65810 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 

panel, which manufacturer fatigue and 

damage tolerance analyses demonstrated 

could have an effect on panel fatigue life. We 

are issuing this AD to detect and correct such 

cracking, which could result in the loss of 

structural integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspection 

Before the accumulation of 35,900 total 

flight cycles or 88,100 total flight hours, 

whichever occurs first: Do a high frequency 

eddy current inspection for cracking of the 

two rows of six fasteners at frame 35 between 

stringers 5 and 6 on the left and right sides, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1244, excluding Appendix 1, dated 

March 17, 2011. Repeat the inspection 

thereafter at intervals not to exceed 28,100 

flight cycles or 56,300 flight hours, 

whichever occurs first. 

(h) Corrective Action 

If any crack is detected during any 

inspection required by paragraph (g) of this 

AD: Before further flight, repair the crack 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) or 

its delegated agent. 

(i) Other FAA AD Provisions 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed 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 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. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0176, dated September 13, 

2011; and Airbus Service Bulletin A320–53– 

1244, excluding Appendix 1, dated March 

17, 2011; for related information. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1244, 

excluding Appendix 1, dated March 17, 

2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@airbus.

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

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

16, 2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26198 Filed 10–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0592; Directorate 

Identifier 2011–NM–253–AD; Amendment 

39–17230 AD 2012–21–14] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Bombardier, Inc. Model CL–600– 

2B19 (Regional Jet Series 100 & 440) 

airplanes. That AD currently requires a 

one-time inspection of the shafts of the 

main landing gear (MLG) side-brace 

fittings to detect corrosion, and the 

forward and aft bushings in the lefthand and right-hand MLG side-brace 

fittings to detect discrepancies. The 

existing AD also requires corrective and 

related actions if necessary. This new 

AD requires repetitive detailed 

inspections for corrosion and damage of 

the MLG side-brace fitting, and 

replacing the side-brace fitting shaft 

with the re-designed side-brace fitting 

shaft of the MLG if necessary. This AD 

also requires eventual replacement of 

certain side-brace fitting shafts with the 

re-designed part. Replacement with a redesigned side-brace fitting shaft of the 

MLG is terminating action for the 

repetitive inspections. This AD was 

prompted by reports of failure of the 

side-brace fitting shaft of the main 

landing gear (MLG) due to corrosion. 

We are issuing this AD to prevent 

fractures of the side-brace fitting shafts 

of the MLG, and possible collapse of the 

MLG. 

DATES: This AD becomes effective 

December 5, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 5, 2012. 

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: 

Jeffrey Zimmer, 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– 

7306; 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 12, 2012 (77 FR 34870), 

and proposed to supersede AD 2004– 

22–23, Amendment 39–13851 (69 FR 

64856, November 9, 2004). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Due to the failure of the main landing gear 

(MLG) side brace fitting shaft, caused by 

corrosion, [Transport Canada Civil Aviation 

(TCCA)] Airworthiness Directive (AD) CF– 

2002–41 was issued to require inspection and 

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Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 65811 

if needed, parts replacement. However, the 

existing MLG side-brace fitting shafts 

continued to fail. Failure of the MLG side 

brace fitting shaft could result in the collapse 

of the main landing gear. 

This [TCCA] directive mandates the 

repetitive detailed visual inspection [for 

cracking and corrosion] of the MLG side 

brace fitting and the incorporation of the redesigned MLG side brace fitting shaft part 

number (P/N) 601R10247–3 as the 

terminating action. 

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. 

Request to Reference Revised Service 

Bulletin 

Comair, Inc. requested that we allow 

the use of Bombardier Service Bulletin 

601R–57–052, Revision A, dated 

October 28, 2011, in the AD. Comair, 

Inc. provided no reasons for the request. 

We agree to reference the most recent 

service information. Bombardier, Inc. 

has issued Service Bulletin 601R–57– 

052, Revision A, dated October 28, 

2011. This service bulletin includes 

editorial changes, but does not add work 

for airplanes that have done the actions 

using Bombardier Service Bulletin 

601R–57–052, dated July 28, 2011 

(which was referenced to as the 

appropriate source of service 

information in the NPRM (77 FR 34870, 

June 12, 2012). Therefore we have 

revised paragraphs (g)(1), (g)(2), (h)(1), 

and (h)(2) of this AD to refer to 

Bombardier Service Bulletin 601R–57– 

052, Revision A, dated October 28, 

2011. We have also added paragraph (i) 

to this AD to allow credit for actions 

performed before the effective date of 

this AD using Bombardier Service 

Bulletin 601R–57–052, dated July 28, 

2011. We have re-designated subsequent 

paragraphs accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and except for minor editorial changes. 

We have determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

34870, June 12, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 34870, 

June 12, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 584 products of U.S. registry. 

We estimate that it will take about 10 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about $0 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$496,400, or $850 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 14 work-hours and require parts 

costing $3,860, for a cost of $5,050 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 that 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); 

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. 

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 (77 FR 34870, June 

12, 2012), 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 airworthiness directive (AD) 

2004–22–23, Amendment 39–13851 (69 

FR 64856, November 9, 2004), and 

adding the following new AD: 

2012–21–14 Bombardier, Inc.: Amendment 

39–17230. Docket No. FAA–2012–0592; 

Directorate Identifier 2011–NM–253–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 5, 2012. 

(b) Affected ADs 

This AD supersedes AD 2004–22–23, 

Amendment 39–13851 (69 FR 64856, 

November 9, 2004). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes; certificated in any category; serial 

numbers 7003 through 7990 inclusive, and 

8000 through 8999 inclusive. 

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65812 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of failure 

of the side-brace fitting shaft of the main 

landing gear (MLG) due to corrosion. We are 

issuing this AD to prevent fractures of the 

side-brace fitting shafts of the MLG, and 

possible collapse of the MLG. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection of MLG Side-Brace Fitting 

Shaft and Replacement 

(1) At the applicable times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), and 

(g)(1)(iv) of this AD, do a detailed inspection 

for corrosion and damage of each side-brace 

fitting shaft of the MLG, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–57–052, 

Revision A, dated October 28, 2011. Repeat 

the inspections at the applicable times 

specified in paragraphs (g)(1)(i), (g)(1)(ii), 

(g)(1)(iii), and (g)(1)(iv) of this AD. 

(i) For airplanes that average greater than 

900 flight hours per year and have side-brace 

shafts part number (P/N) 601R10237–1 

installed in either the left- or right-hand 

MLG, or if the side-brace shaft part number 

cannot be identified without removal: Within 

1,000 flight hours after the effective date of 

this AD, do the inspection. Repeat the 

inspections thereafter at intervals not to 

exceed 1,000 flight hours until the 

replacement specified in paragraph (g)(2) or 

(h) of this AD is done. 

(ii) For airplanes that average 900 flight 

hours or less per year and have side-brace 

shafts P/N 601R10237–1 installed on either 

the left- or right-hand MLG, or if the sidebrace shaft part number cannot be identified 

without removal: Within 18 months after the 

effective date of this AD, do the inspection. 

Repeat the inspections thereafter at intervals 

not to exceed 18 months until the 

replacement specified in paragraph (g)(2) or 

(h) of this AD is done. 

(iii) For airplanes that average greater than 

900 flight hours per year and have side-brace 

shafts P/N 601R10237–3 installed on either 

the left- or right-hand MLG: Within 36 

months after the effective date of this AD, do 

the inspection. Repeat the inspections 

thereafter at intervals not to exceed 36 

months until the replacement specified in 

paragraph (g)(2) or (h) of this AD is done. 

(iv) For airplanes that average 900 flight 

hours or less per year and have side-brace 

shafts P/N 601R10237–3 installed on either 

the left- or right-hand MLG: Within 60 

months after the effective date of this AD, do 

the inspection. Repeat the inspections 

thereafter at intervals not to exceed 60 

months until the replacement specified in 

paragraph (g)(2) or (h) of this AD is done. 

(2) If any corrosion or damage is found 

during any inspection required by paragraph 

(g) of this AD: Before further flight, replace 

the side-brace fitting shaft with a new shaft 

P/N 601R10247–3, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–57–052, Revision A, 

dated October 28, 2011. Doing this 

replacement terminates the inspection 

requirements of paragraph (g) of this AD. 

(h) Replacement 

Do the replacement at the applicable time 

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

AD. 

(1) For any airplanes that have side-brace 

shafts P/N 601R10237–1 installed, or if the 

side-brace shaft part number cannot be 

identified without removal: Within 27 

months after the effective date of this AD, 

replace the side-brace fitting shaft of the MLG 

with a new shaft having P/N 601R10247–3, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–57–052, Revision A, dated October 28, 

2011. Doing this replacement terminates the 

inspection requirements of paragraph (g) of 

this AD. 

(2) For airplanes that have side-brace shafts 

P/N 601R10237–3 installed: Within 117 

months after the effective date of this AD, 

replace the side-brace fitting shaft of the MLG 

with a new shaft P/N 601R10247–3, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–57–052, Revision A, dated October 28, 

2011. Doing this replacement terminates the 

inspection requirements of paragraph (g) of 

this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Bombardier Service Bulletin 601R–57–052, 

dated July 28, 2011 (which is not 

incorporated by reference in this AD). 

(j) Other FAA AD Provisions 

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. 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 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. 

(k) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–39, dated October 25, 

2011; and Bombardier Service Bulletin 601R– 

57–052, dated July 28, 2011; for related 

information. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 601R–57– 

052, Revision A, dated October 28, 2011. 

(ii) Reserved. 

(3) 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; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

14, 2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26088 Filed 10–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0719; Directorate 

Identifier 2011–NM–240–AD; Amendment 

39–17235; AD 2012–21–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 freighter series 

airplanes; Model A330–200 and –300 

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