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2018-03-03: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A 421, 421A, 421B, 421C, and 425 airplanes. This AD requires repetitively inspecting the left and the right forward lower carry through spar cap for cracks and replacing the carry through spar if cracks are found. This AD was prompted by a report of a fully cracked lower forward carry through spar cap found on an affected airplane. We are issuing this AD to address the unsafe condition on these products.
2012-01-07: We are adopting a new airworthiness directive (AD) for BRP-- POWERTRAIN GMBH & CO KG Rotax 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD results from mandatory continuing airworthiness information (MCAI) originated 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 isolated manufacturing deviations reportedly found on the threads of a certain batch of fuel pressure regulators, part number (P/N) 887130, installed on Rotax 914 F series engines, which could result in fuel leakage during engine operation. We are issuing this AD to prevent fuel leaks, which could result in an in-flight fire and damage to the aircraft.
57-14-03: 57-14-03 VICKERS: Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. Investigation of a recent case resulting in asymmetric flaps occurring just prior to touchdown shows excessive end float of the flap torque shaft can occur between the flap gearbox and No. 1 flap unit port and starboard. Following action considered essential by Vickers with which the FAA concurs and considers mandatory. 1. At next daily inspection unscrew flap universal joint cap port and starboard and check engagement of trunnion blocks within universal joint body of the torque tube. With trunnion block journals facing fore and aft ensure maximum outboard float of torque shaft is obtained by gentle tapping if necessary. Where trunnion blocks do not protrude from body more than 0.4 of an inch, aircraft may continue to fly but corrective action (item 3.) must be taken within 300 hours flying. 2. If trunnion blocks protrude more than 0.4 of an inch, corrective action (item 3.) must be taken within 25 hours flying time, or if trunnion blocks protrude 0.52 of an inch or more, corrective action must be taken prior to further flight. 3. Set torque shaft with trunnion blocks flush with end of universal body and prepare and fit tubular fiber or fluon (teflon equivalent) distance piece to suit dimension between inboard vertical face of No. 1 flap unit chain box and adjacent end of torque tube. Internal diameter of distance piece 1.52 inches with suitable recess to clear greaser on chain box if necessary. Before removal, splined shaft must be marked to ensure correct reassembly. On completion of inspection torque tubes should be moved toward gearbox as far as end float permits.
2003-05-03: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires preflight checking and repetitively inspecting for a crack in certain tailbooms that have not been redesigned and replacing the tailboom if a crack is found; modifying and re-identifying certain tailbooms and installing an improved horizontal stabilizer assembly; and assigning a 5,000 hour time-in-service (TIS) life limit. This amendment is prompted by cracking discovered in other areas of certain tailbooms and introduction of a redesigned tailboom with a chemically milled skin, which does not require the current inspections. The actions specified by this AD are intended to prevent separation of the tailboom and subsequent loss of control of the helicopter.
2021-18-05: The FAA is superseding Airworthiness Directive (AD) 2020-15-12 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000 model turbofan engines. AD 2020-15-12 required initial and repetitive ultrasonic or visual inspections of the intermediate-pressure compressor (IPC) stage 1 rotor blade root (front face), IPC stage 2 rotor blade root (front and rear face), and IPC shaft stage 2 dovetail post (front face), and removal of any cracked parts from service. AD 2020-15-12 also required an inspection after asymmetric power and cabin depressurization events. This AD was prompted by IPC rotor blade separations resulting in engine failures. This AD requires initial and repetitive ultrasonic or visual inspections of certain IPC stage 1 rotor blade root, IPC stage 2 rotor blade root, and IPC shaft stage 2 dovetail posts until replacement of the IPC stage 1 and stage 2 rotor blades with redesigned IPC stage 1 and stage 2 rotor blades in kitted sets. The FAA is issuing this AD to address the unsafe condition on these products.
2003-05-04: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce Deutschland Ltd. & Co KG (RRD) Model Tay 620-15 and 650-15 turbofan engines. That AD currently requires initial and repetitive inspections of certain low pressure (LP) fuel tubes. This amendment requires the same inspections and adds two engine models to the applicability. This amendment is prompted by a report that certain Tay 611-8 and 651-54 turbofan engines may use the same LP fuel tube. The actions specified in this AD are intended to prevent a dual-engine flameout due to fuel exhaustion, which could lead to forced landing and possible damage to the airplane.
79-08-04 R2: 79-08-04 R2 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3448 as amended by Amendment 39-4097 is further amended by Amendment 39-5035. Applies to Lockheed-California Company L-1011-385 series airplanes certificated in all categories. To preclude failure of the main landing gear truck pivot pins, P/N 1523058-101 or -103, perform the following, unless already accomplished: (a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, or unless paragraph (b) or (c), below, has already been accomplished, perform a visual inspection of the open end inside surface of the truck pivot pins in accordance with Lockheed wire PSC/78-46863-OL, dated October 25, 1978. If there is a visual indication of a crack, the pin must be inspected before further flight in accordance with paragraph (b) of this AD, or replaced with a new pin. NOTE: For most reliable results, the above visual inspection should be conducted with a good source of lightand a mirror, and only after the open end inside surface is thoroughly cleaned of all accumulated dirt and grease. (b) Within the next 300 hours time in service after the effective date of this AD, unless already accomplished or unless paragraph (c) has already been accomplished, perform the ultrasonic inspection of the open end inside surfaces in accordance with Part I of Lockheed- California Company Service Bulletin 093-32-149, Revision 2. (1) If there is no ultrasonic indication or if it is not in excess of Standard (Reflector) "A", repeat the inspection at 300 hours time in service intervals until paragraph (c) is accomplished. (2) If there is an ultrasonic indication in excess of Standard (Reflector) "A", but less than one inch in the Standard (Reflector) "B" location repeat the inspection at 150 hours time in service intervals until paragraph (c) is accomplished. (3) If there is an ultrasonic indication in excess of one inch in the Standard (Reflector) "B" location remove the cracked pin and replace with like serviceable item before next flight. (c) Install landing gear truck pivot pin "fail-safe" retainer per Part 2 of Lockheed- California Company Service Bulletin 093-32-149, Revision 2 in accordance with the following schedule: (1) Within 1500 hours time in service from the effective date of this AD for all aircraft except as provided otherwise in paragraph (c)(2). (2) Within 2500 hours time in service from the effective date of this AD for aircraft which have been satisfactorily inspected per the requirement of Part 2 of Lockheed- California Company Service Bulletin 093-32-135. NOTE: The installation of the above "fail-safe" retainer is considered to be an interim safety action. (d) Within twelve (12) calendar months after the effective date of this AD, accomplish the installation or modification of the main landing gear uplock snubber, truck pivot pin and bushings using Kits 1630462-101, -103, -105, and -107, or alternate Kits 1630462-109, -111, - 113, and -115, in accordance with Lockheed-California L-1011 Service Bulletin 093-32-154, Revision 2, dated January 5, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Compliance with this paragraph constitutes terminating action for this AD. (e) Special 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 required by this AD. (f) Equivalent inspection procedures and truck pin retainer installation may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to the Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. Amendment 39-3448 became effective May 23, 1979. Amendment 39-4097 became effective May 22, 1981. This Amendment 39-5035 becomes effective May 13, 1985.
55-20-02: 55-20-02 DOUGLAS: Applies to All Douglas DC-7 Aircraft Serial Numbers 44122 to 44146 Inclusive, 44171 to 44174 Inclusive, 44261 to 44289 Inclusive and 44679 to 44684 Inclusive. \n\n\tCompliance required as soon as possible but not later than February 1, 1956. \n\n\tRevising the injection pump timing on the engines creates higher exhaust gas temperatures across the top surface of the wing along the left-hand side of the outboard nacelle. In order to reduce the wing skin temperature, an additional heat shield must be installed between the center and rear spars, and replace the aft section of the existing heat shields between the front and center spars adjacent to the upper left side of the outboard nacelle in the exhaust path area. \n\n\t(Douglas Service Bulletin DC-7 No. 77 dated July 1, 1955, covers this same subject.)
2003-05-02: This amendment adopts a new airworthiness directive (AD) that applies to all aircraft (specifically balloons) that incorporate certain Lindstrand Balloons Ltd (Lindstrand) fuel hoses. This AD requires you to inspect for certain batches of installed fuel hoses and replace any of these fuel hoses. 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 detect and replace defective fuel hoses before they result in propane fuel leaks. Such propane fuel leaks could lead to a propane fuel fire.
70-22-04: 70-22-04 WOOD ELECTRIC: Amdt. 39-1096 as amended by Amendment 39-1207. Applies to Aircraft Incorporating Wood Electric Corp Model 105, 106, 107, 108, 147, 152, 254, 447, 448, or 2100 series circuit breakers. Compliance required as indicated: (a) Within the next 500 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 750 hours' time in service from the last check; to detect jammed circuit breakers, manually open and close all Wood Electric Corp. Model 105, 106, 107, 108, 147, 152, 254, 447, 448, and 2100 series circuit breakers installed in aircraft. All circuit breakers found jammed must be replaced prior to further flight. This check is not required when the modification in Paragraph (b) has been accomplished. (b) Within the next 1250 hours' time in service after the effective date of this AD, unless already accomplished, modify all Wood ElectricCorp. 105, 106, 107, 108, 147, 152, 254, 447, 448 and 2100 series circuit breakers by installing a ring manufactured in accordance with Wood Electric Corp. Drawing Number 64-008 Rev. No. 2 dated June 26, 1970 or later revision or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. To accomplish the modification, position the circuit breaker in either the closed or opened position and place the ring below the step (cap) portion of the button and above the threaded mounting neck of the circuit breaker. Exert enough finger pressure to snap the ring into place. Manually open and close the circuit breaker to insure proper positioning of the ring. (c) Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) The check required by this AD may be performed by the pilot and the modification required by this AD constitutes preventive maintenance and may be performed by persons authorized to perform preventive maintenance under FAR 43. (Wood Electric Corp. Drawing Number 99-001 Rev. 1 dated June 26, 1970; Boeing Model 707/720 Service Bulletin 2693 Rev. 3 dated July 1, 1970; Boeing Model 727 Service Bulletin 24-35 Rev. 3 dated July 1, 1970 and Boeing Model 737 Service Bulletin 24-1019 Rev. 3 dated July 20, 1970 pertain to the modification required by this AD.) Amendment 39-1096 was effective November 4, 1970. This Amendment 39-1207 is effective May 19, 1971.
82-05-05 R1: 82-05-05 R1 FAIRCHILD SWEARINGEN: Amendment 39-4369. Applies to Models SA227-AC (S/N's AC-420 through AC-481, AC-485 through AC-491, AC-496 through AC-499 and AC-503), SA227-AT (S/N's AT-423 through AT-446, AT-454 through AT-487 and AT- 501), and SA227-TT (S/N's TT-421 through TT-462, TT-468 through TT-480 and TT-486 and TT-426A, TT-444A, TT-456A, TT-459A, TT-462A, TT-468A, TT-477A, TT-483A, TT-486A, and TT-489A) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent propeller ice accumulation and potentially hazardous severe aircraft vibration, within the next five hours time-in-service after the effective date of this AD accomplish the following: a) Install black electrician's tape or equivalent over the words "AND ICING CONDITIONS" in the Approved Types of Operations Section of the Operating Limitations Placard which is located above the left side console. b) Install a temporary placard of 1/4-inch minimum lettering which states "NOT APPROVED FOR FLIGHT IN ICING" in front of and in clear view of the pilot and operate the airplane in accordance with this placard. c) In the Approved Types of Operation Section of the Operating Limitations placard shown in Section I, Limitations Section, of the Model SA227-AC Airplane Flight Manual (AFM) and in Section II, Limitation Section, of the Models SA227-AT and -TT AFM, delete or cover the words "AND ICING CONDITIONS." d) The placard and AFM changes required by this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person who must make the prescribed entry in the Airplane Maintenance Records indicating compliance with this AD. e) An equivalent method of compliance with this AD may be used when approved by the Chief, Aircraft Certification Division, FAA, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. The procedures contained in Fairchild Swearingen SA227 Series Alert Service Bulletin SB A 61-002 PROPELLERS-LEADING EDGE PROTECTION dated February 26, 1982, if accomplished in entirety are approved as an equivalent method of compliance with this AD. This amendment becomes effective on May 3, 1982, to all persons except those to whom it has already been made effective by a priority letter from the FAA dated February 26, 1982, and is identified as AD 82-05-05.
2003-05-01: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of WSK PZL-Rzeszow S.A. Franklin 6A-350-C1, -C1A, -C1L, -C2, -C2A, and 4A- 235 series reciprocating engines. This action requires removing diaphragm type AC4886 fuel pump, AC part number (P/N) 5656774, PZL P/N 26.11.1710, before further flight, and prohibits installing diaphragm type AC4886 fuel pump, AC P/N 5656774, PZL P/N 26.11.1710. This amendment is prompted by several reports of failures of the valves and diaphragms in certain diaphragm type AC4886 fuel pumps, AC P/N 5656774, PZL P/N 26.11.1710, and adds the 6A-350-C1R engine to the applicability. The actions specified by this AD are intended to prevent reduction or loss of engine power or external fuel leaks.
2003-04-27: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier CL-600-2C10 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate functional and operational checks of the active and standby actuators of the rudder travel limiter (RTL) system. The actions specified by this AD are intended to prevent a significant latent failure in the RTL, which could lead to a critical loss of RTL function under certain conditions, and consequent loss of controllability of the airplane or structural damage. This action is intended to address the identified unsafe condition.
69-03-03: 69-03-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-719. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance required as indicated, unless already accomplished. To prevent possible jamming of aileron controls due to the aileron tab filler and modification plate assembly block, Part Number AB11/A1303 or AK11/A499, coming loose and fouling between the aileron and the wing structure, accomplish the following: (a) Within 75 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 150 hours' time in service from the last inspection, inspect the right and left aileron tabs for proper bonding within the tab structure of the filler and modification plate assembly P/N AB11/A1303 or AK11/A499 in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin No. 57-A-PM 3793, Issue 2, or later ARB-approved issue or FAA- approved equivalent. (b) If the filler and modification plate assembly is found to be loose during the inspection required by paragraph (a), before next flight, remove the assembly completely, and re- install the modification plate in accordance with BAC Modification No. 3793. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the existing filler and modification plate assembly is permanently secured by the addition of a 1/8" diameter blind rivet or after the incorporation of BAC Modification No. 3793. This amendment becomes effective February 14, 1969.
98-09-10: This amendment adopts a new airworthiness directive (AD) that applies to all EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300 and EA-300S airplanes. This AD requires inspecting the rudder control cables to assure that correctly swaged Nicopress type sleeves are installed at each end of the cables, and replacing any cable assembly where correctly swaged Nicopress type sleeves are not installed. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent a control cable from pulling through an incorrectly swaged sleeve, which could result in loss of rudder control with consequent loss of control of the airplane.
2011-27-51: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. This AD was prompted by reports of the elevator bob-weight (stabilizer weight) traveling past its stop bolt, which allowed the attaching linkage to move over-center, resulting in reduced nose down elevator control, which could result in loss of control of the airplane. We are issuing this AD to detect and correct conditions that could result in reduced nose down elevator control and loss of control of the airplane.
2003-04-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires you to inspect the alternating current (AC) inverter and modify the AC inverter and inverter sync wire shield. This AD is the result of reports that electrical noise causes the inverter to shut down in flight with loss of AC-powered flight instruments. The actions specified by this AD are intended to prevent electrical noise causing the inverter to shut down, which could result in failure of key aircraft electrical systems. Such failure could lead to loss of flight instruments during flight.
55-15-06: 55-15-06 LOCKHEED: Applies to 049, 149 Aircraft, Serial Numbers 1963 Through 1980, 2021 Through 2088; 649-749 Aircraft, Serial Numbers 2503 Through 2590, 2610, 2611, 2614 Through 2618; 1049C Aircraft, Serial Numbers 4501 Through 4548; 1049E Aircraft, Serial Numbers 4549 Through 4555, 4558, 4559, and 4563 Through 4565; 1049D Aircraft, Serial Numbers 4163 Through 4166. Compliance required by April 1, 1956, for Model 1049 aircraft and October 1, 1956, for Models 049/149 and 649/749 aircraft. To improve the fire-resistance integrity of the above aircraft, revisions to the system supplying cooling air to the accessory section of the powerplant installation are considered necessary. For 049-149 aircraft and 649-749 aircraft, the revision consists of installing a shutoff valve in a fireproof duct. For the 1049C and E aircraft, the revision consists of replacing a section of aluminum duct between the oil cooler scoop, and the existing shutoff valve, with a fireproof duct. This section is in zone 1, and provides a possible zone 1 to zone 2 firepath. Lockheed Service Bulletins 49/718, for 049/149 aircraft; 1049/2384, for 1049 aircraft; and 49/391A, for 649-749 aircraft, cover these subjects.
98-08-21: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB10 and TB200 airplanes. This AD requires inspecting the wing rear attachment fittings for cracks, replacing any cracked fitting, and incorporating wing rear attachment fitting reinforcement kits. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing rear attachment fittings caused by cracks in this area, which could result in the wing separating from the airplane if the airplane is operated with cracked wing rear attachment fittings over an extended period of time.
2003-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections for discrepancies of the internal fuselage skin panels located in the stub wing areas; and corrective action if necessary. This action is necessary to detect and correct heat damage to the fuselage skin panels caused by the leakage of hot air from one of the bleed air ducts inside the stub wing, which could result in reduced structural integrity of the engine support structure. This action is intended to address the identified unsafe condition.
2002-25-51: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-25-51, sent previously to all known U.S. owners and operators of the specified Agusta S.p.A. (Agusta) helicopters by individual letters. This Airworthiness Directive (AD) requires reducing the tail rotor (T/R) blade life limit and modifying and re-identifying the T/R hub and grip assembly. It also clarifies the never-exceed speed (Vne) restrictions and modifies the T/R visual inspection intervals. The actions specified by this AD are intended to prevent fatigue failure of the T/R blade and subsequent loss of control of the helicopter.
2003-04-13: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocoper) Model SA341G and SA342J helicopters. This action requires modifying an electric hoist (hoist) junction box (junction box). This amendment is prompted by the discovery of an anomaly affecting the resistor that is located in the junction box. The actions specified in this AD are intended to prevent failure of the hoist emergency load jettison switch, resulting in an inability of the pilot to cut the rescue hoist cable in the event of cable entanglement or other emergency and subsequent loss of control of the helicopter.
98-08-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires installing aluminum bonding bushings over certain screws in certain fuel tank underwing access panels. Several reports from the field revealing fuel tank access panels insufficiently electrically bonded to the airframe prompted this action. The actions specified by this AD are intended to prevent electrical arcing in the fuel tanks and detonation of the fuel-air mixture, which can be created by poor electrical bonding of fuel tank underwing access panels, and could result in a fire on the airplane.
98-08-27: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires modifying the airplane's left-hand (LH) front side lower panel. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent interference between the side trim of the LH front side lower panel and the roll control compass on the LH wheel assembly, which could result in loss of directional control of the airplane.
56-09-02: 56-09-02 MARTIN: Applies to All Models 202, 202A, and 404 Aircraft. Compliance required by September 1, 1956. In order to eliminate shearing of rivets securing the rudder torque tube flange, P/N 2021U42196, to the rudder torque tube, P/N 2021D19331, caused by gust buffeting with gust locks not engaged and resulting in loss of adequate and/or positive rudder control, it is necessary to replace the 3/16-inch rivets with 1/4-inch 24ST heat treated rivets. (Martin Service Instruction Letters No. 202/202A-36 and No. 404-69 cover this same subject.)