Results
47-50-13: 47-50-13 DOWNER (BELLANCA and UNIVERSAL (Stinson): Applies Only to Aircraft Equipped With Koppers Model Aeromatic F200 Propellers. Compliance required no later than the next 25-hour propeller lubrication and at 25 hours of operation thereafter. Inspect propeller hub as follows: Remove balancing band from both ends of hub barrel after index marking each to facilitate proper reassembly. Examine the other surfaces of the hub completely for indications of line cracks or fractures. The areas of primary concern are (1) those beneath the balancing bands, (2) the weld joint where hub barrel and mounting tube meet, and (3) the weld joint where mounting tube and mounting flange meet. Defective hubs should be removed from service. (Koppers Service Bulletin No. 12, dated October 9, 1947, covers this same subject.)
76-19-05: 76-19-05 AVIONS MARCEL DASSAULT (AMD): Amendment 39-2730. Applies to all Model Fan Jet Falcon airplanes, all Series, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent the possible inability of the emergency fuel shut-off valves to shut down the engines, accomplish the following: (a) Within the next 20 hours time in service after the effective date of this AD, unless already accomplished, inspect the fuel shut-off control in accordance with AMD Service Bulletin No. 551, dated March 3, 1976, or FAA-approved equivalent, for each engine to determine the time for the engine to flame-out after actuation of the emergency fuel shut-off control with the engine operating initially at ground idle rpm. If flame-out time is found to exceed 15 seconds, prior to further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repair can be performed, readjust the emergency fuel shut-off control in accordance with Fan Jet Falcon Maintenance Manual Chapter 76-20-2, pages 501 through 503, or an FAA-approved equivalent. (b) Within the next 150 hours time in service or 60 days after the effective date of this AD, whichever occurs later, unless already accomplished, inspect for proper assembly and repair, as necessary, the fuel shut-off valves, Zenith P/N B99-26203 and B99-26204, in accordance with AMD Service Bulletin No. 550, dated March 3, 1976, or an FAA-approved equivalent. This amendment becomes effective October 7, 1976.
2016-04-11: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 turbofan engine models. This AD was prompted by reports of two separate, single engine in-flight shutdowns [[Page 9752]] (IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade failure. This AD requires inspection and conditional removal of affected HPT rotor stage 1 blades. We are issuing this AD to prevent failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
2003-03-13: This amendment adopts a new airworthiness directive (AD) that applies to all MORAVAN a.s. (Moravan) Model Z-242L airplanes. This AD establishes a technical service life for these airplanes by restricting Acrobatic and Utility category operations and requiring replacement of the wings after a certain operational time period. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent structural failure of the wing due to fatigue cracking. Such failure could result in a wing separating from the airplane with consequent loss of airplane control.
2018-18-09: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes; and certain Model C-295 airplanes. This AD was prompted by a report that cracks were found on the stabilizer-to- fuselage rear attachment fitting. This AD requires a detailed inspection of the upper and lower lugs of each horizontal stabilizer- to-fuselage rear attachment fitting, repair if necessary, and a report of findings. We are issuing this AD to address the unsafe condition on these products.
2008-22-12: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires repetitive inspections for any crack in the area of the elevator side fitting/hinge fitting joint and for any crack or elongation inside and outside of the holes in the clevis and in the lug, corrective actions if necessary, and other specified actions. This AD results from reports of elongated holes and cracks found in the lugs of the attachment fittings of the elevator quadrant upper support assembly at the tip of the vertical fin. We are issuing this AD to detect and correct damage to the aft attachment lugs of the elevator quadrant support assembly that could lead to failure of the lugs. This condition could accelerate wear elsewhere in the elevator control system, which could reduce the crew's ability to maintain safe flight.
75-06-09: 75-06-09 BEECH: Amendment 39-2129. Applies to Models 60 and A60 (Serial Numbers P-3 through P-200) airplanes with more than 150 hours' time in service. Compliance: Required as indicated, unless already accomplished. To prevent malfunctions of the elevator inboard hinge supports, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: Remove the left and right elevator inboard hinge supports (P/N 60-524078-1 and 60- 524078-2) and install improved supports in accordance with Beech Kit No. 60-4005 or any equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instruction No. 0342-132, Revision III, or later revision refers to this subject. This amendment supersedes Amendment 39-1463, AD 72-13-01. This amendment becomes effective March 20, 1975.
2003-12-05: This amendment supersedes an existing airworthiness directive (AD), that is applicable to McCauley Propeller Systems 1A103/TCM series propellers. That AD currently requires an initial inspection for cracks in the propeller hub in accordance with a dye penetrant inspection procedure, replacement of propellers with cracks that do not meet acceptable limits, rework of propellers with cracks that meet acceptable limits, and repetitive inspections of all affected propellers. This amendment allows additional rework operations to be performed at more than one bolt hole location. This amendment is prompted by the need to clarify the requirement to use a steel backing plate and Mylar gasket during installation of the propeller, and to relax the replacement requirements. The actions specified in the proposed AD are intended to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane.
2003-03-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires replacement of the screws in the aileron, rudder, and elevator trim tabs with new screws; and removal and re-installation of screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab; as applicable. This action is necessary to prevent reduced structural integrity of the screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab, due to countersinks that were not manufactured correctly, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-02-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-02-51 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires an airplane flight manual (AFM) revision to introduce new quantity limitations for the center fuel tank and associated procedures; to limit flight to within 30 minutes of a suitable alternative airport; and to limit the center tank fuel quantity to 1,500 lbs. (680 kgs.) maximum at takeoff. This action is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified by this AD are intended to detect and correct discrepancies in the fuel distribution system, which could cause the center tank to overfill and fuel to leak from the center tank vent system or to become inaccessible, and could result in engine fuel starvation.