Results
2024-23-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations for certain brake accumulators are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD also requires determining the accumulated landings on the affected brake accumulators. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires, among other actions, modifying the down drive brackets of the left- and right-hand sides of the inboard flap track 1 assembly and installation of bigger bolts and washers, and testing the torque value of the nuts. The actions specified by this AD are intended to prevent failure of the bolts due to flexural loads caused by transmission jam loading, which could lead to a "flap-locked" condition, causing reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
50-41-02: 50-41-02 MARTIN: Applies to All Model 202 Aircraft. Compliance required not later than December 1, 1950. To maintain a sufficient hydraulic reservoir capacity for the operation of the hydraulic units in the event of failure in the emergency brake system, install a hydraulic fuse (Simmonds P/N G45-6E-402-80) or equivalent, adjacent to the main line tee in the emergency brake system between the main line and the emergency brake accumulator. (Martin 202 Service Bulletin No. 105 covers this same subject.) When the manually operated charging valve is installed in accordance with AD 51-11-01, this hydraulic fuse is no longer required.
74-18-03: 74-18-03 CURTISS-WRIGHT: Amendment 39-1937. Applies to all Model C-46 Series airplanes certificated in all categories. To prevent failures of the main landing gear axle elbows, Part Number 8107-63L and 8107-63R, accomplish the following, unless already accomplished: (a) For aircraft having main landing gear axle elbows with less than 7800 hours' time in service on the effective date of this AD, at 8,000 hours' time in service and thereafter, at intervals not to exceed 500 hours' time in service, inspect the part numbers 8107-63L and -63R elbows for cracks visually with a ten power or higher glass or in an equivalent FAA approved manner. (b) For aircraft having main landing gear axle elbows with more than 7800 hours' time in service on the effective date of this AD, within 200 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 500 hours' time in service, inspect the Part Numbers 8107-63L and -63R elbows for cracks visually with a ten power or higher glass or in an equivalent FAA approved manner. (c) Replace cracked elbows with serviceable parts before further flight. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This amendment becomes effective August 30, 1974.
2021-06-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 series and A330-300 series airplanes. This AD was prompted by reports of cracked flexible hoses in the courier area oxygen system (CAOS). This AD requires repetitive detailed inspections of the CAOS and replacement of affected parts if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
56-25-02: 56-25-02 BELL: Applies to All Model 47 Series Helicopters Except the Following: Model 47G Serial Numbers 1529, 1530, 1687 and Up; Model 47G2 Serial Numbers 1505, 1506, 1508, 1617 and Up; Model 47H1 Serial Numbers 1369, 1371 and Up; Model 47J. Compliance required by December 22, 1956. Excessive tolerance resulting from wear of the tail rotor pitch change rod assembly can result in the loss of the S1RP or 7R4AX1C bearings. To preclude loss of these bearings, the AN 960-416 washer or washers, P/N 47-641-113-1, made to the dimensions 0.562-0.557 inch must be replaced with washers that have an O.D. dimension not greater than 0.552 inch or less than 0.549 inch. (Bell Mandatory Service Bulletin No. 113 Revision B dated October 23, 1956, covers this same subject.) This supersedes AD 56-20-02.
2001-09-07: This amendment supersedes an emergency airworthiness directive (AD) 2001-08-52 that was sent previously to all known U.S. owners and operators of Pratt and Whitney (PW) model PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines by individual letters. That emergency AD requires limiting the number of PW4000 engines, listed by serial number (SN) in that AD, with potentially reduced stability to no more than one engine on each airplane; removal of certain PW4000 engines, listed by SN in this AD, before exceeding cyclic limits that are determined by airplane model; removal of certain PW4000 engines, listed by SN in this AD, that have a high pressure compressor with 1,500 or more cycles-since-overhaul (CSO) greater than the high pressure turbine (HPT) CSO; and requires a minimum rebuild standard for engines that are returned to service. This amendment supersedes emergency AD 2001-08-52 to provide clarifications and additions to the compliance and applicability of certain paragraphs of AD 2001-08-52. This AD is prompted by a report of a dual-engine surge event during take-off on an Airbus Industrie A300 airplane. The actions specified by this AD are intended to prevent multiple-engine power losses due to high pressure compressor (HPC) surge at a critical phase of flight such as takeoff or climb.
2003-16-14: This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 747 series airplanes equipped with Pratt & Whitney JT9D-3 or JT9D-7 series engines (except JT9D-70 series engines), that requires detailed inspections of the upper and lower surface of the forward lower spar of the nacelle strut for cracking or other damage, and for any loose or damaged fasteners. This amendment also requires replacement of loose or damaged fasteners and, if necessary, associated repair of the forward lower spar. This action is necessary to detect and correct cracking or other damage to the upper or lower surface of the forward lower spar and any loose or damaged fasteners, which could result in reduced structural capability of nacelle struts one through four, and possible separation of a strut and engine from the airplane during flight. This action is intended to address the identified unsafe condition.
2016-06-08: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787-8 and 787-9 airplanes powered by GE GEnx engines. This AD requires revising the airplane flight manual to provide the flight crew a new fan ice removal procedure to reduce the likelihood of engine damage due to fan ice shedding. This AD also requires, for certain airplanes, reworking the fan stator module assembly on GE GEnx-1B Performance Improvement Program (PIP) 2 engines. This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent reduced fan tip clearance, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines.
70-14-04: 70-14-04 BOEING: Amendment 39-1027. Applies to 747-100 series airplanes which incorporate 65B82749-3 Compensator Assembly. \n\tCompliance required as indicated. \n\tTo prevent steering malfunction, accomplish the following: \n\t(a)\tWithin 10 hours after the effective date of this AD, unless already accomplished, install a placard as noted below in full view of the captain and first officer, or provide an equivalent procedure acceptable to the cognizant Air Carrier District Office. \n\tPlacard wording is as follows: \n\t\t1.\tWithout using the tiller check that the nose wheel is tracking straight while taxiing. \n\t\t2.\tAllow aircraft to roll forward to assure nose wheel alignment prior to applying takeoff power. \n\t\t3.\tIf metering or directional control problems occur, the takeoff should be discontinued. \n\tThe requirement for (a) is eliminated upon accomplishment of the provisions of (b) below. \n\t(b)\tWithin the next 1000 hours' time in service after the effective date of this AD, unlessalready accomplished, replace the 65B-82749-3 compensator assembly with the 65B-82749-4 compensator assembly per Boeing Service Bulletin No. 32-2032, dated June 19, 1970, or later FAA approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective July 16, 1970.