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86-18-10: 86-18-10 PIPER AIRCRAFT CORPORATION: Amendment 39-5446. Applies to Model PA-42-1000 (S/N's 42-5527002 through 42-5527033) airplanes certificated in any category. Compliance: Required within the next 10 hours time in service after receipt of this AD, unless already accomplished. To prevent loss of power and wing damage accomplish the following: (a) Fabricate a checking device from 3/8 inch O.D. polyethylene plastic tubing, 48 inches in length with a wall thickness of approximately 0.060 inches. NOTE 1: Polyethylene tubing is used in plumbing and air conditioning installations and may be found in hardware stores. Other types of plastic tubing may not work due to friction buildup. (b) Chamfer the end of the tube which will be inserted into the vent lines. Mark the tube at a point 40 inches from the chamfered end. (c) Remove the vent well covers located on top of the left and the right wing tip tanks. (d) Insert the checking device into each wingtip tank vent line up to the 40 inch mark. (e) If the checking device can be inserted to the 40 inch mark, the vent line is clear. Reinstall the vent well covers. No further action is required. (f) If the checking device cannot be inserted to the 40 inch mark, prior to further flight: (1) Drain the fuel from the airplane on the affected side(s). (2) Remove the forward outboard access cover from the bottom of the left and/or right wing(s) as required. (3) Visually inspect the affected tip tank vent lines for blockage or deformation. (4) Remove the fuel cap on the affected tip tank(s), depress the antisiphon flapper valve and using a light and mirror, visually inspect the upper portion of the wing tip tanks fuel vent line for blockage or deformation. (5) Replace any lines found blocked or deformed. (6) Reinstall the wing access plates with the sealant specified in the airplane maintenance instructions. (7) Fuel the airplane and check for leaks. NOTE 2: Piper Telex Service Bulletin No. 846, dated August 26, 1986, applies to the subject of this AD. (g) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (h) Within five (5) days of accomplishing this AD, report, in writing, all defects found during accomplishment of this AD to the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, GA 30337. (Reporting approved by the Offices of Management and Budget under OMB No. 2120-0056.) (i) An alternate method of compliance which provides an equivalent level of safety, may be approved by the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Thisamendment becomes effective on October 27, 1986, to all persons except those to whom it has already been made effective by priority letter from the FAA dated September 4, 1986, and is identified as AD 86-18-10.
2020-21-03: The FAA is superseding Airworthiness Directive (AD) 2015-14- 01, which applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2015-14-01 required a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. This AD retains the inspections of AD 2015-14-01 and adds airplanes to the applicability. For all airplanes, this AD also requires a modification of the door crank handle, which will terminate the inspection requirements. This AD was prompted by reports of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft, and of sealant missing from these bolts on another translating door. The FAA is issuing this AD to address the unsafe condition on these products.
81-10-07: 81-10-07 BELL HELICOPTER TEXTRON (BHT): Amendment 39-4108. Applies to all Model 212 series helicopters which have swashplate support part number (P/N) 204-011-404- 017 installed (Airworthiness Docket No. 81-ASW-18). To prevent possible loss of main rotor control, accomplish the following: (a) Within the next 10 flight hours following the effective date of this AD and continuing at intervals not to exceed 10 flight hours, thoroughly clean the 204-011-404-017 swashplate support-to-gimbal-ring attachment lugs. Using an inspection mirror and flashlight, inspect the lugs for cracks. Particular attention should be given to both inner attachment lugs. If a crack is found, remove and replace the swashplate support. (b) The inspection is not required after swashplate support P/N 204-011-404-017 is replaced with P/N 204-011-404-121. (c) Effective June 1, 1981, the retirement life of swashplate support P/N 204-011- 404-017 is reduced from 1,000 flight hours to 400 flight hours when used on the Model 212 helicopter. The new retirement life shall be recorded on the appropriate helicopter maintenance record. (d) Prior to April 30, 1982, all swashplate support assemblies P/N 204-011-404-017 on Bell Model 212 helicopters must be replaced with P/N 204-011-404-121. (e) Bell Helicopter Textron Alert Service Bulletin 212-81-22 applies for inspection techniques and areas to be inspected. Note: Swashplate supports P/N 204-011-404-017 may have been installed on Model 204 or 205 helicopters and subsequently removed and installed on Model 212 helicopters. For those parts having such a history, determine the equivalent hours as follows: Take the time the part has been installed on a Model 204 or 205 helicopter and divide this time by 2.5; to this result, add the time the part has been on a Model 212 helicopter. The answer is the equivalent hours on the part, and this number must not exceed 400 hours. (f) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (g) In accordance with FAR 21.197, flight is permitted to a base where the inspection and repairs required by this AD may be accomplished. This amendment becomes effective May 14, 1981.
2003-21-09: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. The existing AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass; and certain inspections of the lubrication pump (pump) and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that a before a MGB or pump with any time-in-service (TIS) can be installed, it must meet the AD requirements. This amendment requires the same actions as the existing AD but corrects the wording to state that the check of the chip detector is for sludge rather than metal particles. This amendment is prompted by the need to correct the wording because the term "metal particles" may be misleading. The actions specified by this AD are intended to detect sludge on the chip detector, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter.
94-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Precision Airmotive Corporation (formerly Facet Aerospace Products and Marvel-Schebler) Model HA-6 series carburetors, that requires a modification in those carburetors not equipped with a mixture control retainer clip. This amendment is prompted by eight reports of excessive retention screw wear causing rough engine operation or engine power loss on engines equipped with a Model HA-6 series carburetor between January 1986 and August 1992. The actions specified by this AD are intended to prevent the interruption of fuel flow to the engine caused by the mixture control shaft moving out of position because of excessive wear of the mixture control shaft retention screw.
2020-21-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that the latches for the forward and aft pressure relief doors could be opened during exposure to fire, leading to a breach in the engine core firewall. This AD requires modification and re-identification of the affected thrust reversers (TRs) and latch access doors (LADs), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
60-10-03: 60-10-03\tBOEING: Amdt. 144 Part 507 Federal Register May 7, 1960. Applies to the following 707 series aircraft only: Serial Numbers 17586 through 17596, 17609 through 17612, 17628 through 17648, 17658 through 17672, 17696 through 17702, 17925 through 17927. \n\tCompliance required as indicated. \n\n\tAs a result of one known incident wherein aggravated dutch roll was experienced due to improper rigging of the outboard aileron balance tab, the following modifications shall be accomplished: \n\n\tUnless already accomplished, prior to July 1, 1960: \n\n\t(a)\tReplace aileron quadrant rod assembly P/N 90-2480-3001 with redesigned rod assembly P/N 69-10829 (LH and RH side). \n\n\t(b)\tReplace support channel P/N 6-83872-2000 located on beam installation P/N 9- 65133 (aileron lockout crank) with new channel P/N 69-10833. Adjust stop in accordance with maintenance manual procedure. \n\n\t(c)\tRevise rigging of outboard aileron balance tab to 1.5 degrees (plus-minus 0.5 degrees) down with the aileron in the neutral position. \n\n\t(Boeing Service Bulletin No. 583 dated September 24, 1959, pertains to this same subject.)
83-19-01: 83-19-01 PIPER: Amendment 39-4727. Applies to Model PA-38-112 (S/Ns 38-78A0001 thru 38-82A0122) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible inflight failure of the fin and stabilizer attachment because of fatigue damage, accomplish the following: a) Within the next 25 hours time-in-service on airplanes that have 500 or more hours time-in-service on the effective date of this AD, or upon the accumulation of 525 hours time-in-service on airplanes that have less than 500 hours time-in-service on the effective date of this AD, and at intervals not exceeding 100 hours time-in-service thereafter: 1) Inspect and, if necessary, repair or modify the forward and aft fin spars in accordance with the directions and criteria contained in the INSTRUCTIONS section of Piper Service Bulletin No. 763A dated July 25, 1983. b) The repetitive inspections required by this AD may be discontinued upon the incorporation of Piper Kit No. 764 965. c) The interval between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, FAA, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. This amendment becomes effective on September 29, 1983.
80-11-08: 80-11-08 BOEING VERTOL (VERTOL): Amendment 39-3778. Applies to Vertol Model 107-II helicopters with pilot or copilot cyclic stick boots, P/Ns 107S2226-9, -13 or -17, certificated in all categories. To prevent possible restriction of cyclic stick travel accomplish the following within the next 25 hours in service after the effective date of this AD, unless already accomplished. a. Loosen the velcro tape and camloc fasteners securing the pilot and copilot cyclic stick boots, P/N 107S2226-9, -13 or -17, and remove the boots. b. Remove the two rivets which attach the forward spring, P/N 107S2226-12, to the forward end of the boot base and discard the forward spring. c. Install washers and new rivets to plug the resulting two empty holes in the boot base. d. Reinstall the pilot and copilot stick boots. e. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective May 28, 1980.
2009-12-16: We are superseding an existing airworthiness directive (AD) for the products listed above. 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: The manufacturer reported findings of missing primer on the internal of the elevator and rudder of aircraft S/N 8200. The aircraft S/N 8200 was with RUAG for maintenance purposes. Investigation performed by RUAG showed that the paint removal procedure for the rudder and elevator was changed from a paint stripping with brush and scraper to a procedure where the parts were submerged in a tank filled with hot liquid stripper. The stripper is called TURCO 5669 from Henkel Surface Technologies. The stripping process is described in the Technical Process Bulletin No. 238799 dated 09/01/1999. This paint stripping process change was not communicated to andnot approved by the TC-Holder. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-21-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that sticking effects have been observed affecting the breathing bag on certain passenger oxygen masks. This AD requires replacement of affected passenger oxygen masks, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
83-06-01: 83-06-01 BOEING: Amendment 39-4589. Applies to Boeing Model 767 Series Airplanes certificated in all categories. To prevent loss of engine throttle control due to power lever cable icing, accomplish the following within 30 days from the effective date of this AD, unless already accomplished. \n\tA.\tInstall ice shields on the number 6 and 7 slats per Boeing Service Bulletin 767-30-2, dated December 13, 1982, or later FAA approved revision. \n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\tC.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThis amendment becomes effective April 4, 1983.
2003-21-07: The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. This AD is the result of analysis that reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
94-24-06: This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Corporate Jets Model BH/HS 125-600A and -700A series airplanes, that requires installation of two new circuit breakers in the 6 volt output circuits of the flight deck lighting transformers on electrical Panel 'RY,' below the right pilot's seat. This amendment is prompted by a report of smoke in the flight deck due to a lighting transformer 6 volt output circuit short circuiting to ground. The actions specified by this AD are intended to prevent smoke or fire in the flight deck due to inadequate circuit protection for 6 volt circuits of the flight deck lighting transformer.
61-20-01: 61-20-01 AUTO CRAT MANUFACTURING COMPANY SAFETY BELT: Amdt. 341 Part 507 Federal Register September 23, 1961. Applies to All Aircraft Equipped With Auto Crat Model BN 1-1700 Series Safety Belts. Compliance required within the next 25 hours' time in service after the effective date of this AD. It has been determined by static test that the Auto Crat safety belt Model BN 1-1700 assemblies manufactured under Technical Standard Order C22 standards do not meet the minimum strength requirements of this TSO. Accordingly, these belt assemblies must either be replaced with belt assemblies that conform to TSO-C22 standards, or be reworked to incorporate a steel frame buckle BN 1-2000AW supplied by Auto Crat, or equivalent. When this steel frame buckle is installed, the modified belt assembly becomes Model BN 1-2000, which meets the TSO requirements and shall be marked with the new model number. (Auto Crat letters to various air carriers dated May 10, 1961, pertains to the same subject.) This directive effective October 24, 1961.
2020-20-09: The FAA is superseding Airworthiness Directives (ADs) 2015-14- 07, 2016-07-10, and 2016-24-09. AD 2015-14-07 applied to certain The Boeing Company Model 787-8 airplanes. AD 2016-07-10 and AD 2016-24-09 applied to all The Boeing Company Model 787-8 and 787-9 airplanes. ADs 2015-14-07, 2016-07-10, and 2016-24-09 required actions related to certain flight control module (FCM) software. This AD requires installing flight control electronics (FCE) common block point 5 (CBP5) software, which terminates the requirements of the ADs superseded by this AD. This AD was prompted by certain deficiencies in the FCM software, including a report of an unannunciated dual symmetric inboard slat skew. The FAA is issuing this AD to address the unsafe condition on these products.
2003-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect the right inboard forward flap bell crank for cracks, deformation, and missing/incomplete welds. If cracks, deformation, or missing/incomplete welds are found, the AD would require you to immediately replace the flap bell crank or temporarily incorporate certain flap limitations. This AD is the result of reports of cracks and missing/incomplete welds in the right inboard forward flap bell crank. We are issuing this AD to prevent failure of the right inboard forward flap bell crank due to cracks, deformation, or missing/ incomplete welds. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
61-25-01: 61-25-01 CESSNA: Amdt. 376 Part 507 Federal Register December 9, 1961. Applies to All Models 120, 140, and 140A Aircraft, On Which A Met-Co-Aire Tricycle Landing Gear (STC SA4-916) Has Been Installed. Compliance required as indicated. To correct an unsafe condition in the main gear the following shall be accomplished: (a) Within 20 hours' time in service after the effective date of this AD and at periods thereafter not to exceed 100 hours' time in service: (1) Tighten and torque to 50-70 inch-pounds the four AN 4 bolts (two on each side) which extend through the Cessna main gear wedges and the Met-Co-Aire support plate, P/N RD-1001C-11. Care should be taken to insure that the AN 365 stop nuts have not bottomed on the bolt threads before adequately tightening the wedge in place as specified above; use metal washers under the nut or bolt heads as necessary. (2) Conduct a close visual inspection for cracks in the corners of the slots in the support plate, P/N RD-1001C-11, and in the attach plate. Parts exhibiting evidence of cracks shall be replaced with Met-Co-Aire P/N RD-1001C-6 or FAA approved equivalent. When a new part is installed, the repetitive inspection prescribed in this subparagraph may be discontinued. (b) Within 20 hours' time in service after the effective date of this AD: (1) Inspect the attachment of the top flanges of the bulkheads in the landing gear attachment box and perform such work as necessary to assure that all rivets which secure the box to the floor structure are properly installed. Refer to Met-Co-Aire installation instructions dated August 29, 1959, as revised January 1, 1961, for description and location of necessary rivets. (2) If installed, remove the adapter plates, Cessna P/N 0441147, which may have been used to extend the main gear wheels forward. (Met-Co-Aire Service Directive SD-1003 covers this same subject.) This directive effective December 20, 1961.
81-13-09 R2: 81-13-09 R2 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-4175 as amended by Amendment 39-4280. Applies to Models AS350 and AS355 Series Helicopters, certificated in all categories, that are equipped with tail rotor blade pitch horns, P/N 350A12-1368-01 or -02 (Airworthiness Docket No. 81-ASW-28). Compliance required as indicated. To detect possible cracks and prevent failure of the tail rotor blade pitch horns, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, unless already accomplished per Aerospatiale Telex Service No. 01.07A dated June 5, 1981, remove each pitch horn, clean and remove paint, inspect for flatness and inspect for cracks as specified in Aerospatiale Telex Service No. 01.07A. (b) Replace horns before further flight if not flat or if cracked. (c) Serviceable pitch horns that comply with this AD must be reinstalled as specified in the Aerospatiale Telex Service No. 01.07A. (d) For pitch horns, P/N 350A-12-1368-01, after initial compliance with paragraphs (a) and (c) of this AD and prior to the first flight of each day, conduct the following: (1) Clean thoroughly, the surface of each horn at the two-mounting bolts. (2) Inspect each horn for cracks using a five power or higher magnifying glass and light in the area of the mounting bolt countersink or spotface and adjacent radii of the yoke. (3) If a crack is found, remove the affected horn prior to further flight and install a serviceable horn as specified in paragraph (c) of this AD. (e) Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (f) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to fly aircraft to a base where paragraphs (a) through (c) of this AD can be accomplished. (g) For pitch horns, P/N 350A12-1368-01, accomplish the following: (1) Horns with 400 hours' or more total time in service on July 31, 1981, remove from service within the next 50 hours' time in service. (2) Horns with less than 400 hours' total time in service on July 31, 1981, remove from service before attaining 450 hours' total time in service. (h) For pitch horns, P/N 350A-12-1368-02, remove from service on or before attaining 1,250 hours' total time in service. (i) AS350 Service Bulletin No. 01.07 Revision 2 and AS355 Service Bulletin No. 01.01 Revision 1 may be used instead of TELEX Service No. 01.07A. (Aerospatiale Telex Service No. 01.07B dated June 30, 1981, pertains to the 450 hour' limit.) Amendment 39-4175 became effective July 31, 1981, to all persons including those persons to whom it was made effective by priority mail AD No. 81-13-09 issued June 16, 1981, and to whom part of the amendment was made effective by priority mail AD 81-13-09 issued June 16, 1981. This amendment 39-4280 becomes effective December 18, 1981.
2020-20-16: The FAA is superseding Airworthiness Directive (AD) 2018-17- 05, which applied to all Airbus SAS \n\n((Page 63435)) \n\nModel A350-941 and -1041 airplanes. AD 2018-17-05 required a check of the insulation resistance of the direct drive solenoid valve (DDSOV) of each affected electro-hydrostatic actuator (EHA) and applicable corrective actions. Since the FAA issued AD 2018-17-05, it was determined that certain EHA part numbers can be modified and re- identified as specified in a European Union Aviation Safety Agency (EASA) AD, which could inadvertently remove certain part numbers from the applicability in other EHA-related ADs including AD 2018-17-05. This AD was prompted by reports of EHA units that were returned to the manufacturer with degraded insulation resistance in the DDSOV; investigation results revealed that moisture ingress, due to incorrect sealing application, had caused this degradation. This AD was also prompted by a report of a technical issue detected on EHAs installed on inboard ailerons and elevators, causing potential erroneous monitoring of those actuators. This AD requires a check of the insulation resistance of the DDSOV of each affected EHA and applicable corrective actions, and modification or replacement of certain EHAs; as specified in two EASA ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-20-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, AS350B3, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting the main rotor (M/R) servo actuators, and depending on the inspection results, replacing the affected part, applying a slippage mark, and reporting information. This AD was prompted by an incident of a sudden, strong nose-up attitude followed by intensive vibrations and increased loads on the flight controls during a cruise flight. The actions of this AD are intended to address an unsafe condition on these products.
2003-21-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment requires a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed-through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The actions specified by this AD are intended to prevent the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit. This action is intended to address the identified unsafe condition.
80-21-01: 80-21-01 MCDONNELL DOUGLAS: Amendment 39-3933. Applies to DC-10 Series Airplanes fuselage numbers 1 through 243. \n\n\tCompliance required as indicated, unless already accomplished. To prevent restriction of travel of the wing and tail engine fuel shutoff valve, thereby adversely affecting operation of the engine emergency fire shutoff handles and loss of associated fire fighting safeguards, accomplish the following: \n\n\t(a)\tWithin 300 hours additional time in service after the effective date of this AD replace P/N AA 2603 type cable guard pins in accordance with McDonnell Douglas Alert Service Bulletin A76-28 as dated September 8, 1980. \n\n\t(b)\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 modifications required by this AD. \n\n\t(c)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective October 13, 1980.
94-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, KC-10A (military) airplanes, and Model MD-11 series airplanes, that requires the installation of retainers and supports at the lateral control mixer bracket on the center of the wing rear spar of the airplane. This amendment is prompted by an analysis conducted by the manufacturer, which revealed that failure of a lateral control mixer bracket could result in uncommanded deployment of the spoiler. The actions specified by this AD are intended to prevent inadvertent asymmetric deployment of the spoiler, which may lead to reduced controllability of the airplane.
2021-10-17: The FAA is adopting a new airworthiness directive (AD) for certain Mooney International Corporation (Mooney) Model M20V airplanes. This AD was prompted by reports of short circuit and arcing of the alternator main power cable in the engine compartment. This condition, if unaddressed, could result in a fire hazard, loss of engine thrust control, and reduced control of the airplane. This AD requires inspecting the alternator main power cable and the exhaust crossover tube for damage, replacing damaged parts as necessary, and installing an additional alternator cable clamp. The FAA is issuing this AD to address the unsafe condition on these products.