Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36129 

fuel leak is detected in the vicinity of a wing 

rear spar, whichever occurs first: Do a 

detailed inspection for cracks, corrosion, and 

other defects (defects include scratches, 

dents, holes, damage to fastener holes, or 

damage to surface protection and finish) of 

the rear face of the wing rear spars, in 

accordance with the Accomplishment 

Instructions of BAE SYSTEMS (Operations) 

Limited Alert Service Bulletin J41–A57–029, 

dated May 6, 2011. 

(1) If any cracking, corrosion, or other 

defect is found to be within the criteria 

defined in Subject 57–00–00, Wings General, 

of Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007: Before 

further flight, repair the damage, in 

accordance with the repair instructions 

specified in Subject 57–00–00, Wings 

General, of Chapter 57, Wings, of the 

Jetstream Series 4100 Structural Repair 

Manual, Volume 1, Revision 30, dated April 

15, 2007. 

(2) If any cracking, corrosion, or other 

defect is found exceeding the criteria as 

specified in Subject 57–00–00, Wings 

General, of Chapter 57, Wings, of the 

Jetstream Series 4100 Structural Repair 

Manual, Volume 1, Revision 30, dated April 

15, 2007: Before further flight, repair the 

condition, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or EASA (or its delegated 

agent). 

(h) Reporting 

Submit a report of the findings of the 

inspection required by paragraph (g) of this 

AD, including a report of no defects, to BAE 

SYSTEMS (Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/

RegionalAircraft/index.htm, at the applicable 

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

this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1175; 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

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

Information Collection Clearance Officer, 

AES–200. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0096, dated May 25, 2011, 

and the service information specified in 

paragraphs (j)(1) and (j)(2) of this AD, for 

related information. 

(1) BAE SYSTEMS (Operations) Limited 

Alert Service Bulletin J41–A57–029, dated 

May 6, 2011. 

(2) Subject 57–00–00, Wings General, of 

Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) BAE SYSTEMS (Operations) Limited 

Alert Service Bulletin J41–A57–029, dated 

May 6, 2011. 

(ii) Subject 57–00–00, Wings General, of 

Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007. The 

revision level and date of this document are 

identified only in the Record of Revisions 

section of this document. 

(3) For service information identified in 

this AD, contact BAE SYSTEMS (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@baesystems.

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

Businesses/RegionalAircraft/index.htm. 

(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 also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on March 

31, 2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13800 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0293; Directorate 

Identifier 2012–NM–034–AD; Amendment 

39–17081; AD 2012–12–02] 

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 certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, and 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes. This AD was 

prompted by reports of a bleed air leak 

from the high pressure ducts which was 

not immediately detected by the bleed 

leak detection system. This AD requires 

installing new sensing elements in the 

main landing gear wheel well and the 

overwing area, protective blankets on 

the upper surface of the wing box and 

fuel tubes, and protective shields on the 

rudder quadrant support-beam in the aft 

equipment compartment. We are issuing 

this AD to prevent an undetected bleed 


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36130 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

air leak which can cause loss of rudder 

control, can lead to degradation of 

structural integrity, and could be a 

potential heat source that can lead to 

fuel being ignited. 

DATES: This AD becomes effective July 

23, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 23, 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: 

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 published in the Federal 

Register on March 21, 2012 (77 FR 

16490). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been multiple events reported 

where a bleed air leak from the high pressure 

ducts was not immediately detected by the 

Bleed Leak Detection System (BLDS). 

An investigation revealed that if a bleed air 

leak develops due to a cracked or ruptured 

duct, the duct shroud may not channel 

sufficient bleed air to the sensing loop 

elements to enable an automatic shutdown of 

the bleed air system. The inability to detect 

a bleed air leak could result in the rudder 

quadrant bracket, pressure floor, pressure 

floor beam, fuel vent boot or fuel tubes being 

exposed to high temperatures. This could 

potentially lead to the loss of rudder control, 

degrade the structural integrity of primary 

structure or fuel ignition. 

This [Canadian] Airworthiness Directive 

(AD) mandates the installation of newly 

designed sensing elements in the main 

landing gear wheel well and the overwing 

area, protective blankets on the upper surface 

of the wing box and fuel tubes, as well as 

protective shields on the rudder quadrant 

support-beam in the aft equipment 

compartment. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 16490, March 21, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

409 products of U.S. registry. We also 

estimate that it will take about 78 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 $21,353 

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 

$11,445,047, or $27,983 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 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 16490, 

March 21, 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: 

2012–12–02 Bombardier, Inc.: Amendment 

39–17081. Docket No. FAA–2012–0293; 

Directorate Identifier 2012–NM–034–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 23, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36131 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10003 through 

10331 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

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

(Regional Jet Series 900) airplanes, serial 

numbers 15001 through 15279 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 36: Pneumatic. 

(e) Reason 

This AD was prompted by reports of a 

bleed air leak from the high pressure ducts 

which was not immediately detected by the 

bleed leak detection system. We are issuing 

this AD to prevent an undetected bleed air 

leak which can cause loss of rudder control, 

can lead to degradation of structural 

integrity, and could be a potential heat 

source that can lead to fuel being ignited. 

(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) Install Protective Shields 

For Model CL–600–2C10 airplanes having 

serial numbers 10003 through 10326 

inclusive, and Model CL–600–2D15 and CL– 

600–2D24 airplanes having serial numbers 

15001 through 15267 inclusive: Within 6,600 

flight hours or 24 months after the effective 

date of this AD, whichever occurs first, 

install protective shields on the rudder 

quadrant support-beam in the aft equipment 

compartment, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–36–014, Revision A, 

dated October 11, 2011. 

(h) Install Protective Blankets and Sensing 

Elements 

For Model CL–600–2C10 airplanes having 

serial numbers 10003 through 10331 

inclusive and Models CL–600–2D15 and CL– 

600–2D24 airplanes having serial numbers 

15001 through 15279 inclusive: Within 6,600 

flight hours or 24 months after the effective 

date of this AD, whichever occurs first, 

install protective blankets on the upper 

surface of the wing box and fuel components, 

and install new sensing elements in the 

wheel well of the main landing gear and the 

overwing area, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–36–016, Revision A, 

dated October 11, 2011. 

(i) Credit for Previous Actions 

This paragraph provides credit for 

installations, required by paragraphs (g) and 

(h) of this AD, if those actions were 

performed before the effective date of this AD 

using Bombardier Service Bulletin 670BA– 

36–014 or 670BA–36–016, both dated April 

7, 2011, as applicable. 

(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, 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–2012–06, dated January 26, 

2012, and the service bulletins specified in 

paragraphs (k)(1) and (k)(2) of this AD, for 

related information. 

(1) Bombardier Service Bulletin 670BA– 

36–014, Revision A, dated October 11, 2011. 

(2) Bombardier Service Bulletin 670BA– 

36–016, Revision A, dated October 11, 2011. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 670BA–36– 

014, Revision A, dated October 11, 2011. 

(ii) Bombardier Service Bulletin 670BA– 

36–016, Revision A, dated October 11, 2011. 

(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 also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14042 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0562; Directorate 

Identifier 2012–SW–038–AD; Amendment 

39–17068; AD 2012–11–05] 

RIN 2120–AA64 

Airworthiness Directives; Enstrom 

Helicopter Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Enstrom Helicopter Corporation 

(Enstrom) Model F–28C, F–28C–2, F– 

28F, 280C, 280F, 280FX, TH–28, 480, 

and 480B helicopters to add another 

trim relay to the applicability and to 

revise the modification instructions. 

This AD is prompted by the discovery 

that another part-numbered trim relay, 

inadvertently omitted from the current 

AD, may contain the same unsafe 

condition. These actions are intended to 

prevent failure of the cyclic trim system 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 23, 2012 (77 FR 

729, January 6, 2012). 

We must receive comments on this 

AD by August 17, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 


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