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67-32-05: 67-32-05 VICKERS: Amdt. 39-524 Part 39 Federal Register December 12, 1967. Applies to Viscount Models 744, 745D and 810 Series Airplanes. Compliance required as indicated. To prevent failure of the hydraulic flexible hoses installed in the nose wheel steering system, accomplish the following: (a) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 7246-1, located on the top of the nose oleo in the nose steering system, with 6,500 or more hours' time in service or which have been installed for 4 1/2 or more years on the effective date of this AD with new hoses of the same part number within the next 8 months or 1,500 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (b) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 72426-1, located on the top of the nose oleo leg in the nose steering system, with less than 6,500 hours' time in service and which have been installed for less than 4 1/2 years on the effective date of this AD with new hoses of the same part number before the accumulation of 5 years or 8,000 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (British Aircraft Corporation Preliminary Technical Leaflets (PTLS) Nos. 268 (700 Series) and 131 (800 Series), Issue 1, dated June 22, 1967, pertain to this subject.) This amendment effective January 11, 1968.
99-04-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires inspecting the main landing gear hydraulic actuators to determine whether a certain Frisby Aerospace actuator is installed, and reworking or replacing any of these Frisby Aerospace actuators. This AD is the result of reports of fatigue cracks in the end cap of main landing gear hydraulic actuators manufactured by Frisby Aerospace and installed on the affected airplanes. The actions specified by this AD are intended to prevent the main landing gear from failing to lock down due to the hydraulic actuator cracking and separating, which could result in loss of control of the airplane during landing, taxi, or ground operations.
99-03-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -700IGW, and -800 series airplanes. This action requires repetitive inspections to detect discrepancies of the quick-disconnect coupling on the fuel hose, located at the fan case firewall; corrective action, if necessary; and installation of a clamp shell on the coupling to prevent separation of the coupling halves. This amendment is prompted by a report that a quick-disconnect coupling on the fuel hose on an in-service airplane was found loose and leaking fuel. The actions specified in this AD are intended to detect and correct excessive wear of the quick-disconnect coupling on the fuel hose, which could result in major fuel leakage, fire in the engine nacelle, and consequent loss of thrust from the affected engine.
2021-20-01: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st- stage blade retaining plate installed. This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life- cycle limits for each part. This AD requires removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is issuing this AD to address the unsafe condition on these products.
68-12-05: 68-12-05 AERO COMMANDER: Amdt. 39-611. Applies to Models 100 and 100A, and Volaire Models 10A and 10, Serial Numbers 001 through 250. Compliance required as indicated. To preclude failure of the left and right arms, P/N 35321, of the rudder control system, accomplish the following: NOTE: The arms are those to which the rudder system left and right cables and springs are attached, and extend forward from the cross-bar assembly supporting the rudder pedals. (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect and modify the left and right arms, P/N 35321, as follows: Clean to bare metal all surfaces of the web and flanges of each arm over an area extending from the center of the 3/16 inch diameter cable attach hole to a point 3/4 inch aft of the hole. Visually inspect the exposed areas of the webs for cracks using a 10-power magnifying glass, or in an equivalent manner approved by the Chief,Engineering and Manufacturing Branch, FAA Southern Region. Weld the 1/16 inch deep square notches which are located in the webs at the forward ends of the upper and lower flanges of each arm, completely filling the notches with weld metal. Weld all cracks detected during the inspection with full penetration welds over the full length of each crack. Recoat the exposed area with oxide primer or equivalent. (b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, modify the left and right arms, P/N 35321, in accordance with the instructions contained in Aero Commander Service Bulletin 1009, dated May 24, 1968, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective June 14, 1968.
99-03-06: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires a one-time visual inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane.
2003-06-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-06-51 that was sent previously to all known U.S. owners and operators of certain Learjet Model 45 airplanes by individual notices. This AD requires an inspection to determine the part number of the horizontal stabilizer actuator assembly (A66), and replacement of any suspect horizontal stabilizer actuator assembly (A66) with a new or serviceable actuator assembly (A66). This action is prompted by a report of severe vibration followed by a rapid nose down pitch change on a Learjet Model 45 airplane. The actions specified by this AD are intended to prevent structural failure of the horizontal stabilizer actuator assembly, which could result in possible loss of control of the airplane.
2012-12-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus Model A340-200 series airplanes; and Airbus Model A340-300 series airplanes. This AD was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. This AD requires performing a detailed inspection of the outer skin rivets at the frame fork ends of the forward and aft cargo door for sheared, loose, and missing rivets; repairing the outer skin rivets, if necessary; and performing repetitive inspections. We are issuing this AD to detect and correct sheared, loose, or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door.
72-15-04: 72-15-04 CANADAIR: Amdt. 39-1485. Applies to Canadair Limited Type CL-215-1A10 airplanes, Serial Nos. 1005, 1006, 1010, 1011, 1013 through 1018, 1021, and 1023 through 1030. Compliance required within the next 125 hours' time in service, unless already accomplished, after the effective date of this AD. To reduce the risk of flame propagation in the event of a fire in the engine fire zone, modify the oil system and hydraulic system hoses in accordance with the instructions and effectivities listed in the following Canadair Service Bulletins or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (a) Canadair Service Bulletin CL-215-138 dated February 2, 1971, and revision "A" dated April 23, 1971 or later approved revision. (b) Canadair Service Bulletin CL-215-140 dated January 18, 1971 or later approved revision. Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective July 25, 1972.
2012-12-07: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of cracks underneath the passenger door in a butt-joint on the forward fuselage of a Model F.28 Mark 0100 airplane. This AD requires repetitive low frequency eddy current inspections of the forward fuselage butt-joints for cracks, and if necessary, a temporary repair followed by a permanent repair. We are issuing this AD to detect and correct cracking of the butt-joint on the forward fuselage, which could result in explosive decompression and consequent loss of control of the airplane.