68306 Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 / Rules and Regulations 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Several occurrences of cracked central and 

lateral spreaders on passenger seats models 

9401 and 9402 * * *. 

This condition, if not corrected, can lead 

to further cracking of the seat spreaders, 

causing injury to passengers or crew 

members during heavy turbulence in flight or 

in the event of an emergency landing. 

* * * * * 

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. 

Repetitive Inspections, Repair, and 

Replacement 

(g) Within 6 months after the effective date 

of this AD, perform a detailed inspection for 

cracking of the central and lateral spreaders 

of the affected seats, in accordance with 

paragraph 2/A1., ‘‘Checking procedures of 

lateral and central spreaders,’’ of the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 94–25–013, Issue 4, 

dated February 12, 2008. 

(1) If no cracking is found on any central 

spreader, repeat the detailed inspection 

thereafter at intervals not to exceed 550 flight 

hours until the replacement specified in 

paragraph (h) of this AD is done. 

(2) If no cracking or only cracks that are 

shorter than 8 millimeters (mm) (0.315 inch) 

are found on any lateral spreader, repeat the 

detailed inspection thereafter at intervals not 

to exceed 550 flight hours until the 

replacement specified in paragraph (h) of this 

AD is done. 

(3) If all cracks found on any central 

spreader are shorter than 8 mm (0.315 inch), 

before further flight, repair the affected 

spreader, in accordance with paragraphs 2/A 

through C2. of the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 94–25–011, Revision 3, dated June 

30, 2008. Within 550 flight hours after doing 

the repair, do the detailed inspection 

specified in paragraph (g) of this AD, and 

repeat the inspection thereafter at intervals 

not to exceed 550 flight hours until the 

replacement specified in paragraph (h) of this 

AD is done. 

(4) If one or more cracks are found that are 

8 mm (0.315 inch) or longer on any lateral 

or central spreader, before further flight, 

replace the affected spreader, in accordance 

with paragraphs 2/A through D2. of the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 94–25–012, Revision 1, 

dated June 26, 2008. 

Optional Terminating Action 

(h) Replacing all central and lateral 

spreaders on an affected seat assembly 

(modify to ‘‘Amendment B’’ standard), in 

accordance with paragraphs 2/A through D2. 

of the Accomplishment Instructions of Sicma 

Aero Seat Service Bulletin 94–25–012, 

Revision 1, dated June 26, 2008, terminates 

the inspections required by this AD for that 

seat assembly. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Actions done before the effective date of 

this AD in accordance with Sicma Aero Seat 

Service Bulletin 94–25–011, Issue 2, dated 

November 6, 2007; and Sicma Aero Seat 

Service Bulletin 94–25–012, dated September 

25, 2007; are acceptable for compliance with 

the corresponding actions of this AD. 

Parts Installation 

(j) As of 6 months after the effective date 

of this AD, no person may install any 

passenger seat assembly identified in 

paragraph (c) of this AD, on any airplane, 

unless it has been modified to ‘‘Amendment 

B’’ standard in accordance with the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 94–25–012, Revision 1, 

dated June 26, 2008. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Boston Aircraft 

Certification Office, 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: Jeffrey Lee, 

Aerospace Engineer, Boston Aircraft 

Certification Office, FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 238– 

7161; fax (781) 238–7170; email; 

jeffrey.lee@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. 

Related Information 

(l) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency AD 2008–0097, dated 

May 20, 2008; Sicma Aero Seat Service 

Bulletin 94–25–011, Revision 3, dated June 

30, 2008; Sicma Aero Seat Service Bulletin 

94–25–012, Revision 1, dated June 26, 2008; 

and Sicma Aero Seat Service Bulletin 94–25– 

013, Issue 4, dated February 12, 2008; for 

related information. 

(m) Contact Jeffrey Lee, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7161; fax (781) 

238–7170; email; jeffrey.lee@faa.gov, for 

more information about this AD. 

Material Incorporated by Reference 

(n) You must use Sicma Aero Seat Service 

Bulletin 94–25–011, Revision 3, dated June 

30, 2008; Sicma Aero Seat Service Bulletin 

94–25–012, Revision 1, dated June 26, 2008; 

and Sicma Aero Seat Service Bulletin 94–25– 

013, Issue 4, dated February 12, 2008; 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 Sicma Aero Seat, 7 Rue 

Lucien Coupet, 36100 ISSOUDUN, France, 

telephone: +33 (0) 2 54 03 39 39; fax: +33 (0) 

2 54 03 39 00; email Customerservices.sas 

@zodiacaerospace.com; Internet http:// 

www.sicma.zodiacaerospace.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 October 

20, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–28357 Filed 11–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0031; Directorate 

Identifier 2010–NM–135–AD; Amendment 

39–16860; AD 2011–23–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 


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and CL–600–2D24 (Regional Jet Series 

900) airplanes. 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 two reported cases of 

failure of the MLG [main landing gear] piston 

axle, P/N [part number] 49203–3 or 49203– 

5, resulting from fretting between the inboard 

axle sleeve and axle thrust face, damage to 

the protective coating and consequent stress 

corrosion. In both cases, the MLG did not 

collapse. 

* * * * * 

The unsafe condition is failure of the 

MLG, which could adversely affect the 

airplane’s safe landing. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

December 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 9, 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: 

Andreas Rambalakos, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office (ACO), 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7345; 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 January 25, 2011 (76 FR 

4264). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been two reported cases of 

failure of the MLG [main landing gear] piston 

axle, P/N [part number] 49203–3 or 49203– 

5, resulting from fretting between the inboard 

axle sleeve and axle thrust face, damage to 

the protective coating and consequent stress 

corrosion. In both cases, the MLG did not 

collapse. 

In order to avoid future axle failures, 

which could potentially result in gear 

collapse and collateral damage, this 

[Canadian] directive mandates repetitive 

visual inspection [for damage and corrosion 

of the protective coating] and repair, as 

necessary, of the MLG piston axles, P/N 

49203–3 and 49203–5. 

The unsafe condition is failure of the 

MLG, which could adversely affect the 

airplane’s safe landing. 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 comments received. 

Request To Include Additional Piston 

Axle Part Numbers 

Comair, Inc. (Comair) requested that 

we revise paragraph (g) of the NPRM (76 

FR 4264, January 25, 2011) to include 

MLG piston axles having P/Ns 49263–1 

and 49263–3. Comair explained that it 

has been in contact with Goodrich 

regarding these part numbers. Comair 

expressed that Goodrich’s response 

supports what Comair surmised from 

the Goodrich component maintenance 

manual (CMM) for P/N 49000, which 

was that P/Ns 49263–1 and 49263–3 are 

a next higher assembly (NHA) part 

number consisting of a piston axle with 

a metering pin assembly installed. 

Comair stated that the Goodrich CMM 

for P/N 49000 uses the following 

nomenclature, ‘‘Piston/Axle/Metering 

Pin Assy (Pre SB 32–45).’’ 

Comair also explained that there have 

been several instances where Comair 

has sent Goodrich Landing Gear 

Services a piston/axle having P/N 

49203–3 for repair. Comair stated that 

while the piston/axle was at Goodrich, 

a metering pin was installed. 

Comair expressed that when the 

piston/axle was returned, the authorized 

release certificate (Form One) only 

contained P/N 49263–1, and that Form 

One does not list the part number for 

the piston/axle and metering pin, only 

the higher assembly part number. 

Comair further explained that when 

they received the piston/axle back into 

stock, the part number had changed 

from 49203–3 to 49263–1, during the 

receiving process. Comair stated that, 

consequently, when the piston/axle is 

installed on the airplane, it shows that 

P/N 49263–1 is installed; therefore, as 

the NPRM is written, Comair asserted 

that the NPRM would not apply by part 

number. Comair suggested that if P/Ns 

49203–3 and 49203–5 exhibit an unsafe 

condition, then P/Ns 49263–1 and 

49263–3 should be considered to have 

the same fretting concern and the same 

unsafe condition. 

We agree, for clarification, to include 

MLG piston axles having P/Ns 49263–1 

and 49263–3, in a note in the final rule. 

It has also come to our attention that 

several operators failed to do the 

inspection because the MLG rework 

paperwork (Form One) from Goodrich 

only annotated piston/axle/metering pin 

assembly NHA having P/N 49263–1 or 

49263–3, while the NPRM only 

proposed to require inspection for MLG 

piston axles having P/N 49203–3 or 

49203–5. While neither this AD nor 

Canadian AD CF–2010–15, dated May 

13, 2010, require inspection for MLG 

piston axles having P/N 49263–1 or 

49263–3, we want to avoid the 

possibility of an operator overlooking 

the intent of this final rule simply 

because the operator’s overhaul 

paperwork is the only document that 

references the NHA part number. This 

change has been coordinated with 

Transport Canada Civil Aviation. We 

have revised this final rule to include 

new Note 2 to inform operators that 

MLG piston axles having P/N 49203–3 

or 49203–5 that are installed on the 

airplane could be identified as having 

P/N 49263–1 or 49263–3. We have reidentified subsequent notes accordingly. 

Request To Extend the Proposed 

Compliance Time 

Mesa Airlines (Mesa) requested that 

we revise the NPRM (76 FR 4264, 

January 25, 2011) to extend the 

proposed compliance time of 12 months 

for the initial inspection specified in 

paragraph (h)(1) of the NPRM to 24 

months. Mesa explained that its request 

is due to the number of applicable 

components, the size of its fleet, repair 

vendor capacity, and the turn time for 

the piston axle if needed. 

We disagree to extend the compliance 

time specified in paragraph (h)(1) of the 

final rule. In developing an appropriate 

compliance time for this action, we 

considered the urgency associated with 

the subject unsafe condition, the 

availability of required parts, and the 

practical aspect of accomplishing the 

required inspection within a period of 

time that corresponds to the normal 

scheduled maintenance for most 

affected operators. According to the 

manufacturer, an ample number of 

required parts will be available to 

modify the airplanes identified in the 

Applicability section of this final rule 

within the compliance time. In 

consideration of these items, we have 

determined that a 12-month compliance 

time for the initial inspection in 

paragraph (h)(1) of this final rule is 

appropriate. However, under the 

provisions of paragraph (l) of the final 

rule, we will consider requests for 

approval of an extension of the 

compliance time if sufficient data are 

submitted to substantiate that the new 

compliance time would provide an 


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acceptable level of safety. We have not 

changed the final rule in this regard. 

Request To Add a Compliance Time for 

Proposed Terminating Action 

In its request to extend the proposed 

compliance time for the initial 

inspection, Mesa added the following 

statement, ‘‘6,000 hrs. to terminate.’’ 

Mesa did not provide any explanation 

for this request. 

From this statement, we infer that 

Mesa requested that we include a 

compliance time of 6,000 flight hours 

after the initial inspection for the 

terminating action required by 

paragraph (j) of the final rule. We 

disagree with adding a compliance time 

to paragraph (j) of the final rule. Mesa 

has not provided any justification for 

this request. Further, including an 

additional compliance time would 

necessitate additional rulemaking, and 

we do not consider that delaying this 

action until that time is warranted, since 

the actions required by this AD are 

adequate to ensure continued safety of 

the affected fleet. We have not changed 

the final rule in this regard. 

Request To Add a Provision for Piston 

Axles That Require Overhaul 

Mesa also requested that we revise the 

NPRM (76 FR 4264, January 25, 2011) to 

add a paragraph to paragraph (h) of the 

NPRM to allow for a provision for MLG 

piston axles which are scheduled for 

overhaul. Mesa suggested the following 

wording: ‘‘(4) For any piston axle that 

has been in service more than 48 

months, of the effective date of this AD 

and is due to be overhauled within 36 

months of the effective date of this AD, 

must be complied with at schedule 

overhaul.’’ 

We disagree to include a provision for 

MLG axles which are scheduled for 

overhaul. Mesa has not provided any 

technical justification for this request. 

However, affected operators may request 

to allow for a provision for MLG piston 

axles which are scheduled for overhaul, 

under the provisions of paragraph (l) of 

this final rule by submitting data, 

substantiating that the change would 

provide an acceptable level of safety. 

We have not changed the final rule in 

this regard. 

Request To Clarify Paragraph (i) of the 

NPRM (76 FR 4264, January 25, 2011) 

Mesa also requested that we clarify 

paragraph (i) of the NPRM (76 FR 4264, 

January 25, 2011). Mesa has not 

specified what aspect of the requirement 

it wants clarified, nor has it provided 

any reason for this request. 

We agree to clarify paragraph (i) in 

this comment section of this final rule. 

Paragraph (i) of this final rule states the 

compliance time for doing the 

inspections specified in paragraph (h) of 

this AD for airplanes that have the mark 

‘‘32–45’’ in the MOD STATUS field on 

the piston axle nameplate, or for 

airplanes that have done one of the 

repair engineering orders listed in the 

service information in paragraph (i) of 

this AD; within the compliance times 

required in paragraph (i) of this AD, 

these airplanes do the inspection and 

repeat the inspection as required by 

paragraph (h) of this AD. We have also 

added paragraphs (i)(1), (i)(2), and (i)(3) 

to the final rule to clarify the 

compliance times for paragraph (i). 

Clarification 

We have revised paragraph (g) of this 

final rule to clarify that the compliance 

times for doing the inspection required 

by paragraph (g) of this final rule are the 

same as the applicable compliance 

times specified in paragraphs (h) and (i) 

of this final rule. 

We have also added Note 3 to this 

final rule to clarify that 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 the 

inspection be done on all airplanes. 

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 

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 

380 products of U.S. registry. We also 

estimate that it will take about 22 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 this AD to the U.S. operators to 

be $710,600, or $1,870 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 (76 FR 4264, 

January 25, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 


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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: 

2011–23–09 Bombardier, Inc.: Amendment 

39–16860. Docket No. FAA–2011–0031; 

Directorate Identifier 2010–NM–135–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Bombardier, Inc. 

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

701 & 702), CL–600–2D15 (Regional Jet Series 

705), and CL–600–2D24 (Regional Jet Series 

900) airplanes; certificated in any category. 

Note 1: This AD is not applicable to piston 

axles having part number (P/N) 49203–7 or 

P/N 49203–9, which were installed in 

production on Bombardier, Inc. Model CL– 

600–2C10 airplanes having serial numbers 

(S/Ns) 10266 and subsequent; and Models 

CL–600–2D15 and CL–600–2D24 airplanes 

having S/Ns 15155 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 two reported cases of 

failure of the MLG [main landing gear] piston 

axle, P/N 49203–3 or 49203–5, resulting from 

fretting between the inboard axle sleeve and 

axle thrust face, damage to the protective 

coating and consequent stress corrosion. In 

both cases, the MLG did not collapse. 

* * * * * 

The unsafe condition is failure of the MLG, 

which could adversely affect the airplane’s 

safe landing. 

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 Repair 

(g) At the applicable time in paragraph 

(h)(1), (h)(2), (h)(3) or (i) of this AD, inspect 

to determine whether the airplane has a main 

landing gear piston axle having P/N 49203– 

3 or 49203–5. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the main 

landing gear piston axle can be conclusively 

determined from that review. 

Note 2: Operators should be aware that the 

Goodrich authorized release certificate (Form 

One) provided for MLG piston axles 

following overhaul, refers to only the higher 

assembly P/N 49263–1 or 49263–3; therefore, 

it is possible that MLG piston axles having 

P/N 49203–3 or 49203–5 that are installed on 

the airplane could be identified as having P/ 

N 49263–1 or 49263–3. 

(h) Except as required by paragraph (i) of 

this AD, if, during the inspection required by 

paragraph (g) of this AD, the landing gear 

piston axle is determined to have P/N 49203– 

3 or 49203–5: At the applicable time 

specified in paragraph (h)(1), (h)(2), or (h)(3) 

of this AD, do a detailed inspection for 

corrosion and damage of the inboard and 

outboard piston axles, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–023, Revision C, 

dated January 29, 2009. Before further flight, 

repair any corrosion or damage found, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–023, Revision C, dated January 

29, 2009. Within 30 months after the initial 

inspection, or within 12 months after the 

effective date of this AD, whichever occurs 

later, do the inspection specified in this 

paragraph; and repeat the inspection 

thereafter at intervals not to exceed 30 

months. 

(1) For any piston axle that has been in 

service for 48 months or more as of the 

effective date of this AD: Inspect within 12 

months after the effective date of this AD. 

(2) For any piston axle that has been in 

service for 24 months or more, but less than 

48 months, as of the effective date of this AD: 

Inspect within 24 months after the effective 

date of this AD. 

(3) For any piston axle that has been in 

service for less than 24 months as of the 

effective date of this AD: Inspect within 36 

months after the effective date of this AD. 

(i) For airplanes that have mark ‘‘32–45’’ in 

the MOD STATUS field of the piston axle 

nameplate or that have incorporated one of 

the Bombardier repair engineering orders 

listed in paragraph 1.D. of Bombardier 

Service Bulletin 670BA–32–023, Revision C, 

dated January 29, 2009: At the latest of the 

applicable times specified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD, do the 

inspection specified in paragraph (h) of this 

AD and repeat the inspection thereafter at the 

time specified in paragraph (h) of this AD: 

(1) Within 30 months after marking ‘‘32– 

45’’ in the MOD STATUS field of the piston 

axle nameplate. 

(2) Within 30 months after incorporating 

one of the Bombardier repair engineering 

orders listed in paragraph 1.D. of Bombardier 

Service Bulletin 670BA–32–023, Revision C, 

dated January 29, 2009. 

(3) Within 12 months after the effective 

date of this AD. 

Terminating Action 

(j) Installing a piston axle having P/N 

49203–7 or P/N 49203–9 on any airplane 

constitutes a terminating action for the 

requirements of paragraphs (h), (h)(1), (h)(2), 

and (h)(3) of this AD, for that airplane. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(k) Inspections and repairs accomplished 

before the effective date of this AD according 

to any service bulletin specified in table 1 of 

this AD, are considered acceptable for 

compliance with the corresponding 

inspections and repairs specified in 

paragraph (h) of this AD. 

TABLE 1—CREDIT FOR ACCOMPLISHMENT OF PREVIOUS SERVICE INFORMATION

Document Revision Date 

Bombardier Service Bulletin 670BA–32–023 ............................................................................... Original ........................ October 24, 2007. 

Bombardier Service Bulletin 670BA–32–023 ............................................................................... A .................................. January 7, 2008. 

Bombardier Service Bulletin 670BA–32–023 ............................................................................... B .................................. March 5, 2008. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 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 the inspection be done on all 

airplanes. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 


jlentini on DSK4TPTVN1PROD with RULES
68310 Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 / Rules and Regulations 

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. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–15, dated May 13, 2010; 

and Bombardier Service Bulletin 670BA–32– 

023, Revision C, dated January 29, 2009; for 

related information. 

Material Incorporated by Reference 

(n) You must use Bombardier Service 

Bulletin 670BA–32–023, Revision C, dated 

January 29, 2009, including Appendix A, 

Revision B, dated March 5, 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 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. 

(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 October 

21, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–28360 Filed 11–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 902 

50 CFR Part 622 

[Docket No. 110620342–1659–03] 

RIN 0648–BB55 

Fisheries of the Caribbean, Gulf of 

Mexico, and South Atlantic; SnapperGrouper Fishery Off the Southern 

Atlantic States; Amendment 15B 

AGENCY: National Marine Fisheries 

Service (NMFS), National Oceanic and 

Atmospheric Administration (NOAA), 

Commerce. 

ACTION: Final rule; effectiveness of 

collection-of-information requirements. 

SUMMARY: NMFS announces approval by 

the Office of Management and Budget 

(OMB) of collection-of-information 

requirements contained in regulations 

implementing Amendment 15B to the 

Fishery Management Plan for the 

Snapper-Grouper Fishery of the South 

Atlantic Region (FMP). This rule makes 

effective the collection-of-information 

requirements published on November 

16, 2009, and identified below. 

DATES: The amendments to 15 CFR 

902.1 in this rule are effective December 

5, 2011. Amendments to 

§§ 622.5(a)(1)(iv), (b)(1), and (b)(2); 

§ 622.8(a)(6); and § 622.18(b)(1)(ii) 

published at 74 FR 58902 (November 

16, 2009) are effective December 5, 

2011. 

ADDRESSES: Written comments 

regarding the burden-hour estimates or 

other aspects of the collection-ofinformation requirements contained in 

this final rule may be submitted to Rich 

Malinowski, Southeast Regional Office, 

NMFS, 263 13th Ave South, St. 

Petersburg, FL 33701; and OMB, by 

email at OIRASubmission@omb.eop.gov, 

or fax to (202) 395–7285. 

FOR FURTHER INFORMATION CONTACT: Kate 

Michie, telephone: (727) 824–5305. 

SUPPLEMENTARY INFORMATION: On 

November 16, 2009 (74 FR 58902), 

NMFS published a final rule to 

implement Amendment 15B to the FMP. 

That final rule contained collection-ofinformation requirements subject to the 

Paperwork Reduction Act (PRA) that 

were pending OMB approval at the time 

of publication. The rule delayed the 

effectiveness of those provisions of the 

rule with public reporting requirements 

until NMFS published OMB’s approval 

of the collections. OMB approved these 

collection-of-information requirements 

on January 4, 2010 and January 27, 

2010, under OMB control number 0648– 

0603 (South Atlantic snapper-grouper 

reporting requirements), and on April 

12, 2011, under OMB control number 

0648–0593 (South Atlantic snappergrouper observer coverage 

requirements). Accordingly, this final 

rule makes effective the collection-ofinformation requirements at 

§ 622.5(a)(1)(iv), (b)(1), and (b)(2); 

§ 622.8(a)(6); and § 622.18(b)(1)(ii) on 

December 5, 2011. The collection-ofinformation requirement at § 622.5(g), 

which includes reporting requirements 

for the South Atlantic snapper-grouper 

recreational sector, will not be 

submitted for approval until further 

information on burden hour estimates 

can be obtained from the fishery. 

Classification 

This final rule has been determined to 

be not significant for purposes of 

Executive Order 12866. 

This final rule contains collection-ofinformation requirements subject to the 

PRA which have been approved under 

OMB control numbers 0648–0603 and 

0648–0593. The public reporting 

burdens for these collections of 

information are estimated to average: (1) 

4 minutes for each notification of a 

vessel trip, (2) 20 minutes for each 

vessel and gear characterization form, 

(3) 31 minutes for each electronic 

logbook installation and data download, 

(4) 8 hours for each video monitor 

installation and data download, and (5) 

20 minutes for each change of 

ownership. These estimates of the 

public reporting burdens include the 

time for reviewing instructions, 

searching existing data sources, 

gathering and maintaining the data 

needed, and completing and reviewing 

the collections of information. Send 

comments regarding the burden 

estimates or any other aspect of the 

collection-of-information requirements, 

including suggestions for reducing the 

burden, to NMFS and to OMB (see 

ADDRESSES). 

Notwithstanding any other provision 

of the law, no person is required to 

respond to, and no person shall be 

subject to penalty for failure to comply 

with, a collection of information subject 

to the requirements of the PRA, unless 

that collection of information displays a 

currently valid OMB control number. 

List of Subjects in 15 CFR Part 902 

Reporting and recordkeeping 

requirements. 


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