## 69166 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules

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 24 months after the effective date of this AD, modify the crossfeed valve control and power supply, the crossfeed indication logic and power supply, and the fuel fire shut-off valve indication logic, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–28–047, Revision 3, dated May 2, 2011, including Fokker Manual Change Notification—Operational Documentation MCNO–F100–060, dated June 10, 2011, and Manual Change Notification—Operational Document MCNO–F100–049, Revision 1, dated May 30, 2011, including the drawings specified in paragraphs (g)(1) through (g)(15) of this AD.

(1) Fokker Drawing D42770, Sheet 6, Issue U, dated May 2, 2011.

(2) Fokker Drawing D42780, Sheet 6, Issue T, dated May 2, 2011.

(3) Fokker Drawing W41074, Sheet 100, Issue GB, dated May 2, 2011.

(4) Fokker Drawing W41074, Sheet 101, Issue FW, dated May 2, 2011.

(5) Fokker Drawing W41194, Sheets 010 and 012, Issue J, dated May 2, 2011.

(6) Fokker Drawing W41194, Sheets 011, 013, and 015, Issue U, dated May 2, 2011.

(7) Fokker Drawing W41194, Sheets 014, 019, and 020, Issue S, dated May 2, 2011.

(8) Fokker Drawing W41194, Sheet 017, Issue Q, dated May 2, 2011.

(9) Fokker Drawing W41319, Sheets 063, 064, 065, 066, 069, 071, and 074, Issue DY, dated May 2, 2011.

(10) Fokker Drawing W41319, Sheets 067, 068, 070, 072, and 073, Issue DW, dated May 2, 2011.

(11) Fokker Drawing W46211, Sheet 71, Issue DL, dated April 21, 2009.

(12) Fokker Drawing W46211, Sheet 74, Issue DN, dated July 16, 2010.

(13) Fokker Drawing W46254, Sheets 30 through 36, Issue BL, dated March 30, 2009;

(14) Fokker Drawing W46254, Sheet 37, Issue BP, dated March 30, 2009.

(15) Fokker Drawing W59221, Sheets 161 and 162, Issue FC, July 9, 2010.

(h) Before or concurrent with the modification specified in paragraph (g) of this AD, do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD:

(1) For all airplanes: Modify the overhead panel (introduce provisions for a modified crossfeed indication) in accordance with the Accomplishment Instructions of Fokker Profroma Service Bulletin SBF100–28–043, Revision 1, dated March 31, 2009, including Appendix II, Revision 2, dated July 22, 2010, including the drawings specified in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD.

(i) Fokker Drawing W41194, Sheet 009, Issue F, dated March 31, 2009.

(ii) Fokker Drawing W41194, Sheet 016, Issue N, dated March 31, 2009.

(iii) Fokker Drawing W41194, Sheet 018, Issue S, dated March 31, 2009.

(iv) Fokker Drawing W59221, Sheet 159, Issue ED, dated October 2, 2009. (2) For airplanes with serial numbers 11442 through 11585, equipped with the automatic fuel transfer system: Modify the transfer logic of the center wing fuel tank, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–28–052, including Fokker Manual Change Notification—Operational Documentation MCNO–F100–052 and Manual Change Notification—Maintenance Documentation MCNM–F100–126, dated June 15, 2009, including the drawings specified in paragraphs (h)(2)(i) through (h)(2)(v) of this AD.

(i) Fokker Drawing D42126, Sheet 38, Issue AR, October 6, 1993.

(ii) Fokker Drawing D42213, Sheet 2, Issue H, dated May 23, 1990.

(iii) Fokker Drawing D42220, Sheet 60, Issue V, dated September 1, 1991.

(iv) Fokker Drawing D42220, Sheet 71, Issue AQ, dated June 7, 1993.

(v) Fokker Drawing D42250, Sheet 23, Issue U, dated April 1993.
Credit for Actions Accomplished in Accordance With Previous Service Information

(i) Modifications accomplished before the effective date of this AD according to the service bulletins specified in paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, as applicable, are considered acceptable for compliance with the corresponding action specified in this AD.

(1) Fokker Service Bulletin SBF100–28– 043, including Appendix II, dated March 31,
2009.

(2) Fokker Service Bulletin SBF100–28– 047, Revision 2, dated August 4, 2010.

(3) Fokker Service Bulletin SBF100–28– 047, Revision 1, dated July 22, 2010.

(4) Fokker Service Bulletin SBF100–28– 047, dated May 10, 2010.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1137; 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.

Related Information

(k) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010– 0158R1, dated November 8, 2010; and the service bulletins specified in paragraphs (g) and (h) of this AD; for related information.

Issued in Renton, Washington, on October 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–28836 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–2011–1228; Directorate Identifier 2011–NM–176–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 certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702), CL–600–2D15 (Regional Jet Series 705), CL–600–2D24 (Regional Jet Series 900), and CL–600–2E25 (Regional Jet Series 1000) 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:

[I]t was found that the * * * ADG [air driven generator] GCU [generator control unit] transformer primary winding can break due to thermal fatigue. Broken transformer primary winding can prevent the supply of power from the ADG to the essential buses. In the event of an emergency, failure for the essential buses to remain powered can prevent continued safe flight.


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


## 69167 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**

### : Assata Dessaline, Aerospace Engineer, Avionics and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7301; 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–2011–1228; Directorate Identifier 2011–NM–176–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–2011–27, dated July 25, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

There have been several occurrences of the air driven generator (ADG) failure to power essential buses during functional tests of the ADG on aeroplane models CL–600–2B16 and CL–600–2B19. The aeroplane models CL– 600–2C10, CL–600–2D15, CL–600–2D24, and CL–600–2E25 use the same ADG generator control unit (GCU) as models CL–600–2B16 and CL–600–2B19. However the aeroplane models CL–600–2C10, CL–600–2D15, CL– 600–2D24, and CL–600–2E25 are installed with a different hydraulic pump and do not experience the same failure due to the low threshold setting of the circuit protection. However, it was found that the same ADG GCU transformer primary winding can break due to thermal fatigue. Broken transformer primary winding can prevent the supply of power from the ADG to the essential buses. In the event of an emergency, failure for the essential buses to remain powered can prevent continued safe flight.

This [TCCA] directive mandates the replacement of the ADG GCU. 

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

Relevant Service Information

Bombardier, Inc. has issued Service Bulletin 670BA–24–031, dated May 30, 2011. 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 402 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 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 the proposed AD on U.S. operators to be $68,340, or $170 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


## 69168 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules

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 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– 1228; Directorate Identifier 2011–NM– 176–AD.

Comments Due Date

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

Affected ADs

(b) None.
Applicability

(c) This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.

(1) Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10003 through 10319 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 15260 inclusive.

(3) Bombardier, Inc. Model CL–600–2E25 (Regional Jet Series 1000) airplanes, serial numbers 19001 through 19012 inclusive.
Subject

(d) Air Transport Association (ATA) of America Code 24: Electrical Power.

Reason

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

[I]t was found that the * * * ADG [air driven generator] GCU [generator control unit] transformer primary winding can break due to thermal fatigue. Broken transformer primary winding can prevent the supply of power from the ADG to the essential buses. In the event of an emergency, failure for the essential buses to remain powered can prevent continued safe flight.


### * * * * *
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 10,000 flight hours or 60 months after the effective date of this AD, whichever occurs first, remove the ADG GCU, part number (P/N) 604–90800–7, and install a new or serviceable ADG GCU, P/N 604– 90800–27, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–24–031, dated May 30, 2011.

Parts Installation

(h) As of the effective date of this AD, no person may install an ADG GCU, P/N 604– 90800–7, on any airplane.

FAA AD Differences

Note 1: 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 Canadian Airworthiness Directive CF–2011–27, dated July 25, 2011; and Bombardier Service Bulletin 670BA–24– 031, dated May 30, 2011; for related information.

Issued in Renton, Washington, on October 31, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–28834 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–2011–1225; Directorate Identifier 2010–NM–269–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

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

**ACTION** 

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

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600 series airplanes); and Model A310 series 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:

During a routine visual inspection on two A310 in-service aeroplanes, cracks were found in the wing MLG [main landing gear] rib 5 aft bearing forward lug. Laboratory examination of the cracked ribs confirmed that the cracks were the result of pitting corrosion in the forward lug hole. Also on both aeroplanes, medium to heavy corrosion was found in the forward lugs on the opposite wing after removal of the bushes. * * * This situation, if not corrected, could