Results
98-16-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires a one-time inspection for missing fasteners of the splice fitting of the forward inner chord of the Body Station (BS) 2598 bulkhead; and corrective actions, if necessary. This amendment is prompted by a report that fasteners were missing from the splice fitting of the forward inner chord. The actions specified in this AD are intended to prevent accelerated fatigue cracking of the inner chords of the BS 2598 bulkhead, which could result in inability of the structure to carry horizontal stabilizer flight loads, and consequent reduced controllability of the airplane.
98-16-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive inspections to measure for free play (wear on nut assembly) of the horizontal stabilizer actuator assembly, and corrective actions, if necessary. This amendment is prompted by reports of wear of the horizontal stabilizer actuator assembly due to a jackscrew surface finish that was manufactured incorrectly. The actions specified in this AD are intended to prevent excessive free play and wear of the horizontal stabilizer actuator assembly, which could result in a free-floating horizontal stabilizer, and consequent loss of aircraft pitch control.
89-16-07: 89-16-07 BOEING: Amendment 39-6278. \n\tApplicability: Model 747 series airplanes equipped with General Electric CF6-80C2 engines, as listed in Boeing Alert Service Bulletin 747-54A2129 dated June 8, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo eliminate the potential for a fire due to an inadequately sealed firewall in the outboard struts, accomplish the following: \n\n\tA.\tWithin the next 60 days after the effective date of this AD, modify the existing seal configuration in the aft outboard strut trailing edge fairing door/inconel pan area in accordance with the accomplishment instructions of Boeing Alert Service Bulletin 747-54A2129, dated June 8, 1989. \n\n\tB.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6278, AD 89-16-07) becomes effective on August 11, 1989.
60-11-08: 60-11-08 SENSENICH: Amdt. 166 Part 507 Federal Register May 28, 1960. Applies to M74DM Propellers Installed On Lycoming O-320-B Series Engines Except Propellers With An "A" or "K" prefix to the Serial Number. Compliance required within the next 100 hours of flight time or by August 1, 1960, whichever comes first, and at each periodic inspection thereafter. As a result of three incidents of cracked hubs, the following shall be accomplished: (a) Remove the propeller and visually inspect for cracks originating in the pilot bore. In case of doubt, any of the approved methods for aluminum alloy inspections should be used. If cracks are found, the propeller shall be retired immediately from service. (b) If no cracks are found, polish out any scratches in the bore and break and polish any sharp edges at the front and rear chamfer of the pilot bore. (c) When the propeller is reinstalled, torque retaining bolts to 300 inch-pounds. (Sensenich Service Bulletin No. R-8-1 covers the same subject.) Revised November 14, 1961.
2002-14-13: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires installing a clipnut and bracket and revising the routing of the wire assembly of the forward lower cargo door. This action is necessary to prevent failure of the wire assemblies and damage of a ballast of a light fixture, and consequent smoke and/or fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
98-15-23: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 340B series airplanes. This amendment requires adjustment of the cargo baggage net, replacement of baggage net placards, and installation of new baggage net placards. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the cargo bulkhead floor attachments, which could result in damage to the airplane structure and possible injury to passengers and crewmembers.
64-01-01: 64-01-01 AIRBORNE MECHANISMS: Amdt. 666 Part 507 Federal Register January 3, 1964. Applies to All Aircraft Using Vacuum Pumps Models 113A5 and 113A8, Serial Numbers 7G2494 through 7G2678, 8G2679 through 8G2892, 9G2893 through 9G3250 and 10G3251 through 10G3714, and All Vacuum Pumps Models 113A1, 113A2, 113A5 and 113A8 in Which the Splined Drive Coupling, Airborne Mechanisms P/N B1001A2, Has Been Replaced After July 22, 1963. Compliance required within 10 hours' time in service after the effective date of this AD. In order to remove defective splined drive couplings which render the vacuum flight instruments inoperative accomplish the following: (a) On Piper aircraft, unless already accomplished, replace all the vacuum pump splined couplings identified in Piper Service Bulletin No. 218, in accordance with that service bulletin before further flight. (b) On other aircraft, inspect all Airborne Mechanisms P/N B1001A2 couplings for a bright yellow band on the shoulder of the coupling. (The band is visible through the openings in the pump base.) Replace couplings which do not have a yellow band with a coupling having the yellow band before further flight. (Airborne Mechanisms Service Letter No. 5 dated November 5, 1963, and Piper Service Bulletin No. 218 dated November 11, 1963, pertain to this same subject.) This directive effective January 9, 1964.
2000-05-10: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company GE90-85B series turbofan engines. This action requires removing from service aft mount whiffletrees prior to reaching a new cyclic life limit, and replacing with serviceable parts. This amendment is prompted by a reassessment of the low cycle fatigue capability of the engine mount system due to an increase in engine and propulsion system weight. The actions specified in this AD are intended to prevent aft mount whiffletree failure, which if it occurred with other critical aft mount component failures, could possibly result in an engine mount system failure, and separation of the engine from the aircraft.
98-15-16: This amendment adopts a new airworthiness directive (AD) that is applicable to Bombardier-Rotax GmbH 912 F series reciprocating engines. This action requires installation of an improved fuel pump and fuel supply tube. This amendment is prompted by reports of fuel leaks at the outlet port of the fuel pump. The actions specified in this AD are intended to prevent fuel leaks from the fuel pump, which could result in undetected loss of fuel in flight or, an engine fire.
83-03-52: 83-03-52 BOEING: Amendment 39-4584. Applies to Boeing Model 767-200 airplanes certificated in all categories. This AD is required to detect improperly heat treated horizontal stabilizer hinge fittings, which could fail during flight, resulting in a possible reduction in controllability of the airplane. \n\n\tUnless previously accomplished, perform the following prior to further flight on those airplanes listed in Boeing Alert Service Bulletin 767-53A1 dated February 3, 1983, or later FAA approved revision: \n\n\tA.\tInspect the horizontal stabilizer hinge fittings for correct heat treatment in accordance with the accomplishment instructions of paragraph III of Boeing Alert Service Bulletin 767-53A1, dated February 3, 1983, or later FAA approved revision. \n\n\tB.\tReplace any hinge fittings found not to have the correct heat treatment with serviceable fittings prior to further flight.\n \n\tC.\tFerry flights not permitted without prior concurrence of the Manager, Seattle Aircraft Certification Office. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. \n\n\tThis amendment becomes effective March 22, 1983, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T83-03-52 issued February 4, 1983, which contained this amendment.