Results
2014-20-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, and Model 777 airplanes. This AD was prompted by testing reports on certain Honeywell phase 3 display units (DUs). These DUs exhibited susceptibility to radio frequency emissions in WiFi frequency bands at radiated power levels below the levels that the displays are required to tolerate for certification of WiFi system installations. The phase 3 DUs provide primary flight information including airspeed, altitude, pitch and roll attitude, heading, and navigation information to the flightcrew. This AD requires replacing the existing phase 3 DUs with phase 1, phase 2, or phase 3A DUs, and for certain replacement DUs, installing new DU database software. We are issuing this AD to prevent loss of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery, or controlled flight into terrain.
2014-20-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of an incorrectly assembled check tee fitting used in fire extinguishing (FIREEX) distribution lines. This AD requires inspecting to determine the part number and for all affected check tee fittings measuring for correct depth, and replacing if necessary. We are issuing this AD to detect and correct faulty check tee fittings, which will reduce fire extinguishing protection.
70-19-03: 70-19-03 DORNIER AG: Amdt. 39-1080. Applies to Model Do-28D-1 Airplanes. To prevent interference between the jumper wires and the aileron and flap control systems, within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, rework the jumper wire installations located in the right and left wing by installing shorter jumper wires, covering the jumper wires with insulation tubing, and rerouting wires in accordance with Dornier Service Bulletin No. 1030-1408, dated 6 July 1970, or an FAA approved equivalent. This amendment becomes effective September 22, 1970.
2018-25-16: We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN-235, CN-235-200 and CN-235-300 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2014-19-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by an analysis by the manufacturer, which revealed that certain fuse pins for the strut-to-wing attachment of the outboard aft upper spar are susceptible to migration in the event of a failed fuse pin through bolt. This AD requires replacing the fuse pins for the strut-to-wing attachment of the outboard aft upper spar with new fuse pins, and replacing the access cover assemblies with new access cover assemblies. We are issuing this AD to prevent migration of these fuse pins, which could result in the complete disconnect and loss of the strut-to-wing attachment load path for the outboard aft upper spar. The complete loss of an outboard aft upper spar strut-to-wing attachment load path could result in divergent flutter in certain parts of the flight envelope, which could result in loss of control of the airplane.
2014-19-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of rudder bearings falling out of the fore rudder hinge bracket during assembly. This AD requires a proof load test and detailed inspections; and installation of a new bearing, reaming, or repair of the bearing if necessary. We are issuing this AD to detect and correct improper bearing installation, which could result in abnormal wear and potential increased freeplay in the rudder system, and resultant airframe vibration, leading to compromise of the flutter margins of the airplane.
75-08-16: 75-08-16 BEECH: Amendment 39-2168. Applies to Models 65-90, 65-A90 and B90 (Serial Numbers LJ-1 through LJ-484) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude fuel contamination in the aft fuselage area, accomplish the following: A) On airplanes (Serial Numbers LJ-1 through LJ-395) not modified per Beechcraft Service Instruction 0230-412, Rev. I, or later approved revision, including optional Cabin Heat Out light, within 50 hours' time in service after the effective date of this AD, install a temporary placard on the heater control panel stating: "IF HEATER FAILS TO HEAT, TURN OFF IMMEDIATELY" and operate the aircraft in accordance with this limitation. NOTE: This placard may be fabricated from embossed tape or typed or printed on paper of a contrasting background. B) On airplanes (Serial Numbers LJ-1 through LJ-484) not modified in accordance with Beechcraft Service Instruction 0268-103, Rev. I, or laterapproved revision, within 50 hours' time in service after the effective date of this AD, modify the drainage and sealing of the aft fuselage area as follows: 1. Remove the tail cone and the aft fuselage access door. 2. Drill out the 5 holes in the fuselage skin just aft of the aft pressure bulkhead (station 298.0), the 2 holes just aft of the station 364.0 bulkhead, the hole just aft of the 380.0 bulkhead and the hole in the lower surface of the tail cone to .191 to .196 inch. NOTE: In some cases some of these holes may not exist. If this is the case, do not drill new holes. 3. Fill these holes with MS20470B6 rivets of appropriate length. Seal the rivet butts with EC1239 or equivalent sealant. 4. Drill a 250 inch hole at the lower fuselage centerline .20 inch aft of the aft pressure bulkhead (fuselage station 298.20). 5. Drill a .250 inch hole in the fuselage skin at the lower fuselage centerline .44 inch aft of the fuselage station 380.0 bulkhead (just forward of the tail cone). NOTE: Steps 4 and 5 will allow moisture to drain through the ventral fin. 6. Drill 4 .12 inch diameter drain holes in the lower edge of the ventral fin. These holes should be spaced as follows: a. 1 hole 24.0 inches aft of the forward end of the ventral fin, b. 1 hole 1.6 inches forward of the station 380.0 bulkhead, c. 1 hole 22.0 inches forward of the station 380.0 bulkhead d. 1 hole 52.0 inches forward of the station 380.0 bulkhead 7. On airplanes having a hinged aft fuselage access door, open this door, drill out the 2 drain holes in the door and 3 holes in the forward edge of the door frame. NOTE: In some cases some of these holes may not exist. If this is the case, do not drill new holes. a. Place tape over the 3 holes in the forward edge of the door frame. Fill these holes with EC1239 or equivalent sealant. Do not remove the tape until the sealant cures. b. Fill the remainder of the holes with MS20470B6 rivets of appropriate length. Seal the rivet butts with EC1239 or equivalent sealant. c. Using PPP-T-60 two (2) inch wide tape, or equivalent, temporarily seal the closed aft fuselage access door in a manner that will cover both the door opening edges and fastening screws. C) On or before May 1, 1976, on airplanes (Serial Numbers LJ-1 through LJ-484), modify the aft fuselage in accordance with Beechcraft Service Instructions No. 0268-103, Rev. I, or later approved revisions, and on airplanes (Serial Numbers LJ-1 through LJ-395) modify the heater installation, including installation of cabin heat out light, in accordance with Beechcraft Service Instructions 0230-412, Rev. II, or later approved revisions. D) When Paragraph C is accomplished the temporary placard specified in Paragraph A and temporary sealing of aft fuselage door specified in Paragraph B) 7.c. may be removed. E) Any equivalent method of compliance with this AD must be approvedby the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective April 17, 1975.
75-11-11: 75-11-11 SIKORSKY AIRCRAFT: Amendment 39-2217 as amended by Amendment 39-2432. Applies to all Sikorsky Aircraft Model S-64E and Model S-64F helicopters. To prevent failure of the torquemeter engine to gearbox shaft and gear assembly and consequent secondary damage to the main rotor control system components, remove prior to further flight, torquemeter engine to gearbox shaft and gear assemblies, P/N 6435-20564-042, with 3000 or more hours total time in service. Replace those assemblies removed with P/N 6435-20564-042 assemblies which have less than 3000 hours total time in service, or with P/N 6435-20564-044 assemblies, or with an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. All replacement P/N 6435-20564-042 assemblies must be removed prior to the accumulation of 3000 hours time in service. Amendment 39-2217 became effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram. This amendment 39-2432 becomes effective December 2, 1975.
2013-15-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and --315 airplanes. This AD was prompted by reports of dual alternating current (AC) generator failure during flight. The failure was attributed to wire chafing along the wing lower flap shroud. This AD requires revising the maintenance program to incorporate certain tasks for the electrical wiring interconnection system inspection program. We are issuing this AD to prevent failure of both AC generators due to wire chafing, which could result in loss of power to the anti-icing heaters for the elevator horn, engine inlet, and propeller, and consequent ice accumulation in these areas, which could adversely affect the controllability of the airplane.
2014-18-03: We are adopting a new airworthiness directive (AD) for APEX Aircraft Model R 3000/160 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as small pieces of paint from the engine air intake box blocking the engine carburetor. We are issuing this AD to require actions to address the unsafe condition on these products.