Airworthiness Directive · Amendment 39-17431 · Stabilizers
Revo, Incorporated Airplanes
This AD applies to the following Revo, Incorporated Models COLONIAL C-1, COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes, all serial numbers, that are certificated in any category, and have horizontal stabilizer attachment fittings part number (P/N) 1-2200-14, 2200-14, or 2-2200-21 installed.
We are superseding an existing airworthiness directive (AD) for certain Revo, Incorporated Models COLONIAL C-1, COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes. That AD currently requires a one-time, dye-penetrant inspection of the horizontal stabilizer attachment fitting and repetitive visual inspections of the fitting for any evidence of fretting, cracking, or corrosion (with necessary replacement and modification); replacement of the fitting upon reaching the 850-hours time-in-service (TIS) safe life; and reporting to the FAA the results of the initial inspection and any cracks found on repetitive inspections. This new AD requires the same actions of AD 2005-12-02 except using revised service documents and procedures, adds Model COLONIAL C-1 airplanes to the Applicability, and adds an optional terminating action for the requirements. This AD was prompted by a report from Revo, Incorporated that, while the drawing numbers are different, the attachment fittings on the Model COLONIAL C-1 airplanes are identical in every other respect to those installed on the airplanes referenced in AD 2005-12- 02. We are issuing this AD to correct the unsafe condition on these products.
(1) This AD provides credit for the actions in paragraph (h)(1) of this AD, if the dye penetrant inspection was done before the effective date of this AD, following Revo Inc. Service Bulletin B-78 R2, Revision 2, dated October 26, 2011; Revo Inc. Service Bulletin B-78 R1, Revision 1, dated July 26, 2005; or Revo Inc. Service Bulletin B-78, dated April 3, 1998. However; the horizontal stabilizer attachment fitting must have been removed from the airplane during the inspection.
(2) This AD provides credit for the actions in paragraphs (h)(2) and (j)(1) of this AD, if the horizontal stabilizer attachment fitting has been replaced before the effective date of this AD, following Revo Inc. Service Bulletin B-78 R2, Revision 2, dated October 26, 2011; Revo Inc. Service Bulletin B-78 R1, Revision 1, dated July 26, 2005; or Revo Inc. Service Bulletin B-78, dated April 3, 1998.
(1) For airplanes with less than 825 hours time-in-service (TIS) on any horizontal stabilizer attachment fitting: Remove the horizontal stabilizer attachment (P/N 1-2200-14, 2200-14, or 2-2200-21) from the airplane and do a one-time dye-penetrant inspection for cracks, fretting, or corrosion using the applicable compliance times and service information stated below.
(i) For COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes: Within the next 25 hours TIS after July 8, 2005 (the effective date of AD 2005-12-02 (70 FR 33820, June 10, 2005)). Follow Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012; Revo Inc. Service Bulletin B-78 R2, Revision 2, dated October 26, 2011; Revo Inc. Service Bulletin B-78 R1, Revision 1, dated July 26, 2005; or Revo Inc. Service Bulletin B-78, dated April 3, 1998 (which was incorporated by reference in AD 2005-12-02 and is retained in this AD).
(ii) For COLONIAL C-1 airplanes: Within the next 25 hours TIS after June 13, 2013 (the effective date of this AD). Follow Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012.
(2) If cracks, fretting, or corrosion is found during the inspection required in paragraph (h)(1) of this AD, before further flight, replace the horizontal stabilizer attachment with an airworthy P/N 2-2200-21, P/N 1-2200-14, or 2200-14 following Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012. After replacement with an airworthy part, the repetitive inspections specified in paragraph (i) of this AD and the repetitive replacements specified in paragraph (j) of this AD are still required.
(3) For the purposes of this AD, an airworthy part is defined as a new part or a used part that has less than 850 hours TIS and has been inspected following paragraph (h)(1) of this AD and found free of cracks, fretting, or corrosion before installation.
(1) Within 50 hours TIS or 12 months, whichever occurs first, after the dye-penetrant inspection required in paragraph (h)(1) of this AD or after replacement of the fitting required in paragraphs (h)(2), (i)(2), or (j) of this AD and repetitively thereafter at intervals not to exceed 50 hours TIS or 12 months, whichever occurs first, visually inspect the horizontal stabilizer attachment 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 Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012, to see where the crack is likely to begin.
(2) If any cracks are found during any of the inspections required in paragraph (i) of this AD, before further flight, replace the fitting with an airworthy part following Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012.
(3) For the purposes of this AD, an airworthy part is defined as a new part or a used part that has less than 850 hours TIS and has been inspected following paragraph (h)(1) of this AD and found free of cracks, fretting, or corrosion before installation.
(1) For COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes: Before or when the horizontal stabilizer attachment fitting accumulates 850 hours TIS or within 25 hours TIS after July 8, 2005 (the effective date of AD 2005-12-02 (70 FR 33820, June 10, 2005)), whichever occurs later, and repetitively thereafter at intervals not to exceed 850 hours TIS replace the horizontal stabilizer attachment fitting P/N 1-2200-14, 2200-14, or 2-2200-21 with an airworthy part. Follow Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012; Revo Inc. Service Bulletin B-78 R2, Revision 2, dated October 26, 2011; Revo Inc. Service Bulletin B-78 R1, Revision 1, dated July 26, 2005; or Revo Inc. Service Bulletin B-78, dated April 3, 1998 (which was incorporated by reference in AD 2005-12-02 and is retained in this AD).
(2) For COLONIAL C-1 airplanes: Before or when the horizontal stabilizer attachment fitting accumulates 850 hours TIS or within 25 hours TIS after June 13, 2013 (the effective date of this AD), whichever occurs later, and repetitively thereafter at intervals not to exceed 850 hours TIS replace the horizontal stabilizer attachment fitting P/N 1-2200-14, 2200-14, or 2-2200-21 with an airworthy part following Revo Inc. Service Bulletin B-78 R3, Revision 3, dated January 10, 2012.
(3) For the purposes of this AD, an airworthy part is defined as a new part or a used part that has less than 850 hours TIS and has been inspected following paragraph (h)(1) of this AD and found free of cracks, fretting, or corrosion before installation.
You may at any time install the following supplemental type certificates (STC) to terminate the requirements of this AD; however, the actions required by the limitations section in the instructions for continued airworthiness for the STCs still apply:
(1) Lake Central Aircraft Services Lake Amphibian stabilizer fitting (STC SA02153NY) (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/1dae07f8e33da91486257093004f73b8/$FILE/SA02153NY.pdf) following Lake Central Aircraft Services Lake Amphibian Stabilizer Fitting LC-2200-21 Installation Instructions, Rev B, dated August 26, 2005; and Lake Central Air Services Stabilizer Fitting LC-2200-21 Maintenance Manual Supplement Document MS-LC-2200-21, Rev B, dated August 26, 2005; or
(2) Robert L. Copeland (XLS Co., LLC) horizontal stabilizer support fitting system (STC SA03217AT) (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/93cfc6dba1fdeadb862571080056c0c2/$FILE/SA03217AT.pdf) following XLS Company, LLC Report XLS-2-2200-21-500, Installation Instructions for XLS Co., LLC Horizontal Stabilizer Support Fitting System for Colonial C-1, Colonial C-2, Lake LA-4, Lake LA-4A, Lake-4P, and Lake LA-4-200 Aircraft, Revision B, dated November 18, 2005; and XLS Company, LLC Report XLS-2-2200-21-ICA, Instructions for Continued Airworthiness for XLS Co., LLC Horizontal Stabilizer Support Fitting System for Colonial C-1, Colonial C-2, Lake LA-4, Lake LA-4A, Lake-4P, and Lake LA-4-200 Aircraft, dated October 15, 2005.
Note 1 to paragraph (k)(2) of this AD: New parts are not currently available for STC SA03217AT (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/93cfc6dba1fdeadb862571080056c0c2/$FILE/SA03217AT.pdf); however, the STC number has been included here if the parts become available later.
(1) Measure the gap between the horizontal skin and the horizontal stabilizer attachment fitting (P/N 1-2200-14, 2200-14, or 2-2200-21). If gap is less than 1/16 inch, trim the skin to provide at least 1/16 inch gap.
(2) After any replacement of the fitting required by paragraphs (h)(2), (i)(2), or (j) of this AD, before further flight, do the actions in paragraph (l)(1) of this AD.
Using the form in Appendix 1 of this AD, report the results of the inspections required in paragraphs (h) and (i) of this AD. Send the results to the FAA using the following contact information: Hal Horsburgh, FAA Atlanta Aircraft Certification Office (ACO), 1701 Columbia Ave., College Park, GA 30337; fax (404) 474-5606; or email: hal.horsburgh@faa.gov. Send the results within the following compliance times:
(1) Within 30 days after the inspection required in paragraph (h)(1) of this AD even if no damage is found.
(2) Within 30 days after any inspection required by paragraph (i) of this AD if cracks are found.
