Airworthiness Directives; Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously the Lancair Company)) Models LC40-550FG, LC41-550FG, and LC42-550FG Airplanes, 66009-66013 [2010-27212]

Download as PDF Federal Register / Vol. 75, No. 207 / Wednesday, October 27, 2010 / Proposed Rules requirements for new Federal buildings and Federal buildings undergoing major renovations. The correction is necessary because the proposed rulemaking referenced the EA number as (DOE–EA– 1463). The correct EA number in the NOPR should be (DOE/EA–1778). DEPARTMENT OF TRANSPORTATION FOR FURTHER INFORMATION CONTACT: RIN 2120–AA64 Margo Appel, U.S. Department of Energy, Office of Energy Efficiency and Renewable Energy, Building Technologies Program, EE–2J, 1000 Independence Avenue, SW., Washington, DC 20585–0121, (202) 586– 9495, e-mail: margo.appel@hq.doe.gov, or Ami Grace-Tardy, U.S. Department of Energy, Office of the General Counsel, Forrestal Building, GC–71, 1000 Independence Avenue, SW., Washington, DC 20585, (202) 586–5709, e-mail: Ami.Grace-Tardy@hq.doe.gov. The U.S. Department of Energy (DOE) published a notice of proposed rulemaking in the Federal Register on October 15, 2010 (75 FR 63404), announcing a public meeting and seeking comments regarding the fossil fuel-generated energy consumption requirements for new Federal buildings and major renovations of Federal buildings. DOE prepared a draft EA for this rulemaking. The draft EA has been added to the docket for this rulemaking. The NOPR incorrectly referenced the EA Number as (DOE–EA–1463) on page 63413, third column, fourth paragraph, third line. The correct EA number in the NOPR should be (DOE/EA–1778). For additional information regarding the NOPR and the public meeting, including detailed instructions for the submission of comments and access to the docket to read background documents or comments received, please refer to the October 15, 2010, notice (75 FR 63404). SUPPLEMENTARY INFORMATION: Issued in Washington, DC, on October 20, 2010. Joseph Hagerman, Acting Program Manager, Building Technologies Program, Energy Efficiency and Renewable Energy. [FR Doc. 2010–27152 Filed 10–26–10; 8:45 am] jlentini on DSKJ8SOYB1PROD with PROPOSALS BILLING CODE 6450–01–P VerDate Mar<15>2010 16:25 Oct 26, 2010 Jkt 223001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1186; Directorate Identifier 2009–CE–065–AD] Airworthiness Directives; Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously the Lancair Company)) Models LC40–550FG, LC41–550FG, and LC42–550FG Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for the products listed above. That NPRM proposed to retain the inspection requirements of AD 2009–09–09 and add a terminating action for the repetitive inspection requirements. That NPRM resulted from the manufacturer developing a modification that, when incorporated, would terminate the repetitive inspections required by AD 2009–09–09. Since we issued the earlier NPRM, the manufacturer revised the service information to include additional airplane serial numbers into the Effectivity section and revised the modification kit instructions. This action revises that NPRM by adding airplanes to the Applicability section and incorporating new service information. We are proposing this supplemental NPRM to retain the inspection requirements of AD 2009– 09–09 and add a terminating action for the repetitive inspection requirements using the revised service information. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this supplemental NPRM by December 13, 2010. 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. SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 66009 • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 942–9006; Internet: https://www.cessna.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4123; fax: (316) 946–4107; e-mail: gary.park@faa.gov. 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–2009–1186; Directorate Identifier 2009–CE–065–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 because of 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. E:\FR\FM\27OCP1.SGM 27OCP1 66010 Federal Register / Vol. 75, No. 207 / Wednesday, October 27, 2010 / Proposed Rules Discussion We issued an NPRM to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Cessna Aircraft Company (Cessna) Models LC40–550FG, LC41– 550FG, and LC42–550FG airplanes. That NPRM was published in the Federal Register on December 17, 2009 (74 FR 66927). That NPRM proposed to supersede AD 2009–09–09 (74 FR 19873, April 30, 2009) with a new AD that would retain the inspection requirements of AD 2009–09–09 and add a terminating action for the repetitive inspection requirements. Actions Since Previous NPRM Was Issued Since we issued the previous NPRM, the manufacturer revised the service information to include additional airplane serial numbers into the Effectivity section and revised the modification kit instructions. requirements of AD 2009–09–09 and adding a terminating action for the repetitive inspection requirements using the revised service information. Cessna has issued Single Engine Service Bulletin SB09–27–01, Revision 3, dated July 20, 2010, which describes procedures for repetitively inspecting the rudder hinges and the rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration. The service information also describes procedures for incorporating Cessna Single Engine Modification Kit MK400– 07–01A, dated July 20, 2010, which when incorporated, will terminate the required repetitive inspections. Comments We gave the public the opportunity to comment on the original NPRM. We received no comments on that NPRM or on the determination of the cost to the public. FAA’s Determination We are proposing this supplemental NPRM because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Certain changes described above expand the scope of the original NPRM. As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this supplemental NPRM. Costs of Compliance We estimate that this proposed AD affects 790 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Proposed Requirements of the Supplemental NPRM This supplemental NPRM would require retaining the inspection ESTIMATED COSTS Action Labor cost Inspecting the rudder hinges and rudder hinge brackets for damage with rudder removed (affects 570 airplanes). Inspecting the rudder hinges and rudder hinge brackets for damage without rudder removed (affects 570 airplanes). Incorporating the modification kit for Models LC40–550FG and LC42– 550FG airplanes (affects 247 airplanes). Incorporating the modification kit for Model LC41–550FG airplanes (affects 523 airplanes). Inspecting the rudder hinge and the rudder brackets attachment hardware for correct thread engagement (affects 20 airplanes). Inspecting the rudder travel (affects 20 airplanes). Parts cost Cost per product Cost on U.S. operators 1.5 work-hours × $85 per hour = $127.50 per inspection cycle. Not applicable ............... $127.50 per inspection cycle. $72,675 per inspection cycle. .5 work-hour × $85 per hour = $42.50 per inspection cycle. Not applicable ............... $42.50 per inspection cycle. $24,225 per inspection cycle. 1 work-hour × $85 per hour = $85. $739 .............................. $824 .............................. $203,528. 1 work-hour × $85 per hour = $85. $848 .............................. $933 .............................. $487,959. .5 work-hour × $85 per hour = $42.50. Not applicable ............... $42.50 ........................... $850. 1 work-hour × $85 per hour = $85. Not applicable ............... $85 ................................ $1,700. We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection of the rudder hinge and the rudder brackets attachment hardware for correct thread engagement and the rudder travel. We have no way of determining the number of aircraft that might need these repairs: ON-CONDITION COSTS jlentini on DSKJ8SOYB1PROD with PROPOSALS Labor cost Repair the rudder hinge and the rudder brackets attachment hardware thread engagement (could affect 20 airplanes). Repair the rudder travel (could affect 20 airplanes) ........................... .5 work-hour × $85 per hour = $42.50 ........... $14 $56.50 .5 work-hour × $85 per hour = $42.50 ........... 14 56.50 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Mar<15>2010 16:25 Oct 26, 2010 Jkt 223001 rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Parts cost Cost per product Action Aviation Programs’’ describes in more detail the scope of the Agency’s authority. E:\FR\FM\27OCP1.SGM 27OCP1 Federal Register / Vol. 75, No. 207 / Wednesday, October 27, 2010 / Proposed Rules (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), (3) Will not affect intrastate aviation in Alaska, and (4) 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 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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: 66011 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): Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously The Lancair Company)): Docket No. FAA–2009–1186; Directorate Identifier 2009–CE–065–AD. Comments Due Date (a) We must receive comments by December 13, 2010. Affected ADs (b) This AD supersedes AD 2009–09–09, Amendment 39–15895. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Applicability (c) This AD applies to the following Cessna Aircraft Company (type certificate previously held by Columbia Aircraft Manufacturing (previously The Lancair Company)) airplane models and serial numbers that are certificated in any category: 1. The authority citation for part 39 continues to read as follows: GROUP 1 AIRPLANES Model Serial Nos. LC40–550FG (300) .............. LC41–550FG (400) .............. 40001, 40002, and 40004 through 40079. 41001 through 41569, 41571 through 41800, 411001 through 411087, 411089 through 411110, 411112 through 411138, 411140, 411142, and 411147. 42001 through 42009, 42011 through 42558, 42560 through 42569, 421001 through 421013, 421015 through 421017, and 421019. LC42–550FG (350) .............. GROUP 2 AIRPLANES Model LC41–550FG (400) .............. LC42–550FG (350) .............. Serial Nos. 41570, 411088, 411111, 411139, 411141, 411143 through 411146, and 411148 through 411153. 42010, 42559, 421014, 421018, and 421020. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 55, Stabilizers. the rudder hinges and the rudder hinge brackets, which could result in failure of the rudder. This failure could lead to loss of control. Unsafe Condition (e) This AD is the result of reports received of a cracked lower rudder hinge bracket on two of the affected airplanes. We are issuing this AD to detect and correct damage, i.e., cracking, deformation, and discoloration, in Compliance (f) To address this problem, you must do the following, unless already done: (1) For Group 1 airplanes specified in paragraph (c) of this AD: Using the compliance times specified in table 1 of this AD, inspect the rudder hinges and rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration. Do the inspections following Cessna Single Engine Service Bulletin SB09–27–01, dated April 13, 2009; Cessna Single Engine Service Bulletin SB09–27–01, Revision 2, dated November 23, 2009; or Cessna Single Engine Service Bulletin SB09–27–01, Revision 3, dated July 20, 2010. jlentini on DSKJ8SOYB1PROD with PROPOSALS TABLE 1—INSPECTION COMPLIANCE TIMES Condition Initially inspect . . . Repetitively inspect . . . (i) For airplanes with 25 hours time-in-service (TIS) or more as of May 11, 2009 (the effective date of AD 2009–09–09): With the rudder removed and using 10× visual magnification, inspect all three rudder hinges and rudder hinge brackets at whichever of the following occurs first: Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done: VerDate Mar<15>2010 16:25 Oct 26, 2010 Jkt 223001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\27OCP1.SGM 27OCP1 66012 Federal Register / Vol. 75, No. 207 / Wednesday, October 27, 2010 / Proposed Rules TABLE 1—INSPECTION COMPLIANCE TIMES—Continued Condition Initially inspect . . . Repetitively inspect . . . (A) Within the next 10 hours TIS after May 11, 2009 (the effective date of AD 2009– 09–09); or (A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets; and (B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed and using 10× visual magnification, inspect all three rudder hinges and rudder hinge brackets. Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done: (B) Within the next 30 days after May 11, 2009 (the effective date of AD 009–09–09). (ii) For airplanes with less than 25 hours TIS as of May 11, 2009 (the effective date of AD 2009–09–09): Without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets, at whichever of the following occurs later: (A) Upon accumulating 25 hours TIS; or ......... jlentini on DSKJ8SOYB1PROD with PROPOSALS (B) Within the next 10 hours TIS after May 11, 2009 (the effective date of AD 2009– 09–09). (2) For Group 1 airplanes specified in paragraph (c) of this AD: Before further flight after any inspection required in paragraphs (f)(1)(i) or (f)(1)(ii) of this AD in which damage is found on any of the rudder hinges and/or rudder hinge brackets, incorporate Cessna Single Engine Modification Kit MK400–27–01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400–27–01A dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09–27–01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09–27–01, Revision 3, dated July 20, 2010. Incorporating either Modification Kit MK400–27–01 or Modification Kit MK400–27–01A, terminates the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. (3) For Group 1 airplanes specified in paragraph (c) of this AD: If the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD become due at the same time, credit for both inspections will be given by doing the rudder removal and 10× visual inspection. (4) For Group 1 airplanes specified in paragraph (c) of this AD: Within the next 24 months after the effective date of this AD, incorporate Cessna Single Engine Modification Kit MK400–27–01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400–27–01A, dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09–27–01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09– 27–01, Revision 3, dated July 20, 2010, unless already done as specified in paragraph (f)(2) of this AD. Incorporating either Modification Kit MK400–27–01 or Modification Kit MK400–27–01A, terminates the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. (5) For Group 1 airplanes specified in paragraph (c) of this AD: At any time after the initial inspections required in paragraphs VerDate Mar<15>2010 16:25 Oct 26, 2010 Jkt 223001 (f)(1)(i) and (f)(1)(ii) of this AD, as long as no damage is found, and no later than the compliance time specified in paragraph (f)(4) of this AD, you may incorporate Cessna Single Engine Modification Kit MK400–27– 01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400–27– 01A, dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09– 27–01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09–27–01, Revision 3, dated July 20, 2010, to terminate the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. (6) For any Group 1 airplane with Cessna Single Engine Service Bulletin SB09–27–01, Revision 1, dated August 31, 2009, already incorporated and for all Group 2 airplanes: Within the next 30 days after the effective date of this AD, inspect for proper rudder hinge and rudder bracket hardware thread engagement and inspect the rudder travel. Do these inspections following the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27– 01, dated November 23, 2009; or the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27– 01A, dated July 20, 2010. (i) Before further flight after the inspection required in paragraph (f)(6) of this AD, if any discrepancies are found in the rudder hinge or rudder bracket hardware, replace the affected hardware. Do the replacements following the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27–01, dated November 23, 2009; or the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27– 01A, dated July 20, 2010. (ii) Before further flight after the inspection required in paragraph (f)(6) of this AD, if the rudder travel is outside the limits specified in the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27–01, dated November 23, 2009; or PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 (A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets; and (B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed and using 10× visual magnification, inspect all three rudder hinges and rudder hinge brackets. the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400–27– 01A, dated July 20, 2010, reinstall the rudder following the Accomplishment Instructions in either Cessna Single Engine Modification Kit MK400–27–01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400–27–01A, dated July 20, 2010. (iii) After the inspection and any necessary corrective actions required in paragraphs (f)(6), (f)(6)(i), and (f)(6)(ii) of this AD, no further action is required. Credit for Actions Accomplished in Accordance With Previous Service Information (g) For all airplanes specified in paragraph (c) of this AD: As of the effective date of this AD, if Cessna Single Engine Service Bulletin SB09–27–01, Revision 2, dated November 23, 2009, has been already been incorporated, no further action is required. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (3) AMOCs approved for AD 2009–09–09 are approved for this AD. Related Information (i) For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, E:\FR\FM\27OCP1.SGM 27OCP1 Federal Register / Vol. 75, No. 207 / Wednesday, October 27, 2010 / Proposed Rules Room 100, Wichita, Kansas 67209; telephone: (316) 946–4123; fax: (316) 946–4107; e-mail: gary.park@faa.gov. (j) For service information identified in this AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 942–9006; Internet: https:// www.cessna.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. Issued in Kansas City, Missouri, on October 21, 2010. Christina L. Marsh, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–27212 Filed 10–26–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2010–0843; Airspace Docket No. 10–ASW–12] Proposed Amendment of Class E Airspace; Horseshoe Bay, TX Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend Class E airspace at Horseshoe Bay, TX. Decommissioning of the Horseshoe Bay Resort non-directional beacon (NDB) at Horseshoe Bay Resort Airport, Horseshoe Bay, TX, has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport. DATES: 0901 UTC. Comments must be received on or before December 13, 2010. SUMMARY: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. You must identify the docket number FAA–2010– 0843/Airspace Docket No. 10–ASW–12, at the beginning of your comments. You may also submit comments through the Internet at https://www.regulations.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– jlentini on DSKJ8SOYB1PROD with PROPOSALS ADDRESSES: VerDate Mar<15>2010 16:25 Oct 26, 2010 Jkt 223001 5527), is on the ground floor of the building at the above address. FOR FURTHER INFORMATION CONTACT: Scott Enander, Central Service Center, Operations Support Group, Federal Aviation Administration, Southwest Region, 2601 Meacham Blvd, Fort Worth, TX 76137; telephone: (817) 321– 7716. SUPPLEMENTARY INFORMATION: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers and be submitted in triplicate to the address listed above. Commenters wishing the FAA to acknowledge receipt of their comments on this notice must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. FAA–2010–0843/Airspace Docket No. 10–ASW–12.’’ The postcard will be date/time stamped and returned to the commenter. Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at https://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https:// www.faa.gov/airports_airtraffic/ air_traffic/publications/ airspace_amendments/. You may review the public docket containing the proposal, any comments received and any final disposition in person in the Dockets Office (see ADDRESSES section for address and phone number) between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the office of the Central Service Center, 2601 Meacham Blvd, Fort Worth, TX 76137. Persons interested in being placed on a mailing list for future NPRMs should contact the FAA’s Office of Rulemaking (202) 267–9677, to request a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 66013 The Proposal This action proposes to amend Title 14, Code of Federal Regulations (14 CFR), part 71 by modifying Class E airspace extending upward from 700 feet above the surface for standard instrument approach procedures at Horseshoe Bay Resort Airport, Horseshoe Bay, TX. Airspace reconfiguration is necessary due to the decommissioning of the Horseshoe Bay Resort NDB and the cancellation of the NDB approach. This action would also reflect the name change of the airport from Horseshoe Bay Airpark to Horseshoe Bay Resort Airport. Controlled airspace is necessary for the safety and management of IFR operations at the airport. Class E airspace areas are published in Paragraph 6005 of FAA Order 7400.9U, dated August 18, 2010, and effective September 15, 2010, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document would be published subsequently in the Order. The FAA has determined that this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore, (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) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the U.S. Code. Subtitle 1, section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in subtitle VII, part A, subpart I, section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it would modify controlled airspace at Horseshoe Bay Resort Airport, Horseshoe Bay, TX. E:\FR\FM\27OCP1.SGM 27OCP1

Agencies

[Federal Register Volume 75, Number 207 (Wednesday, October 27, 2010)]
[Proposed Rules]
[Pages 66009-66013]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-27212]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company (Type 
Certificate Previously Held by Columbia Aircraft Manufacturing 
(Previously the Lancair Company)) Models LC40-550FG, LC41-550FG, and 
LC42-550FG Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for the products listed above. That NPRM proposed to retain the 
inspection requirements of AD 2009-09-09 and add a terminating action 
for the repetitive inspection requirements. That NPRM resulted from the 
manufacturer developing a modification that, when incorporated, would 
terminate the repetitive inspections required by AD 2009-09-09. Since 
we issued the earlier NPRM, the manufacturer revised the service 
information to include additional airplane serial numbers into the 
Effectivity section and revised the modification kit instructions. This 
action revises that NPRM by adding airplanes to the Applicability 
section and incorporating new service information. We are proposing 
this supplemental NPRM to retain the inspection requirements of AD 
2009-09-09 and add a terminating action for the repetitive inspection 
requirements using the revised service information. Since these actions 
impose an additional burden over that proposed in the NPRM, we are 
reopening the comment period to allow the public the chance to comment 
on these proposed changes.

DATES: We must receive comments on this supplemental NPRM by December 
13, 2010.

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 W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Cessna 
Aircraft Company, Product Support, P.O. Box 7706; Wichita, Kansas 
67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet: https://www.cessna.com. You may review copies of the referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call 816-329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita 
Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107; 
e-mail: gary.park@faa.gov.

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-2009-1186; 
Directorate Identifier 2009-CE-065-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 because of 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.

[[Page 66010]]

Discussion

    We issued an NPRM to amend 14 CFR part 39 to include an 
airworthiness directive (AD) that would apply to certain Cessna 
Aircraft Company (Cessna) Models LC40-550FG, LC41-550FG, and LC42-550FG 
airplanes. That NPRM was published in the Federal Register on December 
17, 2009 (74 FR 66927). That NPRM proposed to supersede AD 2009-09-09 
(74 FR 19873, April 30, 2009) with a new AD that would retain the 
inspection requirements of AD 2009-09-09 and add a terminating action 
for the repetitive inspection requirements.

Actions Since Previous NPRM Was Issued

    Since we issued the previous NPRM, the manufacturer revised the 
service information to include additional airplane serial numbers into 
the Effectivity section and revised the modification kit instructions.

Comments

    We gave the public the opportunity to comment on the original NPRM. 
We received no comments on that NPRM or on the determination of the 
cost to the public.

FAA's Determination

    We are proposing this supplemental NPRM because we evaluated all 
the relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design. Certain changes described above expand the scope of the 
original NPRM. As a result, we have determined that it is necessary to 
reopen the comment period to provide additional opportunity for the 
public to comment on this supplemental NPRM.

Proposed Requirements of the Supplemental NPRM

    This supplemental NPRM would require retaining the inspection 
requirements of AD 2009-09-09 and adding a terminating action for the 
repetitive inspection requirements using the revised service 
information.
    Cessna has issued Single Engine Service Bulletin SB09-27-01, 
Revision 3, dated July 20, 2010, which describes procedures for 
repetitively inspecting the rudder hinges and the rudder hinge brackets 
for damage, i.e., cracking, deformation, and discoloration. The service 
information also describes procedures for incorporating Cessna Single 
Engine Modification Kit MK400-07-01A, dated July 20, 2010, which when 
incorporated, will terminate the required repetitive inspections.

Costs of Compliance

    We estimate that this proposed AD affects 790 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspecting the rudder hinges and  1.5 work-hours x    Not applicable....  $127.50 per         $72,675 per
 rudder hinge brackets for         $85 per hour =                          inspection cycle.   inspection cycle.
 damage with rudder removed        $127.50 per
 (affects 570 airplanes).          inspection cycle.
Inspecting the rudder hinges and  .5 work-hour x $85  Not applicable....  $42.50 per          $24,225 per
 rudder hinge brackets for         per hour = $42.50                       inspection cycle.   inspection cycle.
 damage without rudder removed     per inspection
 (affects 570 airplanes).          cycle.
Incorporating the modification    1 work-hour x $85   $739..............  $824..............  $203,528.
 kit for Models LC40-550FG and     per hour = $85.
 LC42-550FG airplanes (affects
 247 airplanes).
Incorporating the modification    1 work-hour x $85   $848..............  $933..............  $487,959.
 kit for Model LC41-550FG          per hour = $85.
 airplanes (affects 523
 airplanes).
Inspecting the rudder hinge and   .5 work-hour x $85  Not applicable....  $42.50............  $850.
 the rudder brackets attachment    per hour = $42.50.
 hardware for correct thread
 engagement (affects 20
 airplanes).
Inspecting the rudder travel      1 work-hour x $85   Not applicable....  $85...............  $1,700.
 (affects 20 airplanes).           per hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection of 
the rudder hinge and the rudder brackets attachment hardware for 
correct thread engagement and the rudder travel. We have no way of 
determining the number of aircraft that might need these repairs:

                           On-Condition Costs
------------------------------------------------------------------------
                                                               Cost per
            Action                Labor cost     Parts cost    product
------------------------------------------------------------------------
Repair the rudder hinge and    .5 work-hour x           $14       $56.50
 the rudder brackets            $85 per hour =
 attachment hardware thread     $42.50.
 engagement (could affect 20
 airplanes).
Repair the rudder travel       .5 work-hour x            14        56.50
 (could affect 20 airplanes).   $85 per hour =
                                $42.50.
------------------------------------------------------------------------

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.

[[Page 66011]]

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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, 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 
airworthiness directive (AD):

Cessna Aircraft Company (Type Certificate Previously Held by 
Columbia Aircraft Manufacturing (Previously The Lancair Company)): 
Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD.

Comments Due Date

    (a) We must receive comments by December 13, 2010.

Affected ADs

    (b) This AD supersedes AD 2009-09-09, Amendment 39-15895.

Applicability

    (c) This AD applies to the following Cessna Aircraft Company 
(type certificate previously held by Columbia Aircraft Manufacturing 
(previously The Lancair Company)) airplane models and serial numbers 
that are certificated in any category:

                            Group 1 Airplanes
------------------------------------------------------------------------
            Model                             Serial Nos.
------------------------------------------------------------------------
LC40-550FG (300).............  40001, 40002, and 40004 through 40079.
LC41-550FG (400).............  41001 through 41569, 41571 through 41800,
                                411001 through 411087, 411089 through
                                411110, 411112 through 411138, 411140,
                                411142, and 411147.
LC42-550FG (350).............  42001 through 42009, 42011 through 42558,
                                42560 through 42569, 421001 through
                                421013, 421015 through 421017, and
                                421019.
------------------------------------------------------------------------


                            Group 2 Airplanes
------------------------------------------------------------------------
            Model                             Serial Nos.
------------------------------------------------------------------------
LC41-550FG (400).............  41570, 411088, 411111, 411139, 411141,
                                411143 through 411146, and 411148
                                through 411153.
LC42-550FG (350).............  42010, 42559, 421014, 421018, and 421020.
------------------------------------------------------------------------

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 55, Stabilizers.

Unsafe Condition

    (e) This AD is the result of reports received of a cracked lower 
rudder hinge bracket on two of the affected airplanes. We are 
issuing this AD to detect and correct damage, i.e., cracking, 
deformation, and discoloration, in the rudder hinges and the rudder 
hinge brackets, which could result in failure of the rudder. This 
failure could lead to loss of control.

Compliance

    (f) To address this problem, you must do the following, unless 
already done:
    (1) For Group 1 airplanes specified in paragraph (c) of this AD: 
Using the compliance times specified in table 1 of this AD, inspect 
the rudder hinges and rudder hinge brackets for damage, i.e., 
cracking, deformation, and discoloration. Do the inspections 
following Cessna Single Engine Service Bulletin SB09-27-01, dated 
April 13, 2009; Cessna Single Engine Service Bulletin SB09-27-01, 
Revision 2, dated November 23, 2009; or Cessna Single Engine Service 
Bulletin SB09-27-01, Revision 3, dated July 20, 2010.

                  Table 1--Inspection Compliance Times
------------------------------------------------------------------------
                               Initially inspect .  Repetitively inspect
          Condition                    . .                  . . .
------------------------------------------------------------------------
(i) For airplanes with 25     With the rudder       Thereafter inspect
 hours time-in-service (TIS)   removed and using     as follows until
 or more as of May 11, 2009    10x visual            the modification
 (the effective date of AD     magnification,        required in
 2009-09-09):                  inspect all three     paragraph (f)(5) of
                               rudder hinges and     this AD is done:
                               rudder hinge
                               brackets at
                               whichever of the
                               following occurs
                               first:

[[Page 66012]]

 
                              (A) Within the next   (A) Every 25 hours
                               10 hours TIS after    TIS or 3 months,
                               May 11, 2009 (the     whichever occurs
                               effective date of     first, without
                               AD 2009-09-09); or    removing the
                                                     rudder, visually
                                                     inspect all three
                                                     rudder hinges and
                                                     rudder hinge
                                                     brackets; and
                              (B) Within the next   (B) Every 50 hours
                               30 days after May     TIS or 6 months,
                               11, 2009 (the         whichever occurs
                               effective date of     first, with the
                               AD 009-09-09).        rudder removed and
                                                     using 10x visual
                                                     magnification,
                                                     inspect all three
                                                     rudder hinges and
                                                     rudder hinge
                                                     brackets.
(ii) For airplanes with less  Without removing the  Thereafter inspect
 than 25 hours TIS as of May   rudder, visually      as follows until
 11, 2009 (the effective       inspect all three     the modification
 date of AD 2009-09-09):       rudder hinges and     required in
                               rudder hinge          paragraph (f)(5) of
                               brackets, at          this AD is done:
                               whichever of the
                               following occurs
                               later:
                              (A) Upon              (A) Every 25 hours
                               accumulating 25       TIS or 3 months,
                               hours TIS; or.        whichever occurs
                                                     first, without
                                                     removing the
                                                     rudder, visually
                                                     inspect all three
                                                     rudder hinges and
                                                     rudder hinge
                                                     brackets; and
                              (B) Within the next   (B) Every 50 hours
                               10 hours TIS after    TIS or 6 months,
                               May 11, 2009 (the     whichever occurs
                               effective date of     first, with the
                               AD 2009-09-09).       rudder removed and
                                                     using 10x visual
                                                     magnification,
                                                     inspect all three
                                                     rudder hinges and
                                                     rudder hinge
                                                     brackets.
------------------------------------------------------------------------

     (2) For Group 1 airplanes specified in paragraph (c) of this 
AD: Before further flight after any inspection required in 
paragraphs (f)(1)(i) or (f)(1)(ii) of this AD in which damage is 
found on any of the rudder hinges and/or rudder hinge brackets, 
incorporate Cessna Single Engine Modification Kit MK400-27-01, dated 
November 23, 2009; or Cessna Single Engine Modification Kit MK400-
27-01A dated July 20, 2010, as specified in Cessna Single Engine 
Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; 
and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, 
dated July 20, 2010. Incorporating either Modification Kit MK400-27-
01 or Modification Kit MK400-27-01A, terminates the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (3) For Group 1 airplanes specified in paragraph (c) of this AD: 
If the repetitive inspections required in paragraphs (f)(1)(i) and 
(f)(1)(ii) of this AD become due at the same time, credit for both 
inspections will be given by doing the rudder removal and 10x visual 
inspection.
    (4) For Group 1 airplanes specified in paragraph (c) of this AD: 
Within the next 24 months after the effective date of this AD, 
incorporate Cessna Single Engine Modification Kit MK400-27-01, dated 
November 23, 2009; or Cessna Single Engine Modification Kit MK400-
27-01A, dated July 20, 2010, as specified in Cessna Single Engine 
Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; 
and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, 
dated July 20, 2010, unless already done as specified in paragraph 
(f)(2) of this AD. Incorporating either Modification Kit MK400-27-01 
or Modification Kit MK400-27-01A, terminates the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (5) For Group 1 airplanes specified in paragraph (c) of this AD: 
At any time after the initial inspections required in paragraphs 
(f)(1)(i) and (f)(1)(ii) of this AD, as long as no damage is found, 
and no later than the compliance time specified in paragraph (f)(4) 
of this AD, you may incorporate Cessna Single Engine Modification 
Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine 
Modification Kit MK400-27-01A, dated July 20, 2010, as specified in 
Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated 
November 23, 2009; and Cessna Single Engine Service Bulletin SB09-
27-01, Revision 3, dated July 20, 2010, to terminate the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (6) For any Group 1 airplane with Cessna Single Engine Service 
Bulletin SB09-27-01, Revision 1, dated August 31, 2009, already 
incorporated and for all Group 2 airplanes: Within the next 30 days 
after the effective date of this AD, inspect for proper rudder hinge 
and rudder bracket hardware thread engagement and inspect the rudder 
travel. Do these inspections following the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009; or the Accomplishment Instructions in 
Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 
2010.
    (i) Before further flight after the inspection required in 
paragraph (f)(6) of this AD, if any discrepancies are found in the 
rudder hinge or rudder bracket hardware, replace the affected 
hardware. Do the replacements following the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009; or the Accomplishment Instructions in 
Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 
2010.
    (ii) Before further flight after the inspection required in 
paragraph (f)(6) of this AD, if the rudder travel is outside the 
limits specified in the Accomplishment Instructions in Cessna Single 
Engine Modification Kit MK400-27-01, dated November 23, 2009; or the 
Accomplishment Instructions in Cessna Single Engine Modification Kit 
MK400-27-01A, dated July 20, 2010, reinstall the rudder following 
the Accomplishment Instructions in either Cessna Single Engine 
Modification Kit MK400-27-01, dated November 23, 2009; or Cessna 
Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
    (iii) After the inspection and any necessary corrective actions 
required in paragraphs (f)(6), (f)(6)(i), and (f)(6)(ii) of this AD, 
no further action is required.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (g) For all airplanes specified in paragraph (c) of this AD: As 
of the effective date of this AD, if Cessna Single Engine Service 
Bulletin SB09-27-01, Revision 2, dated November 23, 2009, has been 
already been incorporated, no further action is required.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (3) AMOCs approved for AD 2009-09-09 are approved for this AD.

Related Information

    (i) For more information about this AD, contact Gary Park, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road,

[[Page 66013]]

Room 100, Wichita, Kansas 67209; telephone: (316) 946-4123; fax: 
(316) 946-4107; e-mail: gary.park@faa.gov.
    (j) For service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; 
Internet: https://www.cessna.com. You may review copies of the 
referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
816-329-4148.

    Issued in Kansas City, Missouri, on October 21, 2010.
Christina L. Marsh,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-27212 Filed 10-26-10; 8:45 am]
BILLING CODE 4910-13-P