Results
2011-27-08: We are adopting a new airworthiness directive (AD) for all Agusta S.p.A. (Agusta) model A109S and AW109SP helicopters. This AD is prompted by a fatigue crack found in the left elevator assembly along the riveting of the upper skin to the fourth rib on an Agusta A109S helicopter. These actions are intended to detect a crack, which could lead to a failure of the elevator, reduced maneuverability of the helicopter, and subsequent loss of control of the helicopter.
57-08-04: 57-08-04 HARTZELL: Applies to All HC-83X and HC-93Z Three-bladed Feathering Propellers Installed on Aero Commander Models 520, 560, 560A, 560E and 680, Beech Model 50, and Piaggio P.136 Aircraft. Compliance required as soon as possible but not later than May 15, 1957. There have been several cases reported that screw P/N AN 501-A10-6 securing the RG- 50 safety link bar unscrewed, without breaking the safety wire, from the link arm mounting pin P/N A-872-1 located at piston end of pitch change link arm P/N A-861 on Hartzell HC-83X and HC-93Z three-bladed feathering propellers installed on twin engine aircraft. This occurs because link arm P/N A-861 rotates during propeller operation and thus applies a torsional force to the link arm mounting pin P/N A-872-1, thereby causing it to rotate. To preclude possible loss of propeller blade pitch control from this cause, accomplish the following modification on these propellers: 1. Feather propeller and remove safety link RG-50 and link pin A-872-1 from propeller pitch change piston. 2. Replace screw AN 501-A10-6 with screw AN 501-A10-18 that will extend through safety link pin P/N A-872-1 a maximum of two threads. 3. Peen projecting end of screw to prevent screw from backing out of link pin. 4. Replace safety link and link pin assembly in the piston. Be sure safety link RG- 50 is not held away from piston lug surface due to peened screw threads bottoming in pin hole. (This AD covers the same subject as CAA telegraphic instructions dated April 12, 1957.) (Hartzell Service Bulletin No. 46 covers this same subject.)
2021-20-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, A321, A330-200, A330-200 Freighter, A330-300, A330-800, A330-900, A340-200, A340-300, A340-500, A340-600, and A380-800 series airplanes. This AD was prompted by a report that repetitive disconnection and reconnection of certain batteries during airplane parking or storage could lead to a reduction in capacity of those batteries. This AD requires replacing certain nickel-cadmium (Ni- Cd) batteries with serviceable Ni-Cd batteries, or maintaining the electrical storage capacity of those Ni-Cd batteries during airplane storage or parking, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-09-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This action requires repetitive inspections of the internal and external spring sleeves of the aileron artificial feel unit (AFU) for proper lubrication, and lubrication if necessary. This action is necessary to prevent ice accumulation due to water entering the AFU, which could restrict or jam the aileron, resulting in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2021-20-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by multiple reports of cracking of the main landing gear (MLG) shock strut lower pin. This AD requires repetitive lubrication and repetitive detailed visual inspections (DVI) and non- destructive test (NDT) inspections of the MLG shock strut lower pins, and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
70-17-01: 70-17-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1061. Applies to Model BAC 1-11 Series 401 Type AK airplanes. To prevent overheating of the heating elements fitted to the S8 and S9 right-hand and left-hand static vent plates located at Station 66, within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, accomplish one of the following: (a) Deactivate the static plate heaters in accordance with Part (B) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 30-PM4306 dated November 28, 1969, or a later ARB-approved issue or an FAA-approved equivalent; or (b) Modify the pitot/static plate heater circuit to provide a separate power supply for each circuit in accordance with Part (A) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 4306 dated November 28, 1969, or a later ARB-approved issue or an FAA-approved equivalent. This amendment becomes effective September 5, 1970.
98-13-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit the use of mach trim and to add speed restrictions if the autopilot is disengaged or inoperative. That AD also requires installation of an associated placard. This amendment adds requirements for replacement of the horizontal stabilizer trim control unit (HSTCU) with a new HSTCU, and reactivation of the mach trim engage/disengage switch/light (if deactivated). Accomplishment of these actions terminates the requirements of the existing AD. This amendment also limits the applicability of the existing AD. 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 deficiencies of the HSTCU, which could result in a nose-up trim runaway when a single component in the mach trim circuit fails.
98-13-09: This amendment adopts a new airworthiness directive (AD) that applies to certain AERMACCHI S.p.A. (AERMACCHI) Models F.260, F.260B, F.260C, and F.260D airplanes. This AD requires marking the airspeed indicator to indicate the correct flap operation range and stall speed of the airplane. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent the airplane from stalling at an airspeed higher than anticipated, which could result in loss of control of the airplane.
54-01-01: 54-01-01 HAMILTON STANDARD: Applies to All Hamilton Standard Reversing Propellers Models 43D, 43E, 34D, 34E, 232 and 242. Compliance required as indicated. Subsequent to December 31, 1954, Hamilton Standard Model 67000 reverse solenoid valves shall not be used on civil aircraft. Analysis has shown that unwanted reversal of Hamilton Standard propellers could possibly occur with use of the Hamilton Standard Model 67000 reverse solenoid valve if any of the following malfunctions of the valve were experienced: 1. A broken plunger spring. This could cause the valve to open fully. 2. A film of oil between the armature and the valve body. This could cause the valve to remain fully open. 3. A foreign particle lodged between the valve and its seat. This could cause a pressure buildup in the reverse oil passage. Although there is no record of such malfunctions of this valve on civil aircraft, the potential hazards that exist indicate the desirability of precluding future use of this obsolete component.
2021-19-14: The FAA is adopting a new airworthiness directive (AD) for AERO Sp. z o.o. (AERO) Model AT-3R100 airplanes with an ELPROP 3-1-1P propeller. 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 identifies the unsafe condition as cracks in the propeller hub. The FAA is issuing this AD to address the unsafe condition on these products.