Results
57-15-02: 57-15-02 CURTISS-WRIGHT: Applies to all Model C-46 Series aircraft. Compliance required as indicated. Due to repeated service failures of H-3-38-M1 wheel assemblies (Hayes and/or Goodrich Model No. 1900M), the following action is required: 1. At each 100 to 125 hours, conduct a visual inspection of the demountable flange in the area of the lightening holes with the aid of a flashlight or equivalent. If cracks are detected, the flange must be either retired or reworked in accordance with paragraphs 3.5.2.2.1 and 3.5.2.2.2 of Goodrich Manual No. 14932. 2. Unless already inspected within the period specified herein, all H-3-38-M1 wheel assemblies (used or unused) must be disassembled and inspected prior to installation and thereafter at each 85th landing or regular periodic inspection period nearest to 330 hours, whichever occurs first. (a) Visually inspect the lock ring groove area for corrosion. All corrosion in this area must be removed by hand working with No. 300 sandpaper or equivalent, remachining or grinding away of metal is not permitted. Corrosion in the lock ring groove area of the wheelbase can be removed only to a depth of 0.015 inch from the original surface of the groove. Should corrosion and pitting be in excess of this dimension, the wheelbase must be retired from service. The nominal lock ring groove diameter in the wheel is 17.250 inches. After corrosion cleanup this diameter should not be less than 17.220 inches. The O.D. of the wheelbase in the lock ring groove area and the bottom of the lock ring groove should be concentric within 0.015 inch. The lock ring groove should be retreated to prevent corrosion at every wheel disassembly per treatment specified in B.F. Goodrich Service Letter No. 1022 or equivalent. Note: The original rim lock ring, P/N G85-30, was of tubular steel construction and cadmium plated for rust prevention. This lock ring causes an electrolitic reaction between the magnesium and steel when exposed to moisture and is therefore conducive to corrosion. These lock rings have been superseded by a new solid aluminum type of the same part number. (b) Inspect the following critical areas for cracks using Zyglo, dye penetrant or equivalent method. All paint must be removed using a stripping agent of the waxless solvent type that does not react chemically with magnesium. (1) Brake drum mounting register, (2) tire bead radius of the fixed flange, (3) tire bead seat radius of the demountable flange, (4) radius of the demountable flange step, (5) flange retaining ring groove in the wheel, and (6) rim lock ring. All parts with cracks in any of the critical areas must be retired from service. Rim lock rings P/N G85-30 with cracks must be replaced with the solid aluminum part or equivalent. 3. The following should be accomplished at the first disassembly of wheel unless already accomplished: (a) The lock ring groove area should be steam cleaned with high pressure steam to insure that this area had not been previously reworked and refinished by filling corroded areas with metal putty. Corroded areas may only be reworked in accordance with item 2(a) above. (b) Rework all demountable flanges by removing the sharp edges of the lightening holes in accordance with Goodrich Service Letter No. 1022. This supersedes AD 56-17-1.
59-24-02: 59-24-02 KIDDE and C-O-TWO: Applies to Smoke Detectors, Kidde Model A4532-M1, and C-O-TWO Models ASDC-2 and ASDT-3, Installed in Civil Transport Category Aircraft. The Walter Kidde Model A4532-M1 and the C-O-TWO Models ASDC-2 and ASDT-3 smoke detectors have unstable and over-sensitive alarm settings; thus resulting in false indications. Due to this unsatisfactory characteristic, the manufacturers, Walter Kidde and Company and the C-O-TWO Division of Fyr-Fyter Company have withdrawn their statements of conformance with Technical Standard Orders, TSO-C1 and C1a for these smoke detectors. Therefore, their TSO approvals are invalidated. All Models A4532-M1, ASDC-2 and ASDT-3 smoke detectors installed in transport category aircraft shall be removed from service prior to January 31, 1960, except when these models are approved as a part of the airplane installation under a supplemental type certificate. The TSO identification shall be eliminated from the detector label of such detectors approved as a part of the airplane installation.
2006-12-24: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-45/-50 series turbofan engines. That AD currently requires an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks, and replacement of the side links and pylon attachment bolts and inspection of the fail-safe bolt and platform lug if the side links are cracked. That AD also requires a shop-level refurbishment of the side links as a terminating action to the on-wing inspection program. This ad requires inspecting and refurbishing the side link at every exposure of the side link. This AD also requires the same actions on certain part number side links installed on CF6-80A turbofan engines. This AD results from a report of a cracked side link. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane.
2006-12-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the Airplane Flight Manual (AFM) and the FAA-approved maintenance program. This AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane.
2018-13-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report indicating that certain lanyards for the passenger oxygen masks located in the airplane's entry area are too long. This AD requires replacement of certain oxygen mask lanyards with shorter lanyards. We are issuing this AD to address the unsafe condition on these products.
95-19-01: This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A330 and A340 series airplanes equipped with certain BFGoodrich evacuation slides and slide/rafts. This action requires an inspection to detect the presence of certain discrepancies of the packboard associated with the evacuation slides and slide/rafts, and replacement or modification of the packboard unit, if necessary. It also requires the eventual modification of all affected packboard units. This amendment is prompted by reports indicating that these packboards have disengaged from the door mounting, due to cracking of the packboard and associated latch assembly that was incurred during hard landings. The actions specified in this AD are intended to prevent the packboard from disengaging from the door and restraining the door from fully opening, thereby preventing the evacuation slide from inflating and making both the slide and the door unusable during an emergency evacuation.
2006-12-20: The FAA is adopting a new airworthiness directive (AD) for all Raytheon Model BAe.125 series 800A (including variants C-29A and U- 125), 800B, 1000A, and 1000B airplanes and Model Hawker 800 (including variant U-125A) and 1000 airplanes; and for certain Raytheon Model HS.125 series 700A and 700B airplanes and Model Hawker 800XP airplanes. This AD requires measuring the resistance of the current limiters for the PE, PS1, and PS2 busses, and replacing a current limiter with a new part if necessary. This AD also requires reporting certain information to the airplane manufacturer. This AD allows a records review for determining if suspect current limiters were installed, which may exempt airplanes from the required measurement. This AD results from reports that certain current limiters have opened within two to four hours after installation. We are issuing this AD to prevent loss of all primary electrical power, which could result in the airplane operating only under emergency power.
2018-11-16: We are adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines. This AD requires a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks, a visual inspection of the engine fan hub for damage, and removal of parts if damage or defects are found that are outside serviceable limits. This AD was prompted by an uncontained failure of the engine fan hub. We are issuing this AD to address the unsafe condition on these products.
2018-13-02: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4052, PW4056, PW4060, PW4062, PW4062A, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engine models, including engines identified with suffixes -1C, -1E, -3, -3A, or -3B. This AD was prompted by the discovery of multiple cracked 4th stage low-pressure turbine (LPT) air seals in the fleet. This AD requires removal from service of certain 4th stage LPT air seals. We are issuing this AD to address the unsafe condition on these products.
95-16-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model BAe ATP airplanes. This action requires modification of the electrical connections at the switches of the scavenge oil filter and pressure oil filter. This amendment is prompted by reports indicating that the electrical connections were miswired at the switches of the scavenge oil filter and pressure oil filter. The actions specified in this AD are intended to prevent the circulation of unfiltered oil through the engine without warning to the flightcrew, due to miswiring of electrical connections. Unfiltered oil containing contaminants could lead to a precautionary shutdown of the engine.