Results
2006-15-14: This amendment adopts a new airworthiness directive (AD) for Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A-3 helicopters that requires replacing certain fixed bolts and nuts, re-identifying certain main rotor nuts, and revising the Airworthiness Limitations-- Time Change Items (TCI) list to reflect the new life limits and new part numbers. This amendment is prompted by a re-evaluation of certain fatigue-critical parts, which resulted in establishing new life limits for certain like-numbered parts and re-identifying a certain existing part with a different part number, or in some cases, replacing them with new parts. The actions specified by this AD are intended to prevent fatigue failure of the fixed bolts and nuts, and subsequent loss of control of the helicopter.
98-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the main landing gear (MLG), and follow-on 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 detect and correct a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the bearing, and consequent collapse of the MLG during landing.
97-24-17: This document publishes in the Federal Register an amendment adopting priority letter airworthiness directive (AD) 97-24-17, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires inspections of components in the tail rotor drive system for scratches, cracks, fretting, corrosion, and proper torquing, lubrications of the oil cooler blower shaft hanger bearings and oil cooler hanger bearings (hanger bearings), and removal of corrosion inhibitive adhesive barrier tape (barrier tape) from the tail rotor gearbox and the tail rotor gearbox support assembly faying surfaces. This amendment is prompted by numerous reports of three problems, all of which are related to the tail rotor drive system. The actions specified by this AD are intended to: detect scratches, cracks, fretting, and corrosion in the disc pack couplings; prevent inadequate lubrication of the hanger bearingsand oil cooler blower shaft; and prevent loss of mounting torque on the tail rotor gearbox. Failure of any of these components could result in loss of power to the tail rotor and subsequent loss of control of the helicopter.
88-01-09: 88-01-09 BOEING: Amendment 39-5818. Applies to Model 737-300 series airplanes listed in Boeing Service Bulletin 737-34-1220 dated April 30, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent loss of the primary Electronic Flight Instrument System (EFIS) displays, accomplish the following: \n\n\tA.\tReplace the EFIS symbol generators in accordance with Boeing Service Bulletin 737-34-1220 dated April 30, 1987, or later FAA-approved revisions. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, and which has the concurrence of an FAA Principal Maintenance Inspector, 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 accomplishmentof the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 16, 1988.
2006-15-12: The FAA is adopting a new airworthiness directive (AD) for certain CASA Model C-212-CC airplanes. This AD restricts the operation of the airplane to carrying either passengers or cargo (but not both) in the same compartment, unless the airplane is modified to include an approved protective liner between the passengers and the cargo. This AD results from our determination that affected airplanes, when carrying both cargo and passengers in the same compartment, cannot achieve the required level of performance. We are issuing this AD to prevent a hazardous quantity of smoke, flames, and/or fire extinguishing agent from the cargo compartment from entering a compartment occupied by passengers or crew.
98-13-03: This amendment supersedes Airworthiness Directive (AD) 82-20-04 R1, which currently requires repetitively inspecting the main landing gear (MLG) hinge fitting, support angles, and attachment bolts on British Aerospace H.P. 137 Mk1 and Jetstream series 200 airplanes, and repairing or replacing any part that is cracked beyond certain limits. This AD requires installing improved design MLG fittings, as terminating action for the repetitive inspections that are currently required by AD 82-20-04 R1, and will incorporate the Jetstream Model 3101 airplanes into the Applicability of the AD. The Federal Aviation Administration's policy on aging 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 actions specified by this AD are intended to prevent structural failure of the MLG caused by fatigue cracking, which could result in loss of control of the airplane during landing operations.
2000-22-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires modification of the canted pressure deck drain system in the wheel well of the main landing gear (MLG). This amendment is prompted by reports of ice accumulation on the aileron control cables and on the MLG door and door seal during flight, due to fluid entering the canted pressure deck area, leaking into the MLG wheel well, and freezing. The actions specified by this AD are intended to prevent such ice accumulation, which could render one of the aileron control systems and/or the MLG doors inoperative, resulting in reduced controllability of the airplane.
89-13-08: 89-13-08 BOEING: Amendment 39-6241. \n\tApplicability: Model 757 series airplanes, listed in Boeing Service Bulletin 757-32- 0083, dated December 15, 1988, certificated in any category. \n\n\tCompliance: Required within the next 750 landings after the effective date of this AD or prior to the accumulation of 10,000 landings, whichever occurs later, unless previously accomplished. \n\n\tTo prevent the partial loss of braking and, potentially, the complete loss of braking, accomplish the following: \n\n\tA.\tReplace aluminum brake metering valve actuation shafts with steel shafts, in accordance with Boeing Service Bulletin 757-32-0083, dated December 15, 1988. \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 for the accomplishment of the inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents 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 (39-6241, AD 89-13-08) becomes effective on July 24, 1989.
2019-06-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 A-1, MBB-BK 117A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, MBB-BK 117 C-1, and MBB-BK 117 C-2 helicopters. This AD requires repetitive inspections of the tail rotor (T/R) gearbox housing. This AD was prompted by a report that a crack was found in a T/R gearbox housing. The actions of this AD are intended to correct an unsafe condition on these products.
99-15-04 R1: This amendment revises Airworthiness Directive (AD) 99-15-04, which currently requires you to calibrate, inspect, and repair or replace portions of the turbine inlet temperature system on all The New Piper Aircraft, Inc. (New Piper) Models PA-46-310P and PA-46-350P airplanes (different actions for different airplane models). Information reveals that the AD should not apply to airplanes where the factory installed turbine inlet temperature gauge and associated probe have been replaced through supplemental type certificate (STC). This AD retains the actions of AD 99-15-04, and restricts the applicability accordingly. The actions specified by this AD are intended to prevent improper engine operation caused by improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes, which could result in engine damage/failure with consequent loss of control of the airplane.