Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes, 19719-19721 [2011-8412]

Download as PDF 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 mstockstill on DSKH9S0YB1PROD with PROPOSALS 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 VerDate Mar<15>2010 16:32 Apr 07, 2011 Jkt 223001 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 19719 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 https://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, ¨ Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; e-mail saab2000.techsupport@saabgroup.com; Internet https://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 https:// 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 E:\FR\FM\08APP1.SGM 08APP1 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 https:// 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. mstockstill on DSKH9S0YB1PROD with PROPOSALS 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 VerDate Mar<15>2010 16:32 Apr 07, 2011 Jkt 223001 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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 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 E:\FR\FM\08APP1.SGM 08APP1 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. mstockstill on DSKH9S0YB1PROD with PROPOSALS * * * * * 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 strut actuator mounting bracket of both the left- VerDate Mar<15>2010 16:32 Apr 07, 2011 Jkt 223001 hand 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– PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 19721 3356; telephone (425) 227–1112; fax (425) 227-1149. Information may be e-mailed to: 9ANM-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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: SUMMARY: 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. * * * E:\FR\FM\08APP1.SGM 08APP1

Agencies

[Federal Register Volume 76, Number 68 (Friday, April 8, 2011)]
[Proposed Rules]
[Pages 19719-19721]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-8412]


-----------------------------------------------------------------------

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 https://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, Link[ouml]ping, Sweden; telephone 
+46 13 18 5591; fax +46 13 18 4874; e-mail 
saab2000.techsupport@saabgroup.com; Internet https://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 https://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

[[Page 19720]]

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 https://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

[[Page 19721]]

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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  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 
strut actuator mounting bracket of both the left-hand 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