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

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


## 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 alsoestimate 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.


## 36131 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations

(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 Co ˆ teVertu 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