## 19719 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules

(3) For certification maintenance requirements tasks specified in Subject 05– 10–20, ‘‘ Certification Maintenance Requirements Description and Operation, ’’ of Chapter 05 of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 33, dated February 15, 2010: Prior to the accumulation of the applicable flight hours specified in the ‘‘Time Between Checks ’’ column in Subject 05–10–20, or within 90 days after the effective date of this AD, whichever occurs later; except for tasks that specify ‘‘ first flight of the day’’ in the

‘‘Time Between Checks ’’ column in Subject 05–10–20, the initial compliance time is the first flight of the next day after doing the revision required by paragraph (i) of this AD, or within 90 days after the effective date of this AD, whichever occurs later.

No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs)

(j) After accomplishing the revision required by paragraph (i) of this AD, no alternative actions ( e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: Although EASA Airworthiness Directive 2010–0098, dated May 27, 2010, specifies both revising the maintenance program to include limitations, and doing certain repetitive actions ( e.g., inspections) and/or maintaining Critical Design Configuration Control Limitations (CDCCLs), this AD only requires the revision. Requiring a revision of the maintenance program, rather than requiring individual repetitive actions and/or maintaining CDCCLs, requires operators to record AD compliance only at the time the revision is made. Repetitive actions and/or maintaining CDCCLs specified in the airworthiness limitations must be complied with in accordance with 14 CFR 91.403(c).

Other FAA AD Provisions

(k) 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: 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. 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

(l) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0098, dated May 27, 2010; Subjects 05–10–10,

‘‘Airworthiness Limitations, ’’ 05–10–20,

‘‘ Certification Maintenance Requirements, ’’ and 05–10–30, ‘‘ Critical Design Configuration Control Limitations (CDCCL)—Fuel System, ’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 31, dated February 15, 2009; and Subjects 05– 10–00, ‘‘ Time Limits Description and Operation, ’’ 05–10–10, ‘‘Airworthiness Limitations Description and Operation, ’’ 05– 10–20, ‘‘ Certification Maintenance Requirements Description and Operation, ’’ and 05–10–30, ‘‘ Critical Design Configuration Control Limitations (CDCCL)—Fuel System Description and Operation, ’’ of Chapter 05 of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 33, dated February 15, 2010; for related information.

Issued in Renton, Washington, on March 30, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–8410 Filed 4–7–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0307; Directorate Identifier 2010–NM–111–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Saab AB, **Saab Aerosystems Model SAAB 2000 Airplanes** 

**AGENCY** 

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

**ACTION** 

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

**SUMMARY** 

### : We propose to adopt a new airworthiness directive (AD) for the products listed above. 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 report has been received of an incident where one of the two bolts attaching the actuator mounting bracket to the MLG [main landing gear] Shock Strut was found loose, leading to failure of the other attachment bolt, subsequently resulting in failure of the bracket.

This condition, if not detected and corrected, could prevent the MLG to extend to the full down-and-locked position, possibly resulting in MLG collapse upon landing or during roll-out, with consequent damage to the aeroplane and injury to the occupants.


### * * * * *

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

**DATES** 

### : We must receive comments on this proposed AD by May 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 W12–40, 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 Saab AB, Saab Aerosystems, SE–581 88, Linko  ̈ ping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; e-mail saab2000.techsupport@saabgroup.com; Internet http://www.saabgroup.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


## 19720 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules

be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT** 

### : Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149.

**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–2011–0307; Directorate Identifier 2010–NM–111–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

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0069, dated April 14, 2010 (referred to after this as ‘‘the MCAI’’ ), to correct an unsafe condition for the specified products. The MCAI states:

A report has been received of an incident where one of the two bolts attaching the actuator mounting bracket to the MLG Shock Strut was found loose, leading to failure of the other attachment bolt, subsequently resulting in failure of the bracket.

This condition, if not detected and corrected, could prevent the MLG to extend to the full down-and-locked position, possibly resulting in MLG collapse upon landing or during roll-out, with consequent damage to the aeroplane and injury to the occupants.

To correct this potentially unsafe condition, SAAB has published Service Bulletin (SB) 2000–32–073, describing a [detailed] inspection of the attachment bolts [and nuts] to detect any loose bolts [and nuts], follow-up corrective action(s), depending on findings, and the installation of the correct number of washers.

For the reasons described above, this EASA AD requires the accomplishment of the actions described in SAAB SB 2000–32–073. 

### Required actions, if any loose parts are found, include replacing the bolt with a new bolt, and then doing a detailed inspection of the bolts for uniform or fretting corrosion; a detailed inspection of the actuator mounting bracket and shock struts for damage, cracks, and signs of corrosion; and doing corrective actions if necessary. Corrective actions include removing corrosion, replacing affected bolts with new bolts, tightening loose nuts, repairing, and installing the correct number of washers. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Saab has issued Service Bulletin 2000–32–073, Revision 01, dated October 20, 2009. 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 8 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. Required parts would cost about $1,039 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 $8,992, or $1,124 per product.

In addition, we estimate that any necessary follow-on actions would take about 10 work-hours and require parts costing $1,039, for a cost of $1,889 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 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


## 19721 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules

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:
Saab AB, Saab Aerosystems: Docket No. FAA–2011–0307; Directorate Identifier 2010–NM–111–AD.

Comments Due Date

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

Affected ADs

(b) None.
Applicability

(c) This AD applies to all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, certificated in any category.
Subject

(d) Air Transport Association (ATA) of America Code 32: Landing gear.

Reason

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

A report has been received of an incident where one of the two bolts attaching the actuator mounting bracket to the MLG [main landing gear] Shock Strut was found loose, leading to failure of the other attachment bolt, subsequently resulting in failure of the bracket.

This condition, if not detected and corrected, could prevent the MLG to extend to the full down-and-locked position, possibly resulting in MLG collapse upon landing or during roll-out, with consequent damage to the aeroplane and injury to the occupants.


### * * * * *
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.
Inspection

(g) Within 12 months after the effective date of this AD, do a detailed inspection for any loose top bolt and nut of the shock strutactuator mounting bracket of both the lefthand and right-hand main landing gear (MLG), in accordance with paragraph 2.B. of the Accomplishment Instructions of Saab Service Bulletin 2000–32–073, Revision 01, dated October 20, 2009.

Corrective Action

(h) If any loose bolt or nut is found during the inspection required by paragraph (g) of this AD, before further flight, replace the bolt with a new bolt and accomplish paragraphs (h)(1) and (h)(2) of this AD, in accordance with paragraph 2.C. of the Accomplishment Instructions Saab Service Bulletin 2000–32– 073, Revision 01, dated October 20, 2009.

(1) Do a detailed inspection of the bottom bolts for uniform or fretting corrosion. If any corrosion is found, before further flight, accomplish all applicable corrective actions, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 32–073, Revision 01, dated October 20, 2009.

(2) Do a detailed inspection for damage, cracks, and other signs of deterioration of the actuator mounting bracket and shock strut. If signs of damage, cracks, or other signs of deterioration are found on the actuator mounting bracket or the shock strut, before further flight, repair in accordance with a method approved by the FAA or the European Aviation Safety Agency (EASA) (or its delegated agent).

(i) Within 12 months after the effective date of this AD, unless already accomplished in accordance with paragraph (h) of this AD, install the correct number of washers for both the top and bottom bolts of the shock strut actuator mounting bracket of both MLG, in accordance with paragraph 2.C.of the Accomplishment Instructions of Saab Service Bulletin 2000–32–073, Revision 01, dated October 20, 2009.
Credit for Actions Accomplished in Accordance With Previous Service Information

(j) Actions accomplished before the effective date of this AD in accordance with Saab Service Bulletin 2000–32–073, dated June 26, 2009, are considered acceptable for compliance with the corresponding actions specified in this AD.

FAA AD Differences

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

Other FAA AD Provisions

(k) 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227-1149. Information may be e-mailed 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

(l) Refer to MCAI EASA Airworthiness Directive 2010–0069, dated April 14, 2010; and Saab Service Bulletin 2000–32–073, Revision 01, dated October 20, 2009; for related information.

Issued in Renton, Washington, on March 31, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–8412 Filed 4–7–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0308; Directorate Identifier 2010–NM–233–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; 328 Support **Services GmbH (Type Certificate Previously Held by AvCraft Aerospace**  **GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328–**  **100 and –300 Airplanes**

**AGENCY** 

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

**ACTION** 

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

**SUMMARY** 

### : We propose to adopt a new airworthiness directive (AD) for the products listed above. 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 maintenance, it has been discovered that at the installation of the fixation brackets for rudder spring tabs and trim tabs an incorrect installation of the fixation brackets may have occurred. * * *