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2022-08-09: The FAA is adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a failure of the dual ethernet communication channel on a dual-channel data concentration and processing unit, which triggered the opening of electronic circuit breakers that caused several unintended system activations. This AD requires installing a software (SW) upgrade to the utility management system (UMS), 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.
89-20-02: 89-20-02 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6324. (Docket No. 89-ASW-32) Applicability: Model 369D and E helicopters, certificated in any category, with hubs of four-bladed tail rotors, Part Number (P/N) 369D21700-3 installed. Compliance: Required as indicated, unless already accomplished. To prevent fatigue failure of four-bladed tail rotor hubs which could result in loss of control of the helicopter, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, remove each tail rotor hub, (P/N) 369D21700-3, with serial numbers 196 through 251, installed on a helicopter and visually inspect for electrical arc burns and dye penetrant inspect for cracks. If arcing burns or cracks are observed as a result of this inspection, replace the hub with a serviceable unit prior to further flight. NOTE: McDonnell Douglas Helicopter Company Service Information Notices DN-160 and EN-50 pertain to this inspection. (b) Within 100 hours' time in service after the effective date of this AD, remove each tail rotor hub, (P/N) 369D21700-3, with serial numbers from 1 through 195, and visually inspect for electrical arc burns and dye penetrant inspect for cracks. If arc burns or cracks are observed as a result of this inspection, replace the hub with a serviceable unit prior to further flight. (c) Prior to installation in a helicopter, visually inspect each four-bladed tail rotor hub, (P/N) 369D21700-3, serial numbers 1 through 251, in spares inventory for electrical arc burns and dye penetrant inspect for cracks. If arc burns or cracks are observed as a result of this inspection, reject the hub. (d) Enter the results of the above inspections required by paragraphs (a) and (b) in the aircraft log and report cracks or arc burns to the Los Angeles FAA Aircraft Certification Office within 10 days of the inspection. Include in the report the helicopter model and serial number, hub part number, hub serial number, vendor identification (if possible), total hours of service for the hub, the location of any cracks and arc burns, and the geographical location (city, state) of the helicopter at the time of inspection. (e) Report the results of the inspections of paragraph (c) on hub spares, when arc burns or cracks are found, to the Los Angeles FAA Aircraft Certification Office within 10 days of the inspection. Include the date of the inspection, hub part number, hub serial number, vendor identification (if possible), total hours in service (if previously used, or zero hours if new), the location of arc burns and/or cracks, and the geographical location of the inspection. NOTE: All new hubs (zero service life) which are rejected should be returned to MDHC for further inspection and evaluation. (f) The reporting requirements of this regulation have been approved by the Office of Management and Budget under OMB No. 2120-0056. (g) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance with the AD may be accomplished. (h) An alternate method of compliance with this AD which provides an equivalent level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office, FAA, 3229 E. Spring Street, Long Beach, California. This amendment (39-6324, AD 89-20-02) becomes effective on October 16, 1989.
46-44-04: 46-44-04 CESSNA: (Was Mandatory Note 4 of AD-768-4.) Applies to 120 and 140 Aircraft Serial Numbers Up to and Including 9721. Replacement required prior to December 1, 1946. All U. S. Rubber Co. P-212 and P-212L Series flexible ducts installed in the carburetor hot air system should be replaced by U. S. Rubber Co. P-208-S duct or P-208 duct coated with neoprene by Cessna or its distributors. (Cessna Service Letter No. 16-120 and 140 covers this same subject.)
2022-09-17: The FAA is adopting a new airworthiness directive (AD) for certain Scheibe-Aircraft-GmbH Model SF 25 C gliders. This AD was prompted by 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 severe corrosion on the inner surface of the control stick tube. This AD requires inspecting the left-hand (LH) and right-hand (RH) control sticks for corrosion and, if corrosion is found, replacing the affected control stick. The FAA is issuing this AD to address the unsafe condition on these products.
2004-16-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Thales Avionics TA/RA VSI-TCAS indicators, installed on but not limited to certain transport category airplanes equipped with TCAS II change 7 computers (ACAS II), that requires a revision to the airplane flight manual (AFM) to advise the flightcrew to follow the audio annunciation when an RA fail message is triggered during a multi-aircraft encounter. This action also requires modification of the software for the TA/RA VSI-TCAS indicator, which would terminate the requirement for the AFM revision. This action is necessary to prevent the TA/RA VSI-TCAS indicator from displaying a conflicting "RA FAIL" message during a multi-aircraft encounter, which could result in the flightcrew ignoring the correct aural command and traffic display information if the flightcrew believes the TCAS II computer has malfunctioned, and consequently lead to a mid-air collision with other aircraft. This action is intended to address the identified unsafe condition.
2022-09-07: The FAA is superseding Airworthiness Directive (AD) 2019-11-05 for certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 429 helicopters. AD 2019-11-05 required inspecting the tail rotor (TR) pitch link assemblies, and replacing certain pitch link bearings. This AD was prompted by a report of a worn pitch link, and the FAA's determination that all TR pitch link assemblies are affected by the unsafe condition. This AD continues to require the actions specified in AD 2019-11-05, and revises the applicability and requires inspections of certain other TR pitch link assemblies. The FAA is issuing this AD to address the unsafe condition on these products.
96-19-03: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 and MD-11 series airplanes and KC-10A (military) airplanes, that requires repetitive inspections to detect corrosion or failure of the steel Hi-Lok fasteners at the inboard flap inboard track, and replacement of corroded/failed steel Hi-Lok fasteners with inconel Hi-Lok fasteners. This amendment also provides for termination of the repetitive inspections by replacing all of the steel Hi-Lok fasteners with inconel Hi-Lok fasteners. This amendment is prompted by reports of failed and/or corroded steel fasteners found in the inboard flap inboard track due to stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in binding of the flap and inability of the flap to extend or retract; this situation may lead to asymmetric flap deployment and subsequent reduced controllability of the airplane during flight.
47-49-06: 47-49-06 LOCKHEED: (Was Mandatory Note 39 of AD-763-3.) Applies to Model 49 Serials 2076 to 2088, Inclusive. Compliance required not later than next No. 3 inspection (or not later than next 150 hours for non-air-carrier operations). The rear oil pressure gage operational placard on the flight engineer's panel, LAC P/N 296770, must be removed or replaced with new placard, LAC P/N 296995 or equivalent. (LAC Service Bulletin 49/SB-245 covers this same subject.)
2004-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes equipped with off-wing escape slides, that requires an inspection of the door-opening actuators for the off-wing slide compartment on the right and left sides of the airplane to determine the actuator cartridge serial number, and corrective actions, if necessary. This action is necessary to prevent the door-opening actuators for the off- wing slide compartment from not firing, which could cause the door to open improperly and prevent the deployment of the off-wing escape slide, leading to the loss of an evacuation route. This action is intended to address the identified unsafe condition.
71-08-05: 71-08-05 FAIRCHILD-HILLER: Amdt. 39-1183 as amended by Amendment 39-1204 is further amended by Amendment 39-1315. Applies to all FH-227 and F-27 airplanes certificated in all categories. Compliance required as indicated. To detect cracks in FH-227 and F-27 Main Landing Gear Drag Strut Assemblies P/N 2.00259.002 Issue 2 and Issue 3, having 5000 hours' time or more accomplish the following: a) Within the next 100 hours after the effective date of this AD unless already accomplished within the past 1100 hours and thereafter at intervals not to exceed 1200 hours: 1) Inspect the end fittings of Drag Strut Assembly P/N 2.00259.002 Issue 2 and Issue 3 at the taper dowel holes using a penetrant flaw detection method in conjunction with a glass of at least 10 power or an equivalent method approved by the FAA. 2) Replace cracked parts before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can beperformed. 3) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Equivalent inspections, and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. 4) Report the results of the initial inspection findings required by this AD to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region (reporting approved by the Bureau of the Budget under B.O.B. No. 04-R0174). Amendment 39-1183 was effective April 16, 1971. Amendment 39-1204 was effective May 11, 1971. This Amendment 39-1315 is effective October 14, 1971.