Results
2008-22-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Two operators of A300 aircraft fitted with General Electric (GE) CF6-50 engine series have reported cracks on the lower side of Rib 5 in the pylon box. * * * * * Investigations disclosed that these cracks are due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. * * * * * Cracking of the engine pylons could result in reduced structural integrity of the engine support structure. We are issuing this AD to require actions to correct the unsafe condition on these products.
2006-10-05: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B airplanes. This AD requires a one-time inspection to see if a faulty uplock axle for the shock strut of the main landing gear (MLG) is installed, and replacing the uplock axle with a new uplock axle if necessary. This AD results from a report of a cracked uplock axle caused by hydrogen embrittlement during the manufacturing process. We are issuing this AD to prevent failure of the uplock mechanism, which, combined with a loss of hydraulic pressure, could result in an uncommanded extension of the MLG.
2020-16-12: The FAA is adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. 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 inadvertent fuel shut-off to the engine during the operation of the flaps due to the fuel and flap control levers being located too closely together. The FAA is issuing this AD to address the unsafe condition on these products.
56-13-02: 56-13-02 SIKORSKY: Applies to All Model S-51 Helicopters. Compliance required as indicated. As a result of recent service experience, the main rotor hubs are to be retired from service at the times indicated. 1. Main rotor hubs, S10-10-1015 and S510117, are to be replaced every 480 hours. Magnaflux inspections are to be conducted at the 200-240 hour interval. 2. Main rotor hubs, S10-10-1033, with 1/16 inch or larger chamfer at the base on the outer edge of each arm, with 240 hours of service, must be replaced by September 15, 1956, or prior to the accumulation of 480 hours, whichever occurs first. The S510122 outer arm locknuts are to be checked for looseness every 30 hours on hubs continuing in service beyond 240 hours. With any indication of looseness, the hub is to be removed and a Magnaflux inspection for cracks at the root radius of the threads on the outer arm is to be conducted. Any hub with a crack is to be replaced. Hubs with 480 hours or more must be replaced prior to further service. After September 15, 1956, all hubs are to be replaced every 240 hours. 3. Main rotor hubs, S10-10-1033, with chamfer less than 1/16 inch at the base on the outer edge of each arm are to be replaced every 960 hours. Magnaflux inspections are to be conducted every 200-240 hours of service. (Service Information Circular No. 76 Revisions D & F cover the same subject.) This supersedes AD 49-44-01.
99-24-09: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires modifying the flap inboard attachment fittings through the installation of a reinforcement angle bracket on the inside of the center web of both flap inner attachment fittings. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the potential of the inboard flap attachment fittings buckling while operating at full flaps with full power into a head-on wind gust, which could result in loss of control of the airplane.
2020-16-19: The FAA is adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD was prompted by two incidents of erroneous low oil pressure caution cockpit indications and unintended actuation of the main gearbox (MGB) auto bypass valve. This AD requires installing auxiliary circuit breaker modification (MOD) kits and inserting a Rotorcraft Flight Manual (RFM) Supplement into the existing RFM for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2020-17-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-2 helicopters. This AD was prompted by the discovery that certain longitudinal trim actuators, lateral trim actuators, and yaw trim actuators, which are certified for installation on MBB-BK 117 C-2 helicopters, were erroneously listed as eligible for installation on MBB-BK 117 D-2 helicopters. This AD requires removing the affected parts from service and prohibits installing the affected parts on MBB- BK 117 D-2 helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
68-08-07: 68-08-07 LOCKHEED: Amendment 39-585. Applies to Model 1329 Airplanes, Serial Numbers 5001 through 5092, 5094 through 5096. Compliance required as indicated. Recent calibration of several airplanes has revealed a difference in the airspeed and altimeter system static position error from the values presented in the AFM. These differences are in excess of tolerances which can be accepted as normal deviation from an Airplane Flight Manual calibration curve. To detect similar discrepancies, the following is required unless the system has previously been calibrated in accordance with the referenced manufacturer's instructions. Within the next 100 hours' time in service after the effective date of this AD, calibrate the pitot static system in accordance with the instructions given in Lockheed-Georgia Service Bulletin 329-250, Section 2a through 2p, or later FAA approved revision; or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective April 19, 1968.
48-06-03: 48-06-03 NAVION: Applies to All models Equipped With Hartzell Propeller Blade Models 8428, 8428C, 8428R Having Serial Numbers Below 61000. Compliance required by April 15, 1948. Examine all Model 8428, 8428C, and 8428R blades having Serial Numbers below 61000 in bright daylight or strong artificial light on the front face in the area approximately 4 inches outboard of the blade clamp. Any fillers used in the blade will be discernible to the naked eye. If fillers are found in this area, the paint should be carefully removed and the fillers removed from the blade. Defects that can be eliminated by removing material to form a shallow saucer not over 1/8 inch at its deepest point, 3/8 inch in width overall, and 1 inch in length overall, should be repaired. Following removal of the defects, the area from which paint has been removed should be repainted and the propeller rebalanced before being returned to service. Blades having defects that cannot be repaired by the above methodor by methods described in the applicable portions of CAM 18, should be returned to the propeller manufacturer. The exact location and the extent of rework necessary to remove any defect should be recorded in the log book. Areas having maximum material removed may not have additional material removed for subsequent injuries.
2002-11-05 R1: The FAA is adopting a new airworthiness directive (AD) to revise AD 2002-11-05, which applies to certain Air Tractor, Inc. (Air Tractor) AT-400 series and Models AT-501, AT-802, and AT-802A airplanes. AD 2002-11-05 establishes a safe life for the wing lower spar cap. Since we issued AD 2002-11-05, we have received reports of cracks found prior to the established safe life on AT-400 series airplanes and on Model AT-802A airplanes. We are issuing separate AD actions for AT-400 series and Models AT-802 and AT-802A airplanes to address the unsafe condition of those airplanes. This AD retains the actions required in AD 2002-11-05 for Model AT-501 airplanes and removes AT-400 series and Models AT-802 and AT-802A airplanes from the applicability of AD 2002-11-05.