Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 7647 

area depicted in Figure 2 of the ASB by 

following the Accomplishment Instructions, 

Part I, ‘‘Cleaning and Preparation,’’ 

paragraphs 1. through 5., of the ASB. 

(iii) Perform an FPI of each crosstube and 

upper center support, P/N 412–050–006–101, 

for a crack, any corrosion, a nick, scratch, 

dent, or any other damage by following the 

Accomplishment Instructions, Part I, 

‘‘Inspection,’’ paragraphs 1. through 3. of the 

ASB. Use Table 2 in the ASB to determine 

the appropriate Inspection Criteria Table to 

use in the maintenance manual, which list 

the maximum repair damage limits for each 

crosstube P/N applicable to this AD. 

(iv) Repair the crosstube or upper center 

support if there is any corrosion, a nick, 

scratch, dent, or any other damage that is 

within the maximum repair damage limits, 

before further flight, or replace the crosstube 

with an airworthy crosstube. 

Note 2 to paragraph (e)(3)(iv) of this AD: 

The repair procedures are specified in the 

Component Repair and Overhaul Manual. 

(v) If there is a crack or other damage 

beyond any of the maximum repair damage 

limits, before further flight, replace the 

crosstube with an airworthy crosstube. 

(4) Before further flight, after completing 

paragraph (e)(3) of this AD, rework each 

crosstube P/N 412–050–011–101, –103, –105, 

or –107 by applying the bonding procedures 

and abrasion strips on the under side of the 

crosstubes at BL 0.0 and BL 14 by following 

the Accomplishment Instructions, Part I, 

‘‘Rework of Crosstubes,’’ paragraphs 1. 

through 10. of the ASB. Record on the 

component history card or equivalent record 

an ‘‘FM’’ to the end of the part number 

sequence of each crosstube that has been 

reworked (for example, 412–050–011– 

107FM). Omit the Larson L101 abrasion strip 

at BL 0.0 on each crosstube when installing 

lower center support, P/N 604–026–003 (see 

item 6 in Figure 1 of the ASB). 

(f) Special Flight Permits 

Special flight permits for inspections only 

may be issued under 14 CFR 21.197 and 

21.199 to operate the helicopter to a location 

where the requirements of this AD can be 

accomplished. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5170; 

email 7-avs-asw-170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3210, Main Landing Gear. 

(i) 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) Bell Helicopter Alert Service Bulletin 

No. 412–09–135, dated August 25, 2009. 

(ii) Reserved. 

(3) For Bell Helicopter service information 

identified in this AD, contact Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

Texas 76101; telephone (817) 280–3391; fax 

(817) 280–6466; or at http:// 

www.bellcustomer.com/files/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on January 9, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02238 Filed 2–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0639; Directorate 

Identifier 2012–NM–005–AD; Amendment 

39–17329; AD 2013–02–08] 

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 all 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by a 

report that the safe life limit and 

inspection requirements for the 

horizontal stabilizer trim actuator 

(HSTA) attachment pins and trunnions 

were not listed in the Airworthiness 

Limitations Section of the maintenance 

program. This AD requires inspecting 

the trunnions and upper and lower pins 

for gouges, scratches, and corrosion, and 

replacing the trunnions if necessary; 

and adding serial numbers and new part 

numbers to certain trunnions, and upper 

and lower pins. This AD also requires 

revising the maintenance program to 

incorporate the information specified in 

certain temporary revisions of the 

limitations section. We are issuing this 

AD to detect and correct cracking, 

gouges, scratches, and corrosion of the 

HSTA attachment pins and trunnions, 

which could result in failure of these 

pins and trunnions and consequent 

disconnection of the horizontal 

stabilizer and subsequent loss of 

controllability of the airplane. 

DATES: This AD becomes effective 

March 11, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 11, 2013. 

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: 

Cesar Gomez, 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– 

7318; 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 20, 2012 (77 FR 36948). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

During a review of the Horizontal 

Stabilizer Trim Actuator (HSTA) system, it 

was discovered that the safe life limits and 

the inspection requirements for the HSTA 

attachment pins and trunnions were not 

listed in the Airworthiness Limitations 

Section of the Instructions for Continued 

Airworthiness. Also, the HSTA attachment 

pins and trunnions were not serialized 

making it impossible to keep accurate records 

of the life of these parts. Failure of these pins 

and trunnions will lead to a disconnect of the 

horizontal stabilizer and subsequent loss of 

the aeroplane. 

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7648 Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 

This [Canadian] Airworthiness Directive 

(AD) mandates the serialization of the HSTA 

attachment pins and trunnions. 

The required actions include a detailed 

inspection of the trunnions and upper 

and lower pins for gouges, scratches, 

and corrosion, and replacing if 

necessary; and adding serial numbers 

and new part numbers to certain 

trunnions, and upper and lower pins. 

The required actions also include 

revising the maintenance program to 

incorporate the information specified in 

certain temporary revisions of the 

limitations section. 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 Allow Alternative Method 

of Identifying Parts 

Air Wisconsin Airlines Corporation 

(Air Wisconsin) requested that we allow 

the use of indelible ink and clear coat 

to mark the identified HSTA. The 

commenter stated that the tolerances 

identified in Bombardier Service 

Bulletin 601R–27–160, dated September 

29, 2011, are too strict to hand vibropeen these individual parts. The 

commenter also noted that Bombardier, 

Inc. is working on a revision to that 

service bulletin to authorize marking all 

of these parts with indelible ink and 

clear coat. 

We agree that an alternative method 

of marking the HSTA would be 

beneficial to operators. Since the 

issuance of the NPRM (77 FR 36948, 

June 20, 2012), Bombardier, Inc. has 

issued Service Bulletin 601R–27–160, 

Revision A, dated October 3, 2012, 

which describes an alternative method 

for marking the HSTA. We have revised 

paragraphs (g), (h), (i), and (n) of this AD 

to reference Bombardier Service 

Bulletin 601R–27–160, Revision A, 

dated October 3, 2012. We have also 

added a new paragraph (j) to this AD to 

allow credit for actions done before the 

effective date of this AD in accordance 

with Bombardier Service Bulletin 601R– 

27–160, dated September 29, 2011. We 

have re-identified the subsequent 

paragraphs accordingly. 

Request To Clarify the Term 

‘‘Horizontal Stabilizer Trim Actuator 

(HSTA) Trunnion Support’’ 

Air Wisconsin requested that we 

clarify what is meant by ‘‘HSTA 

trunnion support,’’ as referenced in 

paragraph (j) of the NPRM (77 FR 36948, 

June 20, 2012) and Bombardier 

Temporary Revision 2B–2180, dated 

August 8, 2011, to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

We agree to clarify the definition of 

HSTA trunnion support. The HSTA 

trunnion support includes the upper 

and lower attachments of the HSTA to 

the airframe mounting structure. No 

change has been made to the AD in this 

regard. 

Request To Make Documents Available 

to Public 

Air Wisconsin requested that the 

documents ‘‘Aerospace Standard 478’’ 

and ‘‘ATA Report 51–93–01 ‘Structural 

Maintenance Program Guidelines for 

Continuing Airworthiness’ ’’ be made 

available to the public. The commenter 

stated that these documents are 

referenced in Bombardier Service 

Bulletin 601R–27–160, dated September 

29, 2011. 

We disagree with the request to make 

these documents available to the public. 

At the final rule stage, we post on 

www.regulations.gov only the service 

information that is approved for 

incorporation by reference in the final 

rule by the Office of the Federal 

Register. Since Aerospace Standard 478 

is not a document that is incorporated 

by reference, we do not make it 

available on that Web site. However, if 

the document is not currently in an 

operator’s possession, it can be obtained 

from the airplane manufacturer at the 

address specified in paragraph (n)(2) of 

this AD. We have added an option to 

paragraph (i) of this AD to allow 

operators to do the actions using a 

method approved by the FAA. ATA 

Report 51–93–01 ‘‘Structural 

Maintenance Program Guidelines for 

Continuing Airworthiness’’ is not 

necessary to accomplish the AD actions. 

It is not necessary for compliance with 

the AD, and is cited as reference 

material only. 

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 changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

36948, June 20, 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 36948, 

June 20, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

586 products of U.S. registry. We also 

estimate that it will take about 20 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $162 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 $1,091,132, 

or $1,862 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 20 work-hours and require parts 

costing $4,391, for a cost of $6,091 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); 

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Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 7649 

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 36948, June 

20, 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 adding 

the following new AD: 

2013–02–08 Bombardier, Inc.: Amendment 

39–17329. Docket No. FAA–2012–0639; 

Directorate Identifier 2012–NM–005–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 11, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to Bombardier, Inc. 

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

& 440) airplanes, certificated in any category, 

all serial numbers. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections) and/or Critical 

Design Configuration Control Limitations 

(CDCCLs). Compliance with these actions 

and/or CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by this AD, the operator 

may not be able to accomplish the actions 

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 (m)(1) of this AD. The request 

should include a description of changes to 

the required actions that will ensure the 

continued operational safety of the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by a report that the 

safe life limit and inspection requirements 

for the horizontal stabilizer trim actuator 

(HSTA) attachment pins and trunnions were 

not listed in the Airworthiness Limitations 

Section of the maintenance program. We are 

issuing this AD to detect and correct 

cracking, gouges, scratches, and corrosion of 

the HSTA attachment pins and trunnions, 

which could result in failure of these pins 

and trunnions and consequent disconnection 

of the horizontal stabilizer and subsequent 

loss of controllability 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) Inspection 

At the earliest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection of the trunnions, 

upper pins, and lower pins identified in table 

1 to paragraphs (g) and (h) of this AD, for 

gouges, scratches, and corrosion, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–160, Revision A, dated October 3, 

2012. 

(1) Within 5,000 flight hours after the 

effective date of this AD. 

(2) Within 60 months after the effective 

date of this AD. 

(3) Before the accumulation of 40,000 total 

flight cycles, or within 60 days after the 

effective date of this AD, whichever occurs 

later. 

TABLE 1 TO PARAGRAPHS (G) AND (H) 

OF THIS AD—Affected Parts 

Part name Part No. 

Upper Pin .............................. 600–92384–5 

Upper Pin .............................. 600–92384–7 

Upper Pin .............................. 601R92310–1 

Lower Pin .............................. 600–92383–5 

Lower Pin .............................. 600–92383–7 

Lower Pin .............................. 601R92309–1 

Trunnion ................................ 601R92386–1 

(h) Replacement 

If, during any inspection required by 

paragraph (g) of this AD, any gouges, 

scratches, or corrosion are found: Before 

further flight, replace the affected part with 

a part other than one identified in table 1 to 

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

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–160, Revision A, dated October 3, 

2012. 

(i) Re-Identification 

If, during any inspection required by 

paragraph (g) of this AD, no gouges, scratches 

or corrosion are found: Before further flight, 

add serial numbers and new part numbers to 

the trunnions, upper pins, and lower pins, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–160, Revision A, dated October 3, 

2012; or using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

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

(i) of this AD, if those actions were performed 

before the effective date of this AD using 

Bombardier Service Bulletin 601R–27–160, 

dated September 29, 2011 (which is not 

incorporated by reference by this AD). 

(k) Revise Maintenance Program 

Within 30 days after the effective date of 

this AD, revise the maintenance program to 

incorporate the information specified in 

Bombardier Temporary Revisions 2B–2180, 

dated August 8, 2011; and 2B–2186, dated 

August 8, 2011; to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual (MRM). The 

compliance time for doing the initial 

replacement for the HSTA trunnion support 

and attaching hardware is before the 

accumulation of 80,000 landings or within 60 

days after the effective date of this AD, 

whichever occurs later. The compliance time 

for doing the initial inspection of the upper 

and lower installation pins of the horizontal 

stabilizer pitch trim actuator is before the 

accumulation of 40,000 landings or within 60 

days after the effective date of this AD, 

whichever occurs later. 

(l) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (k) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (m)(1) of 

this AD. 

(m) 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, 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, 

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7650 Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 

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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2011–45, dated 

December 19, 2011, and the service 

information specified in paragraphs (n)(1)(i), 

(n)(1)(ii), and (n)(1)(iii) of this AD, for related 

information. 

(i) Bombardier Service Bulletin 601R–27– 

160, Revision A, dated October 3, 2012. 

(ii) Bombardier Temporary Revision 2B– 

2180, dated August 8, 2011, to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

(iii) Bombardier Temporary Revision 2B– 

2186, dated August 8, 2011, to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

(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. You may review 

copies of the referenced 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. 

(o) 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–27– 

160, Revision A, dated October 3, 2012. 

(ii) Bombardier Temporary Revision 2B– 

2180, dated August 8, 2011, to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

(iii) Bombardier Temporary Revision 2B– 

2186, dated August 8, 2011, to Appendix B— 

Airworthiness Limitations, of Part 2, 

Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual. 

(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, 

Washington. 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 January 

16, 2013. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–01821 Filed 2–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30882; Amdt. No. 3517] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final Rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective February 4, 

2013. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 4, 

2013. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169 or, 

4. 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. 

Availability—All SIAPs and Takeoff 

Minimums and ODPs are available 

online free of charge. Visit http:// 

www.nfdc.faa.gov to register. 

Additionally, individual SIAP and 

Takeoff Minimums and ODP copies may 

be obtained from: 

1. FAA Public Inquiry Center (APA– 

200), FAA Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; or 

2. The FAA Regional Office of the 

region in which the affected airport is 

located. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham III, Flight Procedure 

Standards Branch (AFS–420), Flight 

Technologies and Programs Divisions, 

Flight Standards Service, Federal 

Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd. Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082, Oklahoma City, OK 73125) 

Telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This rule 

amends Title 14 of the Code of Federal 

Regulations, Part 97 (14 CFR part 97), by 

establishing, amending, suspending, or 

revoking SIAPS, Takeoff Minimums 

and/or ODPS. The complete regulators 

description of each SIAP and its 

associated Takeoff Minimums or ODP 

for an identified airport is listed on FAA 

form documents which are incorporated 

by reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR part 97.20. The applicable FAA 

Forms are FAA Forms 8260–3, 8260–4, 

8260–5, 8260–15A, and 8260–15B when 

required by an entry on 8260–15A. 

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