Results
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.
92-02-17: 92-02-17 BOEING: Amendment 39-8154. Docket No. 91-NM-145-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-25- 2754, dated March 30, 1989, certificated in any category. \n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the girt bar end fittings from disengaging the girt bar floor brackets, accomplish the following: \n\n\t(a)\tReplace the girt bar floor brackets with modified brackets, in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(d)\tThe replacement requirements of this AD shall be done in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(e)\tThis amendment (39-8154, AD 92-02-17) becomes effective on March 2, 1992.
93-09-07: 93-09-07 PACIFIC SCIENTIFIC COMPANY, HTL/KIN-TECH DIVISION: Amendment 39-8573. Docket 93-NM-37-AD. This AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\tApplicability: Fire extinguishers, as listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993; as installed on, but not limited to, Airbus Industrie Model A300, A310, and A320 series airplanes, Boeing Model 757-200 series airplanes equipped with Rolls Royce engines, and McDonnell Douglas Model DC-9-80 (MD-80) and MD-11 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of a fire extinguisher to discharge extinguishant in the event of a fire, accomplish the following: \n\n\t(a)\tPrior to the accumulation of 500 hours time-in-service or within 60 days after the effective date of this AD, whichever occurs first, unless accomplished within the last 8 months prior to the effective date of this AD, perform a test ofthe low pressure indicating circuit to monitor actuation of the pressure switch on the fire extinguisher in accordance with the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t\t(1)\tIf the switch passes the test, no further action is required by this AD. \n\n\t\t(2)\tIf the switch fails this test, prior to further flight, replace the fire extinguisher with a serviceable extinguisher. This replacement extinguisher must have been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in the service bulletin. \n\n\t(b)\tAs of the effective date of this AD, no person shall install, on any airplane, a Pacific Scientific fire extinguisher having a part number listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993, that has not been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t(c)\tFor switches that fail to pass the test required by paragraph (a) of this AD: Within 30 days after accomplishing the test, submit a report of the results of the test to the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or fax to (310) 988-5210. The report must include the following information: \n\n\t\t(1)\tWhen was the inspection performed? \n\n\t\t(2)\tWhat is the part number of the fire extinguisher? \n\n\t\t(3)\tWhat is the airplane model and series from which the extinguisher was removed? \n\n\t\t(4)\tWhere was the extinguisher installed (e.g., Position/Location: left engine, right engine, auxiliary power unit (APU) compartment, etc.)? \n\n\t\t(5)\tWhen was the last hydrostatic check performed on that extinguisher? \n\n\t\t(6)\tWho performed the last hydrostatic check on that extinguisher? \n\n\t\t(7)\tWhen was the last hex key check (low pressure indicating circuit test) performed onthat extinguisher? \n\n\t\t(8)\tWas the extinguisher guard tack welded, completely welded, or not welded to the switch housing? The information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(d)\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, Los Angeles 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(e)\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(f)\tThe testing and replacement shall be done in accordance with Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of May 11, 1993 (58 FR 21912, April 26, 1993). Copies may be obtained from Pacific Scientific Company, HTL/Kin-Tech Division, Attention: Product Support Department, 1800 Highland Avenue, Duarte, California 91010. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register, 800 North Capitol Street,NW., suite 700, Washington, DC. \n\n\tThis AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\t(g)\tThis amendment is effective May 11, 1993.