Results
59-18-03: 59-18-03 CURTISS: Applies to All Models C634S-C400 and C634S-C500 Series Propellers. Compliance required at first propeller overhaul after January 1, 1960, but not later than May 1,1960. Peculiar wear of power unit motor and mating speed reducer splines in Curtiss C634S- C400 and C634S-C500 Series propellers has been observed at a time short of a full overhaul period. In order to minimize the possibility of such occurrences, provide a new motor rotor assembly which incorporates a longer shaft with splines of a larger pitch diameter and a new mating splined sleeve and high speed drive gear. Modification of the 145295-2 power unit assembly in Curtiss C634S-C400 and C634S-C500 Series propellers to the 163308 power unit assembly accomplishes the desired objective. (Curtiss Service Bulletin No. C-24 covers this same subject.) Compliance with AD 59-07-01 is no longer required after compliance with this AD.
98-15-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a revision of the Airplane Flight Manual (AFM) to alert the flightcrew that both flight management computers (FMC's) must be installed and operational. That AD also requires an inspection to determine the serial number of the FMC's; and follow-on corrective actions, if necessary, which terminate the AFM revision. That amendment was prompted by a report indicating that, due to incorrect multiplexers that were installed in the FMC's during production, certain data busses failed simultaneously during a ground test. This amendment removes the terminating action from the existing AD. The actions specified in this AD are intended to prevent loss of airspeed and altitude indications on both primary flight displays in the cockpit, and/or loss or degradation of the autopilot functionality due to installation of incorrectmultiplexers, and consequent failure of the data busses.
2004-09-30: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Model 1900C airplanes. This AD requires you to replace the 200-amp electrical power current limiter in the landing gear with a 60-amp electrical power circuit breaker. This AD is the result of reports about the inability to automatically lower the landing gear and the inability to operate other related electrical systems. We are issuing this AD to prevent heat damage to the electrical wiring in and around the landing gear electrical systems components, which could result in the inability to operate critical control systems. This failure could lead to loss of control of the airplane.
73-14-05: 73-14-05 GRUMMAN AMERICAN AVIATION: Amendment 39-1681. Applies to Grumman Model G-1159 airplanes S/N 1 through 107 and 775, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of the AD, unless already accomplished. To prevent degradation of aircraft control due to inability of the pilot to reach the autopilot disconnect button in the event of a malfunction, relocate the autopilot disconnect button P/N W103MB3W, in accordance with Grumman Aircraft Service Change No. 80 or in an equivalent position approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective July 12, 1973.
2021-20-20: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD was prompted by 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 identifies the unsafe condition as installation of the wing leading edge tank fuel pickup assembly in a pre-stressed condition, which could cause cracks in the wing spar web or the fuel pickup assembly pipe. This AD requires inspecting the angle of the support bracket on the wing leading edge tank fuel pickup assembly and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
54-06-01: 54-06-01 DOUGLAS: Applies to Models DC-6, DC-6A and DC-6B Series Aircraft. \n\n\tCompliance required as soon as practicable but not later than July 1, 1954, for DC-6A and DC-6B aircraft, and November 1, 1954, for DC-6 aircraft. \n\n\tTo eliminate possible inadvertent discharge of CO2 into cabin heater or hydraulic accessories compartment accompanied by operation of cabin master depressurization control (or closing of the control valve on early DC-6 aircraft), when discharging CO2 into a nacelle, rework the two Kidde 3/4-inch stop valves P/N 870003 by replacing spring P/N 201496 with heavier spring P/N 30568. The reworked valve should be reidentified as P/N 871107. \n\n\t(Douglas General Service Letter No. DC-6 No. 176 revised December 31, 1953, also covers this subject.)
73-05-02: 73-05-02 BELLANCA: Amdt. 39-1599. Applies to Model 17-30A, Serial Numbers 30346 through 73-30496; Model 17-31A, Serial Numbers 32-37 through 73-32-97; and Model 17-31ATC, Serial Numbers 31015 through 73-31045, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible failure of the rudder control system, accomplish the following: (A) Within the next 10 hours time in service after the effective date of this airworthiness directive, unless already accomplished, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, inspect the rudder pedal shaft assemblies, Part Numbers 195266, 195268, 195270 and 195272, equipped with brakes where the vertical tube is welded to the horizontal tube for evidence of cracks or other failures in accordance with Bellanca Service Letter No. 77 dated February 10, 1973, or later approved revisions, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. All shaft assemblies found cracked must be replaced prior to further flight with a new part of the same number utilizing a horizontal tube having a .058" wall thickness. (B) Within the next 100 hours time in service after the effective date of this airworthiness directive unless already accomplished, replace all rudder shaft assemblies, Part Numbers 195266, 195268, 195270, and 195272, on which rudder/brake pedals are installed having .049" thick horizontal tube walls with a new assembly of the same part number utilizing a horizontal tube having a .058" wall thickness in accordance with Bellanca Service Letter No. 77 dated February 10, 1973, or later FAA approved revisions, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. Rudder pedal shaft assemblies not having the brake pedal installed are not affected by this airworthiness directive. (C) The repetitive inspections of paragraph (A) of this airworthiness directive are no longer required when compliance with paragraph (B) of this airworthiness directive is accomplished. (D) Aircraft Serial Numbers 73-30497 through 73-30509, 73-32-98 through 73-32- 100 were produced with .049" wall tubes but with a reinforcement gusset added and are exempt from this airworthiness directive unless the rudder pedals have been replaced during the service life of these aircraft. This amendment becomes effective March 7, 1973.
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).