Airworthiness Directives; The Lancair Company Model LC41-550FG Airplanes, 35370-35372 [05-11880]

Download as PDF 35370 Federal Register / Vol. 70, No. 117 / Monday, June 20, 2005 / Rules and Regulations determine whether a payment is to be issued. (c) For purposes of this subpart, regarding the determination of the APNE, APNEc, APNEf, the LFQ, the LFQc, and the LFQf: (1) If daily quotations are not available for one or more days of the 5day period, the available quotations during the period will be used; (2) If none of the APNE, APNEc, or APNEf prices is available, or if none of the LFQ, LFQc, or LFQf is available, the payment rate shall be zero and shall remain zero unless and until sufficient APNE prices or the LFQ again becomes available, the APNE, APNEc, or APNEf price exceeds the LFQ, the LFQc, or the LFQf, as the case may be, and the LFQ, the LFQc, or the LFQf, as the case may be, adjusted for transportation, is less than 134 percent of the current crop year loan rate for base quality U.S. Pima for 4 consecutive weeks. (d) Payment rates for loose, re-ginned motes and semi-processed motes that are of a suitable quality, without further processing, for spinning, papermaking or bleaching, shall be based on a percentage of the basic rate for baled lint, as specified in the ELS Cotton Domestic User/Exporter Agreement. § 1427.1208 Signed in Washington, DC, on June 2, 2005. James R. Little, Executive Vice President, Commodity Credit Corporation. [FR Doc. 05–12034 Filed 6–17–05; 8:45 am] BILLING CODE 3410–05–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21357; Directorate Identifier 2005–CE–29–AD; Amendment 39– 14136; AD 2005–12–20] RIN 2120–AA64 Payment. (a) Payments under this subpart shall be determined by multiplying: (1) The payment rate, determined under § 1427.127, by (2) The net weight (gross weight minus the weight of bagging and ties) determined under paragraph (b) of this section, of eligible ELS cotton bales that an eligible domestic user opens or an eligible exporter exports during the Friday through Thursday period following a week in which a payment rate is established. (b) For the purposes of this subpart, the net weight shall be based upon: (1) For domestic users, the weight on which settlement for payment of the ELS cotton was based (landed mill weight); (2) For re-ginned motes processed by an end user who converted such motes, without re-baling, to an end use in a continuous manufacturing process, the net weight of the re-ginned motes after final cleaning; (3) For exporters, the shipping warehouse weight or the gin weight if the ELS cotton was not placed in a warehouse, of the eligible cotton unless the exporter obtains and pays the cost of having all the bales in the shipment re-weighed by a licensed weigher and furnishes a copy of the certified weights. (c) For the purposes of this subpart, eligible ELS cotton will be considered: VerDate jul<14>2003 (1) Consumed by the domestic user on the date the bale is opened for consumption; and (2) Exported by the exporter on the date that CCC determines is the date on which the cotton is shipped for export. (d) Payments under this subpart shall be made available upon application for payment and submission of supporting documentation, as required by this subpart, CCC instructions, and the ELS Cotton Domestic User/Exporter Agreement. 14:18 Jun 17, 2005 Jkt 205001 Airworthiness Directives; The Lancair Company Model LC41–550FG Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain The Lancair Company (Lancair) Model LC41–550FG airplanes. This AD requires both visual and dye penetrant inspections of the elevator torque tube assembly for cracks. If a crack is found, this AD requires replacement with a modified assembly that incorporates a steel doubler. This AD also requires replacement of the modified elevator torque tube assembly every 300 hours time-in-service or 18 months (whichever occurs first). This AD results from cracks found in the weld area of the elevator torque tube assembly. We are issuing this AD to detect and correct cracks in the elevator torque tube assembly, which could result in failure of the elevator torque tube assembly and subsequent loss of control of the airplane. This AD becomes effective on June 21, 2005. As of June 21, 2005, the Director of the Federal Register approved the DATES: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 incorporation by reference of certain publications listed in the regulation. We must receive any comments on this AD by August 10, 2005. ADDRESSES: Use one of the following to submit comments on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001. • Fax: 1–202–493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this AD, contact The Lancair Company, 22550 Nelson Road, Bend Oregon 97701; telephone: (541) 330–4191; e-mail: product_ support@lancair.com. To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA–2005–21357. FOR FURTHER INFORMATION CONTACT: Mr. Jeffrey Morfitt, Program Manager, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98055–4065; telephone: (425) 917–6405; facsimile: (425) 917– 6590. SUPPLEMENTARY INFORMATION: What events have caused this AD? Maintenance personnel found a large crack in the weld area on the elevator torque tube assembly during an elevator disassembly of a Lancair Model LC41– 550FG airplane. The airplane had only 54 hours total time-in-service. This incident prompted an inspection of the elevator torque tube assemblies held in inventory at Lancair. The inspection revealed 70 percent of the factory inventory had cracks. A combination of design aspects and manufacturing flaws caused the cracks. These flaws lead to rapid fatigue failure of the elevator torque tube assembly. What is the potential impact if FAA took no action? Cracks in the elevator torque tube assembly could cause the elevator torque tube assembly to fail. This failure could result in loss of control of the airplane. Is there service information that applies to this subject? Lancair has issued Mandatory Service Bulletin No. SB–05–005A, dated May 20, 2005. E:\FR\FM\20JNR1.SGM 20JNR1 Federal Register / Vol. 70, No. 117 / Monday, June 20, 2005 / Rules and Regulations What are the provisions of this service information? The service bulletin includes procedures for inspecting, both visually and with dye penetrant, the elevator torque tube assemblies for cracks. The service bulletin also includes procedures for replacing and reworking cracked elevator torque tube assemblies. FAA’s Determination and Requirements of the AD What has FAA decided? We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Since the unsafe condition described previously is likely to exist or develop on other Lancair Model LC41–550FG airplanes of the same type design, we are issuing this AD to prevent failure of the elevator torque tube assembly. This failure could cause loss of control of the airplane. What does this AD require? This AD requires incorporation of the actions in the previously-referenced service bulletin. In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket. How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs FAA’s AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Comments Invited Will I have the opportunity to comment before you issue the rule? This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21357; Directorate Identifier 2005CE–29–AD’’ in the subject line of your comments. If you want us to acknowledge receipt of your mailed VerDate jul<14>2003 14:48 Jun 17, 2005 Jkt 205001 comments, send us a self-addressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us through a nonwritten communication, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments. Authority for This Rulemaking What authority does FAA have for issuing this rulemaking action? 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 AD. Regulatory Findings Will this AD impact various entities? We have 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. Will this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that 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 summary of the costs to comply with this AD and placed it in PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 35371 the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket FAA–2005–21357; Directorate Identifier 2005–CE–29–AD’’ in your request. 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–12–20 The Lancair Company: Amendment 39–14136; Docket No. FAA–2005–21357; Directorate Identifier 2005-CE–29-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 21, 2005. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model LC41–550F airplanes, serial numbers 41001 through 41082, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD results from cracks found in the weld area of the elevator torque tube assembly. We are issuing this AD to detect and correct cracks in the elevator torque tube assembly, which could result in failure of the elevator torque tube assembly and subsequent loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Note 1: The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05– 005A, Model 400, dated May 20, 2005, allows the pilot to perform the visual inspection of the elevator torque tube assembly. The Federal Aviation Regulations (14 CFR 43.3) only allow the pilot to perform preventive maintenance as described in 14 CFR part 43, App. A, paragraph (c). These visual inspections are not considered preventive maintenance under 14 CFR part 43, App. A, paragraph (c). Therefore, an appropriatelyrated mechanic must perform all actions of this AD. E:\FR\FM\20JNR1.SGM 20JNR1 35372 Federal Register / Vol. 70, No. 117 / Monday, June 20, 2005 / Rules and Regulations Actions Compliance Procedures (1) Visually inspect the area of weld joining the torque tube to the elevator end rib for cracks. Before further flight after June 21, 2005 (the effective date of this AD), and before each flight until the action required in paragraph (e)(2) of this AD is done until a crack is found, whichever occurs first. It is acceptable to do the dye penetrant inspection and modification required in paragraph (e)(2) of this AD before further flight and eliminate the need for the visual inspection(s). Within 10 hours TIS after June 21, 2005 (the effective date of this AD). Doing the dye penetrant inspection and modification terminates the repetitive visual inspection required in paragraph (e)(1) of this AD. This modified elevator torque tube assembly has a safe limit of 300 hours TIS or 18 months after modification, whichever occurs first, and you must replace it at that interval. Any time a crack is found during any inspection required in paragraphs (e)(1) and (e)(2) of this AD. You may do the replacement sooner if desired, in which case, you may discontinue the inspections in paragraphs (e)(1) and (e)(2) of this AD. The new replacement assembly has a safe life limit of 300 hours TIS or 18 months after replacement, whichever occurs first, and you must replace it at that interval. Follow Part 1 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005. (2) Do a dye penetrant inspection of the area of weld joining the torque tube to the elevator end rib for cracks and modify the elevator torque tube assembly by installing a steel doubler. (3) Replace the elevator torque tube assembly with a new assembly that incorporates a steel doubler in the area of weld joining the torque tube to the elevator end rib. Note 2: The compliance times in this AD take precedence over the compliance times in the service information. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Seattle Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact Mr. Jeffrey Morfitt, Program Manager, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98055–4065; telephone: (425) 917–6405; facsimile: (425) 917–6590. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact The Lancair Company 22550 Nelson Road, Bend Oregon 97701; telephone: (541) 330–4191; e-mail: product_support@lancair.com. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ VerDate jul<14>2003 14:18 Jun 17, 2005 Jkt 205001 ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–05– 21357; Directorate Identifier 2005–CE–29– AD. Issued in Kansas City, Missouri, on June 10, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11880 Filed 6–17–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Parts 34 and 131 [Docket No. RM05–11–000; Order No. 657] Electronic Filing of the Application for Authorization for the Issuance of Securities or the Assumption of Liabilities May 27, 2005. Federal Energy Regulatory Commission. ACTION: Final rule. AGENCY: SUMMARY: The Federal Energy Regulatory Commission (Commission) is amending its regulations to provide for PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Follow Part 2 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005, and Revision B to Chapter 4 of Maintenance Manual RC050001, dated May 25, 2005. Follow Part 2 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005, and Revision B to Chapter 4 of Maintenance Manual RC050001, dated May 25, 2005. electronic filing of Applications for Authorization for the Issuance of Securities or the Assumption of Liabilities. The Commission is making these changes as part of its effort to modernize its reporting and filing requirements and to eliminate unnecessary filing burdens for those entities that file applications or reports with the Commission pursuant to 18 CFR part 34. The proposed revisions will reduce the Commission’s and the respondent’s costs by allowing the submission of financial information in electronic format in lieu of the present hard copy format; the type of financial data that jurisdictional entities submit in this application is already routinely stored in electronic format, making hard copy filing of such information burdensome. In this Final Rule the Commission continues to move toward electronic filing, as the Government Paperwork Elimination Act mandates. The modifications in this Final Rule are the result of a review conducted by the Commission’s Information Assessment Team (FIAT), identifying the Commission’s current information collections, evaluating their original purposes and current uses, and proposing ways to reduce the reporting burden on industry through the elimination, reduction, streamlining or reformatting of current collections. EFFECTIVE DATE: The rule will become effective at the time of the next e-filing release during the Commission’s next fiscal year, i.e., no earlier than October E:\FR\FM\20JNR1.SGM 20JNR1

Agencies

[Federal Register Volume 70, Number 117 (Monday, June 20, 2005)]
[Rules and Regulations]
[Pages 35370-35372]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11880]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21357; Directorate Identifier 2005-CE-29-AD; 
Amendment 39-14136; AD 2005-12-20]
RIN 2120-AA64


Airworthiness Directives; The Lancair Company Model LC41-550FG 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain The Lancair Company (Lancair) Model LC41-550FG airplanes. This 
AD requires both visual and dye penetrant inspections of the elevator 
torque tube assembly for cracks. If a crack is found, this AD requires 
replacement with a modified assembly that incorporates a steel doubler. 
This AD also requires replacement of the modified elevator torque tube 
assembly every 300 hours time-in-service or 18 months (whichever occurs 
first). This AD results from cracks found in the weld area of the 
elevator torque tube assembly. We are issuing this AD to detect and 
correct cracks in the elevator torque tube assembly, which could result 
in failure of the elevator torque tube assembly and subsequent loss of 
control of the airplane.

DATES: This AD becomes effective on June 21, 2005.
    As of June 21, 2005, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.
    We must receive any comments on this AD by August 10, 2005.

ADDRESSES: Use one of the following to submit comments on this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: 1-202-493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    To get the service information identified in this AD, contact The 
Lancair Company, 22550 Nelson Road, Bend Oregon 97701; telephone: (541) 
330-4191; e-mail: product_support@lancair.com.
    To view the comments to this AD, go to http://dms.dot.gov. The 
docket number is FAA-2005-21357.

FOR FURTHER INFORMATION CONTACT: Mr. Jeffrey Morfitt, Program Manager, 
FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, 
SW., Renton, Washington 98055-4065; telephone: (425) 917-6405; 
facsimile: (425) 917-6590.

SUPPLEMENTARY INFORMATION:
    What events have caused this AD? Maintenance personnel found a 
large crack in the weld area on the elevator torque tube assembly 
during an elevator disassembly of a Lancair Model LC41-550FG airplane. 
The airplane had only 54 hours total time-in-service.
    This incident prompted an inspection of the elevator torque tube 
assemblies held in inventory at Lancair. The inspection revealed 70 
percent of the factory inventory had cracks.
    A combination of design aspects and manufacturing flaws caused the 
cracks. These flaws lead to rapid fatigue failure of the elevator 
torque tube assembly.
    What is the potential impact if FAA took no action? Cracks in the 
elevator torque tube assembly could cause the elevator torque tube 
assembly to fail. This failure could result in loss of control of the 
airplane.
    Is there service information that applies to this subject? Lancair 
has issued Mandatory Service Bulletin No. SB-05-005A, dated May 20, 
2005.

[[Page 35371]]

    What are the provisions of this service information? The service 
bulletin includes procedures for inspecting, both visually and with dye 
penetrant, the elevator torque tube assemblies for cracks. The service 
bulletin also includes procedures for replacing and reworking cracked 
elevator torque tube assemblies.

FAA's Determination and Requirements of the AD

    What has FAA decided? We have evaluated all pertinent information 
and identified an unsafe condition that is likely to exist or develop 
on other products of this same type design.
    Since the unsafe condition described previously is likely to exist 
or develop on other Lancair Model LC41-550FG airplanes of the same type 
design, we are issuing this AD to prevent failure of the elevator 
torque tube assembly. This failure could cause loss of control of the 
airplane.
    What does this AD require? This AD requires incorporation of the 
actions in the previously-referenced service bulletin.
    In preparing this rule, we contacted type clubs and aircraft 
operators to get technical information and information on operational 
and economic impacts. We did not receive any information through these 
contacts. If received, we would have included a discussion of any 
information that may have influenced this action in the rulemaking 
docket.
    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 
22, 2002), which governs FAA's AD system. This regulation now includes 
material that relates to altered products, special flight permits, and 
alternative methods of compliance. This material previously was 
included in each individual AD. Since this material is included in 14 
CFR part 39, we will not include it in future AD actions.

Comments Invited

    Will I have the opportunity to comment before you issue the rule? 
This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-21357; 
Directorate Identifier 2005-CE-29-AD'' in the subject line of your 
comments. If you want us to acknowledge receipt of your mailed 
comments, send us a self-addressed, stamped postcard with the docket 
number written on it; we will date-stamp your postcard and mail it back 
to you. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it. If a person contacts us through a 
nonwritten communication, and that contact relates to a substantive 
part of this AD, we will summarize the contact and place the summary in 
the docket. We will consider all comments received by the closing date 
and may amend the AD in light of those comments.

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
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 AD.

Regulatory Findings

    Will this AD impact various entities? We have 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket FAA-2005-21357; Directorate Identifier 2005-CE-29-AD'' in 
your request.

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 Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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 airworthiness 
directive (AD):

2005-12-20 The Lancair Company: Amendment 39-14136; Docket No. FAA-
2005-21357; Directorate Identifier 2005-CE-29-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on June 21, 2005.

Are Any Other ADs Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model LC41-550F airplanes, serial numbers 
41001 through 41082, that are certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD results from cracks found in the weld area of the 
elevator torque tube assembly. We are issuing this AD to detect and 
correct cracks in the elevator torque tube assembly, which could 
result in failure of the elevator torque tube assembly and 
subsequent loss of control of the airplane.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

    Note 1: The Lancair Company Certified Aircraft Mandatory Service 
Bulletin SB-05-005A, Model 400, dated May 20, 2005, allows the pilot 
to perform the visual inspection of the elevator torque tube 
assembly. The Federal Aviation Regulations (14 CFR 43.3) only allow 
the pilot to perform preventive maintenance as described in 14 CFR 
part 43, App. A, paragraph (c). These visual inspections are not 
considered preventive maintenance under 14 CFR part 43, App. A, 
paragraph (c). Therefore, an appropriately-rated mechanic must 
perform all actions of this AD.


[[Page 35372]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Visually inspect the      Before further        Follow Part 1 of The
 area of weld joining the      flight after June     Lancair Company
 torque tube to the elevator   21, 2005 (the         Certified Aircraft
 end rib for cracks.           effective date of     Mandatory Service
                               this AD), and         Bulletin SB-05-
                               before each flight    005A, Model 400,
                               until the action      dated May 20, 2005.
                               required in
                               paragraph (e)(2) of
                               this AD is done
                               until a crack is
                               found, whichever
                               occurs first. It is
                               acceptable to do
                               the dye penetrant
                               inspection and
                               modification
                               required in
                               paragraph (e)(2) of
                               this AD before
                               further flight and
                               eliminate the need
                               for the visual
                               inspection(s).
(2) Do a dye penetrant        Within 10 hours TIS   Follow Part 2 of The
 inspection of the area of     after June 21, 2005   Lancair Company
 weld joining the torque       (the effective date   Certified Aircraft
 tube to the elevator end      of this AD). Doing    Mandatory Service
 rib for cracks and modify     the dye penetrant     Bulletin SB-05-
 the elevator torque tube      inspection and        005A, Model 400,
 assembly by installing a      modification          dated May 20, 2005,
 steel doubler.                terminates the        and Revision B to
                               repetitive visual     Chapter 4 of
                               inspection required   Maintenance Manual
                               in paragraph (e)(1)   RC050001, dated May
                               of this AD. This      25, 2005.
                               modified elevator
                               torque tube
                               assembly has a safe
                               limit of 300 hours
                               TIS or 18 months
                               after modification,
                               whichever occurs
                               first, and you must
                               replace it at that
                               interval.
(3) Replace the elevator      Any time a crack is   Follow Part 2 of The
 torque tube assembly with a   found during any      Lancair Company
 new assembly that             inspection required   Certified Aircraft
 incorporates a steel          in paragraphs         Mandatory Service
 doubler in the area of weld   (e)(1) and (e)(2)     Bulletin SB-05-
 joining the torque tube to    of this AD. You may   005A, Model 400,
 the elevator end rib.         do the replacement    dated May 20, 2005,
                               sooner if desired,    and Revision B to
                               in which case, you    Chapter 4 of
                               may discontinue the   Maintenance Manual
                               inspections in        RC050001, dated May
                               paragraphs (e)(1)     25, 2005.
                               and (e)(2) of this
                               AD. The new
                               replacement
                               assembly has a safe
                               life limit of 300
                               hours TIS or 18
                               months after
                               replacement,
                               whichever occurs
                               first, and you must
                               replace it at that
                               interval.
------------------------------------------------------------------------


    Note 2: The compliance times in this AD take precedence over the 
compliance times in the service information.

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Seattle Aircraft 
Certification Office, FAA. For information on any already approved 
alternative methods of compliance, contact Mr. Jeffrey Morfitt, 
Program Manager, FAA, Seattle Aircraft Certification Office (ACO), 
1601 Lind Avenue, SW., Renton, Washington 98055-4065; telephone: 
(425) 917-6405; facsimile: (425) 917-6590.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in The Lancair Company Certified Aircraft Mandatory 
Service Bulletin SB-05-005A, Model 400, dated May 20, 2005. The 
Director of the Federal Register approved the incorporation by 
reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. To get a copy of this service information, 
contact The Lancair Company 22550 Nelson Road, Bend Oregon 97701; 
telephone: (541) 330-4191; e-mail: product_support@lancair.com. To 
review copies of this service information, go to the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030. To view the AD docket, 
go to the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-001 or on the Internet at http://
dms.dot.gov. The docket number is FAA-05-21357; Directorate 
Identifier 2005-CE-29-AD.

    Issued in Kansas City, Missouri, on June 10, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11880 Filed 6-17-05; 8:45 am]
BILLING CODE 4910-13-P