Results
2018-16-02: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318-111 and -112 airplanes, Model A319-111, -112, - 113, -114, and -115 airplanes, Model A320-211, -212, -214, and -216 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in \n\n((Page 39327)) \n\nfailure of the retainer. This AD requires modifying and re-identifying the aft engine mount assemblies. We are issuing this AD to address the unsafe condition on these products.
2000-08-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires the deactivation of the forward and center cargo control units (CCU). That amendment was prompted by a report of failure of a CCU, which produced overheating of the electrical pins inside the CCU; the subsequent release of hot gases and flames ignited an adjacent insulation blanket. This amendment expands the applicability of the existing AD to include additional airplanes. The actions specified in this AD are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
59-18-05: 59-18-05 FAIRCHILD: Applies to all F-27 Series aircraft equipped with the heater system. Compliance required not later than October 15, 1959. (a) In order to provide drainage of possible leakage at the heater fuel line fittings, remove three shroud assemblies, P/N 27-774575-1, attached to tube connections at top of heater fuel control, P/N 43C80, and heater P/N 49C65. Modify shroud assemblies by punching one (1) 1/8-inch diameter hole in side of shroud 1 13/64 inches from top. (b) Remove fuel control drain tube assembly, P/N 27-774554-11 or -51, whichever installed. (c) On airplanes Nos. 1 to 6 inclusive, drill 5/8-inch diameter hole in bottom fuselage skin between stringers Nos. 102 and 103, 2 1/2 inches aft of Station 731, and install AN 931-6-10 grommet removed from former location of drain line. Install flush skin patch over former drain hole location in accordance with Chapter 51-7 of F-27 Structural Repair Manual. (d) On all affected airplanes, install new drain tube assembly, P/N 27-774750-11 in place of 27-774554-11 or -51. (e) Install modified shroud assemblies, using three each new half clamp assemblies, P/N 27-774749-11, half clamp P/N 27-774749-3, bolt P/N AN 3-3A, and nuts P/N MS 20365-1032. (f) Install one each new hose, P/N 27-774094-3 and -5 between heater fuel control shrouds and drain tube and P/N 27-774094-7 between heater shroud and drain tube, using six new clamps, P/N AN 737RM22. (g) Install two new plates, P/N 27-774749-9, on the heater fuel control unit, and four new clamps, P/N AN 742-8, two on the plates at the fuel control unit to support 27-774094-3 and -5 hose and two on the flanges of the fuselage former at Stations 730 and 731 to support 27-774094-7 hose. Use four each new screws P/N AN 525-10R6, and nuts P/N MS 20365-1032. (Fairchild F-27 Service Bulletin No. 21-49 dated June 12, 1959, covers this same subject.) Compliance with AD 59-12-01 no longer required after compliance with this directive.
2006-16-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to require actions to correct the unsafe condition on these products.
2006-16-20: We are adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Model DG-1000S sailplanes. This AD requires you to modify the elevator control at the stabilizer assembly, replace a placard on the fin, and incorporate changes in the FAA-approved sailplane flight manual (SFM). This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the rigging of the horizontal stabilizer without properly connecting the elevator, which, if not prevented, could lead to an inoperative elevator. An inoperative elevator could lead to loss of control of the sailplane.
2018-16-03: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-133 airplanes and Model A321-232 airplanes. This AD requires modification and re-identification, or replacement, of certain engine fan cowl doors (FCDs) and installation of a placard in the flight deck. This AD was prompted by reports of in-service engine FCD losses, and the development of a new FCD front latch and keeper assembly that addresses this unsafe condition. We are issuing this AD to address the unsafe condition on these products.
51-26-03: 51-26-03 CONTINENTAL: Applies to All Continental Model E185 Engines Serially Numbered 2600 and Below Which Have Not Been Major Overhauled Since November 1, 1947, by Continental Motor Corp., or July 1, 1948, by Field Overhaul Agencies. To be accomplished as soon as possible, but not later than January 1, 1952. To preclude valve failures as caused by partially deflated hydraulic valve lifters, the engine must be inspected and modified, if necessary, to assure proper oil flow to the lifters and zero valve lash under all operating conditions. This will require either a partial engine disassembly or a special test as outlined below: (1) Partial Disassembly Method: Remove the cylinders and the hydraulic units of the valve lifters. Check each valve lifter guide bore for proper position of the oil feed hole. (2) Special Test (Alternate Method): By application of air pressure to the crankcase oil galley lines after removal of each rocker arm, determine the number of degrees of crankshaft rotation that the oil groove on each valve lifter in registration with the oil feed hole. A minimum of 145 degrees registration is required. If any oil feed hole is shown by the method chosen to be drilled incorrectly, the end of the hole must be enlarged. As lack of oil flow to the rocker boxes also can result in valve mechanism malfunctioning, the diameter of the pushrod holes should be checked. If 1/32-inch diameter replace with push rods incorporating 1/16-inch diameter holes. (Continental Motors Corp. Service Bulletins Numbers M48-12 and M51-2, Supp. No. 1, cover this same subject and describe both of the above compliance methods.) This supersedes AD 51-08-01.
2006-16-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200B, 747-200C, 747-200F, 747-300, and 747SR series airplanes. This AD requires doing repetitive inspections of engine struts 1 through 4, as applicable, for heat discoloration, cracking, buckling, or wrinkling. This AD also requires doing a conductivity test to detect the extent of the heat damage and an inspection to detect cracking of the heat-discolored, buckled, or wrinkled area; and repair; if necessary. This AD results from reports of heat damage and cracking of the skin and internal structure adjacent to and aft of the precooler exhaust vent on several engine struts. We are issuing this AD to detect and correct cracking, buckling, wrinkling, or heat damage of the skin and internal structure of the engine struts, which could result in extensive damage to the engine struts and consequent possible separation of an engine from the airplane during flight.
2018-15-06: We are adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC Model HA-420 airplanes. This AD requires incorporating new and revised airworthiness limitations into the airplane's maintenance program. This AD was prompted by a report that several maintenance tasks were omitted from the airworthiness limitations section of the Honda Aircraft Company, Inc. Model HA-420 Airworthiness Limitation and Inspection Manual (ALIM). We are issuing this AD to address the unsafe condition on these products.
86-15-10 R2: This amendment revises an existing airworthiness directive (AD), applicable to Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, F2 and N helicopters, that currently requires repetitive inspections of the main rotor head components, the main gearbox (MGB) suspension bars, and the ground resonance prevention system components at intervals not to exceed 400 hours time-in-service (TIS). This amendment requires the same inspections, but at intervals not to exceed 500 hours TIS. This amendment is prompted by reports of confusion and unnecessary costs associated with the difference in the current 400 hours TIS inspection interval and the current manufacturer's master service recommendation of 500 hours TIS inspection interval. The actions specified by this AD are intended to eliminate confusion and unnecessary costs and to prevent ground resonance due to reduced structural stiffness, which could lead to failure of a main rotor head or MGB suspensioncomponent and subsequent loss of control of the helicopter.