Results
2004-09-02: The FAA adopts a new airworthiness directive (AD) for all Glasflugel--Ing. E. Hanle (Glasflugel) Model GLASFLUGEL Kestrel sailplanes. This AD requires you to inspect the airbrake actuating shaft for deformation and cracks (herein referred to as damage). If any damage is found, this AD also requires you to repair or replace the airbrake actuation shaft. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct damage to the airbrake actuation shaft, which could result in failure of the airbrake control. This failure could lead to loss of control of the sailplane.
2012-01-08: We are adopting a new airworthiness directive (AD) for all 328 Support Services GmbH (Type Certificate previously held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and 328-300 airplanes. This AD was prompted by a manufacturer safety analyses review on flight control which resulted in recommendations for reduced repetitive inspection intervals for the flight controls certification maintenance requirements (CMR) of the tab-to-actuator linkage. This AD requires revising the airplane maintenance program by incorporating certain CMR tasks. We are issuing this AD to prevent failure of these components or their constituent parts which could lead to reduced control of the airplane.
2021-20-17: The FAA is superseding emergency Airworthiness Directive (AD) 2018-23-52, which applied to all Leonardo S.p.a. Model AW169 and AW189 helicopters. AD 2018-23-52 required inspecting the nut, cotter pin, lock-wire, and hinge bracket connected to the tail rotor servo-actuator (TRA) feedback lever link, and each connection of the TRA feedback lever link, and repair if necessary. AD 2018-23-52 also required applying a paint stripe or torque seal on the nut and reporting certain information. This AD requires repetitive inspections of the TRA, repetitive inspections and checks of the tail rotor duplex bearings (TR DB), installation of an improved TRA and TR DB, repetitive installations and checks of thermal strips, replacement of the improved TR DB (life limit), and applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of an accident of a Model AW169 helicopter, which was observed to have lost yaw control prior to the accident and a determination that certain inspections and checks of the TR DB, installation of an improved TRA and TR DB, certain other actions, and applicable corrective actions are necessary to address the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
65-21-06: 65-21-06 VICKERS: Amdt. 39-131 Part 39 Federal Register September 3, 1965. Applies to Viscount Models 744, 745D, and 810 Series Airplanes That Are Equipped With Pyrene Fire Extinguishers, Type DCD 2, DCD 2-1/4, DCD 10, or DCD 11. Compliance required at first airplane overhaul or within six months after the effective date of the AD, whichever occurs first, unless already accomplished. To prevent further failures of Pyrene fire extinguishers of the subject models, accomplish the following: (a) Overhaul, inspect, and test the fire extinguishing systems that are equipped with electric discharge facility, in accordance with revised requirements in British Aircraft Corporation (Weybridge Division) Preliminary Technical Leaflets No. 256 (700 Series), No. 120 (800/810 Series), (Amendment TR 25 to Viscount Maintenance and Instruction Manuals and Amendment TR3 to the Accessories Manual cover the same subject.) Subsequent overhaul of the fire extinguishing system must be carried out in accordance with these specified periods in the FAA-approved maintenance schedule. (b) The spray ring system must be blown through with warm dry air to insure that the piping and discharge holes are free of obstruction(s) during the overhaul of the airplane at periods specified in the FAA-approved maintenance schedule. This directive effective October 3, 1965.
98-15-03: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) GE90 series turbofan engines. This action requires initial and repetitive eddy current inspections (ECI) for cracks in the high pressure compressor (HPC) stage 2-6 spool, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracks in the stage 3-4 and stage 4-5 interstage seal teeth and spacer arms. The actions specified in this AD are intended to identify cracks in the HPC stage 2-6 spool, which could result in an uncontained engine failure and damage to the aircraft.
2021-20-11: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 429 helicopters. This AD was prompted by reports of incorrectly staked spherical bearings in the directional control bellcrank assembly. This AD requires a one-time inspection of the lower surface of the spherical bearing in the directional control bellcrank assembly to determine if it is properly staked and, depending on the findings, applicable corrective actions. For certain helicopters, this AD also requires repetitive inspections and, depending on the findings, applicable corrective actions. This AD also provides a terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
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.
71-08-06: 71-08-06 AVCO LYCOMING: Amdt. 39-1192. Applies to all Avco Lycoming T5313A and T5313B turboshaft engines which incorporate part number 1-180-230-01 or -03 Overspeed Pickup Housing Assembly. Compliance required as follows: (a) To detect possible failure of the overspeed pickup gear bearings, perform the following inspection within the next 25 hours' time in service after the effective date of this AD and every 25 hours' time in service thereafter until item (b) is accomplished. Inspect Part Number 1-180-230-01 or -03 Overspeed Pickup Housing Assembly in accordance with the procedure given in Part 1 of Avco Lycoming Service Bulletin, Product Support, No. 0022, Rev. 1, dated 1 March 1971. (b) To prevent secondary failure of the power turbine (N2) accessory drive system as a result of failure of the overspeed gear bearings, accomplish the following within the next 200 hours time in service after the effective date of this AD. Replace Overspeed Pickup Housing Assembly P/N 1-180-230-01 or -03 with P/N 1-180-230-04 (Note: Part II of Avco Lycoming Service Bulletin, Product Support, No. 0022 provides information for modifying Part numbers 1-180-230-01 and -03 to the -04 configuration). The manufacturer's Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Avco, Lycoming Division, Avco Corp., 550 So. Main Street, Stratford, Conn. These documents may also be examined at the FAA, Eastern Region, Federal Building, J.F. Kennedy International Airport, Jamaica, New York and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and in the Eastern Region. This amendment is effective April 16, 1971.
2004-09-37: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier transport category airplanes, that currently requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. That AD also provides for two optional terminating actions for the detailed inspection(s). This action requires performing one or the other of the terminating actions. The actions specified by this AD are intended to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective June 11, 2004. The incorporation by reference of certain publications listed in the regulations was previously approved by the Director of the Federal Register as of May 8, 2003 (68 FR 19940, April 23, 2003).
2011-26-11: We are adopting a new airworthiness directive (AD) for the products listed above, with certain part number (P/N) high-pressure compressor (HPC) stages 2-5 spools installed. This AD was prompted by an aborted takeoff caused by liberation of small pieces from the HPC stages 1-2 seal teeth and two shop findings of cracks in the seal teeth. This AD requires eddy current inspection (ECI) or spot fluorescent penetrant inspection (FPI) of the stages 1-2 seal teeth of the HPC stages 2-5 spool for cracks. This AD only allows installation of either HPC stator stage 1 interstage seals that are pregrooved or previously worn seals with acceptable wear marks to prevent heavy rubs. We are issuing this AD to detect cracks in the HPC stages 1-2 seal teeth due to heavy rubs that could result in failure of the seal of the HPC stages 2-5 spool, uncontained engine failure, and damage to the airplane.
2021-19-12: The FAA is adopting a new airworthiness directive (AD) for MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports and a design review indicating that there could be possible corrosion on the main landing gear (MLG) outer cylinder at the interface with the gland nut on the shock strut installation and on the forward and aft trunnion pins in the MLG dressed shock strut assembly. This AD requires detailed inspections for corrosion on the MLG outer cylinder assemblies, certain MLG dressed shock strut assemblies, and the MLG outer cylinder at the gland nut threads, thread relief groove, and chamfer; a detailed inspection for the presence of corrosion-inhibiting compound (CIC) on the MLG forward and aft trunnion pins and grease adapter assemblies; applicable corrective actions; application of primer, paint, and CIC as applicable; re-identification of certain part numbers; and marking of the MOD STATUS field of the nameplate of certain parts. The FAA is issuing this AD to address the unsafe condition on these products.
72-21-01: 72-21-01 AERO COMMANDER DIVISION, NORTH AMERICAN ROCKWELL CORPORATION: Amdt. 39-1527. Applies to all Aero Commander (Intermountain) (CallAir) Models B-1 and B-1A series airplanes, S/N's 10,000 through 10,035. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failures of the landing gear shock struts, accomplish the following: (a) Remove main landing gear shock struts, P/N 18004-1 (left hand) and P/N 18004- 2 (right hand) and discard struts and all hardware except the wire cutters, P/N 18026. (b) Install replacement shock struts. P/N 18045-1 (left hand) and P/N 18045-2 (right hand). Attach these struts with the following hardware: (1) Upper strut attachment (2 required per strut): NAS 1306-26 Bolt AN 960-616 Washer AN 365-624 Nut (2) Lower strut attachment (1 required per strut): NAS 1306-38 Bolt AN 960-616 Washer AN 365-624 Nut(c) Replace the wire cutter, P/N 18026, on the new landing gear shock strut with two AN 3-6A bolts, two AN 960-10 washers, and two AN 365-1032 nuts. Repeat for the opposite strut. Aero Commander Service Bulletin A-23 pertains to this same subject. This amendment becomes effective October 6, 1972.
2004-09-16: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 and -300 series airplanes, that requires repetitive inspections of the bearing lugs of the rudder spring tab lever assembly for cracking, and corrective action if necessary. This action is necessary to prevent failure of the rudder flight control system due to such cracking, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2011-27-01: We are adopting a new airworthiness directive (AD) for Turbomeca Arriel 1B turboshaft engines. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as an increase in hot gas ingestion and an increase of temperature in the gas generator (GG) turbine rotor, potentially resulting in turbine damage and an uncommanded in-flight shutdown. We are issuing this AD to prevent over-temperature damage of the GG turbine, which could result in an uncommanded in-flight engine shutdown, and a subsequent forced autorotation landing or accident.
2021-19-13: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42-500 and ATR72- 212A airplanes. This AD was prompted by reports indicating that certain Thales global positioning system (GPS) satellite based augmentation system (SBAS) receivers provided, under certain conditions, erroneous outputs on aircraft positions. This AD requires replacing affected GPS SBAS receivers with new, improved receivers, 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.
2021-19-06: The FAA is superseding Airworthiness Directive (AD) 2007-02- 13, which applied to certain Dornier Luftfahrt GmbH (type certificate currently held by RUAG Aerospace Services GmbH) Model Dornier 228-212 airplanes. AD 2007-02-13 required inspecting the landing gear carbon brake assembly. This AD requires inspecting certain carbon brake assemblies and corrective actions if necessary. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the European Union Aviation Safety Agency (EASA) to correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as loose bolts and nuts on the landing gear carbon brake assembly. The FAA is issuing this AD to address the unsafe condition on these products.