Results
99-22-01: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-22-01, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and T1 helicopters by individual letters. This AD requires, before further flight and at specified time intervals until a modified tail boom connecting frame flange (frame flange) is installed, inspecting and replacing, if necessary, the frame flange. This AD also requires, within 7 days, installing an additional bearing support on the frame flange. Thereafter, this AD requires visually inspecting the frame flange for cracks or misalignment of the slippage marks at specified time intervals. This amendment is prompted by the discovery of a crack in the frame flange at the attachment points of the tail rotor drive shaft bearing support. The actions specified by this AD are intended to prevent a fracture of the bearing frame flange, failure of the tailrotor drive shaft, and subsequent loss of control of the helicopter.
2014-12-03: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-725A1-12 turbofan engines. This AD requires removal of affected fuel metering units (FMUs) on RRD BR700-725A1-12 engines. This AD was prompted by reports of wear on the receptors of the double-ended unions in the FMU housing on BR700-725A1-12 engines causing fuel leakage. We are issuing this AD to prevent failure of the FMU, which could lead to damage to one or more engines and damage to the airplane.
57-06-04: 57-06-04 WRIGHT: Applies to All Aircraft Incorporating C18CA, C18CB, TC18DA, and TC18EA Series Engines. Compliance required as indicated. Results of recent investigations indicate that the engine front section bearing durability can be improved by accomplishing the following: 1. At next engine overhaul the engine front section must be assembled with the propeller shaft thrust bearing (ball bearing) behind the radial bearing (roller bearing) as viewed from the propeller end of the engine. (Wright Aeronautical Division Service Bulletins Nos. C18C-252, TC18D-255, and TC-18E-66 cover this same subject.) Propellers must be balanced in accordance with instructions contained in applicable propeller manufacturer's recommendations. 2. Engines overhauled after April 15, 1957, must incorporate engine propeller shaft thrust bearings (ball bearings) and radial bearings (roller bearings) that have been inspected for proper internal bearing clearances in accordance with instructions issued by the Wright Aeronautical Division in their Service Letter dated March 22, 1957.
99-24-18: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model AS-350B, B1, B2, B3, BA, and D, and AS-355E, F, F1, F2, and N helicopters, that requires inspecting certain versions of the tail rotor spider plate bearing (bearing) for the proper rotational torque, axial play, and any brinelling of the bearing. This amendment has the same inspection requirements as the current AD. Also, this AD expands the applicability to include additional part numbers (P/N's) and reduces the initial and recurring inspection compliance times. This amendment is prompted by additional reports of deterioration of the bearing. The actions specified by this AD are intended to prevent seizure of the bearing, loss of tail rotor control, and subsequent loss of control of the helicopter.
99-24-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires removal of cable guards in the lateral control system and replacement with new, improved cable guards. This amendment is prompted by reports of high control wheel forces and restricted control wheel movement. The actions specified by this AD are intended to prevent deterioration of cable guards in the lateral control system, which could result in a jam of the lateral control system and consequent reduced lateral controllability of the airplane.
83-13-05: 83-13-05 AIRBUS INDUSTRIE: Amendment 39-4675. Applies to the model A300 series airplanes, certificated in all categories. To prevent failure of certain components of the main and nose landing gears, within 250 landings after the effective date of this AD or prior to the accumulation of the number of landings specified in each paragraph below, whichever occurs later, accomplish the following, unless previously accomplished: A. Reinforce the lower torque link pins of the main landing gear in accordance with the instructions of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-065, dated September 3, 1976, prior to the accumulation of 12,000 landings on B1 model aircraft, and 16,000 landings on B2-100, B2-200, B2-300, B4-100, B4-200 and C4-200 model aircraft, having the serial numbers specified in Airbus Industrie (AI) Service Bulletin A300-32-077, Revision 1, dated February 19, 1980. B. Modify the main landing gear drag strut of aircraft with serial numbers specifiedby AI Service Bulletin A300-32-114, dated January 13, 1978, in accordance with the instructions of MHB Service Bulletin 470-32-110, dated November 28, 1977, prior to the accumulation of 20,000 landings. C. Modify the actuating cylinder of the main landing gear for aircraft with serial numbers specified by AI Service Bulletin A310-32-116, Revision 6, dated September 17, 1982, in accordance with the instructions of MHB Service Bulletin 470-32-108, Revision 1, dated November 24, 1978, according to the following schedule: 1. For aircraft with modifications AI 1799 and 2025 originally installed, prior to the accumulation of 32,000 landings on B2 models or 22,000 landings on B4 models. 2. For aircraft with modifications AI 1799 and 2025 not originally installed, prior to the accumulation of 12,000 landings on both models B2 and B4. D. Incorporate modifications MHB 151 and 161 on the shock strut connecting rod of the main landing gear of aircraft with serial numbers specified in AI Service Bulletins A300-32- 096, Revision 4, and A300-32-076, Revision 3, both dated September 17, 1982, in accordance with the instructions of MHB Service Bulletins 470-32-039 and 470-32-040, Revision 1, both dated October 31, 1980, prior to the accumulation of 12,000 landings. E. Incorporate modification MHB 59 on the brace assembly actuating cylinder of the main landing gear of aircraft with serial numbers specified in AI Service Bulletin A300-32-036, Revision 2, dated September 17, 1982, in accordance with the instructions of MHB Service Bulletin 470-32-031, dated January 8, 1976, prior to the accumulation of 17,500 landings. F. Replace the actuating cylinder piston of the nose landing gear of aircraft with serial numbers specified in AI Service Bulletin A300-32-904, Revision 5, dated September 17, 1982, in accordance with the instructions of MHB Service Bulletin 470-32-033, dated January 9, 1976, prior to the accumulation of 14,000 landings. G. For the purpose of this AD, and when approved by an FAA maintenance inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. H. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. I. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective July 7, 1983.
99-25-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. This action requires a one-time inspection to verify correct installation of the fastener that connects the input rod of the spoiler mixer mechanism to the torque tube crank, and corrective actions, if necessary. For certain airplanes, this action requires replacement of the nut, bolt, and cotter pin that connects the input rod of the spoiler mixer mechanism to the torque tube crank with a new or serviceable nut, bolt, and cotter pin. This amendment is prompted by reports indicating numerous discrepancies in the installation of the fastener that connects the input rod of the spoiler mixer mechanism to the torque tube crank. The actions specified in this AD are intended to prevent the linkage between the ratio changer input rod and the aft aileron control quadrant from becoming disconnected, which could result in reduced controllability of the airplane.
82-18-01: 82-18-01 EMBRAER: Amendment 39-4440. Applies to EMB-110P1 and EMB-110P2 models (S/Ns 110001 through 110329 and 110331 through 110339), airplanes certificated in any category. Compliance: Required on or before December 31, 1982, unless previously accomplished. To prevent leakage of water into the fuel tank, accomplish the following: (a) Defuel the airplane in accordance with the EMB-110 maintenance manual. (b) Remove the fuel filler neck components from each tank and install EMBRAER Kit S.B. 110-28-020 in accordance with the instructions contained in EMBRAER Service Bulletin 110-28-020, dated July 2, 1981. (c) An equivalent method of compliance may be used, if approved by the Chief, Atlanta Aircraft Certification Office, ACE-115A, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective September 27, 1982.
2022-18-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by unclear and incomplete placard instructions for the doghouse door lock. This AD requires installing improved handling instruction placards on affected doghouses and re-identifying the doghouses, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected doghouses under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-12-01: We are superseding Airworthiness Directive (AD) 2013-11-05 for Bell Model 214B, 214B-1, and 214ST helicopters with certain tail rotor [[Page 32860]] hanger bearings (bearing) installed. AD 2013-11-05 required inspecting the bearing to determine whether an incorrectly manufactured seal material is installed on the bearing. This new AD retains the repetitive inspection of the bearings and also requires replacing the defective bearings. This AD was prompted by a report that certain bearings were manufactured with an incorrect seal material that does not meet Bell specifications. We are issuing this AD to prevent failure of the bearing and subsequent loss of control of the helicopter.