Results
2022-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD was prompted by a report of in-flight smoke and fire that initiated from the windshield heat power wire braid. This AD requires incorporating temporary revisions into the airplane flight manual (AFM) and the quick reference handbook (QRH) that modify procedures for windshield heat operation until the affected windshield assemblies are replaced. The FAA is issuing this AD to address the unsafe condition on these products.
47-20-09: 47-20-09 ERCO: (Was Service Note 1 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required at each 100-hour inspection and immediately after each electrical system malfunction. Check the operation of the voltage regulator by observing the ammeter reading after starting and until the battery becomes charged. A normal operation would indicate a charging rate up to 11-13 amperes for periods of time up to 20 minutes after starting. The charging rate should reduce to 2 amperes or less within 2 hours or operation. (Ercoupe Service Department Memorandum No. 23 covers this same subject.)
2022-06-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low-pressure compressor (LPC) blades''-- these terms are used interchangeably in this AD). This AD requires installation of debris shields on the thrust reverser (T/R) inner wall at the left and right sides of the lower bifurcation, inspection of the fan cowl doors for moisture ingression, repetitive functional checks of the hydraulic pump shutoff valves to ensure they close in response to the fire handle input, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that requires installing a lightning bonding jumper from the lower rotating beacon to the airframe. This action is necessary to prevent possible multiple avionics failures caused by a lightning strike, which could reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
93-14-16: 93-14-16 BRITISH AEROSPACE (COMMERCIAL AIRCRAFT), LIMITED: Amendment 39-8640. Docket 93-NM-03-AD. Applicability: Model ATP airplanes having aft isolator bracket attachment bolts, part number A102-4E or A102-5E; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the engine support structure, accomplish the following: (a) For airplanes on which the aft isolator bracket attachment bolts have accumulated less than 5,000 total landings as of the effective date of this AD: Prior to the accumulation of 5,000 total landings on the bolts, or within 1,250 hours time-in-service after the effective date of this AD, whichever occurs later, remove the bolts and replace them with new or serviceable parts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. Thereafter, prior to the accumulation of 5,000 total landings onany bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (b) For airplanes on which the aft isolator bracket attachment bolts will have accumulated 5,000 or more total landings before it is replaced in accordance with paragraph (a) of this AD: Prior to the accumulation of 5,000 total landings or within 150 hours time-in-service after the effective date of this AD, whichever occurs later, perform a visual inspection of the aft isolator bracket attachment bolts to determine if each bolt is in position, and to detect failed or cracked bolts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. (1) If any bolt is missing, failed, or cracked, prior to further flight, replace all four bolts in the assembly with new or serviceable parts, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (2) If no bolt is missing, failed, or cracked, repeat the visual inspection thereafter at intervals not to exceed 150 hours time-in-service. Within 1,250 hours time-in-service after the effective date of this AD, replace each bolt with a new or serviceable part, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (c) Replacement of the existing bolts on the aft isolator brackets on the engine mounting beams with improved bolts (Modification 35256A) in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, constitutes terminating action for replacement of the bolts every 5,000 landings, as required by paragraphs (a), (b)(1), and (b)(2) of this AD. (d) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special 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. (f) The replacement and inspection shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992; or Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, Revision 1, dated May 10, 1993. The modification shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 April 16, 1993 2-5 0 March 2, 1993 6 (This page is not used) 7 1 (Not Dated) 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2022-06-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low- pressure compressor (LPC) blades''--these terms are used interchangeably in this AD). This AD requires modifying the engine inlet to withstand fan blade failure event loads. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-22: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206B engines that have incorporated PWC Service Bulletin (SB) No. 28119, and PW206C, PW206E, PW207D, and PW207E turboshaft engines. This AD requires checking the automatic low-cycle- fatigue (LCF) counting data made by the engine Data Collection Unit (DCU) on installed engines, and validating proper DCU automatic LCF counting before an engine is installed. This AD results from two reports of irregular LCF counting, observed between engines on the same helicopter, during weekly recording of LCF data in the engine log books. We are issuing this AD to prevent critical rotating parts from exceeding published life limits, which could result in uncontained engine failure and possible loss of the helicopter.
47-21-15: 47-21-15 REPUBLIC: (Was Mandatory Note 5 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 488 to 602, Inclusive. Compliance required as soon as possible, but not later than July 1, 1947. Inspect the radio filter mounted on left-hand rear engine baffle. Filters in steel boxes 4 inches by 2 inches should be further inspected and reworked or replaced as described below, in order to minimize the possibility of a short circuit. Those filters which are in a smaller box need not be reworked. 1. If the coil is bolted to the box and the condenser is fastened in place with a clamp, the filter is satisfactory. If the coil is bolted to the box but the condenser is glued in place, the filter may be used provided a 1 1/8-inch diameter clamp is added to fasten the condenser in place. 2. Filters in which the coil is not bolted to the box should be replaced by a new filter assembly, Republic P/N SK-17-83053-1. (Republic RC-3 Seabee Service Bulletin No. 15 dated April8, 1947, covers this same subject.)
2012-22-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S airplanes. This AD was prompted by reports of chafed fuel return line assemblies, which were caused by the fuel return line assembly rubbing against the right steering tube assembly during full rudder pedal actuation. This AD requires you to inspect the fuel return line assembly for chafing; replace the fuel return line assembly if chafing is found; inspect the clearance between the fuel return line assembly and both the right steering tube assembly and the airplane structure; and adjust as necessary. We are issuing this AD to correct the unsafe condition on these products.
2022-05-12: The FAA is superseding Airworthiness Directive (AD) 2020-12-08 for all Embraer S.A. Model EMB-505 airplanes. AD 2020-12-08 required inspections of the mass-balance weights of the elevators, ailerons, and rudder (flight control surfaces) and their attachment parts, and corrective actions if necessary, and revising the airworthiness limitation section (ALS) of the maintenance manual or instructions for continued airworthiness to incorporate new airworthiness limitations. This AD retains the actions required by AD 2020-12-08 and requires, for certain airplanes, cleaning and weighing certain mass-balances and installation or replacement, as applicable; and for certain other mass- balances for certain airplanes, replacement of those mass-balances. This AD was prompted by a determination that new applicable airplane serial numbers and new criteria for the replacement of affected parts are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-08-23: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the "Y" chord; and corrective actions, if necessary. This amendment is prompted by several reports of fatigue cracking found at that location on Model 737 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.
84-14-01: 84-14-01 AVCO LYCOMING: Letter issued July 20, 1984. Pursuant to the authority of the Federal Aviation Act of 1958, delegated to me by the Administrator, the following AD is issued and made applicable to Avco Lycoming LTS101-600A-2 model engines. Compliance required in the sequence indicated, unless already accomplished: 1. Perform a T4 indicator system check on those AS350D helicopters having Brion Leroux T4 indicator part number 5626-524-00-00 installed, in accordance with Aerospatiale Maintenance Manual Maintenance Work Card (MWC) 77.00.00.501 at four approximately equal increments between 680 degrees C and 820 degrees C, within the next 50 engine operating hours and thereafter at intervals not to exceed 300 engine operating hours. (NOTE: Approved calibration equipment is described in Aerospatiale Telex Number AHC/SE/BH/84T/114T, paragraph EE.) Comply with following instructions (A), (B), and (C) if the T4 indicator system error is greater than zero plus minus 5 degreesC at any of the four increments and comply additionally with paragraph 4 below prior to further flight if the T4 indicator system reads low by 15 degrees C or greater at any of the four increments. (A) Check that the thermocouple loop resistance (without indicator) is not greater than 5.7 OHMS. (B) If the thermocouple loop resistance (without indicator) is greater than 5.7 OHMS, check the harness for loose or contaminated connections. Tighten, clean, or replace the aircraft harness components, or check and replace engine thermocouple components as required to bring the resistance to 5.7 OHMS or less. (C) When the thermocouple loop resistance (without indicator) is 5.7 OHMS or less, calibrate the T4 indicator system to result in zero plus minus 5 degrees C error at a selected point within the range of 760 degrees C to 770 degrees C, by adjusting the indicator setscrew (reference MWC 77.00.00.501) or replacing the indicator if required. 2. Perform an engine condition checkin accordance with the Aerospatiale AS350D helicopter flight manual, Section II, paragraph 10, within the next 50 engine operating hours. If the condition of the engine is proved to be unsatisfactory and cannot be corrected through normal maintenance procedures, comply with paragraph 4 below prior to further flight. 3. Perform an engine vibration survey in accordance with Avco Lycoming Service Bulletin Number LTS 101A-71-00-0061, Section II, Item B, within the next 50 engine operating hours. If the revised vibration limits are exceeded, comply with paragraph 4 below prior to further flight. 4. Comply with the accomplishment instructions in Avco Lycoming Service Bulletin Number LTS 101A-71-00-0061, Section II, Items F, G, H, and I, at each 600 hour periodic inspection and prior to further flight as directed by the preceding paragraphs. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, FAA, New England Region. This airworthiness directive becomes effective upon receipt.
2004-14-19: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive detailed inspections of the aft pressure bulkhead for indications of oil cans and previous oil can repairs, and corrective actions, if necessary. An oil can is an area on a pressure dome web that moves when pushed from the forward side. This action is necessary to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression of the passenger cabin, possible damage or interference with the airplane control systems that pass through the bulkhead, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
49-13-02: 49-13-02 BELLANCA: Applies to Models 14-13, 14-13-2 and 14-13-3 Aircraft As Indicated by Serial Numbers Below. Compliance required by July 1, 1949. 1. (Applies to Serial Numbers 1060 through 1567, and 1570 through 1573.) In order to strengthen the fitting on the rear wing spar to which the landing gear drag strut attaches, Bellanca P/N 7560, a 0.065 x 1 1/4 x 1 3/8 4130 steel plate should be welded in place at the forward intersection of the two channel sections. (Bellanca Service Bulletin No. 18 covers this same subject.) 2. (Applies to all Serial Numbers prior to 1589.) In order to prevent overstressing the landing gear drag strut, a suitable stop should be provided at the lower end of the landing gear retracting screw. The stop should be so installed and adjusted as to limit the drag strut travel to that necessary to fully extend the gear. (Bellanca Service Bulletin No. 24 covers this same subject.)
2022-05-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report that some tie-rod assemblies may have been overtightened during the installation of interior monuments (such as galleys, lavatories, and forward stowage or wardrobes). This AD requires adjusting the tie-rod assemblies, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
47-21-09: 47-21-09 NAVION: (Was Mandatory Note 8 of AD-782-3.) Applies to All Serials Up to and Including Number NAV-4-947. Compliance required prior to September 1, 1947. Due to malfunctioning of the hydraulic system which has resulted in the failure of components of that system, including actuating cylinders, the following modifications must be accomplished: (a) If an engine-driven hydraulic pump is installed in the airplane, rework the hydraulic power system to install the manually controlled relief valve, North American P/N 145- 58027, and replace the existing placard "Hyd. System Pull Off" with new placard "Hyd. Power On". (North American Field Service Bulletin No. 26 covers this same subject.) (b) Install the swivel head type nose gear actuating cylinder, North American P/N 145-58014. (North American Field Service Bulletin No. 19 covers this same subject.) (c) Visually inspect all flap and landing gear actuating cylinders for evidence of cracks or other damage. Any cylinders found to be damaged should be replaced.
2004-14-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, and -106 airplanes, that requires repetitive detailed inspections of the left and right aileron tab actuator arm channels for cracking, and corrective actions if necessary. This proposal also provides an optional terminating action for the repetitive inspections. This action is necessary to prevent increased roll forces due to cracking of the left and right aileron tab actuator arms, which could be interpreted by the pilot as a flight control problem and might lead to loss of control of the airplane. This action is intended to address the identified unsafe condition.
2022-05-02: The FAA is superseding Airworthiness Directive (AD) 2021-11- 25, which applied to certain Airbus Helicopters (type certificate previously held by Eurocopter France) Model AS350B3 and EC130T2 helicopters. AD 2021-11-25 required revising the existing rotorcraft flight manual (RFM) for your helicopter by inserting a new procedure (temporary). Since the FAA issued AD 2021-11-25, the manufacturer identified an additional affected full authority digital engine control (FADEC) part number and developed an optional modification for the affected FADECs. This AD requires revising the existing RFM for your helicopter by inserting a new procedure (temporary). This AD also requires, for helicopter on which an optional terminating action (installation of serviceable FADECs) was done, removing the applicable temporary procedure from the existing RFM for your helicopter. In addition, this AD also adds helicopters to the applicability. Furthermore, this AD prohibits the installation of an affected FADEC. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747- 400F, and 747 SR series airplanes, that requires inspection of fire extinguisher bottles in the engine and the auxiliary power unit (APU) to determine the part number; and replacement of the fire extinguisher bottles with new fire extinguisher bottles, if necessary. This action is necessary to prevent fractured discharge heads, which could cause the fire extinguishing agent to leak, which could result in an uncontrolled engine fire that could spread to the strut and wing, or an uncontrolled APU fire that could spread to the airplane structure. This action is intended to address the identified unsafe condition.
96-17-01: This amendment adopts a new airworthiness directive (AD) that is applicable to AlliedSignal Inc. (formerly Textron Lycoming) Model T5313B turboshaft engines. This action supersedes priority letter AD 96-15-07 that currently requires, prior to further flight, removal from service of all suspect second stage power turbine disks, identified by serial number, and replacement with serviceable parts. This action corrects an incorrect second stage power turbine disk serial number. This amendment is prompted by report of a typographical error in the serial number listing. The actions specified by this AD are intended to prevent possible failure of a second stage power turbine disk, uncontained engine failure, and damage to aircraft.
94-14-15: 94-14-15 DASSAULT AVIATION: Amendment 39-8963. Docket 93-NM-159-AD. Applicability: Model Mystere-Falcon 50 series airplanes, serial numbers 2 through 216, inclusive; equipped with exhaust duct attachment clamps, part number (P/N) NH1002299-10 or P/N NH1007763- 10; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of attachment clamps installed on the engine exhaust ducts, which could cause exhaust gas to leak and, subsequently, could trigger a false engine fire alarm, accomplish the following: (a) For airplanes equipped with exhaust duct attachment clamps having P/N NH1002299-10: Within 300 flight hours after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, replace attachment clamps having P/N NH1002299-10 with attachment clamps having P/N NH1007763-10, in accordance with Dassault Aviation Service Bulletin F50-229 (F50- 54-13), Revision 1, dated July 21, 1993. (b) For airplanes equipped with exhaust duct attachment clamps having P/N NH1007763-10: Within 1,400 flight hours after the effective date of this AD, inspect the attachment clamps installed on the engine exhaust ducts to verify if the clamp screw is straight (not bent), in accordance with Dassault Aviation Service Bulletin F50-229 (F50-54-13), Revision 1, dated July 21, 1993. (1) If the clamp screw is straight, prior to further flight, verify if the tightening torque value of the screw is marked on the attachment clamp as follows: "NORMAL NET TORQUE 100-120 IN-LBS." (i) If the marking is as specified in paragraph (b)(1) of this AD, no further action is required. (ii) If the marking is not as specified in paragraph (b)(1) of this AD, prior to further flight, erase the incorrect marking and replace it with the correct tightening torque value. (iii) After correcting the marking, prior to further flight, ensure that the clamp screw is secured to the tightening torque value specified in paragraph (b)(1) of this AD. (2) If the clamp screw is bent, prior to further flight, replace the discrepant attachment clamp with a new attachment clamp having the same part number, in accordance with the Accomplishment Instructions of Dassault Aviation Service Bulletin F50-229 (F50-54-13), Revision 1, dated July 21, 1993. (c) As of the effective date of this AD, no person shall install an exhaust duct attachment clamp having P/N NH1007763-10 on any airplane, unless that attachment clamp is marked "NORMAL NET TORQUE 100-120 IN-LBS." (d) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The actions shall be done in accordance with Dassault Aviation Service Bulletin F50-229 (F50-54-13), Revision 1, dated July 21, 1993. 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 Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on August 5, 1994.
96-17-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10A (military) series airplanes, that requires modification of the AC generator control units. This amendment is prompted by reports of loss of electrical power from two generators and an engine that flamed out due to an overfrequency condition of a generator. The actions specified by this AD are intended to prevent an overfrequency condition of a generator, which could lead to the loss of all electrical power of the airplane.
2022-02-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report that during a fleet sampling inspection, cracks were found on the inner cylinder pivot pins of the left and right main landing gear (MLG) on one of the airplanes. This AD requires repetitive lubrications of the left and right MLG truck beams and inner cylinder pivot joints; a review of the maintenance program documentation to verify that certain lubrication tasks are incorporated; repetitive inspections of the MLG inner cylinder pivot pins and inner cylinder bushings of the MLG truck beams and inner cylinder joints to detect friction, heat damage, excessive wear, cracking, and smearing of bushing material; and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
50-19-02: 50-19-02 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. Failures of the rudder flight tab balance weight brackets and of the rudder closing spar ahead of the flight tab have been experienced on service aircraft. In order to preclude the possibility of these failures progressing to such an extent that the airworthiness of the airplane is impaired, it is considered necessary that the following be accomplished on all CVAC Model 240 Series aircraft: A. To be accomplished as soon as practicable but not later than next No. 1 inspection and to be repeated at each No. 2 inspection thereafter. Inspect the rudder flight tab balance weight brackets for cracks in the neck down areas approximately 1 inch from the flight tab and also adjacent to the edges of the counterweight. Inspect the rudder closing spar for cracks in the areas adjacent to the rudder flight tab hinge brackets. All cracks, when found, must be replaced or suitably repaired before next flight. B. To be accomplished by January 1, 1951. Reinforce the rudder flight tab balance weight brackets, and the attachment of the brackets to the tab and to the balance weight. (CVAC Service Bulletin 240-355A covers this same subject.) NOTE: Although evidence indicates that these failures will be materially reduced after incorporation of the above, sufficient evidence of trouble-free operation is not available. Therefore, it will be necessary that the inspections outlined under part A, be continued at each No. 3 inspection after the incorporation of part B, until sufficient evidence of trouble-free operation has been supplied to the FAA to warrant discontinuance of this inspection. This supersedes AD 50-06-03.
2004-14-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires deactivating both thrust reversers and revising the airplane flight manual (AFM) to ensure safe and appropriate performance during certain takeoff conditions. This amendment requires installing modifications that will add an independent third line of defense on the thrust reversers, which would enhance their redundancy and terminate the requirements of the existing AD. The actions specified by this AD are intended to prevent in-flight deployment of the thrust reversers, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.