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44-04-03:
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2006-01-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 B2 and B4 series airplanes. This AD requires repetitive replacement of the angle of attack (AOA) sensors with new or overhauled AOA sensors. This AD also provides an optional terminating action for the repetitive replacements. This AD results from reports of several false stall warnings associated with stick-shaker activation, occurring during take-off. We are issuing this AD to prevent false stall warnings associated with stick-shaker activation, which could result in increased pilot workload as the pilot tries to determine the cause of the stall warning and possible reduction in the pilot's ability to control the airplane.
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47-07-06: 47-07-06 FAIRCHILD: (Was Mandatory Note 8 of AD-724-2.) Applies to M-62 Series Aircraft.
Compliance required at next periodic inspection.
In order to reinforce the forward attachment of the vertical fin, trim the leading edge as required and install bracket, Fairchild P/N 66317 and either maple filler block, Fairchild P/N SK- 2089-1, or blocks, Fairchild P/N 66300-22 and 66300-23.
(Fairchild Service Bulletin 44-62-1 dated October 31, 1944, covers this same subject.)
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46-06-02: 46-06-02 KINNER: (Was Mandatory Note 8 of AD-749-1 and Special Note 11 of AM-231.) Applies Only to Jobmaster DGA-18K and Ryan ST-3KR Airplanes With R-5 Series 2 Engines With the Following Serial Numbers: 371, 378, 379, 380, 383, 386, 398, 399, 400, 401, 404, 405, 406, 407, 409, 410, 411, 413, 414, 415.
Install master rod (P/N 835) before exceeding 200 hours total operation with the early type rod. This replacement should preclude further master rod failures and involves the rebalancing of the crankshaft and rod assembly.
(Kinner Service Bulletin No. E-1-8 dated July 24, 1942, covers this same subject.)
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48-02-02: 48-02-02 DOUGLAS: Applies to C-54 and DC-4 Aircraft With Wilcolator Fire Detectors Installed in the Engine Power Section of the Nacelle. \n\nCompliance required by next engine change. \n\nRevise the method of attachment of the A-4981 Wilcolator fire detectors located on the cowl flap support wing in zone 1 by clamping the detector to its mounting plate with a retainer strip of 0.062-thickness low carbon steel sheet, cadmium plated, secured with the same screws which attach the detector to the support box. Failure of the supports is caused by vibration during engine operation. \n\n(Douglas Service Bulletin DC-4 No. 75 covers this same subject.)
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48-11-02: 48-11-02 DOUGLAS: Applies to DC-6 Aircraft. \n\n\tTo be accomplished prior to return to service in class C operation-with cabin supercharging, cabin heating, and thermal deicing including thermal windshield deicing, in operation. \n\n\tRework must be accomplished in accordance with the following Douglas Co. data: \n\n\t1.\tAccomplish all rework covered by data listed in Notes 48-10-01 and 48-11-01 for classes A and B operation, including paragraphs 1 and 2 but excluding paragraph 3 of Note 48-10-01, and excluding paragraph (a) of Note 48-11-01. \n\n\t2.\tRework in accordance with the following must also be accomplished: \n\n\tService Bulletin DC-6 No. 258, Cabin Supercharger Revisions and Bearing Oil Control, dated February 13, 1948. (Also, all superchargers must incorporate low sped drive shaft per Douglas Installation Drawing No. 5350684-C.) \n\n\tService Bulletin DC-6 No. 257, Relocation of Cabin Supercharger Oil Cooler, as revised February 18, 1948. \n\n\tThe rework outlined in the data listed above is based upon an airplane which incorporates certain production changes. Therefore, in order to satisfactorily complete the rework required, some aircraft* must be revised in accordance with the following: \n\n\tService Bulletin DC-6 No. 13, Installation of an Oil Pressure Warning Switch for each Cabin Supercharger Gear Box, dated August 28, 1947. \n\n\t*Serial numbers of airplanes affected by this rework are listed on the pertinent Service Bulletin(s). Also, additional information may be obtained from the "Supplement" to "Cross Reference List-Service Changes and Modification Items" which has been prepared and revised by the Douglas Co. as of February 11, 1948.
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47-11-01: 47-11-01 NAVION: (Was Mandatory Note 1 of AD-782-3.) Applies Only to Serial Numbers NAV-4-2 to NAV-4-550, Inclusive.
To be accomplished immediately.
Remove present rudder-nose gear steering bellcrank, P/N 145-34175 and replace with new part of the same number furnished by North American. The replacement part is to be identified by a yellow dot and the stamp (SPL).
(North American Service Bulletin No. 21, dated January 23, 1947, covers this same subject.)
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2005-22-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 airplanes, and Model A320- 200 series airplanes, that requires a detailed inspection of the tail cone triangle to determine its position, and corrective actions if necessary. This action is necessary to prevent excessive vibrations of the elevators, which could result in reduced structural integrity and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
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47-25-02: 47-25-02 CULVER: (Was Mandatory Note 4 of AD-778-2.) Applies to All Model V Aircraft.
Compliance required prior to August 15, 1947.
Install wing fillets, Culver P/N 10477, at junction of fuselage and wing trailing edge. Attach with 6 x 1/4 PK screws (12) or equivalent.
(Culver Service Bulletin No. 13 covers this same subject.)
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00-00-00:
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