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47-32-02: 47-32-02 BELL: (Was Mandatory Note 2 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 6 and 8 Through 28.
Compliance required not later than next 25-hour inspection after September 15, 1947.
The correct amount of fixed ballast for the Model 47B helicopters, as listed in Bell Service Bulletin 47C27, dated June 25, 1947, should be installed in accordance with the instructions also contained in that Bulletin. Compliance is required in order that the correct center of gravity range may be maintained.
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47-32-12: 47-32-12 BELL: (Was Mandatory Note 12 of AD-1H-1.) Applies to Models 47B and 47B3 Helicopters.
Compliance required not later than the next 25-hour inspection after September 15, 1947.
In order to provide more strength in the lateral cycle control system, the disc links should be replaced with forward and aft links, 47-725-047.
(Bell Service Bulletin 47C35 dated June 18, 1947, also covers this same subject.)
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98-12-11: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires modifying the emergency hydraulic hand-pump by increasing the length of the access aperture. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent difficulty accessing the emergency hydraulic hand-pump because of the current design, which, in the event of a hydraulic system failure, could result in the inability to operate the flaps and landing gear.
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94-24-11: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires a one-time inspection for cracks in the tail rotor drive shaft hanger bearing support brackets (brackets), and repair or replacement, as necessary. This amendment is prompted by reports of cracks in the bend radius of the brackets. The actions specified by this AD are intended to prevent misalignment of the tail rotor drive shaft, failure of the tail rotor drive shaft system, loss of control of the tail rotor, and subsequent loss of control of the helicopter.
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2005-19-25: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive eddy current inspections for cracks of the countersunk rivet holes in the lower lobe, adjacent to the radio altimeter cutouts; additional inspections, for certain airplanes, for cracks and/or corrosion; and further investigative and corrective action if any crack is found. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracks in the fuselage skin of the lower lobe. We are issuing this AD to detect and correct fatigue cracks of the countersunk rivet holes, which could result in cracks of the fuselage skin of the lower lobe, and consequent rapid depressurization of the cabin.
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47-51-07: 47-51-07 CURTISS-WRIGHT Applies to all C-46 Series aircraft.
Compliance required not later than March 1, 1948, and each 1,000 hours of operation thereafter.
Inspect the landing gear drag strut support structure inside nacelle to determine if landing gear drag strut No. 20-720-1018 attaching bolts at the 70 percent spar have loosened and if angle assembly 20-720-1024-1 and bulkhead assemblies 20-720-1021-1 and 20-720-1023-6 are loose. All defective parts, loose or sheared attachment rivets should be replaced and loose bolts tightened.
To accomplish the above, it is necessary to remove one outer panel or provide an access door in order to gain access to the interior of the center panel.
(Curtiss-Wright Service Information Letter No. 735 dated August 20, 1947, covers an acceptable wing panel door installation.)
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48-44-02: 48-44-02 CURTISS-WRIGHT Applies to all C-46 Series aircraft.
Compliance required at original certification and at every 7,500 hours of operation thereafter, or at the approved airframe overhaul period for air carriers.
Check the center wing-to-fuselage attachment bolts, P/N AN 8-23A, AN 8-25A, and AN 8-31A, to determine that they are properly torqued. The proper torque value for these bolts is between 480 to 690 inch-pounds as per Curtiss-Wright Drawing No. 20-230-1000.
For access to the 30 percent spar fitting, a 1 1/2-inch diameter hole can be cut in the wing center section lower skin beneath the fitting, just forward of the beam, and far enough inboard so that the resultant opening will be completely covered upon reinstallation of the wing foot fairing.
This supersedes AD 47-51-06.
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2005-19-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracks of the inboard lower flange and radius of the left- and right-hand outboard floor beams at frame (FR) 48, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of FR48 on both left- and right-hand floor beams; and that an additional crack was found in the flange radius of the floor beam. We are issuing this AD to detect and correct such cracking, which could propagate and result in reduced structural integrity of the fuselage.
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49-46-01: 49-46-01 DOUGLAS: Applies to All Models DC-4 and DC-6 Aircraft Equipped With Vacuum systems, Incorporating Oil Separators Other Than the Type Mentioned in Item 2.\n\n\tTo be accomplished not later than April 1, 1950.\n\n\tTo guard against the possibility of excessive air temperatures in the vacuum system discharge line, one of the following modifications must be accomplished to this system:\n\n\t1.\tInstall a fusible plug in the side of the vacuum pump discharger port at the right angles to the axis of the discharge port boss. Some pumps incorporate a plugged hole in the discharge port which may be enlarged to a 3/8-inch pipe tapped hole to accommodate the fusible plug. This plug should employ an AN 840-8D fitting with a binary eutectic mixture of 67.8 percent tim and 32.2 percent cadmium, which has a melting point of 351 degrees F. Figure 2 describes the design of such a plug. The 3/8-inch fusible plug fitting is intended for pumps such as the Model 3P-211 and 3P-485. For smallerpumps such as the 3P-207, and AN 840-6D fitting, incorporating the same modification as shown below, should be used. Incorporation of an overboard drain line clamped to the fusible plug is recommended but is not mandatory.\n\n\n\n\n\tBrass fittings of the same design as the above dural fittings are acceptable. On installations which do not use an overboard discharge line the possibility exists that the plug may damage other nacelle components if it can hit them upon being out of the adapter as high velocity. Therefore, if no overboard discharge line is provided, the installation must be made in such a manner that the plug will not be directed toward any vulnerable components when it issues from the adapter.\n\n\t2.\tReplace the present oil separator with a new oil separator, Genisco No. 40081 or equivalent. The new separator incorporates a pressure relief valve and can be disassembled for cleaning.\n\n\t(Douglas Service Letter A-129-T-1271/WB-11-Q-4, dated April 1, 1949, covers this same modification.)
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2005-18-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires modification of the splice plate assemblies installed under the floor panels at the forward and aft edges of the cabin aisle. This AD results from reports of cracking of the aluminum splice plates under the floor panels in the cabin aisle. We are issuing this AD to prevent loss of the capability of the cabin floor and seat track structure to support the airplane interior inertia loads under emergency landing conditions. Loss of this support could lead to galley or seat separation from attached restraints, which could result in blocking of the emergency exits and consequent injury to passengers and crew.
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