Airworthiness Directive · Amendment 39-14452 · Frakes Aviation (Gulfstream American) Model G-73 (Mallard) Series Airplanes and Model G-73 Airplanes That Have Been Converted To Have Turbine Engines
Frakes Aviation (Gulfstream American) Model G-73 (Mallard) Series Airplanes and Model G-73 Airplanes That Have Been Converted To Have Turbine Engines
This AD applies to all Frakes Aviation (Gulfstream American) Model G-73 (Mallard) series airplanes; and Model G-73 airplanes that have been converted to have turbine engines; certificated in any category.
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2006-01-51 that was sent previously by individual notices to all known U.S. owners and operators of Frakes Aviation (Gulfstream American) Model G-73 (Mallard) series airplanes and Model G-73 airplanes that have been converted to have turbine engines. This AD requires an inspection to detect repairs, cracking, or corrosion of the wings from wing station (WS) 77L to WS 77R, front spar to rear (main) spar; removal of repairs, if found; removal of sealant from the interior of the wet bays; and repair of any crack or corrosion. This AD results from a report indicating that the right wing of a Frakes Aviation (Gulfstream American) Model G-73 (Mallard) airplane separated from the fuselage on takeoff, which resulted in the airplane impacting the water near Miami Beach, Florida. We are issuing this AD to prevent structural failure of the wing and loss of control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Before further flight, perform a detailed visual inspection to detect repairs, cracking, or corrosion of the wings from wing station (WS) 77L to WS 77R, front spar to rear (main) spar; remove any repair that is found, to allow for inspection of the wing structure underneath the repairs; and remove the sealant from the interior of the wet bays to allow for inspection of the skins, stringers, and both spars. Perform the inspection in accordance with a method approved by the Manager, Airplane Certification Office (ACO), ASW-150, Rotorcraft Directorate, FAA.
Note 1: For the purposes of this AD, a detailed visual inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
Before further flight, submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Robert A. Romero, Aerospace Engineer, ACO, ASW-150, Rotorcraft Directorate, FAA; 2601 Meacham Boulevard, Fort Worth, Texas 76137-4298; fax (817) 222-5960. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of total flight cycles and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
If any cracking or corrosion is found during the inspection required by paragraph (f) of this AD, repair before further flight, in accordance with a method approved by the Manager, ACO, ASW-150, Rotorcraft Directorate, FAA.
