Results
94-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes. This action requires inspections to detect cracking in the ventral aft pressure bulkhead, and repair, if necessary. This amendment is prompted by reports of cracking found in the ventral aft pressure bulkhead on several airplanes. The actions specified in this AD are intended to prevent the propagation of cracks in the ventral aft pressure bulkhead, which could lead to failure of the bulkhead and subsequent rapid decompression of the airplane.
78-14-05: 78-14-05 CONSOLIDATED AERONAUTICS: Amendment 39-3260. Applies to Lake Model LA-4-200 airplanes, Serial Nos. 769 through 830, inclusive. Compliance is required as indicated, unless already accomplished. To prevent operation with flawed (material defect) wing main beam attachment fittings, accomplish the following: 1. Prior to further flight and thereafter prior to the first flight of each day until paragraph 3 is accomplished, visually inspect the outboard portion of the four (4) wing main beam attachment fittings (steel fittings), P/N 1-3214-3, for flaws which appear as spanwise cracks. 2. Flawed fittings found as a result of the inspections of paragraphs 1 above or 3a below, must be replaced prior to further flight with serviceable fittings, P/N 1-3214-3, in accordance with paragraph 4. 3. Within the next 15 hours time in service after the effective date of this AD, visually inspect the outboard end of the four steel wing main beam attachment fittings, P/N 1- 3214-3,for the impression stamped bar stock heat treat lot number. These fittings are visible through the main gear wheel wells. If the fitting impression stamped lot number is 741 or 741R, either: a. Ultrasonic inspect the steel wing main beam attachment fitting(s), P/N 1- 3214-3, for flaws in accordance with Lake Aircraft Division of Consolidated Aeronautics, Inc., Service Bulletin B60, or b. Replace the steel wing main beam attachment fitting(s), P/N 1-3214-3, with serviceable fitting(s), P/N 1-3214-3, in accordance with paragraph 4. NOTE: This paragraph applies whether or not an "H" is impression stamped on the outboard end of the fitting opposite "741" or "741R". 4. Replacement serviceable fittings must be installed in accordance with Lake Aircraft Division of Consolidated Aeronautics, Inc., Service Bulletin B60. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lake 4 Sales Corporation, P.O. Box 399, Tomball, Texas 77375. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at FAA New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective July 19, 1978.
99-06-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires replacement of the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts. This amendment also requires, for certain airplanes, repetitive inspections to detect discrepancies of the rivets; and corrective actions, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the rivets that attach the pressurized floor panel to gantries 4 and 5, which could result in the loss of the floor panel and consequent rapid decompression of the airplane.
97-16-09: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires modification of the hydraulic system, and a revision to the Airplane Flight Manual (AFM) to include revised procedures for lowering the landing gear. This amendment is prompted by a report of uncommanded application of the brakes when the direct current (DC) hydraulic pump was selected ON with the main hydraulic system operative; this situation was caused by build-up of back pressure in the brake supply and hydraulic return systems. The actions specified by this AD are intended to prevent uncommanded application of the brakes during landing, as a result of the build-up of back pressure.
97-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the existing fire, tailpipe, and bleed-air overheat detector control units with new, improved units. This amendment is prompted by reports indicating that false engine and auxiliary power unit (APU) fire warnings were issued from the fire detector control units due to moisture or induced voltages of the detector control unit. The actions specified by this AD are intended to prevent such false fire warnings, which could result in unnecessary diversion of the airplane, and resultant increased risks to the airplane, passengers, and crew, and the potential for an overweight landing.
47-10-24: 47-10-24 LOCKHEED: (Was Mandatory Note 27 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to June 1, 1947. Install thermal relief valve and bypass line in fuel crossfeed line adjacent to No. 4 cross transfer valve. (LAC Service Bulletin 49/SB-48 covers this same subject.)
48-07-02: 48-07-02 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 through 43064; and 43105 Through 43110. \n\n\tTo be accomplished not later than the first engine change after March 1, 1948, but in any event not later than June 1, 1948. \n\n\tTo prevent failure in the engine supercharger control actuator when shifting from low to high blower and vice versa, it is necessary to provide overtravel in the engine supercharger control linkage by installing a new Geneva-Loc supercharger actuator lever, a new Bendix link-supercharger actuating link and a new four-hole mounting support bracket. \n\n\t(Douglas Service Bulletin DC-6 No. 127 covers this same subject.)
94-09-03: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes, that requires that the brake wear limits prescribed in this proposal be incorporated into the FAA-approved maintenance inspection program. This amendment is prompted by an accident in which a transport category airplane executed a rejected takeoff (RTO) and was unable to stop on the runway due to worn brakes; and the subsequent review of allowable brake wear limits for all transport category airplanes. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy RTO.
94-07-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires modification of the cavity vent drain tube assembly at the center wing lower auxiliary fuel tank cavity. This amendment is prompted by a report that the cavity vent tube, if not properly grounded, could act as an electrical path in the event of a lightning strike. The actions specified by this AD are intended to prevent arcing in the tank cavity and possible resulting fire.
92-16-08: 92-16-08 BOEING: Amendment 39-8317. Docket No. 92-NM-08-AD. \n\n\tApplicability: Model 747 series airplanes; equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; or equipped with escape systems installed in accordance with Supplemental Type Certificate SA574GL, SA575GL, SA744GL, SA745GL, or SA1215EA; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent jamming of an emergency exit door, accomplish the following: \n\n\t(a)\tFor airplanes equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; and for airplanes equipped with escape systems installed in accordance with Supplemental Type Certificate (STC) SA574GL, SA575GL, SA744GL, or SA745GL: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(b)\tFor airplanes equipped with escape systems installed in accordance with STC SA1215EA: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with Air Cruisers Service Bulletin 25-139, Revision 1, dated September 18, 1991; or in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tThis amendment becomes effective on September 16, 1992.