Results
76-17-02: 76-17-02 BEECH: Amendment 39-2697 as amended by amendment 39-3324. Applies to Models 58P and 58PA (Serial Numbers TJ-2 through TJ-19, TJ-21 through TJ-45, TJ-47 through TJ-54, and TJ-56 through TJ-58) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To prevent cracking of the cabin window located just forward of the cabin entrance door on the left side of the airplane, with resultant loss of cabin pressurization, accomplish the following: A. On airplanes that do not have the window frame reinforcement installed, as defined in Beechcraft Service Instructions 0828-110, Revision I or later approved revisions, accomplish the following in accordance with said service instructions: 1. Within 25 hours' time in service after the effective date of this AD and at the two next 50 hour time in service intervals thereafter, visually inspect the cabin window just forward of the cabin door on the left side of the airplane for cracks and if cracks are found during any inspection required herein, prior to any flight during which the cabin is pressurized, replace the window and install the window frame reinforcement. 2. If no cracks have been found during any inspection required in Paragraph A.1., within 100 hours' time in service after the initial inspection required by Paragraph A.1. install the window frame reinforcement. B. On airplanes that are flown unpressurized following discovery of a cracked window during any inspection required by Paragraph A of this Airworthiness Directive: 1. Fabricate a placard worded as follows: "DO NOT PRESSURIZE IN FLIGHT" and 2. Install said placard near the cabin pressurization control switch, and 3. Operate the aircraft in accordance with the placard until the cracked window is replaced. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.Amendment 39-2697 became effective August 24, 1976. This amendment 39-3324 becomes effective October 31, 1978.
2022-20-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports of insufficient clearance between the surrounding structure/skin of the aircraft and select bleed air ducts that supply the wing ice protection system (WIPS) in the rear fuselage. This AD requires inspecting the bleed air duct and surrounding structure for minimum clearance and damage, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-03-10: 90-03-10 BELL HELICOPTER TEXTRON, INC. (BHTI); CALIFORNIA DEPARTMENT OF FORESTRY; GARLICK HELICOPTERS; HAWKINS AND POWERS AVIATION; HERCULES; INTERNATIONAL HELICOPTERS, INC.; LENAIR CORPORATION; OFFSHORE CONSTRUCTION; OREGON HELICOPTERS; PILOT PERSONNEL INTERNATIONAL; SMITH HELICOPTERS; SOUTHERN AERO CORPORATION; SOUTHWEST FLORIDA AVIATION; and WEST COAST FABRICATIONS: Amendment 39-8029. Docket No. 90-ASW-09. Final Rule of Priority Letter AD 90-03-10. Applicability: All Model 204B, 205A, 205A-1, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and TH-1L helicopters, certificated in any category, with aluminum tail rotor grips, P/N 204-011-728-19, installed. Compliance: Required before further flight, unless already accomplished. To prevent failure of a tail rotor grip, which could result in loss of tail rotor control, accomplish the following: (a) Determine the part numbers and serial numbers of the tail rotor grips installed on the helicopter. (b) If the tail rotor grip installed is P/N 204-011-728-19 and is identified with any serial number listed below, remove and replace the grip with an airworthy part before further flight: Serial Numbers: A3-66287 A3-66333 A3-66356 A3-66361 A3-66365 A3-66370 A3-66377 A3-67149 A3-67171 A3-67184 A3-67207 (c) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the inspection and grip replacement may be accomplished. (d) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This Amendment (39-8029, AD 90-03-10) becomes effective on October 18, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-03-10 issued January 29, 1990, which contained this amendment.
2022-18-15: 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, Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600- 2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of corrosion on fuel clamshell couplings installed in the fuel tank, and a determination that new or more restrictive airworthiness limitations are necessary. This AD requires removing and replacing the fuel clamshell couplings on certain airplanes, and revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2004-21-03: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Model G-1159, G-1159A, G-1159B, and G-IV series airplanes. This AD requires a one-time inspection of the left and right aileron and elevator actuators to determine the part and serial numbers of each actuator, repetitive inspections of suspect actuators to detect broken damper shafts, and replacement of any actuator having a broken damper shaft. This AD also requires that operators report any broken damper shaft they find to the FAA. This AD also provides an optional terminating action for the repetitive inspection requirements of this AD. This AD is prompted by reports of broken or cracked damper shafts within the aileron and elevator actuator assemblies. We are issuing this AD to detect and correct broken damper shafts, which could result in locking of an aileron or elevator actuator (hard-over condition), subsequent loss of aileron or elevator control, and consequent reduced controllability of the airplane.
2022-20-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B2K-3C, B2-203, B4-2C, and B4-203 airplanes. This AD was prompted by reports of cracking of the flight compartment aft window frame and adjacent fuselage skin. This AD requires require a one-time check for previously accomplished repairs of the window pane and adjacent fuselage panel, and applicable corrective actions, 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.
95-25-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection and other specified actions to ensure that the ground stud assemblies at three locations of the airplane are installed properly and torqued to certain specifications, to verify the integrity of the components of the ground stud assemblies, and to detect heat damage in adjacent areas; and correction of any discrepancy. That AD was prompted by reports indicating that arcing occurred across the pins in the galley external power receptacle due to loose attach hardware on the ground stud. The actions specified in that AD are intended to ensure that the ground stud assemblies are attached correctly so that arcing will not occur. Such arcing, if not corrected, could result in heat damage to adjacent structure and a fire in the forward cargo compartment, the center accessory compartment, or the aft fuselagecompartment. This action would expand the applicability of the existing AD to include additional airplanes.
2004-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Becker Flugfunkwerk GmbH AR 4201 VHF AM transceivers. This AD requires adding an aircraft flight manual (AFM) limitation to the Limitations Section of the AFM, and cockpit placard due to the intermittent malfunctioning of the transceiver, or removing the affected transceiver from service. This AD results from reports of crewmembers having difficulty communicating with Air Traffic Control and other aircraft due to the AR 4201 VHF AM transceiver's inability to block interference from transmitters operating on frequencies other than those set in the transceiver. We are issuing this AD to prevent difficulty in communicating with Air Traffic Control and other aircraft due to intermittent malfunctioning of the transceiver.
99-26-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection to verify the tension values of the aileron control cables of the left- and right-hand wings, and corrective actions, if necessary. This action also requires either replacement of the aileron control cables with new, improved aileron control cables, or replacement of the aileron control cables with new, improved aileron control cables and modification of the pulley bracket on the rear face of the bulkhead at frame station 3100. The FAA is issuing this AD in response to mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interference between the turnbuckles of the aileron control cables and the lightening holes, which could result in binding of the aileron control cables and consequent reduced controllability of the airplane.
2013-17-04: We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A Series Engine. 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 describes the unsafe condition as oil leaks in the intake channel in the area of the valve guide on some cylinder heads could increase the oil consumption and result in engine stoppage. We are issuing this AD to require actions to address the unsafe condition on these products.