Airworthiness Directives; Saab Model SAAB 2000 Airplanes, 67716-67718 [E8-26364]

Download as PDF 67716 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), 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: Aaron Waters, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4174; fax: (316) 946–4107. 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. Material Incorporated by Reference (g) You must use Hawker Beechcraft Mandatory Service Bulletin SB 29–3869, dated January 2008; and Hawker Beechcraft Mandatory Service Bulletin SB 29–3851, dated January 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676–5034; fax: (316) 676–6614; Internet: https:// www.hawkerbeechcraft.com/service_support/ pubs/. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, Missouri, on November 5, 2008. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–26879 Filed 11–14–08; 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; Amendment 39–15723; AD 2008–23–02] hsrobinson on PROD1PC76 with RULES RIN 2120–AA64 Airworthiness Directives; Saab Model SAAB 2000 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Aug<31>2005 17:35 Nov 14, 2008 Jkt 217001 SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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 Part Number (P/N) LM–219–92 Centre Bracket from a P/N 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. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 22, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 22, 2008. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. 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: Discussion We issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That supplemental NPRM was published in the Federal Register on August 29, 2008 (73 FR 50903). That supplemental NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: One Part Number (P/N) LM–219–92 Centre Bracket from a P/N 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. EASA Airworthiness Directive (AD) was issued to require inspection and rework in order to make the centre bracket less sensitive to external damage that may result in a crack. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 This AD, superseding AD 2007–0204, has been issued to introduce an alternative repeatable inspection procedure. A failed mounting assembly, if not corrected, could result in loss of the engine. The corrective actions include an inspection to determine if there are any sharp edges on the aft engine mounting assembly; repetitive visual inspections, or a combination of visual and fluorescent penetrant inspection, for cracking of the center bracket of the aft engine mounting assembly for both engines; rework of sharp edges; replacement of the aft engine mounting assemblies; and re-identification of engine mounting assemblies and reworked center bracket. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the supplemental NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed in the supplemental NPRM. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 6 products of U.S. registry. We also estimate that it will take about 8 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the 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 E:\FR\FM\17NOR1.SGM 17NOR1 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 AD: 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 AD and placed it in the AD docket. hsrobinson on PROD1PC76 with RULES 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 the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, ■ VerDate Aug<31>2005 17:35 Nov 14, 2008 Jkt 217001 the FAA amends 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: ■ 2008–23–02 Saab Aircraft AB: Amendment 39–15723. Docket No. FAA–2008–0115; Directorate Identifier 2007–NM–240–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 22, 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: Powerplant. Reason (e) The mandatory continuing airworthiness information (MCAI) states: One Part Number (P/N) LM–219–92 Centre Bracket from a P/N 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. EASA Airworthiness Directive (AD) was issued to require inspection and rework in order to make the centre bracket less sensitive to external damage that may result in a crack. This AD, superseding AD 2007–0204, has been issued to introduce an alternative repeatable inspection procedure. A failed mounting assembly, if not corrected, could result in loss of the engine. The corrective actions include an inspection to determine if there are any sharp edges on the aft engine mounting assembly; repetitive visual inspections, or a combination of visual and fluorescent penetrant inspection, for cracking of the center bracket of the aft engine mounting assembly for both engines; rework of sharp edges; replacement of the aft engine mounting assemblies; and reidentification of engine mounting assemblies and reworked center bracket. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 1,000 flight hours after the effective date of this AD, do visual inspections of both the aft engine mounting assemblies to find if the center bracket is correct (no sharp edges) from the manufacturer. (2) If no sharp edge is found during the inspection required by paragraph (f)(1) of this PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 67717 AD, before further flight, inspect to determine if the aft engine mounting assembly and center bracket are identified with a ‘‘–1,’’ and before further flight reidentify the parts that are not identified with a ‘‘–1,’’ in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–71–025, dated June 13, 2007. Following the re-identification, no further action is required by this AD for airplanes on which no sharp edge is found during the inspection required by paragraph (f)(1) of this AD. (3) If any sharp edge is found during the inspection required by paragraph (f)(1) of this AD, before further flight, do the action in paragraph (f)(3)(i) or (f)(3)(ii) of this AD in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 71–025, dated June 13, 2007. (i) Do a general visual inspection for cracking of the center bracket of both of the aft engine mounting assemblies, with the bracket on the wing, and repeat the inspection thereafter at intervals not to exceed 250 flight hours until the action required by paragraph (f)(4) of this AD is accomplished. (ii) Do general visual and penetrant inspections for cracking of the center bracket of both of the aft engine mounting assemblies, with the bracket off the wing. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (4) At the applicable time in paragraph (f)(4)(i) or (f)(4)(ii) of this AD, do the applicable actions in those paragraphs in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 71–025, dated June 13, 2007. Doing the applicable action terminates the repetitive inspection requirements of paragraph (f)(3)(i) of this AD. (i) If no cracking is found during any inspection required by paragraph (f)(3) of this AD: Within 4,000 flight hours after the effective date of this AD, rework the center bracket, and re-identify the aft engine mounting assembly and center bracket. (ii) If any cracking is found during any inspection required by paragraph (f)(3) of this AD, before further flight, replace the aft engine mounting assembly with an assembly and bracket identified with a ‘‘–1’’ part number. (5) Actions done before the effective date of this AD in accordance with Saab Service Bulletin 2000–71–023, Revision 01, dated June 13, 2007, are acceptable for compliance with the corresponding requirements of paragraph (f)(3) of this AD. E:\FR\FM\17NOR1.SGM 17NOR1 67718 Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (f)(4) of this AD requires that you replace a cracked 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, 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. 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 FAAapproved 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. hsrobinson on PROD1PC76 with RULES Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0068, dated April 11, 2008; and Saab Service Bulletin 2000–71–025, dated June 13, 2007; for related information. Material Incorporated by Reference (i) You must use Saab Service Bulletin 2000–71–025, dated June 13, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Saab Aircraft AB, SAAB Aircraft Product Support, S–581.88, ¨ Linkoping, Sweden; telephone 011 46 13 18 5591; fax 011 46 13 18 4874; e-mail https:// www.saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on VerDate Aug<31>2005 17:35 Nov 14, 2008 Jkt 217001 the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 24, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–26364 Filed 11–14–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26598, Directorate Identifier 2006–CE–087–AD; Amendment 39–15733; AD 2008–23–12] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S. A. (EMBRAER) Models EMB–110P1 and EMB–110P2 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: It has been found cases of corrosion at the regions of Wings-to-Fuselage attachments, Vertical Stabilizer to Fuselage attachments, Rib 1 Half wing and Passenger Seat Tracks. Such corrosion may lead to subsequent cracking of the affected parts, compromising the aircraft structural integrity, which may in turn lead to structural failure and/or loss of some control surface. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 22, 2008. On December 22, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 8, 2008 (73 FR 38937). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: It has been found cases of corrosion at the regions of Wings-to-Fuselage attachments, Vertical Stabilizer to Fuselage attachments, Rib 1 Half-wing and Passenger Seat Tracks. Such corrosion may lead to subsequent cracking of the affected parts, compromising the aircraft structural integrity, which may in turn lead to structural failure and/or loss of some control surface. Since this condition may occur in other aircraft of the same type design and affects flight safety, a corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated time limit. Inspection for corrosion at regions of Wings-to-Fuselage attachments, Vertical Stabilizer to Fuselage attachments, Rib 1 Half-wing and Passenger Seat Tracks; and if applicable, removal of the detected corrosion. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Embraer requests the FAA follow the required actions of the MCAI and work together with the operators to issue AMOCs to relieve them when the required actions are positively identified as unnecessary. Embraer does not agree with the technical modifications proposed in the supplemental NPRM. Embraer’s position is that the service instructions developed by Embraer present the necessary actions to adequately address the reported unsafe condition. Embraer also states that instructions presented in EMBRAER Service Bulletin S.B. No.: 110–00–0007, REVISION No.: 01, dated January 12, 2007, and EMBRAER Service Bulletin S.B. No.: 110–57–0026, REVISION No.: 03, dated April 2, 2007, were developed based on findings of severe corrosion in the worldwide EMB–110 fleet. Embraer does recognize that since corrosion growth depends on several variables, E:\FR\FM\17NOR1.SGM 17NOR1

Agencies

[Federal Register Volume 73, Number 222 (Monday, November 17, 2008)]
[Rules and Regulations]
[Pages 67716-67718]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26364]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0115; Directorate Identifier 2007-NM-240-AD; 
Amendment 39-15723; AD 2008-23-02]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB 2000 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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 Part Number (P/N) LM-219-92 Centre Bracket from a P/N 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. We are issuing this AD to require actions to correct the 
unsafe condition on these products.

DATES: This AD becomes effective December 22, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 22, 
2008.

ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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: 

Discussion

    We issued a supplemental notice of proposed rulemaking (NPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That supplemental NPRM was published in the Federal Register 
on August 29, 2008 (73 FR 50903). That supplemental NPRM proposed to 
correct an unsafe condition for the specified products. The MCAI 
states:

    One Part Number (P/N) LM-219-92 Centre Bracket from a P/N 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.
    EASA Airworthiness Directive (AD) was issued to require 
inspection and rework in order to make the centre bracket less 
sensitive to external damage that may result in a crack.
    This AD, superseding AD 2007-0204, has been issued to introduce 
an alternative repeatable inspection procedure.

A failed mounting assembly, if not corrected, could result in loss of 
the engine. The corrective actions include an inspection to determine 
if there are any sharp edges on the aft engine mounting assembly; 
repetitive visual inspections, or a combination of visual and 
fluorescent penetrant inspection, for cracking of the center bracket of 
the aft engine mounting assembly for both engines; rework of sharp 
edges; replacement of the aft engine mounting assemblies; and re-
identification of engine mounting assemblies and reworked center 
bracket. You may obtain further information by examining the MCAI in 
the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the supplemental NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed in the 
supplemental NPRM.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 6 products of U.S. 
registry. We also estimate that it will take about 8 work-hours per 
product to comply with the basic requirements of this AD. The average 
labor rate is $80 per work-hour. Based on these figures, we estimate 
the cost of this AD to the 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

[[Page 67717]]

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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-23-02 Saab Aircraft AB: Amendment 39-15723. Docket No. FAA-
2008-0115; Directorate Identifier 2007-NM-240-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
22, 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: 
Powerplant.

Reason

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

    One Part Number (P/N) LM-219-92 Centre Bracket from a P/N 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.
    EASA Airworthiness Directive (AD) was issued to require 
inspection and rework in order to make the centre bracket less 
sensitive to external damage that may result in a crack.
    This AD, superseding AD 2007-0204, has been issued to introduce 
an alternative repeatable inspection procedure.

A failed mounting assembly, if not corrected, could result in loss 
of the engine. The corrective actions include an inspection to 
determine if there are any sharp edges on the aft engine mounting 
assembly; repetitive visual inspections, or a combination of visual 
and fluorescent penetrant inspection, for cracking of the center 
bracket of the aft engine mounting assembly for both engines; rework 
of sharp edges; replacement of the aft engine mounting assemblies; 
and re-identification of engine mounting assemblies and reworked 
center bracket.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 1,000 flight hours after the effective date of this 
AD, do visual inspections of both the aft engine mounting assemblies 
to find if the center bracket is correct (no sharp edges) from the 
manufacturer.
    (2) If no sharp edge is found during the inspection required by 
paragraph (f)(1) of this AD, before further flight, inspect to 
determine if the aft engine mounting assembly and center bracket are 
identified with a ``-1,'' and before further flight re-identify the 
parts that are not identified with a ``-1,'' in accordance with the 
Accomplishment Instructions of Saab Service Bulletin 2000-71-025, 
dated June 13, 2007. Following the re-identification, no further 
action is required by this AD for airplanes on which no sharp edge 
is found during the inspection required by paragraph (f)(1) of this 
AD.
    (3) If any sharp edge is found during the inspection required by 
paragraph (f)(1) of this AD, before further flight, do the action in 
paragraph (f)(3)(i) or (f)(3)(ii) of this AD in accordance with the 
Accomplishment Instructions of Saab Service Bulletin 2000-71-025, 
dated June 13, 2007.
    (i) Do a general visual inspection for cracking of the center 
bracket of both of the aft engine mounting assemblies, with the 
bracket on the wing, and repeat the inspection thereafter at 
intervals not to exceed 250 flight hours until the action required 
by paragraph (f)(4) of this AD is accomplished.
    (ii) Do general visual and penetrant inspections for cracking of 
the center bracket of both of the aft engine mounting assemblies, 
with the bracket off the wing.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (4) At the applicable time in paragraph (f)(4)(i) or (f)(4)(ii) 
of this AD, do the applicable actions in those paragraphs in 
accordance with the Accomplishment Instructions of Saab Service 
Bulletin 2000-71-025, dated June 13, 2007. Doing the applicable 
action terminates the repetitive inspection requirements of 
paragraph (f)(3)(i) of this AD.
    (i) If no cracking is found during any inspection required by 
paragraph (f)(3) of this AD: Within 4,000 flight hours after the 
effective date of this AD, rework the center bracket, and re-
identify the aft engine mounting assembly and center bracket.
    (ii) If any cracking is found during any inspection required by 
paragraph (f)(3) of this AD, before further flight, replace the aft 
engine mounting assembly with an assembly and bracket identified 
with a ``-1'' part number.
    (5) Actions done before the effective date of this AD in 
accordance with Saab Service Bulletin 2000-71-023, Revision 01, 
dated June 13, 2007, are acceptable for compliance with the 
corresponding requirements of paragraph (f)(3) of this AD.

[[Page 67718]]

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: Although the MCAI or service information allows further 
flight after cracks are found during compliance with the required 
action, paragraph (f)(4) of this AD requires that you replace a 
cracked 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, 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. 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 Airworthiness 
Directive 2008-0068, dated April 11, 2008; and Saab Service Bulletin 
2000-71-025, dated June 13, 2007; for related information.

Material Incorporated by Reference

    (i) You must use Saab Service Bulletin 2000-71-025, dated June 
13, 2007, to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Saab 
Aircraft AB, SAAB Aircraft Product Support, S-581.88, 
Link[ouml]ping, Sweden; telephone 011 46 13 18 5591; fax 011 46 13 
18 4874; e-mail http:www.saab2000.techsupport@saabgroup.com">//www.saab2000.techsupport@saabgroup.com; 
Internet https://www.saabgroup.com.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-26364 Filed 11-14-08; 8:45 am]
BILLING CODE 4910-13-P
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