Results
98-18-01: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a retirement life of 60,000 high-power events for the main rotor trunnion (trunnion). This amendment requires changing the method of calculating the retirement life for the trunnion from high-power events to a maximum accumulated Retirement Index Number (RIN). This amendment is prompted by fatigue analyses and tests that show certain trunnions fail sooner than originally anticipated because of the unanticipated higher number of lifts or takeoffs (torque events) performed with those trunnions. The actions specified by this AD are intended to prevent fatigue failure of the trunnion, which could result in loss of the main rotor and subsequent loss of control of the helicopter.
2015-15-02: We are superseding Airworthiness Directive (AD) 2012-13-06, for all Airbus Model A300 series airplanes and all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2012-13-06 required a one-time detailed inspection to determine the length of the fire shut-off valve (FSOV) bonding leads and for contact or chafing of the wires, and corrective actions if necessary. This new AD requires a new one-time detailed inspection of the FSOV bonding leads to ensure that the correct bonding leads are inspected, and corrective action if necessary. This AD was prompted by a determination that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. We are issuing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a sourceof sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.
81-01-52: 81-01-52 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4055. Applies to Models SA330F, G, and J series helicopters, certificated in all categories. Compliance required within five (5) hours' time in service after the effective date of this AD unless already accomplished since December 22, 1980. To prevent possible in-flight loss of the pilot or copilot doors or the copilot's jettisonable panel (if installed), accomplish the following: (a) Inspect the jettisonable pilot door in accordance with Aerospatiale SA330 work cards Nos. 52-10-601 and 52-10-401 of the SA330 Maintenance Manual (Document 8582), or an FAA approved equivalent, and (b) Inspect either - (1) The jettisonable copilot panel in accordance with Aerospatiale SA330 work cards Nos. 52-21-601 and 52-21-401 or an FAA-approved equivalent, or (2) The jettisonable copilot door (if fitted per Aerospatiale Modification No. OP-11-611 or OP-11-970) in accordance with Aerospatiale work cards Nos. 52-10-601 and 52- 10-401 of the maintenance manual, or an FAA-approved equivalent. (c) Rerig improperly rigged doors and panels before further flight. Use serviceable parts in accordance with the respective reference work cards or FAA-approved equivalents. This amendment becomes effective March 16, 1981, to all persons except those persons to whom it was made immediately effective by telegraphic AD T81-01-52, issued December 31, 1980, which contained this amendment.
2001-26-11: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of low pressure compressor (LPC) fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment requires initial inspections at modified thresholds and repetitive inspections at reduced intervals from the current AD using new LPC fan blade inspection criteria, and requires renewal of dry film lubricant on removed blades. This amendment is prompted by reports that an in-service engine experienced LPC fan blade root cracking at a lower life than previously forecast, and, the manufacturer's further investigation that has led to a better understanding of the causes of fan blade root cracking. The actions specified in this AD are intended to prevent LPC fan blade failure due to cracking, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the airplane.
98-07-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires a rototest inspection for fatigue cracking of the vertical support beam at the upper first fastener row of the actuator attachment fitting of the center landing gear (CLG), and follow-on actions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking in the vertical support beam that supports the CLG actuator attachment fitting, which could result in reduced structural integrity of the airplane.
2025-02-15: The FAA is superseding Airworthiness Directive (AD) 2017-21- 05, which applied to certain Saab AB Model 340A (SAAB/SF340A) and SAAB 340B airplanes. AD 2017-21-05 required revising the existing maintenance or inspection program, as applicable, to incorporate airworthiness limitations, including new inspection tasks for the drag brace support fitting of the main landing gear (MLG) and tasks related to the corrosion prevention and control program (CPCP). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2017-21-05 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2015-15-09: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD requires a one-time inspection for damage of the stop arms of the stop plates, an adjustment of the electric trim limit switches, and replacement of the stop plates with newly manufactured stop plates if necessary. This AD was prompted by a report that the pitch trim jammed in the fully down position. We are issuing this AD to detect and correct broken stop arms of the stop plates, which could lead to the pitch trim jamming, loss of control of the elevator trim, and possible reduced control of the airplane.
2015-15-04: We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron, Inc. (Bell), Model 204B, 205A, 205A-1, and 212 helicopters. This AD requires removing a certain part-numbered main rotor (M/R) blade grip (grip) from service. This AD is prompted by an error in a parts manufacturer approval (PMA) that incorrectly allows installation of the grips on the Bell Model 212. The actions specified in this AD are intended to prevent grip failure, separation of the M/R blade, and subsequent loss of control of the helicopter.
58-17-04: 58-17-04 PIAGGIO: Applies to All Models P.136-L1 and P.136-L2 Aircraft. Compliance required by December 1, 1958. Several cases have occurred where the water rudder inadvertently dropped into the extended position during water landings. In order to avoid future occurrences, Piaggio & Co. recommends that a hook be incorporated at the water rudder retraction cylinder, which is controllable by the pilot. In addition, the forward section of the water rudder should be cut off, in order to prevent any interference with the retraction of the water rudder because of the accumulation of debris. This modification is considered mandatory by the Registro Aeronautico Italiano. The FAA concurs and considers compliance therewith mandatory. (Piaggio & Co. Change Order No. 36 L-42, dated May 29, 1958, covers the same subject.)
2001-26-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires replacement of the observer's seat latch assembly with a new, improved seat latch assembly. This action is necessary to prevent the observer's seat from separating from its attachment points in the event of an accident or emergency landing, due to an understrength seat latch assembly. This action is intended to address the identified unsafe condition.
2015-12-04: We are superseding airworthiness directive (AD) 2006-15-08 for all Honeywell International Inc. TPE331-1, -2, -2UA, -3U, -3UW, -5, - 5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, - 10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with certain Honeywell part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, installed. AD 2006-15- 08 required initial and repetitive dimensional inspections of the fuel control drives for wear, and replacement of the FCU and fuel pump. This new AD requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi-engine airplanes. We are issuing this AD to prevent failureof the fuel control drive that could result in damage to the engine and airplane.
81-07-06: 81-07-06 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4071. Applies to Continental A-65, A75, C75, C85, C90, A-100, C125, and O-200 series engines with AC fuel pumps, TCM part number 40585, 40695 or 631391 installed. Compliance required within 30 days after the effective date of this AD, or within the next 25 hours time in service after the effective date of this AD, whichever occurs first, unless already accomplished within the last 12 months and at intervals not to exceed 12 months after the last inspection. To prevent fuel starvation due to fuel flow restriction through the pump screen accomplish the following: a. Remove safety wire and bolt from fuel pump top cover. Discard fiber washer under bolt. b. Remove the fuel pump top cover. Discard cork cover gasket. c. Remove fuel pump screen. d. Inspect the fuel pump and fuel pump screen for contamination. (1) If contaminated, clean fuel pump and fuel pump screen. (2) If fuel pump is damaged by corrosion, replace with an applicable serviceable fuel pump. (3) If fuel pump screen is damaged by corrosion or handling, replace with a serviceable fuel pump screen, TCM P/N 643913. e. Reinstall fuel pump screen, fuel pump cover with new cork cover gasket, TCM P/N 643915 and new bolt gasket P/N 643914. Torque bolt to 30 5 inch-pounds. f. Resafety wire fuel pump top cover bolt and check for leaks. g. Make the appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Teledyne Continental Motors Service Bulletin M81-8, dated March 9, 1981, pertains to this subject. This amendment becomes effective April 1, 1981.
2019-22-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-200B, 747-200C, 747-200F, 747-300, 747- 400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes. This AD was prompted by reports of uncommanded fore and aft movement of the Captain's and First Officer's seats. This AD requires, for the Captain's and First Officer's seats, repetitive horizontal actuator identifications, repetitive checks of the horizontal movement system (HMS), a detailed inspection of the HMS for certain airplanes, and applicable on-condition actions. This AD also requires an inspection to determine the part number and, if applicable, the serial number of the Captain's and First Officer's seats, and applicable on-condition actions. This AD also provides an optional terminating action for the repetitive actions for certain seats. The FAA is issuing this AD to address the unsafe condition on these products.
2017-21-05: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by the determination that new inspection tasks for the drag brace support fitting of the main landing gear (MLG) and corrosion prevention and control program (CPCP) related tasks are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate airworthiness limitations, including new inspection tasks for the drag brace support fitting of the MLG and to implement CPCP related tasks. We are issuing this AD to address the unsafe condition on these products.
2025-02-11: The FAA is adopting a new airworthiness directive (AD) for certain FS 2001 Corp, FS 2002 Corporation, FS 2003 Corporation, Piper, and Piper Aircraft, Inc. (Piper) airplanes. This AD was prompted by reports of broken rudders. This AD requires replacing any rudder equipped with a rudder post made from a certain carbon steel with a rudder equipped with a rudder post made from a certain low-alloy steel. The FAA is issuing this AD to address the unsafe condition on these products.
61-01-02: 61-01-02 MARTIN: Amdt. 239 Part 507 Federal Register January 5, 1961. Applies to All Models 202, 202A and 404 Aircraft With Main Landing Gear Torque Arms Having More Than 12,000 Hours' Time In Service. Compliance required as indicated. Failures of Model 404 main landing gear torque arms have occurred in the lower attachment point where the torque scissors attach to the strut. Also, a failure was found in the apex (upper to lower torque arm attach point). As a result, the following must be accomplished within the next 225 hours' time in service, unless already accomplished within the last 225 hours' time in service, and every 450 hours' time in service thereafter. Inspect all surfaces of the torque arm lugs which attach the torque scissors to the strut for cracks or corrosion, using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Beginning with the first repetitive inspection, also inspect all surfaces of the torque arm apex using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Removal of bolts and bushings is required only if dye penetrant is used. If cracks or corrosion are found, the torque arm must be replaced before the next flight. This directive effective January 6, 1961.
2015-06-02 R1: We are revising an airworthiness directive (AD) 2015-06-02 for GA 8 Airvan (Pty) Ltd Model GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as missing required engine mount fire seal washers, which could reduce the engine retention capability in the event of a fire. We are issuing this AD to require actions to address the unsafe condition on these products.
78-26-10 R1: 78-26-10 R1 GREAT LAKES: Amendment 39-3384 as amended by Amendment 39-5460. Applies to Models 2T-1A-1 and 2T-1A-2 airplanes. COMPLIANCE: Required as indicated unless already accomplished. To preclude contamination of cockpit heater air with carbon monoxide, accomplish the following: A) Within the next 25 hours time-in-service after the effective date of this AD: 1. Determine if the airplane is equipped with a P/N 50146 cockpit heater system and, if not, make an entry in the airplane's maintenance record that the airplane complies with Paragraph A)1 and that further compliance with this AD is not required. This determination and maintenance record entry may be made by the owner or holder of a valid pilot certificate. 2. If the airplane is equipped with a P/N 50146 cockpit heater system, prior to further flight, install a revision in the walk around inspection (Section II C. 2) of the Flight Manual adding an inspection of the exhaust system hanger (Figure1 of this AD). 3. If the airplane is equipped with a P/N 50146 cockpit heater system, prior to further flight, and within each 25 hours time-in-service thereafter: a) Remove the cowl to gain access to the engine installation. b) Disconnect the two cockpit air heater ducts from the heater shroud and remove the shroud. c) Visually inspect the support plates of the heat exchanger at both ends for cracks between the five tube cluster. d) If no cracks are found, return the heat exchanger to service. e) If cracks are found, either replace the heat exchanger system with an airworthy part or, in the alternative, comply with Paragraph B) of this AD. B) Remove the optional heat exchanger system and: 1) Install P/N 50126-1 stack assembly on all aircraft and P/N 50172-1 shield on aircraft equipped with IO-360-BIF6 and AEIO-360-BIG6 engines using QS100-M32W or equivalent clamps. 2) Block existing cockpit heat control valve in closed position by safety wiring control arm to adjacent aircraft structure. 3) Block the cockpit air supply opening in the left vertical engine cooling baffle per AC 43.13 1 and 2. 4) Remove Aircraft Flight Manual Revision specified in Paragraph A)2 of this AD (if installed). C) The actions and inspections specified in paragraphs A)2. and A)3. of this AD may be discontinued upon either removal of the P/N 50146 cockpit heater system per paragraph B) of this AD, or replacement of the P/N 50146 cockpit heater system with a different FAA approved cockpit heater system. D) Any equivalent method of compliance with this AD must be approved by the Manager, Boston Aircraft Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Great Lakes Aircraft Company (GLAC) Service Bulletin No. 9, dated November 17, 1978, or later revisions, pertain to portions of this subject. This amendment revises AD 78-26-10, Amendment 39-3384, which became effective January 4, 1979. This amendment, 39-5460, becomes effective on December 17, 1986. FIGURE 1 AIRPLANE FLIGHT MANUAL REVISION (AD 78-26-10 requires this revision to remain in the below designated airplane flight manual when the airplane is equipped with the optional P/N 50146 cockpit heater system. MODEL N S/N In addition to the presently specified preflight procedures, prior to each flight: 1. Inspect the left engine exhaust tail pipe hanger for deformation or failure. 2. If found failed, the hanger must be repaired prior to further flight.
98-05-12: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model ATP airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2015-14-07: We are adopting a new airworthiness directive (AD) for certain airplanes. This AD was prompted by reports of deficiencies in the flight control module (FCM) software. This AD requires installing certain FCM software. We are issuing this AD to correct deficiencies in the FCM software, which, if not corrected, could prevent continued safe flight and landing.
2015-14-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by an analysis, which indicated that in a limited flight envelope with specific conditions, divergent flutter could occur during a high g-load maneuver in combination with certain system failures. This AD requires replacing the lateral control electronic (LCE) modules, replacing the inboard elevator power control packages (PCPs), installing new external compensators for the PCPs, and revising the maintenance or inspection program. We are issuing this AD to prevent certain system failures from resulting in divergent flutter, and subsequent loss of continued safe flight and landing.
2001-26-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration, that requires, among other actions, modification of the main deck cargo door structure and fuselage structure; replacement of fasteners in the two door-side hinge elements; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
2001-26-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier; as applicable. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
98-05-01: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-366G1 helicopters, with certain main rotor head frequency adapters (frequency adapters) installed. This proposal requires inspecting the frequency adapter to determine if a certain frequency adapter is installed, and if so, removing and discarding the frequency adapter and replacing it with an airworthy frequency adapter before further flight. This amendment is prompted by a report of disbonding of the metal center section of a frequency adapter from the elastomer, caused by a lack of adherence during the production process. The actions specified by this AD are intended to prevent vibrations caused by disbonding of the center section of a frequency adapter from the elastomer, that could result in loss of control of the helicopter.
97-24-07: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes that have kit JK 2496 and modification JM 7537 installed. This action requires installing magnetic latching relays on the ignition system because of the auto-ignition system becoming disabled when switching from ground power to the airplane s internal power. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent loss of the airplane s internal power connection to the auto-ignition system, which could cause loss of engine power and possible loss of control of the airplane.