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2005-12-02 Revo, Incorporated (Type Certificate 1A13 formerly held by Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated Aeronautics, Inc., and Global Amphibians LLC): Amendment 39-14118; Docket No. FAA-2005-21092; Directorate Identifier 2005-CE-20-AD. \n\nWhen Does This AD Become Effective? \n\n\t(a) This AD becomes effective on July 8, 2005. \n\nAre Any Other ADs Affected By This Action? \n\n\t(b) Yes. This AD supersedes AD 98-10-12; Amendment 39-10524. \n\nWhat Airplanes Are Affected by This AD? \n\n\t(c) This AD affects Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200, all serial numbers, that are certificated in any category. \n\nWhat is the Unsafe Condition Presented in This AD? \n\n\t(d) This AD is the result of several reports of fatigue cracks found in the horizontal stabilizer attachment fitting (part number (P/N) 2-2200-21) of Model LA-4-200 airplanes and one report of a Model LA-4-200 airplane accident with a fatality attributed to a fatigue crack in the horizontal stabilizer attachment fitting. We are issuing this AD to detect, correct, and prevent future cracks in the horizontal stabilizer attachment fitting (P/N 2-2200-21), which could result in failure of the horizontal stabilizer attachment fitting. This failure could result in loss of control of the airplane. \n\nWhat Must I Do To Address This Problem? \n\n\t(e) To address this problem, you must do the following: \n\n\nActions \nCompliance \nProcedures \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(1) For airplanes with 825 hours time-in-service (TIS) or more on any horizontal stabilizer attachment fitting as of July 8, 2005 (the effective date of this AD): \n(i) Replace the horizontal stabilizer attachment fitting (part number (P/N) 2-2200-21). \n(ii) If necessary, trim the horizontal stabilizer rear beam doubler flange to provide positive clearance to the fitting. \nWithin the next 25 hours TIS after July 8, \n2005 (the effective date of this AD) Repetitively replace any horizontal stabilizer attachment fitting (P/N 2-2200-21) thereafter following paragraph (e)(3) of this AD. \nFollow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the APPENDIX. \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(2) For airplanes with less than 825 hours TIS on any horizontal stabilizer attachment fitting as of July 8, 2005 (the effective date of this AD): \n(i) Remove the horizontal stabilizer attachment fitting (P/N 2-2200-21) from the airplane and inspect for cracks (using dye penetrant), fretting, or corrosion. To take "already done" \ncredit for this, you must have removed the fitting from the airplane when the inspection was done. \n(ii) Replace any horizontal stabilizer attachment fitting if you find any cracks, fretting, or corrosion. \nInspect within the next 25 hours TIS after July 8, 2005 (the effective date of this AD), unless already done. If cracks, fretting, or corrosion is found, replace before further flight after the inspection. \nFollow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, INSPECTION and REPAIR section and the APPENDIX. \n\n\n\n\n\n\n\n\n\n(3) For all airplanes: Repetitively replace the horizontal stabilizer attachment fittings upon accumulating 850 hours TIS on the fittings. \nEvery 850 hours TIS \nFollow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the APPENDIX. \n\n\n\n\n\n\n\n\n\n\n\n\n(4) For all airplanes: Measure the gap between the horizontal skin and the horizontal stabilizer attachment fitting (P/N 2-2200-21). If gap is less than 116-inch, trim the skin to provide at least 116-inch gap. \nBefore further flight after any replacement of the fitting required by paragraphs (e)(1), (e)(2), and (e)(3) of this AD. \nFollow Revo, Inc. Service Bulletin B-78, dated April 3, 1998.(5) For all airplanes: Repetitively inspect (visual) the horizontal stabilizer attachedment fitting using the following procedures. \n(i) Move the elevator as required to see the fitting, ensuring that the aft face of the fitting is visible. \n(ii) Clean the fitting. Pay special attention to the radius edges of the fitting just outboard of the fitting ear. \n(iii) Visually inspect the fitting for cracks using a flashlight (a small magnifying glass or borescope is recommended). Pay special attention again to the radius edges just outboard of the fitting ear. Also, inspect as far forward on the edge that is possible because \nsome cracks progress along the forward face of the fitting that is mostly hidden by the horizontal stabilizer rear beam. \n(iv) Reference the sketch on page 1 of the Service Bulletin B-78 to see where the crack is likely to begin. \n(v) Replace the fitting prior to furtherflight if cracks are found during any of these inspections. \nRepetitively inspect at whichever of the following that occurs first (first repetitive starts after the initial inspection or replacement): \n? 50 hours TIS; or \n? the next annual inspection \nReplace the fitting prior to further flight after any inspection where cracks are found. \nFollow the procedures presented in the Actions column of this paragraph, including the sketch on page 1 of the Service Bulletin B-78. \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(6) For all airplanes: Report to FAA the results of the initial inspection required by paragraph (e)(2) of this AD even if no damage is found, and report the results of the repetitive inspections required by paragraph (e)(2) of \nthis AD only if cracks are found. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions \nof Paperwork Reduction Act of 1980(44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120-0056. \nWithin 10 days after the inspection required by paragraph (e)(2) or (e)(5) of this AD or within 10 days after July 8, 2005 (the effective date of this AD), whichever occurs later. \nSend the form (Figure 1 of this AD) to FAA, Atlanta ACO, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703-6078; facsimile: (770) 703-6097. \n\n\n\n\n\n\n\n\n\n\n\n\n(7) For all airplanes: Do not install used serviceable fittings, unless you know the number of accumulated hours TIS and have inspected following the requirements of paragraph (e)(2) of this AD. \nAs of July 8, 2005 (the effective date of this AD). \nNot Applicable. \n\n\n\n\nMay I Request an Alternative Method of Compliance? \n\n\t(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, Atlanta Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Cindy Lorenzen, Aerospace Engineer, FAA, Atlanta ACO, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703-6078; facsimile: (770) 703-6097. \n\nMay I Obtain a Special Flight Permit for the Initial Inspection or Replacement Requirement of This AD? \n\n\t(g) Yes. Special flight permits are allowed for this AD with these limitations: \n\t(1) Vne reduced to 121 m.p.h. (105 knots); and \n\t(2) No flight into known turbulence. \n\nDoes This AD Incorporate Any Material by Reference? \n\n\t(h) You must do the actions required by this AD following the instructions in Revo, Inc. Service Bulletin B-78, dated April 3, 1998. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordancewith 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Revo, Incorporated, 1396 Grandview Boulevard, Kissimmee, FL 34744. 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, S.W., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21092; Directorate Identifier 2005-CE-20-AD.
