Results
2000-15-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. That AD also requires that operators submit a report of the inspection results to the FAA. That AD was prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. This amendment expands the applicability of the existing AD to include additional airplanes, and removes the reporting requirement. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection. \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-33A027, dated March 10, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 7, 1999 (64 FR 19695, April 22, 1999).\n\n\tThe incorporation by reference of certain other publications listed in the regulations is approved by the Director of the Federal Register as of August 23, 2000.\n\n\tComments for inclusion in the Rules Docket must be received on or before October 10, 2000.
85-07-02: 85-07-02 BOEING: Amendment 39-5036. Applies to Boeing Model 757 airplanes listed in the Boeing Service Bulletin 757-25A0036, Revision 1, dated September 21, 1984. To prevent degradation of fire protection capability in the cargo compartments, accomplish the following within 120 days after the effective date of this AD, unless already accomplished: \n\n\tA.\tReplace the existing cargo compartment blowout panels in accordance with Boeing Service Bulletin 757-25A0036, Revision 1, dated September 21, 1984, or later FAA approved revision. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of replacements required by this AD. \n\tAll persons affected by this directive who have not already received the above specified service bulletins from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents also may be examined at the FAA, Northwest Mountain Region, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\tThis amendment becomes effective May 13, 1985.
97-20-05: This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model HS 748 series airplanes. This action requires installation of a modified aileron cable pulley guard and rubbing strips. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent jamming or restricting of the aileron cable, which could lead to the loss of aircraft roll control.
98-21-07: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ85A and RJ100A series airplanes, that requires a one-time inspection for evidence of machining (undercutting) into the web of the integral stringers of the bottom skin of the wings, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced wing strength and stiffness, and the onset of premature fatigue cracking, which could result in reduced structural integrity of the airplane.
98-04-48: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332L2 helicopters. This action requires modifying the main rotor blade vibration absorber (vibration absorber) by replacing the weight support assemblies with reinforced weight support assemblies. This amendment is prompted by a report of the failure of a weight support assembly in-flight. The actions specified in this AD are intended to prevent failure of a vibration absorber weight support assembly, which could lead to adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter.
98-03-19: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires deactivation of certain circuit breakers, and a revision to the Airplane Flight Manual (AFM) to provide operational procedures to prevent loss of electrical power following an engine flameout. This AD also requires modifications of the electrical system, which terminate the requirement for the AFM revision and allow reactivation of the circuit breakers. This amendment is prompted by the issuance of mandatory continued airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent generator overload conditions that could result in loss of electrical power and failure of certain flight and landing control systems, and to prevent power interruption to the attitude heading reference system (AHRS) that could result in the display of erroneous heading information.
99-20-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320 series airplanes, that requires replacement of the disc valve and spring in the low pressure non-return valve of the airborne ground check module (AGCM) of the ram air turbine (RAT). This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent malfunction of the low pressure non-return valve in the AGCM. If the RAT is being used due to the loss of other systems, a malfunction of the valve could result in loss of the blue hydraulic system, and consequent loss of certain flight control and electrical systems of the airplane.
98-15-22: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection for delamination, erosion, and condition of fillet sealant and conductive edge sealer of the wing and empennage leading edge area behind the de-ice boots, and follow-on corrective actions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent delamination of the wing and empennage leading edge due to improper installation of the wing de-ice boot, which could result in reduced controllability of the airplane.
78-08-01: 78-08-01 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-3180. Applies to BH/HS 125-600A airplanes, certificated in all categories. Compliance required within one month after the effective date of this AD, unless already accomplished. To prevent possible inability to activate the engine blow-off valve switches in the event that birds are ingested into the engines on take-off, accomplish the following: Remove the existing switch guards for the engine blow-off valve switches and replace with the new design guard, P/N 25-6 NF 2629, in accordance with the section entitled "Accomplishment Instructions" and the associated drawing, contained in Hawker Siddeley Aviation, Ltd. Service Bulletin 75-3(2580), dated June 21, 1977, or an FAA-approved equivalent. This amendment becomes effective May 10, 1978.
95-16-06: This amendment supersedes Airworthiness Directive (AD) 83-05-01, which currently requires the following on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes: repetitively inspecting the wing lower skin panels at the main gear bay cutouts for loose or damaged rivets and cracks, replacing loose or damaged rivets, and repairing any cracked wing lower skin panel. The Federal Aviation Administration's policy on commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. The proposed action would require reinforcing the wing lower skin at both the landing gear cutouts at Wing Station (WS) 115 and the undercarriage bay cutouts at WS 60 and WS 90, as terminating action for the repetitive inspections that are currently required by AD 83-05-01. The actions specified in the proposed AD are intended to prevent wing damage caused by cracks or loose or damaged rivets in the wing lower skin panels, which, if not detected and corrected, could result in structural damage to the point of failure.