Airworthiness Directives; Aircraft Industries a.s. (Type Certificate G60EU previously held by LETECKÉ ZÁVODY a.s. and LET Aeronautical Works) Model L 23 Super Blanik Sailplane, 78929-78931 [E8-30405]

Download as PDF Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations Installation Prohibition 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 a new airworthiness directive, Amendment 39–15772, to read as follows: ■ 2008–26–06 Rolls-Royce Corporation (Formerly Allison Engine Company): Amendment 39–15772. Docket No. FAA–2008–0975; Directorate Identifier 2008–NE–29–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2009. DEPARTMENT OF TRANSPORTATION (g) After the effective date of this AD, don’t return to service, any HPT stage 2 wheel that was installed in any RRC AE 3007A series engine removed as a result of paragraph (f) of this AD, unless the HPT stage 2 wheel was inspected as specified in RRC Alert Service Bulletin (ASB) AE 3007A-A–72–367, dated September 5, 2008. Alternative Methods of Compliance (h) The Manager, Chicago Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. (i) Alternative Methods of Compliance (AMOCs) currently approved for AD 2008– 19–51 will remain in effect until the effective date for this AD. After that date the AMOCs will expire. Special Flight Permits Affected ADs (b) This AD supersedes emergency AD 2008–19–51. Applicability (c) This AD applies to Rolls-Royce Corporation (RRC) AE 3007A series turbofan engines with high-pressure turbine (HPT) stage 2 wheels, part numbers (P/Ns) 23065892, 23069116, 23069438, 23069592, 23074462, 23074644, 23075345, 23084520, or 23084781, installed. These engines are installed on, but not limited to, Empresa Brasileira de Aeronautica S. A. (EMBRAER) EMB–135 and EMB–145 airplanes. Unsafe Condition (d) This AD results from reports of cracked HPT stage 2 wheels. We are issuing this AD to detect cracks in the HPT stage 2 wheel, which could result in a possible uncontained failure of the HPT stage 2 wheel and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Removing Engines From Service (f) For engines with an HPT stage 2 wheel, P/Ns 23065892, 23069116, 23069438, 23069592, 23074462, 23074644, 23075345, 23084520, or 23084781, remove the engine from service by the cycles-in-service (CIS) specified in Table 1 of this AD. (j) Under 14 CFR part 39.23, we are limiting the special flight permits for this AD by restricting the flight to essential flight crew only. Related Information (k) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; e-mail: kyri.zaroyiannis@faa.gov; telephone (847) 294–7836; fax (847) 294–7834, for more information about this AD. (l) Rolls-Royce Corporation ASB AE 3007A-A–72–367, dated September 5, 2008, contains information on performing ECIs on HPT stage 2 wheels. Contact Rolls-Royce Corporation, P.O. Box 420, Speed Code U15, Indianapolis, IN 46206–0420; e-mail: indy.pubs.services@rolls-royce.com, for a copy of this service information. Material Incorporated by Reference (m) None. Issued in Burlington, Massachusetts, on December 12, 2008. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–30051 Filed 12–23–08; 8:45 am] BILLING CODE 4910–13–P TABLE 1—COMPLIANCE TIMES FOR ENGINE REMOVAL FOR ECI OF THE HPT STAGE 2 WHEELS pwalker on PROD1PC71 with RULES If the HPT stage 2 wheel has accumulated on the effective date of this AD: 16,200 cycles-sincenew (CSN) or more. 15,800 to 16,199 CSN 15,500 to 15,799 CSN VerDate Aug<31>2005 Then remove the engine from service: Within 150 CIS. Within 300 CIS. Within 450 CIS. 19:28 Dec 23, 2008 Jkt 217001 PO 00000 Frm 00013 Fmt 4700 78929 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1138; Directorate Identifier 2008–CE–059–AD; Amendment 39–15778; AD 2008–26–12] RIN 2120–AA64 Airworthiness Directives; Aircraft Industries a.s. (Type Certificate G60EU ´ ´ previously held by LETECKE ZAVODY a.s. and LET Aeronautical Works) Model L 23 Super Blanik Sailplane 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) 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: This Airworthiness Directive (AD) is prompted by the discovery on L 23 SUPER– BLANIK sailplanes of cracks in zones where the front and aft control levers attach the connecting rod designated as ‘‘control bridge’’ on the relevant Illustrated Parts Catalogues (IPC). If left uncorrected cracks could propagate and lead to the breakage of the connecting rod with subsequent loss of control of the sailplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 28, 2009. On January 28, 2009, the Director of the Federal Register approves the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: E:\FR\FM\24DER1.SGM 24DER1 78930 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 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 October 29 (73 FR 64282). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Based on these figures, we estimate the cost of this AD on U.S. operators to be $16,800, or $160 per product. In addition, we estimate that any necessary follow-on actions will take about 7 work-hours and require parts costing $2,000, for a cost of $2,560 per product. We have no way of determining the number of products that may need these actions. This Airworthiness Directive (AD) is prompted by the discovery on L 23 SUPER– BLANIK sailplanes of cracks in zones where the front and aft control levers attach the connecting rod designated as ‘‘control bridge’’ on the relevant Illustrated Parts Catalogues (IPC). If left uncorrected cracks could propagate and lead to the breakage of the connecting rod with subsequent loss of control of the sailplane. For the reasons described above, this AD requires an inspection for cracks of the control bridge and its replacement, as necessary. In addition, this AD requires an update of the aircraft Maintenance Manual (MM) to incorporate repetitive inspections of the control bridge. 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. 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 NPRM or on the determination of the cost to the public. 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 FAA policies. Any such differences are highlighted in a NOTE within the AD. 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 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. Costs of Compliance We estimate that this AD will affect 105 products of U.S. registry. We also estimate that it will take about 2 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD pwalker on PROD1PC71 with RULES Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. VerDate Aug<31>2005 19:28 Dec 23, 2008 Jkt 217001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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, 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: ■ 2008–26–12 Aircraft Industries a.s. (Type Certificate G60EU previously held by ´ ´ LETECKE ZAVODY a.s. and LET Aeronautical Works): Amendment 39– 15778; Docket No. FAA–2008–1138; Directorate Identifier 2008–CE–059–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 28, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Model L 23 Super Blanik sailplanes, all serial numbers, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is prompted by the discovery on L 23 SUPER– BLANIK sailplanes of cracks in zones where the front and aft control levers attach the connecting rod designated as ‘‘control bridge’’ on the relevant Illustrated Parts Catalogues (IPC). If left uncorrected cracks could propagate and lead to the breakage of the connecting rod with subsequent loss of control of the sailplane. For the reasons described above, this AD requires an inspection for cracks of the control bridge and its replacement, as necessary. In addition, this AD requires an update of the aircraft Maintenance Manual (MM) to incorporate repetitive inspections of the control bridge. E:\FR\FM\24DER1.SGM 24DER1 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 3 months after January 28, 2009 (the effective date of this AD) and repetitively thereafter at intervals not to exceed 12 months, visually inspect the control bridge in areas of juncture with the two control sticks for cracks. Do the inspection following paragraph A of LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007, except use a 10X magnifier and do a dye penetrant inspection following the procedures in chapter 5, section 5, of FAA Advisory Circular AC 43.13–1B CHG 1, dated September 27, 2001. (2) If cracks are found in the control bridge bedding during any inspection required in paragraph (f)(1) of this AD, before further flight, replace the defective control bridge bedding, Dwg. No. A740 371N, in the control bridge assembly, Dwg. No. A740 370N, following LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; and Appendix No. 1, ‘‘Replacement of Bearings 608 CSN 024630 at Control Bridge Dwg. No. A740 370N in a Bedding Dwg. No. A740 371N,’’ to LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007. (3) Doing the replacement required in paragraph (f)(2) of this AD terminates the 12month repetitive inspection required in paragraph (f)(1) of this AD. After the replacement required in paragraph (f)(2) of this AD, perform subsequent inspections on the new control bridge assembly according to LET Aircraft Industries, a.s. Documentation Bulletin No.: L23/020 d, dated August 6, 2007. FAA AD Differences pwalker on PROD1PC71 with RULES Note: This AD differs from the MCAI and/ or service information as follows: (1) The service information requires a visual inspection with a 6X magnifier. We are requiring a dye penetrant inspection and a 10X magnifier to detect cracks that could go undetected using only a 6X magnifier. (2) The MCAI requires updating the maintenance manuals to add repetitive inspections of the control bridge. Since the maintenance manual is only one way of establishing a maintenance program, the only way we can mandate these repetitive inspections is through an AD action. We have made these repetitive inspections part of this AD. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329– 4090. Before using any approved AMOC on any sailplane to which the AMOC applies, notify your appropriate principal inspector VerDate Aug<31>2005 19:28 Dec 23, 2008 Jkt 217001 (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 (44 U.S.C. 3501 et seq.), 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) AD No. 2007–0261, dated October 2, 2007; LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; Appendix No. 1, ‘‘Replacement of Bearings 608 CSN 024630 at Control Bridge Dwg. No. A740 370N in a Bedding Dwg. No. A740 371N,’’ to LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; LET Aircraft Industries, a.s. Documentation Bulletin No.: L23/020 d, dated August 6, 2007; and FAA Advisory Circular AC 43.13– 1B CHG 1, dated September 27, 2001, for related information. FAA Advisory Circular AC 43.13–1B CHG 1, dated September 27, 2001, can be found on the Internet at http://rgl.faa.gov/. Material Incorporated by Reference (i) You must use LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; Appendix No. 1, ‘‘Replacement of Bearings 608 CSN 024630 at Control Bridge Dwg. No. A740 370N in a Bedding Dwg. No. A740 371N,’’ to LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; and LET Aircraft Industries, a.s. Documentation Bulletin No.: L23/020 d, dated August 6, 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 Aircraft Industries, a.s. Na ´ Zahonech 1177, 686 04 Kunovice, Czech Republic; phone: +420–572816002; fax: +420–572816006; Internet: http://www.let.cz/. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 78931 Issued in Kansas City, Missouri, on December 16, 2008. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–30405 Filed 12–23–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1250; Directorate Identifier 2008–SW–49–AD; Amendment 39– 15755; AD 2008–17–51] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc. Model MD900 Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. SUMMARY: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2008–17–51, which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires, before further flight, fluorescent magnetic particle inspecting the aft threads of the forward directional control cable (control cable) for a crack and replacing the control cable with an airworthy part if you find a crack. If you do not find a crack, this AD requires that you demagnetize the cable threads until you reach a certain gauss level. This AD also requires visually inspecting the aft cable attach bracket for a crack and for interference with movement of the control cable or for deformation of the aft cable attach bracket. If a crack or interference with movement of the control cable or deformation of the aft cable attach bracket exists, this AD requires replacing the bracket with an airworthy part. This AD also requires modifying the control cable conduit and the rotating cone control rod and identifying the rotating cone control rod with a certain part number. This amendment is prompted by three reports of in-flight failure of the control cable and loss of yaw control resulting in emergency landings and subsequent damage to the helicopter. The actions specified by this AD are intended to prevent loss of yaw control and subsequent loss of control of the helicopter. E:\FR\FM\24DER1.SGM 24DER1

Agencies

[Federal Register Volume 73, Number 248 (Wednesday, December 24, 2008)]
[Rules and Regulations]
[Pages 78929-78931]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-30405]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1138; Directorate Identifier 2008-CE-059-AD; 
Amendment 39-15778; AD 2008-26-12]
RIN 2120-AA64


Airworthiness Directives; Aircraft Industries a.s. (Type 
Certificate G60EU previously held by LETECK[Eacute] Z[Aacute]VODY a.s. 
and LET Aeronautical Works) Model L 23 Super Blanik Sailplane

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) 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:

    This Airworthiness Directive (AD) is prompted by the discovery 
on L 23 SUPER-BLANIK sailplanes of cracks in zones where the front 
and aft control levers attach the connecting rod designated as 
``control bridge'' on the relevant Illustrated Parts Catalogues 
(IPC). If left uncorrected cracks could propagate and lead to the 
breakage of the connecting rod with subsequent loss of control of 
the sailplane.

    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective January 28, 2009.
    On January 28, 2009, the Director of the Federal Register approves 
the incorporation by reference of certain publications listed in this 
AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at Document Management Facility, U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 
20590.

FOR FURTHER INFORMATION CONTACT: Greg Davison, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4130; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

[[Page 78930]]

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 October 29 (73 FR 
64282). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    This Airworthiness Directive (AD) is prompted by the discovery 
on L 23 SUPER-BLANIK sailplanes of cracks in zones where the front 
and aft control levers attach the connecting rod designated as 
``control bridge'' on the relevant Illustrated Parts Catalogues 
(IPC). If left uncorrected cracks could propagate and lead to the 
breakage of the connecting rod with subsequent loss of control of 
the sailplane.
    For the reasons described above, this AD requires an inspection 
for cracks of the control bridge and its replacement, as necessary. 
In addition, this AD requires an update of the aircraft Maintenance 
Manual (MM) to incorporate repetitive inspections of the control 
bridge.

    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 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.

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 FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 105 products of U.S. registry. 
We also estimate that it will take about 2 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 on U.S. 
operators to be $16,800, or $160 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 7 work-hours and require parts costing $2,000, for a cost of 
$2,560 per product. We have no way of determining the number of 
products that may need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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 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 http://
www.regulations.gov; or in person at the Docket Management Facility 
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 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:

2008-26-12 Aircraft Industries a.s. (Type Certificate G60EU 
previously held by LETECK[Eacute] Z[Aacute]VODY a.s. and LET 
Aeronautical Works): Amendment 39-15778; Docket No. FAA-2008-1138; 
Directorate Identifier 2008-CE-059-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
28, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model L 23 Super Blanik sailplanes, all 
serial numbers, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    This Airworthiness Directive (AD) is prompted by the discovery 
on L 23 SUPER-BLANIK sailplanes of cracks in zones where the front 
and aft control levers attach the connecting rod designated as 
``control bridge'' on the relevant Illustrated Parts Catalogues 
(IPC). If left uncorrected cracks could propagate and lead to the 
breakage of the connecting rod with subsequent loss of control of 
the sailplane.
    For the reasons described above, this AD requires an inspection 
for cracks of the control bridge and its replacement, as necessary. 
In addition, this AD requires an update of the aircraft Maintenance 
Manual (MM) to incorporate repetitive inspections of the control 
bridge.

[[Page 78931]]

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 3 months after January 28, 2009 (the 
effective date of this AD) and repetitively thereafter at intervals 
not to exceed 12 months, visually inspect the control bridge in 
areas of juncture with the two control sticks for cracks. Do the 
inspection following paragraph A of LET Aircraft Industries, a.s. 
Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 
12, 2007, except use a 10X magnifier and do a dye penetrant 
inspection following the procedures in chapter 5, section 5, of FAA 
Advisory Circular AC 43.13-1B CHG 1, dated September 27, 2001.
    (2) If cracks are found in the control bridge bedding during any 
inspection required in paragraph (f)(1) of this AD, before further 
flight, replace the defective control bridge bedding, Dwg. No. A740 
371N, in the control bridge assembly, Dwg. No. A740 370N, following 
LET Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, 
Revision No. 2, dated September 12, 2007; and Appendix No. 1, 
``Replacement of Bearings 608 CSN 024630 at Control Bridge Dwg. No. 
A740 370N in a Bedding Dwg. No. A740 371N,'' to LET Aircraft 
Industries, a.s. Mandatory Bulletin MB No. L23/050a, Revision No. 2, 
dated September 12, 2007.
    (3) Doing the replacement required in paragraph (f)(2) of this 
AD terminates the 12-month repetitive inspection required in 
paragraph (f)(1) of this AD. After the replacement required in 
paragraph (f)(2) of this AD, perform subsequent inspections on the 
new control bridge assembly according to LET Aircraft Industries, 
a.s. Documentation Bulletin No.: L23/020 d, dated August 6, 2007.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows:
    (1) The service information requires a visual inspection with a 
6X magnifier. We are requiring a dye penetrant inspection and a 10X 
magnifier to detect cracks that could go undetected using only a 6X 
magnifier.
    (2) The MCAI requires updating the maintenance manuals to add 
repetitive inspections of the control bridge. Since the maintenance 
manual is only one way of establishing a maintenance program, the 
only way we can mandate these repetitive inspections is through an 
AD action. We have made these repetitive inspections part of this 
AD.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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: Greg Davison, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4130; fax: (816) 329-4090. Before using 
any approved AMOC on any sailplane 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 (44 
U.S.C. 3501 et seq.), 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) AD No. 
2007-0261, dated October 2, 2007; LET Aircraft Industries, a.s. 
Mandatory Bulletin MB No. L23/050a, Revision No. 2, dated September 
12, 2007; Appendix No. 1, ``Replacement of Bearings 608 CSN 024630 
at Control Bridge Dwg. No. A740 370N in a Bedding Dwg. No. A740 
371N,'' to LET Aircraft Industries, a.s. Mandatory Bulletin MB No. 
L23/050a, Revision No. 2, dated September 12, 2007; LET Aircraft 
Industries, a.s. Documentation Bulletin No.: L23/020 d, dated August 
6, 2007; and FAA Advisory Circular AC 43.13-1B CHG 1, dated 
September 27, 2001, for related information. FAA Advisory Circular 
AC 43.13-1B CHG 1, dated September 27, 2001, can be found on the 
Internet at http://rgl.faa.gov/.

Material Incorporated by Reference

    (i) You must use LET Aircraft Industries, a.s. Mandatory 
Bulletin MB No. L23/050a, Revision No. 2, dated September 12, 2007; 
Appendix No. 1, ``Replacement of Bearings 608 CSN 024630 at Control 
Bridge Dwg. No. A740 370N in a Bedding Dwg. No. A740 371N,'' to LET 
Aircraft Industries, a.s. Mandatory Bulletin MB No. L23/050a, 
Revision No. 2, dated September 12, 2007; and LET Aircraft 
Industries, a.s. Documentation Bulletin No.: L23/020 d, dated August 
6, 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 
Aircraft Industries, a.s. Na Z[aacute]honech 1177, 686 04 Kunovice, 
Czech Republic; phone: +420-572816002; fax: +420-572816006; 
Internet: http://www.let.cz/.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, 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: http://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on December 16, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-30405 Filed 12-23-08; 8:45 am]
BILLING CODE 4910-13-P