Results
98-12-04: This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-500M gliders. This AD requires installing a rudder gap seal and modifying the cooling liquid reservoir mount. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent rudder vibrations caused by flow separation at the rudder gap, which could result in flutter with consequent loss of rudder control.
63-06-03: 63-06-03 GENERAL DYNAMICS/CONVAIR: Amdt. 545 Part 507 Federal Register March 20, 1963. Applies to All Models 340 and 440 Series Aircraft Equipped With a Bendix Redbank Type 35E05 Fault Detection Panel. Compliance required within the next 300 hours' time in service following the effective date of this AD, unless already accomplished. To prevent the loss of electrical power, modify the type 35E05 fault detection panel by installing a blocking rectifier (G.E. IN-93 or FAA approved equivalent). Solder the negative lead to lug No. 3 of the locating relay and the positive lead to terminal No. P on the terminal board. (Convair Airgram No. 200 dated September 24, 1956, and Bendix Redbank Service Bulletin No. R-47 pertains to this same modification.) This directive effective March 20, 1963.
82-23-06: 82-23-06 FAIRCHILD SWEARINGEN: Amendment 39-4493. Applies to Models SA 226-T(B) (S/N T(B) 276, T(B) 292 through T(B) 397); SA 226-T (S/N T201 through T275 and T277 through T291); SA 226-AT (S/N AT001 through AT074); SA 226-TC (S/N TC201 through TC396) airplanes certificated in any category. COMPLIANCE: Required within the next 50 hours time-in-service unless already accomplished. To prevent the main landing gear doors from shifting and locking the gear in the up position, accomplish the following: (a) Inspect, check, and modify the main landing gear door installation in accordance with Accomplishment Instructions IIA through IIL of Fairchild Swearingen Service Bulletin SB 32-026 dated October 16, 1980, as supplemented by the instructions below. (1) When replacing the bushings and refitting the doors for final assembly, assure that the bushings are properly lubricated (do not use thin-film, spray-on liquids which will wash out the grease from the Oilite bushings; use a thick, permanent lubricant such as Lubriplate). (2) Observe standard torque for AN3 bolts. (3) Assure that the door hinge bolts clamp completely and the doors move freely. (4) Remove stripped nutplates and replace them with a castellated nut and cotter pin. Instructions for accomplishing this may be obtained from Fairchild Swearingen Corporation. Use of the drilled bolt and safety wire procedures specified in paragraphs IIG and IIJ of Fairchild Swearingen Service Bulletin SB 32-026 is not required if a castellated nut and cotter pin are used. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
2005-20-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection of the rudder pedal torque tube assembly for cracking; an inspection of the torque tube assembly to determine the thickness of the torque tube wall, if necessary; and replacing the rudder torque tube with a new or serviceable rudder torque tube, if necessary. This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.
98-11-24: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-11-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320, and Model ATR72 series airplanes, that requires modification of the engine fuel drainage system. 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 prevent fuel from overflowing into the engine nacelle, which could result in a fire in the nacelle.
2005-20-22: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes. This AD requires repetitive inspections for environmental damage, including corrosion, of the fuselage and wing structure, and corrective actions if necessary. This AD results from information indicating the potential for environmental damage of the fuselage and wing structure. We are issuing this AD to detect and correct such damage, including corrosion, in the fuselage and wing structure, which could result in cracking and consequent reduced structural integrity of the fuselage and wing structure.
2002-10-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 58P, 60, A60, B60, and 65-88 airplanes. This AD requires you to install new exterior operating instruction placards for the exit doors. This AD is the result of Raytheon improving the visibility and understandability of the door operating instruction placards. This was done as a result of difficulty opening the emergency exits of a similar type design airplane. The actions specified by this AD are intended to assure that clear and complete operating instructions are visible for opening the emergency exit doors. If not visible and understandable, this could result in the inability to open the exit door during an emergency situation.
2017-15-02: We are adopting a new airworthiness directive (AD) for Bell Model 212 and Model 412 helicopters. This AD requires replacing certain oil and fuel check valves and prohibits installing them on any helicopter. This AD is prompted by a report of cracked or leaking check valves. These actions are intended to address an unsafe condition on these helicopters.
98-11-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires an inspection to determine if the latching lever pin of the speed brake passes an axial force check, and a visual inspection to determine if the staking of the latching lever pin is acceptable; and follow-on corrective action, if necessary. This amendment is prompted by reports that the speed brake handle jammed in the ground spoiler position. The actions specified by this AD are intended to prevent a jammed speed brake handle pin, which could result in retraction of the spoilers and full advancement of the left throttle during a go- around.