rework accomplished 

before the effective date of this AD in 

accordance with Bombardier Service Bulletin 

670BA–32–019, dated March 16, 2006, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

(l) The inspections specified in paragraph 

(h) of this AD are not required if the actions 

specified in paragraph (i) of this AD have 

already been accomplished; or if Bombardier 

Repair Engineering Order 670–32–11–0022, 

dated October 22, 2005, or Goodrich Service 

Concession Request SCR 0056–05, dated 

October 22, 2005; has been incorporated. 

FAA AD Differences 

Note 1: The MCAI specifies to inspect only 

airplanes having certain serial numbers that 

are part of the MCAI applicability. Because 

the affected part could be rotated onto any of 

the airplanes listed in the applicability, this 

AD requires that the inspection be done on 

all airplanes. We have coordinated this with 

the Transport Canada Civil Aviation (TCCA). 

Other FAA AD Provisions 

(m) 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, 

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 FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Special Flight Permits 

(n) 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 

(o) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–20, dated May 1, 2009; 

and Bombardier Service Bulletin 670BA–32– 

019, Revision A, dated September 18, 2008; 

for related information. 

Material Incorporated by Reference 

(p) You must use Bombardier Service 

Bulletin 670BA–32–019, Revision A, dated 

September 18, 2008, 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 CoteVertu Road West, Dorval, Quebec H4S 1Y9, 

Canada; phone: 514–855–5000; fax: 514–855– 

7401; e-mail: thd.crj@aero.bombardier.com; 

Internet: http://www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

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

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

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

23, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8196 Filed 4–12–11; 8:45 am] 

BILLING CODE 4910–13–P 


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