Results
46-12-01: 46-12-01 CESSNA: (Was Mandatory Note 8 of AD-722-5.) Applies Only to AT-17 and UC-78 Series Airplanes. Inspection required immediately. On all AT-17 or UC-78 Series airplanes that have not been re-covered with grade A fabric at time of (or subsequent to) the original civil certification, inspect the fabric on wings and control surfaces to determine that the fabric complies with grade A fabric standards and has a sample breaking strength of at least 56 pounds. The lacing cord should also be checked and should have a breaking strength of at least 56 pounds when tested double. This inspection will require the testing of one or more samples of fabric and cord, the location from which the samples are to be taken and the number necessary will be determined by the CAA representative.
2024-23-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by the discovery during a quality review performed during manufacturing, that a torque strip indicator (material "Dykem") had been applied on the orifice fitting on certain slides' inflation reservoirs' venting holes. This AD requires an inspection for discrepancies of affected parts (certain reservoirs having certain orifices) and replacement of discrepant affected parts, and prohibits installing affected parts, 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.
99-18-18 R1: This amendment revises an existing airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Model R381/6-123-F/5 propellers, that requires initial and repetitive visual and ultrasonic inspections of propeller blades for cracks across the camber face, and, if blades are found cracked, replacement with serviceable blades. This amendment is prompted by an engineering analysis of field service data and certification testing that indicate that the repetitive visual inspection interval can be safely increased and that the ultrasonic inspections can be eliminated. The actions specified in this proposed AD are intended to detect propeller blade cracks and propagation, which if not detected could result in propeller blade separation and possible aircraft loss of control.
2016-03-03: We are superseding airworthiness directive (AD) 2013-11-13 for all Rolls-Royce plc (RR) Viper Mk. 601-22 turbojet engines. AD 2013-11- 13 required reducing the life of certain critical parts. This AD adds two new engine models and additional engine parts to the applicability. This AD was prompted by a determination by RR that additional parts for the RR Viper Mk. 601-22 as well as additional engine models are affected. We are issuing this AD to prevent failure of life-limited parts, which could lead to an uncontained part release, damage to the engine, and damage to the airplane.
51-02-02: 51-02-02 TEMCO: Applies to All Models GC-1A and GC-1B Airplanes Through Serial Number 3760, Except Those Equipped With Hanlon-Wilson Muffs. Compliance required by February 15, 1951. To prevent engine malfunctioning due to pieces of asbestos from the carburetor heat muff entering the carburetor, remove all asbestos strips on the right-hand (carburetor heat) muff. After removal of the asbestos, peen the muff collars to provide a tight fit on the exhaust stacks. This supersedes AD 47-25-08.
2024-24-07: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a determination that the overhead bin attachment could fail under certain conditions. This AD requires replacing existing overhead bin hook assemblies and support tubes with a different type, as specified in a Transport Canada AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2016-03-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of premature aging of certain chemical oxygen generators in the passenger compartment that resulted in failure of the generators to activate. This AD requires inspecting to determine if certain passenger chemical oxygen generators are installed, and replacement of affected generators. We are issuing this AD to prevent failure of the chemical oxygen generator to activate during an emergency situation, which could result in unavailability of oxygen and possible incapacitation of the occupants.
2024-24-06: The FAA is superseding Airworthiness Directive (AD) 2023-03- 09, which applied to certain ATR-GIE Avions de Transport R[eacute]gional Model ATR72-101, -102, -201, -202, -211, -212, and - 212A airplanes. AD 2023-03-09 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2023-03- 09 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2003-07-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive inspections for excessive wear of the internal and external splines of the torque tube couplings of the trailing edge flaps, and replacement of the couplings, if necessary. That AD also provides an optional modification that, if installed, constitutes terminating action for the inspection requirements. This amendment expands the applicability of the existing AD and requires new inspections of the torque tube assemblies and certain gearbox assemblies and universal joints in the drive system for the inboard trailing edge flaps, and follow-on actions if necessary. For certain airplanes, this amendment also adds a new optional modification, which, if installed, terminates certain inspections. The actions specified by this AD are intended to prevent separations in the drive system for the inboard trailing edge flaps, which could cause a flap skew condition that could result in damage to the flaps or fuselage, and consequent reduced controllability of the airplane.
48-49-03: 48-49-03 DOUGLAS: Applies to All DC-6 Airplanes. \n\n\tCompliance required not later than March 1, 1949. \n\n\tTo reduce the probability of a loss of power for electrical circuits considered to be essential in flight, these essential circuits were designed to be connected directly to the master bus. Other less essential circuits are connected to the master bus through a 500-ampere Burndy limiter (fuse). \n\n\tIn an undetermined number of aircraft some of the essential circuits were inadvertently connected to the distribution bus rather than to the master bus. \n\n\tIt is necessary, therefore, that all DC-6 aircraft be inspected and such rewiring as necessary be done to assure that the following circuit protectors are connected to the master bus: \n\n\tRadio Master (B1-102), Fuel Booster Pumps (B1-63, 97), Invertor Power (B1-111, 116), Propeller Booster (Curtiss Propellers only, F1-28, 29), Propeller Control (Curtiss: B1-141, 142, 143, 144. Hamilton Standard: B1-188, 189, 190, 191), Propeller Synchronizer (B1-145), Governor Control (Hamilton Standard only, B1-192), Generator Control Panel (Eclipse Generator System only, B1-246, 247, 248, 249. Reference Douglas Service Bulletin DC-6 No. 329. \n\n\t(Douglas Service Letter A214-T.3338/TFW dated October 22, 1948 covers this same subject.)
47-32-03: 47-32-03 BELL: (Was Mandatory Note 3 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 6, 10 Through 17, and 20 Through 22. Compliance required not later than next 25-hour inspection after September 15, 1947. To insure proper operation of the tail rotor control pedal adjustment mechanism at all times, replace the existing pawl stop, P/N 47-722-059-1 in each pedal assembly with a modified pawl stop, P/N 47-722-057-1. Check length of each pedal adjustment mechanism and adjust if necessary to 4 27/64 inches, tolerances +000, -1/32 inch, measured from the center of the pedal adjustment mechanism assembly AN 329-41 pin to lower end of pawl. (Bell Service Bulletin 47C23 dated April 10, 1947, also covers this subject.)
2001-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive eddy current inspections to detect cracks in the upper girder of the two main landing gear (MLG) brackets; and repair of a cracked bracket followed by repetitive inspections, or replacement of a cracked MLG bracket with an improved bracket, as applicable. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to detect and correct cracks in the upper girder of the MLG bracket, which could progress into the vertical stiffeners of the MLG bracket and result in reduced structural integrity of the landing gear. This action is intended to address the identified unsafe condition.
2024-24-11: The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SR20, SR22, and SR22T airplanes. This AD was prompted by a report of failure of the upper power lever. This AD requires repetitively inspecting (visual) the upper power lever for any crack(s) and depending on the results of any visual inspection, either inspecting (fluorescent penetrant) or replacing the upper power lever. This AD also requires reporting all inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
2016-05-02: We are superseding Airworthiness Directive (AD) 2011-13-11 and AD 2013-16-09 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-13-11 required an amendment of the airplane flight manual (AFM), repetitive checks of specific centralized fault display system (CFDS) messages, an inspection of the opening sequence of the main landing gear (MLG) door for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013-16-09 required an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and MLG door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door, and replacement of the MLG door actuator if necessary. AD 2013-16-09 also provided optional terminating action for the repetitive inspections. This new AD reduces the interval of the MLG door opening sequence inspection, requires replacing or modifying certain MLG door actuators, andalso requires a flushing procedure to be performed when installing a new MLG door actuator. This AD was prompted by a determination that the interval of the MLG door opening sequence inspection must be reduced. We are issuing this AD to detect and correct deterioration of the damping ring and associated retaining ring of the MLG door actuator, which can sufficiently increase the friction inside the actuator to restrict opening of [[Page 12414]] the MLG door by gravity, during operation of the landing gear alternate (free-fall) extension system. This condition could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and injury to occupants.
2024-24-51: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of a cracked main rotor hub (MRH) sleeve. This AD requires repetitively inspecting certain MRH sleeves and prohibits installing those MRH sleeves unless the inspection is done, 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.
47-42-05: 47-42-05 DOUGLAS: (Was Mandatory Note 2 of AD-781-1.) Applies to the Following DC-6 Airplanes: AAL Serial Numbers 42854 to 42865, Inclusive; Serial Numbers 42879 and 42880; UAL Serial Numbers 42866 to 42875, Inclusive; and Panagra Serial Numbers 42876 to 42878, Inclusive. \n\nTo be accomplished not later than August 1, 1948. \n\nIn order to prevent window curtain interference when opening emergency exit doors, remove hook assemblies, 2346313, -500, from curtain track, 5337482, and from the window curtain assemblies, 3343932-512, and replace with new slides, 1335554 and hooks 1345849 on each side of the four forward and the two aft cabin emergency exit door window frames. \n\n(Douglas Service Bulletin DC-6 No. 15 covers this same subject.)
2024-23-01: The FAA is adopting a new airworthiness directive (AD) for certain Robinson Helicopter Company Model R44 and R44 II helicopters. This AD was prompted by several reports of failed clutch actuators and failed rivets attaching the belt tension clutch actuator brackets (bracket) to the fan scroll housing. This AD requires inspecting each bracket and, depending on the results, accomplishing additional inspections or taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
98-09-28: This amendment adopts a new airworthiness directive (AD), applicable to all Shorts Model SD3-30 and SD3-60 series airplanes equipped with certain fire extinguishers, that requires replacement of the covers for fire extinguisher adapter assemblies that are installed on certain bulkheads with new covers that swivel to lock the extinguishers in place; and replacement of nozzles and triggers on these fire extinguishers with better fitting nozzles and stronger triggers. It also requires the installation of new fire extinguisher point placards and a revision of the Airplane Flight Manual to instruct the flight crew in the use of the new covers for these adapter assemblies. This amendment is prompted by reports that these fire extinguishers are not discharging properly because they do not fit correctly with the adapter, and that triggers on these extinguishers are failing. The actions specified by this AD are intended to ensure that, in the event of fire in the baggage bay, extinguishing agent is properly distributed within this area, and portable extinguishers operate properly; and to prevent injury to crew and passengers when a portable extinguisher is discharged.
2016-04-04: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA26-AT, SA226-T(B), SA226-AT, SA226-T, SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C- 26B), and SA227-TT airplanes. This AD was prompted by information that the airplane flight manual (AFM) does not provide adequate guidance in the handling of engine failures, which may lead to reliance on the negative torque system (NTS) for reducing drag. This condition could lead the pilot to not fully feather the propeller with consequent loss of control. This AD requires inserting updates into the airplane flight manual (AFM) and/or the pilot operating handbook (POH) that will clearly establish that the NTS is not designed to automatically feather the propeller but only to provide drag protection. We are issuing this AD to correct the unsafe condition on these products.
47-02-05: 47-02-05 DOUGLAS: (Was Mandatory Note 13 of AD-762-7.) Applies to C-54 and DC-4 Aircraft. \n\n\tTo be accomplished not later than next periodic inspection. \n\n\tInspect the entire electrical system for evidence of damage due to chafing, heat, or foreign matter; and of loose terminals and connections. Pay particular attention to wiring subjected to heat from voltage regulators; the buss to the main cabin junction box; and any screws projecting into cable ducts. Correct any unsatisfactory conditions.
47-32-07: 47-32-07 BELL: (Was Mandatory Note 7 of AD-1H-1.) Applies to All Model 47B With Aircooled 6V4-178-B3, -B32, O-335-1, or O-335-3 Engines. Compliance required not later than next 25-hour inspection after September 15, 1947. To eliminate chafing of intake manifold balance pipe against the oil tank an extra piece of hose, Aircooled P/N 11868, should be installed on the pipe at the side of the tank where the oil filter is mounted and approximately 1 3/8 inches from the hose which connects the two manifold pipes. (Franklin Service Bulletin No. 55 dated May 28, 1947, pertains to this same subject.)
2001-20-05: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0100 series airplanes, that currently requires replacement of the anti-skid control boxes with improved units. This amendment requires modification or replacement of the anti-skid control boxes with new, improved units, which render the skid control boxes even less susceptible to electromagnetic interference during power-up and power-down transients. This action is prompted by continuing mandatory airworthiness information from a foreign airworthiness authority. The actions specified by this AD are necessary to prevent electromagnetic interference with the anti-skid control system, which could result in reduced brake pressure during low-speed taxiing, and consequent reduced controllability and performance of the airplane. This action is intended to address the identified unsafe condition.
77-25-04: 77-25-04 ALEXANDER SCHLEICHER: Amendment 39-3095. Applies to Model Rhonlerche II gliders, all serial numbers, certificated in all categories. Compliance is required within the next 5 hours time in service after the effective date of this AD, unless already accomplished. To prevent shearing of the cotter pins which safety the aileron control Clevis pins and possible loss of aileron control, accomplish the following: (a) Inspect the Clevis pins connecting the aileron control cables to the main control shaft and if found not to be inserted from aft to front (Head of Clevis pin must face wheelbox), re-insert the Clevis pins from aft to front and install new cotter pins. (b) Inspect the skid. If it is found to be 3/4 inches or less in thickness, replace the skid with a serviceable skid of the same part number or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy,A.P.O. New York, N.Y. 09667. NOTE: During the inspection required by this paragraph, particular attention should be given to the skid in the area from 24 to 32 inches in front of the wheel-axle. (c) Revise the Rhonlerche II flight and service manual as follows: (1) On Page 5, after the words "connect at the control shaft", insert the words "the Clevis pins must be inserted from aft to front". (2) On Page 9, prior to the words "If the glider is used much on rocky and . . .", insert the sentence "Measured 24 to 32 inches forward of the wheel-axle, the skid must not be thinner than 3/4 inch". Note: Alexander Schleicher Technical Note No. 14 dated September 15, 1977, deals with the same subject as this AD. This amendment becomes effective December 27, 1977.
2024-23-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-8, 737-9, and 737-8200 (737 MAX) airplanes. This AD was prompted by a report of a non-conforming installation of spoiler wire bundles that led to unintended spoiler motion, including one instance of a flight spoiler hardover. Further investigation identified the potential for a hardover of more than one flight spoiler on the same wing, which can exceed full lateral control capability leading to loss of control of the airplane. This AD requires a one-time inspection of the clearance between the spoiler control wire bundles and the adjacent structure, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2016-04-20: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, Model 757 airplanes, Model 767 airplanes, and Model 777 airplanes. This AD results from fuel system reviews conducted by the manufacturer. This AD requires an inspection to determine if certain motor-operated valve (MOV) actuators for the fuel valves are installed, and replacement of any affected actuators. Previous ADs addressed this Special Federal Aviation Regulation No. 88 (SFAR 88) issue for the majority of the airplanes delivered with these actuators. Since those ADs did not cover all of the airplanes, and for some airplanes delivered with improved actuators, there was no restriction on installation of replacement actuators with the unsafe condition, this additional rulemaking action is required. As with the related ADs, we are issuing this AD to prevent electrical energy from lightning, hot shorts, or fault current from entering the fuel tank through the fuel valve actuator shaft, which could result in fuel tank explosions and consequent loss of the airplane.