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2024-16-01: The FAA is superseding Airworthiness Directive (AD) 2000-18- 09, which applied to certain Bell Helicopter Textron, Inc. (now Bell Textron Inc.), Model 412, 412CF, and 412EP helicopters. AD 2000-18-09 required repetitively inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, depending on the results, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD was prompted by a report of a fatigue crack in a tail boom attachment cap angle. This AD retains the requirements of AD 2000-18-09, expands the applicability by adding models and an additional part-numbered cap angle, reduces the inspection intervals, and requires using updated procedures. This AD also updates the reporting requirement. The FAA is issuing this AD to address the unsafe condition on these products.
86-24-06: 86-24-06 BRITISH AEROSPACE: Amendment 39-5472. Applies to Models HP-137 MK 1 and Jetstream 200 Series (all serial numbers), and Model Jetstream 3101 (S/N 601-633, 635-646 and 648-654 inclusive) airplanes certificated in any category. Compliance: Required within 600 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent unacceptable aileron control vibration and aileron jamming, accomplish the following: (a) Inspect the special stud BAe P/N 13705E29 and nut BAe P/N A103-JT for tightness, visible thread length and punch marks, in accordance with Section 2. "Accomplishment Instructions" in BAe Mandatory S/B No. 27-JM-5257, dated June 6, 1986. (1) If the special stud and nut are secure, and the special stud end protrudes 1-1/2 to 2 threads beyond the nut and all three punch marks are visible, no further action is necessary. (2) If the special stud and nut are loose, or the special stud end does not protrude 1-1/2 to 2 threads beyond the nut, or all three punch marks are not visible, prior to further flight, remove aileron quadrant in accordance with Section 2. "Accomplishment Instructions," Paragraph B. "Removal/Installation" in BAe Mandatory S/B No. 27-JM-5257, dated June 6, 1986, and check the security of the nut P/N A103-JT securing the special stud P/N 13705E29 to the quadrant, and determine that peening of the stud is in accordance with the above BAe Service Bulletin. (i) If security and locking are satisfactory, prior to further flight, reinstall aileron control quadrant using steps (13) to (20) inclusive of the above Service Bulletin, and no further action is required. (ii) If the securing nut P/N A103-JT or special stud P/N 13705E29 is loose or the peening of the stud is not in accordance with the above BAe Service Bulletin, prior to further flight, remove and replace nut BAe P/N A103-JT with new nut BAe P/N RMTE 9868-6, install new stud BAe P/N 13705E91 and add splitpin SP90-C7 to lock the nut on, according to the instructions in BAe Mandatory S/B 27-JM-5257, dated June 6, 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to British Aerospace PLC., Manager, Product Support Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 2, 1987.
2024-16-06: The FAA is superseding Airworthiness Directive (AD) 2023-15- 07, which applied to all Air Tractor, Inc. (Air Tractor) Model AT-802 and AT-802A airplanes with Wipaire, Inc. Supplemental Type Certificate (STC) No. SA01795CH installed. AD 2023-15-07 required repetitively inspecting the left and right forward horizontal stabilizer spars for cracks, replacing any forward horizontal stabilizer spar found cracked, and reporting inspection results to the FAA. This AD requires repetitively inspecting the left and right, forward and rear, horizontal stabilizer spars for cracks at shorter intervals than those required by AD 2023-15-07, replacing any horizontal stabilizer spar found cracked or damaged, installing bathtub fittings, and reporting inspection results to the FAA. This AD was prompted by additional reports of cracks in the horizontal stabilizer spars and the need to incorporate a new finlet attach design on the horizontal stabilizer spars to reduce the cracking. The FAA is issuing this AD to address the unsafe condition on these products.
64-06-02: 64-06-02\tBOEING: Amdt 707 Part 507 Federal Register March 17, 1964. Applies to All Model 720 Series Aircraft with Pratt and Whitney JT3C-7 and JT3C-12 Turbojet Engines Installed. \n\n\tCompliance required as indicated. \n\n\tAs the result of the failure of the second and third stage compressor rotor disc spacer assemblies, P/N's 359411 and 359412, respectively, and resultant serious engine damage together with possible aircraft damage, accomplish the following: \n\n\t(a)\tFor spacer assemblies previously inspected by the procedure described in (c), reinspect in accordance with (c) as follows: \n\n\t\t(1)\tInspect spacer assemblies having 200 or more hours' time in service since the last inspection within 50 hours' time in service after the effective date of this AD, and within each 250 hours' time in service thereafter. \n\n\t\t(2)\tInspect spacer assemblies having less than 200 hours' time in service since last inspection prior to the accumulation of 250 hours' time in service and within each 250 hours' time in service thereafter. \n\n\t(b)\tFor spacer assemblies not previously inspected by the procedure described in (c), inspect in accordance with (c) as follows: \n\n\t\t(1)\tInspect spacer assemblies with 950 or more hours' time in service since last overhaul within the next 50 hours' time in service after the effective date of this AD, and every 250 hours' time in service thereafter. \n\n\t\t(2)\tInspect spacer assemblies with less than 950 hours' time in service since last overhaul prior to the accumulation of 1,000 hours' time in service since last overhaul and every 250 hours' time in service from the last inspection. \n\n\t(c)\tIncorporate an inspection hole and plug in the compressor case and second stage vane and shroud assembly and in the compressor case and third stage vane and shroud assembly in accordance with Pratt and Whitney Aircraft letter dated November 22, 1963, and its two enclosed sketches. Using an American Systoscope Markers Incorporated Model B-175-AS-15 or FAA approved equivalent viewing instrument inserted through these holes, inspect the second and third stage compressor rotor disc spacer assemblies for possible cracks in all the visible areas of each spacer. Give particular attention to the front and rear seal edges. If any cracks are found, remove the engine before further flight and disassemble for confirmation of the cracks. Replace any cracked spacer assemblies. \n\n\t(d)\tWhen P/N's 420145 and 429175 second and third stage compressor rotor disc spacer assemblies, respectively, are incorporated, the inspections prescribed by this AD are no longer required. \n\n\t(e)\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. \n\n\t(Pratt and Whitney Aircraft telegraphic message dated November 20, 1963, to Eastern Air Lines and Pratt and Whitney Aircraft letter dated November 22, 1963, and enclosed two sketches to all operators of JT3C-7 turbojet engines cover the same subject.) \n\n\tThis supersedes AD 63-26-01. \n\n\tThis directive effective March 17, 1964.
2017-12-09: We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145MP, -145EP, and -145XR airplanes. This AD was prompted by a report of chafing found between the fuel pump electrical harness and the fuel pump tubing during scheduled maintenance. This AD requires a detailed inspection for chafing on the electrical harness of each electrical fuel pump in the fuel tanks, replacement of the affected electrical fuel pump with a new or serviceable pump if necessary, and installation of clamps on the fuel pump electrical harnesses. We are issuing this AD to address the unsafe condition on these products.
2017-12-08: We are superseding Airworthiness Directive (AD) 2011-24-06 for all BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and - 300A airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes. AD 2011-24-06 required revising the maintenance program to incorporate life limits for certain items, adding new and more restrictive inspections to detect fatigue cracking in certain structures, and adding fuel system critical design configuration control limitations (CDCCLs) to prevent ignition sources in the fuel tanks. AD 2011-24-06 also required modifying the main fittings of the main landing gear (MLG) and revising the maintenance program to incorporate new life limits on MLG up-locks and door up-locks and other MLG components. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD was prompted by a determination that new or revised structural inspection requirements are necessary. We are issuing this AD to address the unsafe condition on these products.
2024-13-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report of heat damage on multiple engine inlets around the engine anti-ice (EAI) duct within the inlet aft compartment. This AD requires doing a records check and updating the operator's existing minimum equipment list (MEL), inspecting the left and right engine inlet cowl assembly for signs of heat damage around the EAI duct, installing or replacing the EAI duct seals, repairing any damage, and replacing the engine inlet if necessary. This AD also prohibits the installation of engine inlets under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
91-13-10 R1: 91-13-10 R1 BOEING: Amendment 39-8158. Docket No. 91-NM-241-AD. Revises AD 91-13-10, Amendment 39- 7041. \n\n\tApplicability: Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines; and Model 767 series airplanes equipped with Pratt and Whitney PW4000, General Electric CF6-80C2-B2F, or General Electric CF6- 80C2-B6F series engines; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\tTo prevent overspeed or uncommanded shutdown of an engine, accomplish the following:\n\n\t(a)\tFor Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines, and Model 767 series airplanes equipped with Pratt and Whitney PW4000 or General Electric CF6-80C2-B6F engines: Within 3 days after May 22, 1989 (the effective date of Amendment 39-6210), add the following to the Limitations Section of the FAA- approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t(b)\tWithin the next 24 months after August 12, 1991 (the effective date of this Amendment 39-7041), replace the EICAS computers in accordance with the appropriate service bulletin listed below. After replacement of the EICAS computers in accordance with the specified service bulletins, the AFM limitation required by paragraph (a) of this AD may be removed. \n\n\t\t(1)\tFor Model 747 series airplanes listed in Boeing Service Bulletin 747-31-2151, dated March 29, 1990. \n\n\t\t(2)\tFor Model 767 series airplanes equipped with Pratt and Whitney PW4000 engines listed in Boeing Service Bulletin 767-31-0033, Revision 1, dated September 27, 1990. \n\n\t\t(3)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B6F engines listed in Boeing Service Bulletin 767-31-0038, dated April 12, 1990. \n\n\t(c)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B2F engines: \n\n\t\t(1)\tWithin the next 3 days after the effective date of this AD, add the following to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t\t(2)\tWithin the next 24 months after the effective date of this AD, replace the EICAS computers in accordance with Boeing Service Bulletin 767-31-0038, dated April 12, 1990. After incorporation of the EICAS computers, the AFM limitation required by paragraph (c)(1) may be removed. \n\n\t(d)\tFor airplanes not subject to paragraph (b) or (c) of this AD, within the next 30 days after the effective date of this AD, remove the AFM limitation required by paragraph (a) of this AD. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance time, which provides anacceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(f)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(g)\tThe replacement requirements shall be done in accordance with the following Boeing Service Bulletins, which incorporate the following list of affected pages: \n\nService Bulletin\tRevision Level\t\tDate\t\t\tPages \n\n747-31-2151\nOriginal\t\nMarch 29, 1990\n1 - 10 \n767-31-0033\n1\nOriginal\t\nSeptember 27, 1990 May 31, 1990\n1, 2, 4, 5 \n3, 6, 7, 8, \n9, 10 \n767-31-0038\nOriginal\t\nApril 12, 1990\n1 - 8 \n\n\n\n\n\t\nThis incorporation by reference was approved by the Director of the Federal Register inaccordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.\n\n\t(h)\tAirworthiness Directive 91-13-10 superseded AD 89-10-06, Amendment 39-6210. \n\t(i)\tThis Airworthiness Directive 91-13-10 R1 revises AD 91-13-10, Amendment 39-7041.\n \t(j)\tThis amendment (39-8158, AD 91-13-10 R1) becomes effective on February 26, 1992.
2024-14-03: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with a certain configuration of the Garmin GFC 500 Autopilot System installed per Supplemental Type Certificate (STC) No. SA01866WI. This AD was prompted by a report of an un- commanded automatic pitch trim runaway when the autopilot was first engaged. This AD requires updating the applicable Garmin GFC 500 Autopilot System software for your airplane and prohibits installing earlier versions of that software. The FAA is issuing this AD to address the unsafe condition on these products.
2017-12-04: We are superseding airworthiness directive (AD) 2016-20-04 for Airbus Helicopters Model SA341G and SA342J helicopters. AD 2016-20-04 prohibited autorotation training flights until the landing gear rear crosstube (crosstube) was inspected. This new AD adds additional part- numbered crosstubes to the applicability and revises the hardness criteria for the inspection. This AD is prompted by a determination that an additional part-numbered crosstube may have the same unsafe condition. The actions of this AD are intended to detect and prevent an unsafe condition on these helicopters.