Results
2001-02-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A, B, L, L1, and L3 helicopters. This AD requires inspecting the collective lever assembly (assembly) for a raised forging boss, inspecting the assembly for adequate clearance between the collective lever and the swashplate outer ring (outer ring), and modifying any assembly with a raised forging boss and inadequate clearance before further flight. Modifying any assembly that has a raised forging boss and adequate clearance would be required before further flight after January 31, 2001. This AD is prompted by the discovery that a raised forging boss could result in control system interference. The actions specified by this AD are intended to prevent interference between the collective lever and the outer ring, damage to flight controls, and subsequent loss of control of the helicopter.
2018-04-02: We are adopting a new airworthiness directive (AD) for Viking Air Limited Models DHC-6-1, DHC-6-100, DHC-6-200, DHC-6-300, and DHC-6- 400 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as aileron cable wear; fouling at the wing root rib, fuselage skin, and wing root rib fairlead; and/or fraying of the cable from the root rib fairlead. We are issuing this AD to require actions to address the unsafe condition on these products.
75-12-06: 75-12-06 PIPER: Amendment 39-2227. Applies to Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 certificated in all categories. Compliance required as indicated. 1. Affects the fin forward spar to fuselage attachment assembly where the channel P/N 20749-0 and the straps P/N 20749-5 and -6 are riveted together. (a) Within the next 25 hours' time in service, unless already accomplished within the last 75 hours' time in service: (i) Inspect the channel P/N 20749-0 and the two straps P/N 20749-5 and -6 in the area of the channel bend relief holes for cracks using a dye penetrant method or an approved equivalent inspection. (ii) Polish the rough edges of the bend relief holes. (b) Within 100 hours' time in service after the inspection specified in "a" above, visually inspect the channel and straps in the area of the channel relief holes for cracks using a magnifying glass of at least 5 power or an approved equivalent inspection. (c) The inspection specified in "b" above shall be repeated at intervals not to exceed 100 hours' time in service from the last inspection. 2. Repair cracked parts with an FAA approved repair or replace parts with an unused part of the same number or an approved equivalent part prior to further flight. 3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 5, 1975.
2007-12-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as some stringer reinforcements (F900DX) and some rivets (F900DX/F2000EX) missing from the skin panels on each side of the fuselage between frames 9 and 10 on certain Falcon 900DX and Falcon 2000EX EASy aircraft; this situation affects the structural integrity of the fuselage. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-14-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes. This AD was prompted by a \n\n\nreport that structural fatigue cracks can develop in certain aluminum pressure module check valves prior to the design limit. This AD requires an inspection to determine the part numbers of the four hydraulic systems A and B pressure module check valves and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-02-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-02-51 that was sent previously to all known U.S. owners and operators of EMBRAER Model EMB-145 and EMB-135 series airplanes by individual notices. This AD requires revising the FAA-approved airplane flight manual and installing placards to alert the flight crew to the maximum speed for airplane retrimming after takeoff and during the climb phase. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent high pitch control forces, which could result in possible loss of control of the airplane.
2019-13-04: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by a determination that new or more restrictive maintenance instructions and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance instructions and airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
75-06-04: 75-06-04 PIPER: Amendment 39-2121. Applies to Model PA-31-350, Serial Nos. 31- 5001 through 31-7405495 certificated in all categories. Compliance required within the next ten hours in service from the effective date of this AD unless previously accomplished, as indicated. 1. Inspect the forward rudder control cable installation as follows: a. Remove the left pilot's seat and associated floor panels. b. Inspect the left- and right-hand forward rudder control cables P/N 41947-03 for proper routing between the pulleys and cable guard pins. c. Remove the forward rudder cable guard pins and inspect the pins for evidence of contact with the control cable. d. If a forward rudder control cable is not properly routed or the cable guard pins show evidence of contact with the control cable, the control cable must be replaced with an acceptable part of the same part number, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where repairs can be made. (Piper Service Bulletin No. 379A refers to this subject.) This amendment is effective March 13, 1975, and was effective for all recipients of the airmail dispatch of February 12, 1975, upon receipt.
2000-23-52: This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-23-52, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters by individual letters. This AD requires, before further flight, performing a fluorescent penetrant inspection of the main rotor shaft assembly (shaft). Also required are recurring fluorescent penetrant inspections and visual inspections for any crack. If any crack is found, the shaft must be replaced with an airworthy shaft before further flight. This amendment is prompted by the discovery of two in-service cracked shafts, one with 477 hours time-in-service (TIS) and one with 313 hours TIS. A third shaft, that had been rejected from the manufacturing process for other reasons, was also discovered to have a crack. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
2007-12-23: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A helicopters that requires inspecting each landing gear fairing support assembly (support assembly), replacing or reworking certain forward and aft landing gear assemblies, and creating an access hole to facilitate inspections and a recurring inspection. A terminating action for the requirements of this AD is also provided. This amendment is prompted by five reports of landing gear strut (strut) failures. The actions specified by this AD are intended to detect a crack that could result in the failure of a strut and subsequent loss of control of the helicopter during landing.