Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B Airplanes, 7568-7570 [E9-3398]

Download as PDF 7568 Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules compliance time ‘‘since date of construction’’ of the airplane, this AD requires compliance since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. New Requirements of This AD New Service Bulletin (k) As of the effective date of this AD: Do the actions required by paragraphs (g) and (h) of this AD in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, except as required by paragraph (n) of this AD. Additional Inspection Areas (l) At the applicable compliance time specified in paragraph (g) of this AD, except as provided by paragraph (o) of this AD; or within six months after the effective date of this AD; whichever occurs later: Do an HFEC inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007 (‘‘the service bulletin’’). Repeat the inspection thereafter at the applicable time specified in paragraph 1.D., ‘‘Compliance,’’ of the service bulletin. Application of corrosion-preventive treatment, in accordance with the Accomplishment Instructions of the service bulletin, extends the repetitive inspection interval, as specified in Table 2 in paragraph 1.D., ‘‘Compliance,’’ of the service bulletin. cprice-sewell on PRODPC61 with PROPOSALS Corrective Action for Additional Inspection (m) If any discrepancy is found during any inspection required by paragraph (l) of this AD: Before further flight, perform applicable related investigative/corrective actions in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1, dated August 6, 2007, except as required by paragraph (n) of this AD. Exception to BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1 (n) If BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, specifies to contact the manufacturer for appropriate action, before further flight, repair per a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). (o) Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, Revision 1, dated August 6, 2007, specifies a compliance time after the issuance of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Where BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–182, Revision 1, dated August 6, 2007, specifies a compliance time ‘‘since date of construction’’ of the airplane, this AD requires compliance VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness. another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: No Reporting (p) Although BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 182, dated March 16, 2005; and Revision 1, dated August 6, 2007; specify to submit information to the manufacturer, this AD does not include such a requirement. Two cases of main hydraulic accumulator failure have been reported, one of which was caused by corrosion. Investigation has shown that a severe failure can occur to any of the four hydraulic accumulators which are installed in the hydraulic compartment. Either one of the two end parts on the accumulator may depart from the pressure vessel due to corrosion. This condition, if not corrected, is likely to degrade the functionality of the hydraulic system, possibly resulting in degradation or total loss of control of the landing gear, flap actuation and brakes. A severe failure during flight may even result in debris penetrating and exiting the fuselage outer skin. When such a failure occurs while the aircraft is on the ground, as in the two reported cases, this may cause severe damage to the fuselage and result in injuries to persons nearby. Alternative Methods of Compliance (AMOCs) (q) 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. Send information 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 on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Related Information (r) European Aviation Safety Agency airworthiness directive 2008–0092 R1, dated May 15, 2008, also addresses the subject of this AD. Issued in Renton, Washington, on February 5, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3400 Filed 2–17–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0134; Directorate Identifier 2008–NM–162–AD] RIN 2120–AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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 20, 2009. 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 Aircraft 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 or 425–227–1152. 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 E:\FR\FM\18FEP1.SGM 18FEP1 Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules 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–2009–0134; Directorate Identifier 2008–NM–162–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. cprice-sewell on PRODPC61 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 2008–0146, dated August 1, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Two cases of main hydraulic accumulator failure have been reported, one of which was caused by corrosion. Investigation has shown that a severe failure can occur to any of the four hydraulic accumulators which are installed in the hydraulic compartment. Either one of the two end parts on the accumulator may depart from the pressure vessel due to corrosion. This condition, if not corrected, is likely to degrade the functionality of the hydraulic system, possibly resulting in degradation or total loss of control of the landing gear, flap actuation and brakes. A severe failure during flight may even result in debris penetrating and exiting the fuselage outer skin. When such a failure occurs while the aircraft is on the ground, as in the two reported cases, this may cause severe damage to the fuselage and result in injuries to persons nearby. To address and correct the unsafe condition, a modified hydraulic accumulator VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 has been developed, which is sealed between the barrel and the screw cap and between the screw cap and the end cap. For the reasons described above, this EASA AD requires the replacement of the affected hydraulic accumulators P/N (part number) 08 8423 001 1 and P/N 08 8423 030 1, as identified in Saab SB 340–29–023, with a modified hydraulic accumulator. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Saab has issued Service Bulletin 340– 29–023, dated June 10, 2008. 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 141 products of U.S. registry. We also estimate that it would take 8 workhours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per workhour. Required parts would cost $3,582 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 7569 charge for these costs. 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 $595,302, or $4,222 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, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, E:\FR\FM\18FEP1.SGM 18FEP1 7570 Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules 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–2009–0134; Directorate Identifier 2008–NM–162–AD. Comments Due Date (a) We must receive comments by March 20, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/ SF340A) and SAAB 340B airplanes, all serial numbers, certificated in any category; on which hydraulic accumulators with part number (P/N) 08 8423 001 1 or P/N 08 8423 030 1 are installed, except accumulators with serial numbers listed in paragraph 3.B. of Saab Service Bulletin 340–29–023, dated June 10, 2008. cprice-sewell on PRODPC61 with PROPOSALS Subject (d) Air Transport Association (ATA) of America Code 29: Hydraulic power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Two cases of main hydraulic accumulator failure have been reported, one of which was caused by corrosion. Investigation has shown that a severe failure can occur to any of the four hydraulic accumulators which are installed in the hydraulic compartment. Either one of the two end parts on the accumulator may depart from the pressure vessel due to corrosion. This condition, if not corrected, is likely to degrade the functionality of the hydraulic system, possibly resulting in degradation or total loss of control of the landing gear, flap actuation and brakes. A severe failure during flight may even result in debris penetrating and exiting the fuselage outer skin. When such a failure occurs while the aircraft is on the ground, as in the two reported cases, this may cause severe damage to the fuselage and result in injuries to persons nearby. To address and correct the unsafe condition, a modified hydraulic accumulator has been developed, which is sealed between the barrel and the screw cap and between the screw cap and the end cap. For the reasons described above, [the MCAI] requires the replacement of the affected hydraulic accumulators P/N (part number) 08 8423 001 1 and P/N 08 8423 030 1, as identified in Saab SB 340–29–023, with a modified hydraulic accumulator. VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 Actions and Compliance (f) Unless already done, replace the accumulator at the applicable time specified in paragraph (f)(1) or (f)(2) of this AD in accordance with the instructions of Saab Service Bulletin 340–29–023, dated June 10, 2008. (1) For airplanes on which the manufacturing date of the hydraulic accumulator is June 2000 or earlier: Replace the accumulator with a new or modified accumulator within 24 months after the effective date of this AD. (2) For airplanes on which the manufacturing date of the accumulator is July 2000 or later: Replace the accumulator with a new or modified accumulator within 10 years after the manufacturing date or within 24 months after the effective date of this AD, whichever occurs later. (3) As of 24 months after the effective date of this AD, no person may install a hydraulic accumulator, P/N 08 8423 001 1 or P/N 08 8423 030 1 on any airplane, except accumulators with serial numbers listed in paragraph 3.B. of Saab Service Bulletin 340– 29–023, dated June 10, 2008. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. 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, 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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (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. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0146, dated August 1, 2008, and Saab Service PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 Bulletin 340–29–023, dated June 10, 2008, for related information. Issued in Renton, Washington, on January 30, 2009. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3398 Filed 2–17–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0132; Directorate Identifier 2008–NM–081–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135BJ, –135ER, –135KE, –135KL, –135LR, –145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During aircraft full scale fatigue test, it has been found the occurrence of cracks in the cockpit windshield post lower eyelet fitting at the attachment of the center post on the forward fuselage (SSI 53–10–19). Further analysis of this cracking resulted in modifications on the aircraft Airworthiness Limitation Items (ALI), to include new inspection tasks and its respective intervals. Undetected fatigue cracking in this area could adversely affect the structural integrity of these airplanes. 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 20, 2009. 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– E:\FR\FM\18FEP1.SGM 18FEP1

Agencies

[Federal Register Volume 74, Number 31 (Wednesday, February 18, 2009)]
[Proposed Rules]
[Pages 7568-7570]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3398]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0134; Directorate Identifier 2008-NM-162-AD]
RIN 2120-AA64


Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 
340A (SAAB/SF340A) and SAAB 340B 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:

    Two cases of main hydraulic accumulator failure have been 
reported, one of which was caused by corrosion. Investigation has 
shown that a severe failure can occur to any of the four hydraulic 
accumulators which are installed in the hydraulic compartment. 
Either one of the two end parts on the accumulator may depart from 
the pressure vessel due to corrosion. This condition, if not 
corrected, is likely to degrade the functionality of the hydraulic 
system, possibly resulting in degradation or total loss of control 
of the landing gear, flap actuation and brakes. A severe failure 
during flight may even result in debris penetrating and exiting the 
fuselage outer skin. When such a failure occurs while the aircraft 
is on the ground, as in the two reported cases, this may cause 
severe damage to the fuselage and result in injuries to persons 
nearby.

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 20, 2009.

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 Aircraft 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 or 425-227-1152.

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

[[Page 7569]]

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-2009-0134; 
Directorate Identifier 2008-NM-162-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 2008-0146, dated August 1, 2008 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Two cases of main hydraulic accumulator failure have been 
reported, one of which was caused by corrosion. Investigation has 
shown that a severe failure can occur to any of the four hydraulic 
accumulators which are installed in the hydraulic compartment. 
Either one of the two end parts on the accumulator may depart from 
the pressure vessel due to corrosion. This condition, if not 
corrected, is likely to degrade the functionality of the hydraulic 
system, possibly resulting in degradation or total loss of control 
of the landing gear, flap actuation and brakes. A severe failure 
during flight may even result in debris penetrating and exiting the 
fuselage outer skin. When such a failure occurs while the aircraft 
is on the ground, as in the two reported cases, this may cause 
severe damage to the fuselage and result in injuries to persons 
nearby.
    To address and correct the unsafe condition, a modified 
hydraulic accumulator has been developed, which is sealed between 
the barrel and the screw cap and between the screw cap and the end 
cap.
    For the reasons described above, this EASA AD requires the 
replacement of the affected hydraulic accumulators P/N (part number) 
08 8423 001 1 and P/N 08 8423 030 1, as identified in Saab SB 340-
29-023, with a modified hydraulic accumulator.

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

Relevant Service Information

    Saab has issued Service Bulletin 340-29-023, dated June 10, 2008. 
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 141 products of U.S. registry. We also estimate that it 
would take 8 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Required parts would cost $3,582 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 costs. 
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 $595,302, or $4,222 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, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 7570]]

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-2009-0134; Directorate 
Identifier 2008-NM-162-AD.

Comments Due Date

    (a) We must receive comments by March 20, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Saab AB, Saab Aerosystems Model SAAB 340A 
(SAAB/SF340A) and SAAB 340B airplanes, all serial numbers, 
certificated in any category; on which hydraulic accumulators with 
part number (P/N) 08 8423 001 1 or P/N 08 8423 030 1 are installed, 
except accumulators with serial numbers listed in paragraph 3.B. of 
Saab Service Bulletin 340-29-023, dated June 10, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 29: 
Hydraulic power.

Reason

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

    Two cases of main hydraulic accumulator failure have been 
reported, one of which was caused by corrosion. Investigation has 
shown that a severe failure can occur to any of the four hydraulic 
accumulators which are installed in the hydraulic compartment. 
Either one of the two end parts on the accumulator may depart from 
the pressure vessel due to corrosion. This condition, if not 
corrected, is likely to degrade the functionality of the hydraulic 
system, possibly resulting in degradation or total loss of control 
of the landing gear, flap actuation and brakes. A severe failure 
during flight may even result in debris penetrating and exiting the 
fuselage outer skin. When such a failure occurs while the aircraft 
is on the ground, as in the two reported cases, this may cause 
severe damage to the fuselage and result in injuries to persons 
nearby.
    To address and correct the unsafe condition, a modified 
hydraulic accumulator has been developed, which is sealed between 
the barrel and the screw cap and between the screw cap and the end 
cap.
    For the reasons described above, [the MCAI] requires the 
replacement of the affected hydraulic accumulators P/N (part number) 
08 8423 001 1 and P/N 08 8423 030 1, as identified in Saab SB 340-
29-023, with a modified hydraulic accumulator.

Actions and Compliance

    (f) Unless already done, replace the accumulator at the 
applicable time specified in paragraph (f)(1) or (f)(2) of this AD 
in accordance with the instructions of Saab Service Bulletin 340-29-
023, dated June 10, 2008.
    (1) For airplanes on which the manufacturing date of the 
hydraulic accumulator is June 2000 or earlier: Replace the 
accumulator with a new or modified accumulator within 24 months 
after the effective date of this AD.
    (2) For airplanes on which the manufacturing date of the 
accumulator is July 2000 or later: Replace the accumulator with a 
new or modified accumulator within 10 years after the manufacturing 
date or within 24 months after the effective date of this AD, 
whichever occurs later.
    (3) As of 24 months after the effective date of this AD, no 
person may install a hydraulic accumulator, P/N 08 8423 001 1 or P/N 
08 8423 030 1 on any airplane, except accumulators with serial 
numbers listed in paragraph 3.B. of Saab Service Bulletin 340-29-
023, dated June 10, 2008.

FAA AD Differences

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

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, 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 
principal maintenance inspector (PMI) or principal avionics 
inspector (PAI), as appropriate, or lacking a principal inspector, 
your local Flight Standards District Office.
    (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 2008-0146, dated August 1, 2008, and Saab Service Bulletin 
340-29-023, dated June 10, 2008, for related information.

    Issued in Renton, Washington, on January 30, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3398 Filed 2-17-09; 8:45 am]
BILLING CODE 4910-13-P
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