Results
2006-20-05: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 airplanes. This AD requires repetitive inspections to measure the depth of chafing or scoring in the skin along the full length of the wing-to-fuselage fairing from forward to aft ends at the contact between the seal and fuselage, and related investigative/corrective actions if necessary. This AD results from a report of chafing in this area. We are issuing this AD to detect and correct such chafing or scoring, which could result in reduced structural integrity of the fuselage.
48-25-02: 48-25-02 CESSNA: Applies to All 120 and 140 Aircraft Equipped With Cessna Welded Exhaust Muffler Assemblies. Inspection required each 25 hours of operation. Remove the carburetor air heater muff and cabin heater muff and inspect the muffler assemblies for any evidence of cracks paying particular attention to the areas of the mufflers and stacks adjacent to where the exhaust stacks and tailpipe are welded to the muffler assembly. The present placard calling for inspection of the mufflers every 100 hours should be revised to call for this inspection every 25 hours. This directive is intended to apply to only those aircraft equipped with exhaust muffler assemblies that are fabricated by welding exhaust stacks to muffler.
47-30-07: 47-30-07 BEECH: (Was Mandatory Note 3 of AD-2-582-2.) Applies Only to AT-11 Aircraft Which Are Not Equipped With Generator Circuit Protective Devices. To be accomplished prior to certification or, if certificated, on next periodic inspection but not later than October 1, 1947. In accordance with Figure 1 install a 50-ampere trip-free circuit breaker, Spencer Thermostat Co. PLM-50 or equivalent, between the battery terminal of each generator cutout and its respective ammeter shunt. The circuit breakers should be accessible in flight and labeled respectively: "LEFT GEN. CIRCUIT" and "RIGHT GEN. CIRCUIT."
2006-19-09: We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Model B300 airplanes. This AD requires you to modify the cabin passenger seats by installing a modification kit on each passenger seat, removing the existing technical standard order (TSO) label, and re-identifying each modified passenger seat assembly with a new part number. This AD results from the seats not meeting the ultimate load requirements of 14 CFR part 23 during structural testing of the seat with design changes. We are issuing this AD to prevent the passenger seats from failing during emergency landing conditions when high inertial loadings occur. Passenger seat failure may result in occupant injury.
2006-18-07: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires replacing the very high frequency (VHF) antenna located in position 1 of the fuselage with a new, improved VHF antenna. This AD results from a report of the loss of all voice communications due to a lightning strike damaging all the VHF antennas. We are issuing this AD to prevent the loss of voice communication, which, when combined with the complexity of the national airspace system, could result in reduced flightcrew situational awareness, increased flightcrew workload, and increased risk of human error, and consequent reduced ability to maintain safe flight and landing of the airplane.
57-14-02: 57-14-02 DAVIS AIRCRAFT PRODUCTS (Safety Belts): Applies to Model FDC-1650 Belts, P/N FDC-1650, FDC-1650-27, FDC-1650-27M1. \n\n\tCompliance required as soon as possible but not later than August 15, 1957. \n\n\tSome of the release fittings of the subject belt assemblies are so constructed as to require one particular side of the fitting UP when being inserted in the buckle. \n\n\tIt is possible to improperly fasten the belts effected so that the buckle may become unfastened under load. The unsatisfactory release fittings have a tab bent up to an angle of approximately 11 degrees with the plane of the fitting (See Figure 1). \n\n\tTo provide for securely assembling the buckle with the release fitting in either position, the tab area indicated in the sketch must be removed or bent flush with the plane of the adjoining metal. \n\n\tThis rework applies only to the release fitting shown in the sketch. Other portions of the buckle assembly than that shown should not be modified. This condition has been corrected on all assemblies of current manufacture.
2006-18-15: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) series propellers with non- suffix serial number (SN) propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines. This AD requires initial and repetitive eddy current inspections (ECI) of the front cylinder half of the propeller hub for cracks and removing cracked hubs from service before further flight. In addition, this AD allows installation of an improved design propeller hub (suffix SN "A" or "B") as terminating action to the repetitive ECI. This AD results from a report of a propeller blade separating from a propeller hub. We are issuing this AD to prevent failure of the propeller hub causing blade separation and subsequent loss of airplane control.
2006-18-14: The FAA is superseding an airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 turbofan engines. That AD currently establishes cyclic life limits for certain part number (P/N) stage 1 high pressure turbine (HPT) discs and stage 1 low pressure turbine (LPT) discs operating under certain flight plan profiles. This AD requires calculating and re-establishing the achieved cyclic life of stage 1 HPT discs, P/N JR32013 or P/N JR33838, and stage 1 LPT discs, P/N JR32318A, that have been exposed to different flight plan profiles. This AD also requires removing from service those stage 1 HPT discs and stage 1 LPT discs operated under Tay 650-15 engine flight plan profiles A, B, C, and D, and operated under Tay 651-54 engine datum flight profile, at reduced cyclic life limits, using a drawdown schedule. This AD results from RRD updating their low-cycle-fatigue analysis for stage 1 HPT discs and stage 1 LPT discs and reducing their cyclic life limits. We are issuing this AD to prevent cracks leading to turbine disc failure, which could result in an uncontained engine failure and damage to the airplane.
70-15-08: 70-15-08 HAWKER SIDDELEY: Amdt. 39-1035. Applies to deHavilland Model DH.114 "Heron" airplanes. Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, accomplish the following: (a) Inspect the right wing and left wing flap datum hinge links for drilled holes around the circumference of the bearing housing recess. If one or more drilled holes or attempted drilled holes (for cotter pin installation) are found located outside the limits given in Hawker Siddeley Aviation, Ltd., Technical News Sheet Heron (114) Issue 1, dated June 15, 1970, or later ARB-approved issue or an FAA-approved equivalent, before further flight replace the flap datum hinge link with a serviceable link of either pre-modification 837 or post-modification 837 standards. The complete flap datum hinge assembly must conform to the modification standard of the flap datum hinge link installed. (b) Install special washers P/N 4WF 465 or an FAA-approved equivalent between the nut on the flap datum hinge bolt and the hinge lever assembly at both the right wing and left wing datum hinge locations. A special washer equivalent to P/N 4WF 465 may be manufactured from 0.028 inch, minimum thickness mild steel sheet material. The special washer must have an outside diameter of at least 0.87 inches, a hole diameter of 0.323 inches, and a flat cut across a sector of the outer circumference producing a straight edge located no closer than 0.35 inches from the center of the hole. (c) Inspect the flange of the ball race housing on both the right wing and left wing flap datum hinge assemblies to determine that it is secured to the wing flap datum hinge link with a 1/16 inch diameter cotter pin for pre-modification 837 flap datum hinge assemblies or a 1/8 inch diameter cotter pin for post-modification 837 datum hinge assemblies. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated June 20, 1970, which contained the amendment.
2006-18-01: This amendment supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD900 helicopters, that currently requires reducing the life limit of certain Notar fan system tension-torsion (TT) straps. That existing AD also requires, at a specified time interval, removing each affected TT strap from the helicopter, doing a visual and X-ray inspection, and replacing any unairworthy part before further flight. This amendment requires the same actions as the existing AD, but also requires revising the life limit on the component history card or equivalent record and doing repetitive visual and X-ray inspections, and removes reporting requirements. This amendment is prompted by two in-flight TT strap failures. The actions specified by this AD are intended to prevent failure of a TT strap, loss of directional control, and subsequent loss of control of the helicopter.