Results
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.
85-25-05: 85-25-05 BOEING: Amendment 39-5178. Applies to Model 757-200 series airplanes listed in Boeing Service Bulletin 757-27-0069, dated November 4, 1985. To detect nuts installed in the aileron, rudder and elevator power control actuators, and rudder ratio changer that have insufficient self-locking torque characteristics, accomplish the following, unless already accomplished: \n\n\tA.\tWithin 30 days after the effective date of this AD, check the self-locking nuts, P/N BACN10JC12CM or BACN10JC12CD, for proper self-locking torque in accordance with Paragraph III of Boeing Service Bulletin 757-27-0069, dated November 4, 1985, or later FAA- approved revision. If any self-locking nut is found not to meet the self-locking torque requirements of Boeing Service Bulletin 757-27-0069, dated November 4, 1985, or later FAA- approved revision, replace it prior to further flight with a nut found to meet the self-locking torque requirements of the above referenced service bulletin. \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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this document who have not already received copies of the service bulletin may obtain copies upon request from 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 December 21, 1985.
85-02-06: 85-02-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4988. Applies to Model 47G-2A, G-2A-1, G-3, G-3B, G-3B-1, G-3B-2, G-3B-2A, G-4, G-4A, G-5, G-5A, J, J-2, J-2A, and K helicopters with 37-foot diameter main rotor systems and hydraulic boost in longitudinal and lateral cyclic flight control systems, certificated in all categories. (Airworthiness Docket No. 83-ASW-47.) Compliance is required within the next 100 hours time in service after the effective date of this AD. To prevent critical flight control failure in the main rotor system, accomplish the following: (a) Inspect for and remove any incorrect AN/NAS standard bolts installed between hydraulic servo and swashplate control plate, Part Number (P/N) 47-150-184-7, which are not listed in the applicable and current illustrated parts breakdown manual. For removal of incorrect AN/NAS standard bolts, utilize the applicable maintenance and overhaul instructions. (b) Install, torque, and safety, required BellHelicopter Textron, Inc., standard bolts, utilizing applicable and current maintenance and overhaul instructions and illustrated parts breakdown manual. (c) Inspect flight control system for safety and security. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (e) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to fly the aircraft to a base where the requirements of this AD may be accomplished. (Bell Helicopter Alert Service Bulletin No. 47-83-8 pertains to this subject.) This amendment becomes effective February 6, 1985.
2019-05-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of a fractured main landing gear (MLG) orifice support tube (OST). This AD requires replacing the MLG OST, and revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
73-18-03: 73-18-03 ROCKWELL INTERNATIONAL: Amendment 39-1707 as amended by Amendment 39-3201. Applies to Model NA-265-40 Serial Numbers 282-1 and subsequent; Model NA-265-50 Serial Number 287-1; Model NA-265-60 Serial Numbers 306-1 through -139; Model NA-265-70 Serial Numbers 370-1 through -9; and Model NA-265-80 Serial Numbers 380-1 through -61. Compliance required as indicated after the effective date of this AD. To detect possible cracks, corrosion, or breaks in the surface finish in the wing spars and related areas, accomplish the following: (a) On or before June 18, 1974, unless previously accomplished within one year, and at intervals not to exceed two years thereafter, inspect the upper and lower flanges of the front and rear spars in the area of the wing center section, and the lugs on the rear spar and wing trailing edge panel rib, per the instructions of Rockwell International, Inc., Sabreliner Division Service Bulletin No. 73-11, dated June 18, 1973, or later FAA-approved revisions, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to further flight, if cracks, corrosion, or breaks in the surface finish are found in the front or rear spars in the area of the wing center section, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Prior to further flight, if cracks are found in the lugs on the rear spar and wing trailing edge rib, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Airplanes may be operated in accordance with FAR 21.197 to a base where maintenance is to be performed. Amendment 39-1707 became effective October 8, 1973. This Amendment 39-3201 becomes effective May 5, 1978.
2006-10-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-223, -321, -322, and -323 airplanes. This AD requires repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the LAPF firewall. We are issuing this AD to detect and correct this cracking, which could reduce the effectiveness of the firewall and result in an uncontrolled engine fire.