Results
2006-13-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727 airplanes. This AD requires repetitive measurements of the freeplay of the left and right outboard aileron balance tabs and of the upper and lower rudder tabs, and related investigative/corrective actions if necessary. This AD also requires repetitive lubrication of the hinge bearings and rod end bearings of the outboard aileron balance tabs. This AD results from reports of freeplay-induced vibration of the outboard aileron balance tabs and rudder tabs. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane.
69-22-01: 69-22-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-863. Applies to BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated unless already accomplished. To prevent a malfunction of the ventral stairway door, accomplish the following: (a) Inspect ventral stairway starboard hinge bolt (M.M. 52-10) for signs of looseness or insecurity within the next 100 hours' time in service after the effective date of this AD unless already accomplished within the last 550 hours' time in service and thereafter at intervals not to exceed 650 hours from the last inspection. (b) If during the inspection required by paragraph (a), the starboard hinge bolt (M.M. 52-10) is found to be insecure or to have rotated loose, secure the hinge bolt before further flight in accordance with BAC 1-11 Alert Service Bulletin 52-A-PM 3701, dated March 24, 1969, or later ARB-approved issue, or FAA-approved equivalent. (c) The repetitive inspection required by paragraph (a) may be discontinued after the hinge bolt has been secured in accordance with paragraph (b). This amendment becomes effective November 17, 1969.
2020-26-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks found in fastener holes at a certain station of the center wing box. This AD requires repetitive external surface high frequency eddy current (HFEC) inspections and repetitive external surface ultrasonic inspections; or repetitive internal detailed inspections; of a certain station of the center wing box for any cracking, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2020-25-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that corrosion was found on the shock strut cylinders during unscheduled maintenance of the nose landing gear (NLG). This AD requires a modification of the NLG shock strut cylinder. The FAA is issuing this AD to address the unsafe condition on these products.
70-10-01: 70-10-01 BEECH: Amdt. 39-986 as amended by Amendment 39-1222. Applies to all 99 Series Airplanes (Serial Numbers U-1 through U-114). Compliance: Required as indicated, unless already accomplished. To prevent a fire hazard, accomplish the following: Within the next 50 hours' time in service after the effective date of the AD, modify the printed circuit boards in the edge lighted instrument panels in accordance with either Beechcraft Service Instruction No. 0203-351 or any other method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. Amendment 39-986 became effective May 12, 1970. This Amendment 39-1222 becomes effective June 3, 1971.
2006-13-14: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This action requires initial and repetitive inspections of each tail rotor counterweight bellcrank (bellcrank) with a specified part number and serial number. If external damage, a crack, roughness, or looseness between the bearing set and bellcrank is found or if bearing set axial play exceeds 0.015 inch, this action requires replacing the bellcrank with an airworthy bellcrank with two prefix letters in the serial number. This amendment is prompted by reports of failure and subsequent loss of a weighted portion of the bellcrank and reports of certain replacement bellcranks having design flaws. The actions specified in this AD are intended to prevent bellcrank failure, loss of a weighted portion of the bellcrank, and subsequent loss of control of the helicopter.
2000-06-05: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2 helicopters. This action requires replacing certain tail rotor blades before further flight after April 30, 2000. This amendment is prompted by loss of control of a helicopter due to a lightning strike on a tail rotor blade. This condition, if not corrected, could result in loss of a tail rotor blade and subsequent loss of control of the helicopter
2009-18-06: 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: During operation in icing conditions, an asymmetric configuration of the de-icing boots was detected, occurring during the inflation and deflation check of the de-icing system. This was found to be due to an unexpected failure mode in the pneumatic and de-icing system's control electronic logic. This condition, if not corrected, could affect the de-icing capabilities of the boots installed on the wing and horizontal stabilizers, potentially leading to loss of control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
72-21-05: 72-21-05 CANADAIR: Amendment 39-1536. Applies to all Canadair CL-44 type aircraft certificated in all categories. Compliance required as indicated. Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 1900 hours in service and at intervals not exceeding 2000 hours in service from the last inspection accomplish the following: 1. Inspect the horizontal stabilizer rear spar to fuselage attachment fittings, P/N 44A45022A and B, for cracks in accordance with Paragraph 3.4 of Canadair Service Information Circular No. 379-CL44, dated 7 July 1971, or equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Replace cracked parts before further flight with parts of the same part number or FAA-approved equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Upon request, with substantiating data submitted through an FAA maintenance inspector, the replacement intervals specified herein may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective October 17, 1972.
2006-13-10: We are adopting a new airworthiness directive (AD) that supersedes AD 92-07-05, which applies to certain Raytheon Aircraft Company (Raytheon) (formerly Beech) 65, 90, 99, and 100 series airplanes. AD 92-07-05 currently requires you to inspect the rudder trim tab for proper moisture drainage provisions, and if the correct drainage provisions do not exist, before further flight, modify the rudder trim tab. This AD results from receiving and evaluating new service information that requires the actions of AD 92-07-05 for the added serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes. This AD retains all the actions of AD 92-07-05 and adds serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes in the applicability section. We are issuing this AD to prevent water accumulation in the rudder trim tab, which could result in a change in the mass properties and possibly a lower flutter speed of the airplane. A lower airplane flutter speed could result in failure and loss of control of the airplane.