Results
94-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 airplanes, that requires modification of the currently installed one-stage shock absorbers on the main landing gear to two-stage shock absorbers. This amendment is prompted by the results of an evaluation of the air-to-ground sensing logic relative to the operation of other airplane systems during landing in adverse weather conditions. The actions specified by this AD are intended to prevent a delay in sensing by the air-to-ground logic system that the airplane is on the ground, which could prevent the airplane from achieving the landing distances specified in the FAA-approved Airplane Flight Manual (AFM).
2022-03-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports of loose or disconnected powerplant FIREX interconnection hoses. This AD requires replacing certain existing FIREX hose assemblies with a newly designed FIREX hose assembly, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires repetitive detailed and eddy current inspections on the main fittings of the main landing gears (MLG) to detect discrepancies, and related investigative/corrective actions if necessary. This action also requires servicing the shock strut of the MLGs; inspecting the shock strut of the MLGs for nitrogen pressure, visible chrome dimension, and oil leakage; and servicing any discrepant strut. This action is necessary to detect and correct premature cracking of the main fittings of the MLGs, which could result in failure of the fittings and consequent collapse of the MLGs during landing. This action is intended to address the identified unsafe condition.
2022-02-20: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 C-2 and MBB- BK 117 D-2 helicopters. This AD was prompted by report that a collective bellcrank-K was found incorrectly installed on a helicopter. This AD requires inspecting the collective bellcrank-K to determine if it is correctly installed and has a correct position marking and, depending on the findings, applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also allows installation of an affected collective bellcrank-K, provided certain instructions are followed. The FAA is issuing this AD to address the unsafe condition on these products.
47-42-07: 47-42-07 DOUGLAS: (Was Mandatory Note 4 of AD-781-1.) Applies to the Following DC-6 Airplanes: AAL Serial Numbers 42855 to 42858, Inclusive; and UAL Serial Numbers 42866 to 42869, Inclusive. \n\nTo be accomplished not later than next engine change. \n\nIn order to prevent possible injury to flight crew members, it is necessary to install a spring in the handle operating mechanism of both windshield corner window assemblies. The purpose of the spring is to return the operating mechanism handle to a flush position when released in the open window position. To accomplish this, remove the AN 393-35 pin and the NAS 75-3-007 bushings from the attaching point of 2335660 wedge and the upper end of 4335656 channel on 5243829 windshield corner window assembly. Install 5243829F-4 clips on the inside of each leg of channel. Rework 2335658F-6 link. Install 5243829F-2 spring to clips and eyebolt. Install wedge to upper end of channel. Repeat the foregoing operations for removal and installation of identical parts to 5243829-1 windshield corner window assembly. \n\n(Douglas Service Bulletin DC-6 No. 19 covers this same subject.)
99-07-01: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Sikorsky Model S-76C helicopters, that currently requires, before further flight, inserting new operating limitations and performance data into the Rotorcraft Flight Manual (RFM) which require lower allowable gross weights for certain operational conditions. This amendment requires the same actions as the priority letter AD, but updates the previously referenced RFM's. This amendment is prompted by the discovery that the RFM's referenced in the priority letter AD have been revised. The actions specified by this AD are intended to provide the correct RFM references and to prevent an inability to achieve the published One-Engine-Inoperative (OEI) performance and subsequent loss of control of the helicopter.
2004-13-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes, that currently requires repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo- controls, and follow-on corrective actions if necessary. This amendment requires the replacement of certain elevator servo-controls with new, improved servo-controls. The actions specified by this AD are intended to detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control. This action is intended to address the identified unsafe condition. DATES: Effective August 13, 2004. The incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of August 13, 2004. The incorporation by reference of certain other publications, aslisted in the regulations, was approved previously by the Director of the Federal Register as of July 20, 2000 (65 FR 37476, June 15, 2000).
48-11-04: 48-11-04 REPUBLIC: Applies to Model RC-3 Aircraft. Compliance required by April 15, 1948. To provide security for the hydraulic pump handle attachment, the four self-locking nuts now used should be replaced by three AN 310-4 and one AN 310-5 castle nuts and cotters. The fulcrum bolt is already drilled for a cotter. The present clevis bolts may be drilled for the cotter or may be replaced by two AN 24-17 and one AN 24-13 clevis bolts. (Republic Service Bulletin No. 22 covers this same subject.)
2022-02-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a report of restricted collective lever movement caused by entanglement of the emergency flashlight strap with the cargo hook emergency release lever, causing the emergency flashlight to leave its seat. This AD requires replacing each affected emergency flashlight with a serviceable part, 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.
48-50-03: 48-50-03 MARTIN: Applies to Model 202 Aircraft. Compliance required prior to reinstalling autopilot servo control systems. Provide guards at joints of the stabilizer and wing flap torque tube systems in accordance with, or equivalent to, Martin Service Bulletin No. 72, dated October 22, 1948.