Results
2013-04-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of an uncommanded slide back of the co-pilot seat to the end stop position. This AD requires a one-time inspection for a part number, a tensile test of the affected seats, and corrective actions if necessary. We are issuing this AD to detect and prevent unwanted movement of a pilot or co-pilot seat in the horizontal direction, which could lead to inadvertent input on the flight control commands and possibly result in loss of controllability of the airplane.
72-19-03: 72-19-03 NORTH AMERICAN ROCKWELL: Amdt. 39-1519. Applies to all Models NA-265, NA-265-20, and NA-265-30 airplanes, plus NA-265-40, serial numbers 282-1 thru 282- 98; NA-265-50, serial number 287-1; and NA-265-60, serial numbers 306-1 thru 306-37. Within the next 25 hours' time in service after receipt of this telegram, but not later than 1 October 1972, whichever occurs first, unless already accomplished, comply with the inspection and parts replacement provisions of North American Rockwell Sabreliner Service Bulletin 72-14 dated 25 August 1972, or later FAA approved revision, or equivalent FAA approved inspection and replacement. This amendment is effective September 15, 1972 and was effective upon receipt for all recipients of the telegram dated 25 August 1972 which contained this amendment.
2004-16-08: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. Model MD900 helicopters. This action requires installing a fan input force limiting control rod assembly fail-safe device (fail-safe device). This AD also requires, after installing a fail-safe device, before the first flight of each day, checking the fail-safe device for bent clips, taut lanyards, and piston rod movement. If any of these conditions are found, this AD requires replacing the control rod assembly with an airworthy control rod assembly before further flight. This amendment is prompted by an accident report of fatigue failure of the piston rod in the spring capsule on a control rod assembly. The actions specified in this AD are intended to provide a temporary backup support system in the event of a piston rod failure and to prevent subsequent loss of control of the helicopter.
47-10-21: 47-10-21 LOCKHEED: (Was Mandatory Note 23 of AD-763-3.) Applies to Model 49 Serials Up to and Including 2088. Compliance required prior to July 1, 1947. Install steel torque links, LAC P/N 293882, on each main landing gear. (LAC Service Instruction 49/SI-100A covers this same subject.)
2013-04-06: We are adopting a new airworthiness directive (AD) for the Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters. This AD requires modifying the main landing gear control panel (control panel) 33G, connector 100G, and wiring. It also requires tests to ensure that these modifications function correctly. This AD was prompted by reports of electro-valve power supply disruptions while a helicopter is on the ground, causing the landing gear to retract and the helicopter nose to drop. This results in damage to the forward section of the helicopter's bottom structure. The actions of this AD are intended to prevent an uncommanded landing gear retraction that would cause the helicopter nose to drop and hit the ground while the rotor blades are spinning.
2022-09-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that on the A350 final assembly line (FAL), certain load sensing drive struts (LSDS) and drive struts (DS) were found not adjusted (the nut was not torqued) and not locked. Investigation revealed that the LSDS and DS had been changed as re-work action due to pre-installation damage, but production operations (adjustment and locking) were not done afterwards. This AD requires, for certain airplanes, inspection of the LSDS for correct adjustment and locking, and replacement if necessary, and, for certain other airplanes, replacement of each affected DS 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.
87-16-05: 87-16-05 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5687. Applies to Lockheed Model L-188A and L-188C airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To ensure the continuing structural integrity of these airplanes, accomplish the following: A. Within one year after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program which provides no less than the requirements specified for the structurally significant details listed in Section III C. of Lockheed Report No. LR29428, dated January 16, 1984, and Revision A, dated May 14, 1986, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Cracks found in the structurally significant details as a result of the supplemental inspections required by paragraph A., above, must be repaired before further flight in accordance with an FAA-approved method.C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base to accomplish the requirements of this AD. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective August 31, 1987.
59-12-07: 59-12-07 WRIGHT: Applies to R-1300-1A Engines Installed in North American T-28A Aircraft. Compliance required by July 1, 1959, or within the next 10 hours of operation, whichever occurs first. There is a possibility that a small number of R-1300-1A engines were released by the military for civil sale and use with crankshafts that had undergone a chrome plating salvage repair operation during the last military overhaul. This operation was found to render the crankshaft unsafe and accordingly was discontinued. Engines with these salvaged crankshafts have a note to this effect in the records and log sheets kept for the engine. No other identification of such engine was provided. A re-examination of the military records of these engines must be made and if any indication is found that the crankshaft has been salvaged by chrome plating it is mandatory that the engine be removed from service consistent with the above stipulated compliance provisions and prior to reuse of the engine in civil aircraft the affected crankshaft must be replaced.
2022-09-09: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP- 1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine (HPT) rotor interstage seals, HPT rotor stage 2 disks, low pressure turbine (LPT) stage 1 disks, LPT stage 2 disks, LPT stage 3 disks, and LPT stage 4 disks. This AD requires revising the airworthiness limitations section (ALS) of the applicable CFM LEAP-1A Engine Shop Manual (ESM) and the operator's existing approved continuous airworthiness maintenance program (CAMP) to incorporate reduced life limits for these parts. This AD also requires the removal of certain LPT stage 4 disks identified by serial number (S/N) prior to their new life limits. The FAA is issuing this AD to address the unsafe condition on these products.
99-17-18: This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters, Inc. (MDHI) Model 600N helicopters, that requires applying serial numbers to several life-limited components related to pitch control and removing and replacing the components according to new life-limits. This amendment is prompted by fatigue tests that indicate a need for shorter service lives for these components. The actions specified by this AD are intended to prevent failure of the collective pitch control tubes, collective stick housings, and collective pitch tube assemblies, which can cause loss of collective pitch control, and subsequent loss of control of the helicopter.