Results
66-30-01: 66-30-01 BEECH: Amdt. 39-325 Part 39 Federal Register December 21, 1966. Applies to Model JRB-6, D18C, D18S, E18S, E18S-9700 with Serial Numbers prior to BA445, C-45G, TC-45G, C-45H, and TC-45J (SNB-5) Airplanes That Have Been Modified in Accordance with Volpar, Inc., Supplemental Type Certificate No. SA4-1531 or SA111WE. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent moisture from collecting in the static line of the subject airplanes, accomplish the following: Install a drain in the static line in accordance with Volpar, Inc., Drawing No. 857, titled "Drain Installation - Static Pressure Line" dated 9-22-66 (Volpar, Inc., Service Bulletin No. 10, page 2) or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the compliance time if the request contains substantiating data to justify the adjustment for that operator. This directive effective December 21, 1966. This amendment effective March 1, 1967. Revised March 1, 1967.
2018-18-08: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes, Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD was prompted by reports of cracked slat tracks at the location of the front stop attachment to the track. This AD requires a detailed inspection, repetitive special detailed inspections, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2005-22-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes. This AD requires inspecting for damage of the ground brackets, ground wires, and terminal lugs of the auxiliary power unit (APU) battery and the APU start transformer rectifier unit (TRU) as applicable; and corrective and related investigative actions. This AD results from reports indicating that during inspections on two airplanes, the ground brackets for the APU battery were found damaged. We are issuing this AD to detect and correct a damaged electrical bonding surface of the APU battery and APU start TRU ground connections, which could cause overheating of the ground connections and lead to possible consequent ignition of the adjacent insulating blankets.
47-32-11: 47-32-11 BELL: (Was Mandatory Note 11 of AD-1H-1.) Applies to Models 47B and 47B3 Helicopters. Compliance required not later than the next 25-hour inspection after September 15, 1947. The antenna mast should be supplemented with antenna mast support, 47-762-023-1. This support is intended to relieve the antenna loads from the lead-in mast. (Bell Service Bulletin 47C33 dated June 12, 1947, also covers this same subject.)
2018-18-14: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A2-20 and BR700- 710C4-11 turbofan engines. This AD was prompted by reports of deterioration of the intumescent heat resistant paint system on the electronic engine controller (EEC) firebox assembly that was found to be beyond acceptable limits. This AD requires replacement of affected EEC firebox assembly parts with improved parts, which have a more durable paint system. We are issuing this AD to address the unsafe condition on these products.
2018-18-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the longitudinal lap splices of the fuselage skin are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the longitudinal lap splices of the fuselage skin for cracking and protruding fasteners, and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
97-26-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires an inspection to detect corrosion of the rear spars of the wings, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct possible corrosion on the rear spars of the wings, which could result in reduced structural integrity of the wings.
47-42-14: 47-42-14 DOUGLAS: (Was Mandatory Note 11 of AD-781-1.) Applies to DC-6 Serial Numbers 42854 to 42880, Inclusive; 42882 to 42884, Inclusive; 43000 and 43001. \n\nTo be accomplished not later than first blower overhaul after January 1, 1948. \n\nTo prevent bearing failures in the voltage regulator blowers, replace the bearings formerly packed with lubricant Z815 with new bearings containing lubricant Z801. \n\n(Douglas Service Bulletin DC-6 No. 43 describes the complete rework.)
66-30-03: 66-30-03 DORNIER: Amdt. 39-320 Part 39 Federal Register December 16, 1966. Applies to All Model DO 28 B-1 Airplanes. Compliance required as indicated. To detect cracks of the horizontal stabilizer spar in fuselage attachment brackets, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of the AD, unless already accomplished within the last 90 hours' time in service before the effective date of this AD and thereafter at intervals as specified below, visually inspect the welded hinge brackets P/N 28.315-01 H01 on the stabilizer front spars for cracks in the base plate in the area of the upper and lower spar flanges, using a lamp, mirror and at least a three-powered glass. (b) If no cracks are found as a result of the inspection required by (a), the bracket is considered serviceable and the inspection must be repeated at intervals not to exceed 100 hours' time in service since the last inspection. (c) If cracks ofless than 1/2 inch in length are found, the inspection must be repeated at intervals not to exceed 10 hours' time in service, up to a maximum of 100 hours' time in service since the initial inspection. Upon accumulation of 100 hours' time in service since initial inspection, replace bracket P/N 28.315-01 H01 with new bracket P/N 28.315-01 H03 or FAA- approved equivalent. (d) If cracks greater than 1/2 inch in length are found, prior to next flight, replace bracket P/N 28.315-01 H01 with new bracket P/N 28.315-01 H03 or FAA-approved equivalent. (e) The repetitive inspections required by (a), (b), and (c) may be discontinued after new replacement bracket P/N 28.315-01 H03 is installed. (Dornier Technical Bulletin No. 28-44 dated October 11, 1966, pertains to this subject.) This directive effective December 26, 1966.
49-52-02: 49-52-02 BELL: Applies to All Models 47B, 47B3, 47D, and 47D1 Series Helicopters. Compliance required as indicated. As a result of recent accidents, the following precautionary measures should be taken: 1. The main rotor hub (Bell P/N 47-120-136-1) must be replaced if it has been involved in an accident or sudden stoppage, for any reason, in which the following has occurred: (a) One or both main rotor blades were damaged to the extent that the steel core shows through the wood at any point. (b) A drag brace end fitting or the equalizer horn, or both, are damaged or distorted. (Bell Service Bulletin No. 65, dated August 2, 1949, covers the subject of this portion of the directive.) 2. All aluminum main rotor hubs (Bell P/N 47-120-136-1) must be replaced after 600 hours of operation unless it is necessary to replace them sooner as a result of being affected by the requirements of paragraph 1. In order to assist those operators who possess a part which has over 600 hours accumulated at the time of receipt of this directive, the following latitude in replacing the parts is permitted: Accumulated Time on Hub at Time of this Directive Replacement Limit 0-500 hours At 600 hours 501-800 Within the next 100 hours 801-899 At 900 hours 900 and up Before the next flight Hubs with less than 300 hours must be inspected visually (with a 10- to 20-power glass) at 300 hours, in addition to the inspections required by the manufacturers "Erection and Maintenance Manual" for the particular model. During this inspection, specific attention must be directed toward locating fatigue cracks in the shotpeened fillet radius, particularly on the leading edge side. The discovery of cracks in any portion of this radius is cause for immediate replacement of the part. In addition to the execution of the Form FAA 1226, "Malfunctioning and Defects Report," such a discovery should be reported immediately to the Bell Aircraft Corp., together with the number of hours accumulated on the hub, the serial number of the hub, model and serial number of the helicopter on which it was installed, and a statement to indicate whether or not the part had been involved in an accident such as described in paragraph 1. This supersedes AD 49-35-02.