Airworthiness Directive · Amendment 39-14118 · Revo, Incorporated Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 Airplanes
Revo, Incorporated Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 Airplanes
Superseded. A later AD replaced this one: AD 2013-08-14. Comply with the one in force.
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.
The FAA is adopting a new airworthiness directive (AD) to supersede Airworthiness Directive (AD) 98-10-12, which applies to all Revo, Incorporated (REVO) (Type Certificate 1A13 formerly held by Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated Aeronautics, Inc., and Global Amphibians LLC) Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. AD 98-10-12 currently requires you to ensure adequate clearance between the attachment fitting and the horizontal stabilizer rear beam and between the attachment fitting and the stabilizer skin with inspections, possible replacement, and adjustments as necessary. This new AD is the result of several reports of fatigue cracks found in the horizontal stabilizer attachment fitting (part number 2-2200-21) of Model LA-4-200 airplanes that were in compliance with AD 98-10-12. This includes an airplane accident with a fatality attributed to a fatigue crack in the horizontal stabilizer attachment fitting. Consequently, this AD requires either a dye penetrant inspection of the horizontal stabilizer attachment fitting for any evidence of fretting, cracking, or corrosion (with necessary replacement and modification) or replacement of the fittings depending on the number of operational hours on the fitting. The AD also requires you to repetitively replace the fitting every 850 hours time-in-service (TIS), repetitively inspect (visually) the fittings between replacement times, and report to FAA the results of the initial inspection and any cracks found on repetitive inspections. We are issuing this AD to detect, correct, and prevent future cracks in the horizontal stabilizer attachment fitting, which could result in failure of the horizontal stabilizer attachment fitting. This failure could result in loss of control of the airplane.
To address this problem, you must do the following:
| Actions | Compliance | Procedures |
|---|---|---|
| (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): (i) Replace the horizontal stabilizer attachment fitting (part number (P/N) 2-2200-21). (ii) If necessary, trim the horizontal stabilizer rear beam doubler flange to provide positive clearance to the fitting. | Within the next 25 hours TIS after July 8, 2005 (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 | Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the APPENDIX. |
| (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): (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” credit for this, you must have removed the fitting from the airplane when the inspection was done. | Inspect 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 | Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, INSPECTION and REPAIR section and the APPENDIX. |
| (ii) Replace any horizontal stabilizer attachment fitting if you find any cracks, fretting, or corrosion. | ||
| (3) For all airplanes: Repetitively replace the horizontal stabilizer attachment fittings upon accumulating 850 hours TIS on the fittings | Every 850 hours TIS | Follow Revo, Inc. Service Bulletin B-78, dated April 3, 1998, paragraphs 2 and 3 of the INSPECTION and REPAIR section and the APPENDIX. |
| (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 1/16 -inch, trim the skin to provide at least 1/16 -inch gap | Before further flight after any replacement of the fitting required by paragraphs (e)(1), (e)(2), and (e)(3) of this AD | Follow 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 (i) Move the elevator as required to see the fitting, ensuring that the aft face of the fitting is visible (ii) Clean the fitting. Pay special attention to the radius edges of the fitting just outboard of the fitting ear (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 some cracks progress along the forward face of the fitting that is mostly hidden by the horizontal stabilizer rear beam (iv) Reference the sketch on page 1 of the Service Bulletin B-78 to see where the crack is likely to begin | Repetitively inspect at whichever of the following that occurs first (first repetitive starts after the initial inspection or replacement): • 50 hours TIS; or • the next annual inspection Replace the fitting prior to further flight after any inspection where cracks are found | Follow the procedures presented in the Actions column of this paragraph, including the sketch on page 1 of the Service Bulletin B-78. |
| (v) Replace the fitting prior to further flight if cracks are found during any of these inspections. | ||
| (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 this 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 of Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120-0056 | Within 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 | Send 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. |
| (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 | As of July 8, 2005 (the effective date of this AD) | Not Applicable. |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
