Airworthiness Directives; Saab Model SAAB 2000 Airplanes, 6640-6642 [E8-1992]

Download as PDF 6640 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules revises the Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700– 715A1–30 engine model and operated against the Hawaiian Flight Mission. This condition, if not corrected, could result in uncontained failure of the LP compressor (fan) disc assembly and damage to the airplane. Actions and Compliance (e) No later than 100 flight cycles after the effective date of this AD, do the following actions, unless already done. rmajette on PROD1PC64 with PROPOSALS BR700–715A1–30 Turbofan Engines (1) For BR700–715A1–30 turbofan engines, amend the Airworthiness Limitations Section of the Time Limits Manual SUBTASK 05–10– 01–860–016, (Hawaiian Flight Mission Only) by revising the ‘‘GIVEN LIFE A1–30 RATING (FLIGHT CYCLES)’’ for both the LP compressor (fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles. (2) Amend any other Reference, where the maximum approved life limit is quoted for the LP compressor (fan) disc assembly P/N BRH10048 or LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700–715A–30 engine model and operated under the Hawaiian Flight Mission, to the revised maximum approved life limit of 25,000 flight cycles. BR700–715B1–30 and BR700–715C1–30 Turbofan Engines (3) For BR700–715B1–30 and BR700– 715C1–30 turbofan engines: (i) Check to see if the LP compressor (fan) disc assembly P/N BRH10048 or LP compressor (fan) disc assembly P/N BRH19253 is currently, or has previously been, installed in the BR700–715A1–30 engine model and operated under the Hawaiian Flight Mission, by checking the Life Limited Parts (LLP) Tracking Sheet. Information on recording and control of the lives of the parts can be found in the Airworthiness Limitations Section of the Time Limits Manual TASK 05–00–01–800– 001. (ii) If the LP compressor (fan) disc assembly has not operated, and is not going to operate in the Hawaiian Flight Mission, no further action is required. (iii) If the LP compressor (fan) disc assembly has operated in the Hawaiian Flight Mission: (A) Apply the prorate calculations and complete the LLP Tracking Sheet using the revised Hawaiian Flight Mission maximum approved life limit of 25,000 flight cycles. (B) Remove LP compressor (fan) disc assemblies from service before reaching 25,000 flight cycles. Other FAA AD Provisions (f) Alternative Methods of Compliance: The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD, if VerDate Aug<31>2005 15:29 Feb 04, 2008 Jkt 214001 requested using the procedures found in 14 CFR 39.19. Related Information (g) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007– 0116–E, dated May 4, 2007, for related information. (h) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199, for more information about this AD. Issued in Burlington, Massachusetts, on January 28, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–2039 Filed 2–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0115; Directorate Identifier 2007–NM–240–AD] RIN 2120–AA64 Airworthiness Directives; Saab 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 product. The MCAI describes the unsafe condition as: SUMMARY: One LM–219–92 Centre Bracket from an LM–219-SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. * * * * * A failed mounting assembly, if not corrected, could result in loss of the engine. 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 March 6, 2008. ADDRESSES: You may send comments by any of the following methods: PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 • 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. 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 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–2008–0115; Directorate Identifier 2007–NM–240–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 E:\FR\FM\05FEP1.SGM 05FEP1 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules Airworthiness Directive 2007–0204, dated August 8, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: One LM–219–92 Centre Bracket from an LM–219–SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. This AD requires rework in order to make the centre bracket less sensitive to external damage that may result in a crack. A failed mounting assembly, if not corrected, could result in loss of the engine. The corrective action also includes a visual and fluorescent penetrant inspection for cracking of the center bracket of the aft engine mounting assembly for both engines, reidentification of a reworked center bracket, additional fluorescent penetrant inspections for cracking of the reworked center bracket, and replacement of the aft engine mounting assembly if any cracked center bracket is found. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Saab has issued Saab 2000 Service Bulletin 2000–71–025, dated June 13, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. rmajette on PROD1PC64 with PROPOSALS 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. VerDate Aug<31>2005 15:29 Feb 04, 2008 Jkt 214001 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 6 products of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $3,840, or $640 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 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. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 6641 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, 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 Aircraft AB: Docket No. FAA–2008– 0115; Directorate Identifier 2007–NM– 240–AD. Comments Due Date (a) We must receive comments by March 6, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Saab Model SAAB 2000 airplanes, certificated in any category, serial number 004 through 063. Subject (d) Air Transport Association (ATA) of America Code 71: Power Plant. Reason (e) The mandatory continuing airworthiness information (MCAI) states: One LM–219–92 Centre Bracket from an LM–219–SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. This AD requires rework in order to make the centre bracket less sensitive to external damage that may result in a crack. A failed mounting assembly, if not corrected, could result in loss of the engine. The corrective action also includes a visual and fluorescent penetrant inspection for cracking of the center bracket of the aft engine mounting assembly for both engines, reidentification of a reworked center bracket, additional fluorescent penetrant inspections for cracking of the reworked center bracket, and replacement of the aft engine mounting assembly if any cracked center bracket is found. Actions and Compliance (f) Unless already done, do the following actions in accordance with the E:\FR\FM\05FEP1.SGM 05FEP1 6642 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules Accomplishment Instructions of Saab 2000 Service Bulletin 2000–71–025, dated June 13, 2007. (1) Within 1,000 flight hours after the effective date of this AD, do a visual and a fluorescent penetrant inspection for cracking of the center bracket of both of the aft engine mounting assemblies. (2) If no cracking is found during the inspections required by paragraph (f)(1) of this AD, within 4,000 flight hours after the effective date of this AD, rework the center bracket of the aft engine mounting assembly, do fluorescent penetrant inspections for cracking of the reworked bracket, and reidentify with new part numbers the reworked center bracket and the applicable aft engine mounting assembly. (3) If any cracking is found during any inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the aft engine mounting assembly, and rework and re-identify the center bracket. FAA AD Differences rmajette on PROD1PC64 with PROPOSALS Note: This AD differs from the MCAI and/ or service information as follows: (1) Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (f)(3) of this AD requires that you replace the aft engine mounting assembly before further flight. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Airplane Directorate, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information 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. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007–0204, dated August 8, 2007, VerDate Aug<31>2005 16:52 Feb 04, 2008 Jkt 214001 and Saab 2000 Service Bulletin 2000–71–025, dated June 13, 2007, for related information. Issued in Renton, Washington, on January 24, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–1992 Filed 2–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 138 [USCG 2005–21780] RIN 1625–AA98 Financial Responsibility for Water Pollution (Vessels) and OPA 90 Limits of Liability (Vessels and Deepwater Ports) Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: ACTION: SUMMARY: The Coast Guard proposes to amend the regulatory requirements, under the Oil Pollution Act of 1990 and the Comprehensive Environmental Response, Compensation and Liability Act, for vessel operators to establish and maintain evidence of financial responsibility. The amendments would ensure the amounts of financial responsibility demonstrated are consistent with recent statutory increases, and future mandated increases, in the limits of liability under the Oil Pollution Act of 1990. The amendments would also implement changes in the Coast Guard’s administration of the certificate of financial responsibility program, and would clarify the current rule. DATES: Comments and related material must reach the Docket Management Facility on or before May 5, 2008. Comments sent to the Office of Management and Budget (OMB) on collection of information must reach OMB on or before May 5, 2008. ADDRESSES: You may submit comments identified by Coast Guard docket number USCG–2005–21780 to the Docket Management Facility at the U.S. Department of Transportation. To avoid duplication, please use only one of the following methods: (1) Online: https:// www.regulations.gov. (2) Mail: Docket Management Facility (M–30), U.S. Department of Transportation, West Building Ground Floor, Room W12–140, 1200 New Jersey PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 Avenue, SE., Washington, DC 20590– 0001. (3) Hand delivery: Room W12–140 on the Ground Floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC 20590 between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The telephone number is 202–366–9329. (4) Fax: 202–493–2251. You must also send comments on collection of information to the Office of Information and Regulatory Affairs, Office of Management and Budget. To ensure that the comments are received on time, the preferred method is by email at nlesser@omb.eop.gov or fax at 202–395–6566. An alternate, though slower, method is by U.S. mail to the Office of Information and Regulatory Affairs, Office of Management and Budget, 725 17th Street, NW., Washington, DC 20503, ATTN: Desk Officer, U.S. Coast Guard. FOR FURTHER INFORMATION CONTACT: If you have questions on this proposed rule, call Benjamin White, National Pollution Funds Center, Coast Guard, telephone 202–493–6863. If you have questions on viewing or submitting material to the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366–9826. SUPPLEMENTARY INFORMATION: I. Public Participation and Request for Comments We encourage you to participate in this rulemaking by submitting comments and related materials. All comments received will be posted, without change, to https:// www.regulations.gov and will include any personal information you have provided. We have an agreement with the Department of Transportation (DOT) to use the Docket Management Facility. Please see DOT’s ‘‘Privacy Act’’ paragraph below. A. Submitting Comments If you submit a comment, please include the docket number for this rulemaking (USCG–2005–21780), indicate the specific section of this document to which each comment applies, and give the reason for each comment. We recommend that you include your name and a mailing address, an e-mail address, or a phone number in the body of your document so that we can contact you if we have questions regarding your submission. For example, we may ask you to resubmit your comment if we are not able to read your original submission. You may submit your comments and material by electronic means, mail, fax, E:\FR\FM\05FEP1.SGM 05FEP1

Agencies

[Federal Register Volume 73, Number 24 (Tuesday, February 5, 2008)]
[Proposed Rules]
[Pages 6640-6642]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1992]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0115; Directorate Identifier 2007-NM-240-AD]
RIN 2120-AA64


Airworthiness Directives; Saab 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:

    One LM-219-92 Centre Bracket from an LM-219-SA28 Aft Engine 
Mounting assembly was found to be cracked while installed on the 
aircraft.
    This reduces the effectiveness of the mounting assembly and 
could eventually cause it to fail.
* * * * *
    A failed mounting assembly, if not corrected, could result in loss 
of the engine. 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 March 6, 2008.

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.

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 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-2008-0115; 
Directorate Identifier 2007-NM-240-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

[[Page 6641]]

Airworthiness Directive 2007-0204, dated August 8, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    One LM-219-92 Centre Bracket from an LM-219-SA28 Aft Engine 
Mounting assembly was found to be cracked while installed on the 
aircraft.
    This reduces the effectiveness of the mounting assembly and 
could eventually cause it to fail.
    This AD requires rework in order to make the centre bracket less 
sensitive to external damage that may result in a crack.

A failed mounting assembly, if not corrected, could result in loss of 
the engine. The corrective action also includes a visual and 
fluorescent penetrant inspection for cracking of the center bracket of 
the aft engine mounting assembly for both engines, re-identification of 
a reworked center bracket, additional fluorescent penetrant inspections 
for cracking of the reworked center bracket, and replacement of the aft 
engine mounting assembly if any cracked center bracket is found. You 
may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    Saab has issued Saab 2000 Service Bulletin 2000-71-025, dated June 
13, 2007. 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 6 products of U.S. registry. We also estimate that 
it would take about 8 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $3,840, or $640 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 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, 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 Aircraft AB: Docket No. FAA-2008-0115; Directorate Identifier 
2007-NM-240-AD.

Comments Due Date

    (a) We must receive comments by March 6, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Saab Model SAAB 2000 airplanes, 
certificated in any category, serial number 004 through 063.

Subject

    (d) Air Transport Association (ATA) of America Code 71: Power 
Plant.

Reason

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

    One LM-219-92 Centre Bracket from an LM-219-SA28 Aft Engine 
Mounting assembly was found to be cracked while installed on the 
aircraft.
    This reduces the effectiveness of the mounting assembly and 
could eventually cause it to fail.
    This AD requires rework in order to make the centre bracket less 
sensitive to external damage that may result in a crack.

A failed mounting assembly, if not corrected, could result in loss 
of the engine. The corrective action also includes a visual and 
fluorescent penetrant inspection for cracking of the center bracket 
of the aft engine mounting assembly for both engines, re-
identification of a reworked center bracket, additional fluorescent 
penetrant inspections for cracking of the reworked center bracket, 
and replacement of the aft engine mounting assembly if any cracked 
center bracket is found.

Actions and Compliance

    (f) Unless already done, do the following actions in accordance 
with the

[[Page 6642]]

Accomplishment Instructions of Saab 2000 Service Bulletin 2000-71-
025, dated June 13, 2007.
    (1) Within 1,000 flight hours after the effective date of this 
AD, do a visual and a fluorescent penetrant inspection for cracking 
of the center bracket of both of the aft engine mounting assemblies.
    (2) If no cracking is found during the inspections required by 
paragraph (f)(1) of this AD, within 4,000 flight hours after the 
effective date of this AD, rework the center bracket of the aft 
engine mounting assembly, do fluorescent penetrant inspections for 
cracking of the reworked bracket, and re-identify with new part 
numbers the reworked center bracket and the applicable aft engine 
mounting assembly.
    (3) If any cracking is found during any inspection required by 
paragraph (f)(1) or (f)(2) of this AD, before further flight, 
replace the aft engine mounting assembly, and rework and re-identify 
the center bracket.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows:
    (1) Although the MCAI or service information allows further 
flight after cracks are found during compliance with the required 
action, paragraph (f)(3) of this AD requires that you replace the 
aft engine mounting assembly before further flight.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, Transport Airplane Directorate, ANM-116, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information 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. Before using any approved AMOC on any airplane to which 
the AMOC applies, notify your appropriate principal inspector (PI) 
in the FAA Flight Standards District Office (FSDO), or lacking a PI, 
your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0204, dated August 8, 2007, and Saab 
2000 Service Bulletin 2000-71-025, dated June 13, 2007, for related 
information.

    Issued in Renton, Washington, on January 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-1992 Filed 2-4-08; 8:45 am]
BILLING CODE 4910-13-P