## 69161 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules

(b) Affected ADs

This AD affects AD 2008–24–08, Amendment 39–15748 (73 FR 72320, November 28, 2008).
(c) Applicability

This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category, with Goodrich Corporation door escape slide part number (P/N) 5A3086– 1, –3, or –301, serial number (S/N) B3F001 through B3F611 inclusive; P/N 5A3088–1, –3, or –301, S/N B3A001 through B3A685 inclusive; or P/N 5A3307–1, –3, –5, or –301, S/N BNG0001 through BNG5707 inclusive.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 25, Equipment/Furnishings.
(e) Unsafe Condition

This AD was prompted by reports of escape slides failing to deploy from the forward and aft right-hand doors during scheduled maintenance slide deployments. We are issuing this AD to prevent failure of an escape slide to deploy, which could result in the slide being unusable during an emergency evacuation and increased likelihood of injury to passengers or crewmembers due to the difficulty in evacuating the aircraft.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Girt Check and Slide Modification

Within 36 months after the effective date of this AD: Do the actions in paragraph (g)(1) and (g)(2) of this AD.

(1) Check the girt for continued serviceability, in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 5A3307–25–389, dated November 8, 2010. If the girt is unserviceable: Before further flight, replace the girt with a new girt, in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 5A3307–25–389, dated November 8, 2010.

(2) Modify the cable routing provision on the girt, modify the valise, replace the regulator padding, and modify the aspirator orientation in the slide pack, in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 5A3307–25–389, dated November 8, 2010
(h) Concurrent Requirements

(1) For slide P/N 5A3307–3 or 5A3307– 301: Prior to or concurrently with accomplishing the actions required by paragraph (g) of this AD, modify the pilot valve regulator P/N 4A3865–2, –3, or –4, as applicable; install a new firing cable and safety pin; and modify the slide valise; in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 5A3307–25–339, Revision 3, dated May 8,
2009.

(2) For slide P/N 5A3307–3, 5A3307–5, or 5A3307–301: Prior to or concurrently with accomplishing the actions required by paragraph (g) of this AD, modify the Vespel piston in the regulator valves or replace the Vespel piston with a new or serviceable Vespel piston P/N 3A3566–2 or 3A3832–2, as applicable, in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 25–349, Revision 1, dated January 11, 2010.
(i) Credit for Actions Accomplished in Accordance With Previous Service Information

(1) Modifying the pilot valve regulator, installing a new firing cable and safety pin, or modifying the slide valise in accordance with Goodrich Service Bulletin 5A3307–25– 339, Revision 1, dated September 26, 2003; or Revision 2, dated March 31, 2004; before the effective date of this AD is acceptable for compliance with the corresponding modification or installations required by paragraph (h) of this AD.

(2) Modifying or replacing the Vespel piston in the regulator valves, in accordance with Goodrich Service Bulletin 25–349, dated September 15, 2004, before the effective date of this AD is acceptable for compliance with the corresponding modification required by paragraph (h) of this AD.
(j) Parts Installation

As of the effective date of this AD, no person may install on any airplane a part identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.

(1) A regulator having P/N 4A3865–2, –3,

or –4.

(2) An evacuation system having P/N 5A3086–1, –3, or –301, serial number (S/N) B3F001 through B3F611 inclusive; P/N 5A3088–1, –3, or –301, S/N B3A001 through B3A685 inclusive; or P/N 5A3307–1, –3, –5, or –301, S/N BNG0001 through BNG5707 inclusive.

(3) Regulator valve padding having P/N 3A4047–13. (k) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle 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 manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.

(2) 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.

(l) Related Information

(1) For more information about this AD, contact Patrick Gillespie, Aerospace Engineer, Cabin Safety & Environmental Systems Branch, ANM–150S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6429; fax: (425) 917– 6590; email: Patrick.Gillespie@faa.gov.

(2) For service information identified in this AD, contact Goodrich Corporation, Aircraft Interior Products, Attn: Technical Publications, 3414 South Fifth Street, Phoenix, Arizona 85040; phone: (602) 243– 2270; email: george.yribarren@goodrich.com; Internet: http://www.goodrich.com/ TechPubs. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, the FAA, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227–1221.

Issued in Renton, Washington, on October 27, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–28856 Filed 11–7–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1227; Directorate Identifier 2011–NM–100–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for all 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 proposed 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:

A number of reports of aileron control stiffness have been received on Bombardier Regional Jet aeroplanes. Bombardier has reviewed the current maintenance tasks for the aileron control system and determined that an additional maintenance task is required. * * * [A]ileron control stiffness during flight * * * could result in reduced controllability of the aeroplane.



### The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.


## 69162 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules

**DATES** 

### : We must receive comments on this proposed AD by December 23,
2011.

**ADDRESSES** 

### : You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Bombardier, Inc., 400 Co ˆ te-Vertu 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. 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 this proposed AD, 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.

**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** 

### :
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2011–1227; Directorate Identifier 2011–NM–100–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2011–07, dated April 26, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

A number of reports of aileron control stiffness have been received on Bombardier Regional Jet aeroplanes. Bombardier has reviewed the current maintenance tasks for the aileron control system and determined that an additional maintenance task is required.

This directive mandates revision of the approved maintenance schedule to incorporate the discard task for outboard wing aileron pulleys to prevent aileron control stiffness during flight which could result in reduced controllability of the aeroplane. 

### You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Bombardier, Inc. has issued Temporary Revision 1–41, dated October 22, 2010, to Section 2— Systems/Powerplant Program of Part 1 of the Bombardier CL–600–2C10, CL– 600–2D15, CL–600–2D24, CL–600–2E25 Maintenance Requirements Manual. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

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 proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 398 products of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $33,830, or $85 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the


## 69163 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules

distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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:
Bombardier, Inc.: Docket No. FAA–2011– 1227; Directorate Identifier 2011–NM– 100–AD.

Comments Due Date

(a) We must receive comments by December 23, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to all 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; certificated in any category.
Subject

(d) Air Transport Association (ATA) of America Code 27: Flight controls.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

A number of reports of aileron control stiffness have been received on Bombardier Regional Jet aeroplanes. Bombardier has reviewed the current maintenance tasks for the aileron control system and determined that an additional maintenance task is required. * * * [A]ileron control stiffness during flight * * * could result in reduced controllability of the aeroplane.
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.

Actions

(g) Within 30 days after the effective date of this AD: Revise the maintenance program to incorporate Task 271000–218, discard of the outboard wing aileron pulleys, as specified in Bombardier Temporary Revision (TR) 1–41, dated October 22, 2010, to Section 2—Systems/Powerplant Program of Part 1 of the Bombardier CL–600–2C10, CL–600– 2D15, CL–600–2D24, CL–600–2E25 Maintenance Requirements Manual (MRM). For this task, the initial compliance time starts at the applicable time specified in paragraphs (g)(1), (g)(2), (g)(3), or (g)(4) of this AD. Thereafter, operate the airplane according to the procedures and compliance times in Bombardier TR 1–41, dated October 22, 2010.

(1) For airplanes with 10,000 or less total flight hours as of the effective date of this AD: Prior to the outboard wing aileron pulley accumulating 12,000 total flight hours.

(2) For airplanes with more than 10,000 total flight hours but with 16,000 total flight hours or less as of the effective date of this AD: Prior to the outboard wing aileron pulley accumulating 17,300 total flight hours, or within 2,000 flight hours after the effective date of this AD, whichever is earlier.

(3) For airplanes with more than 16,000 total flight hours but with 20,000 total flight hours or less as of the effective date of this AD: Prior to the outboard wing aileron pulley accumulating 20,800 total flight hours, or within 1,300 flight hours after the effective date of this AD, whichever is earlier.

(4) For airplanes with more than 20,000 total flight hours as of the effective date of this AD: Within 800 flight hours after the effective date of this AD.

Note 1: The actions required by paragraphs (g) of this AD may be done by inserting a copy of Bombardier TR 1–41, dated October 22, 2010, into Section 2—Systems/ Powerplant Program of Part 1 of the Bombardier CL–600–2C10, CL–600–2D15, CL–600–2D24, CL–600–2E25 MRM. When this TR has been included in the general revisions of the MRM, the general revisions may be inserted in the MRM, and the TR may be removed from the MRM, provided that the relevant information in the general revision is identical to that in Bombardier TR 1–41, dated October 22, 2010.

No Alternative Actions or Intervals

(h) After accomplishing the revision required by paragraph (g) 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 (i)(1) of this AD. FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(i) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7300; fax (516) 794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(j) Refer to MCAI Transport Canada Civil Aviation Airworthiness Directive CF–2011– 07, dated April 26, 2011; and Bombardier Temporary Revision 1–41, dated October 22, 2010, to Section 2—Systems/Powerplant Program of Part 1 of the Bombardier CL–600– 2C10, CL–600–2D15, CL–600–2D24, CL–600– 2E25 MRM; for related information.

Issued in Renton, Washington, on October 31, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–28835 Filed 11–7–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1226; Directorate Identifier 2011–NM–006–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Fokker **Services B.V. Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.