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61-11-01: 61-11-01 BRANTLY: Amdt. 288 Part 507 Federal Register May 23, 1961. Applies to All B-2 Helicopters. \n\n\tCompliance required within the next 10 hours' time in service after effective date of this directive. \tA failure in the skid landing gear drag brace rod end bearing (Kahr Bearing Co. P/N HE-3SFN) occurred during ground handling resulting in collapse of the landing gear. This failure occurred through the area of the lubrication fitting. \n\n\tTo preclude the possibility of additional failures, check the shoulder dimension of the two (2) Kahr P/N HE-3SFN rod end bearings at the forward ends of the Brantly P/N B2-259-1 and B2-259-2 landing gear drag struts. If the dimension shown in the sketch is less than 0.5 inch, the part must be replaced before further flight with a new bearing, Brantly P/N B2-259-11, or an FAA approved equivalent. \n\n\n\n\t(Brantly Service Bulletin No. 11 covers this subject. NOTE: Service Bulletin No. 11 refers to P/N B2-259-11 as "new type.") \n\n\tThis directive effective May 31, 1961.
2020-05-28: The FAA is superseding Airworthiness Directive (AD) 2019-11-08 for all International Aero Engines, LLC (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G- JM, PW1124G1-JM, and PW1122G-JM model turbofan engines. AD 2019-11-08 required the removal of the main gearbox (MGB) assembly and electronic engine control (EEC) software and the installation of a part and software version eligible for installation for engines that operate on extended operations (ETOPS) flights. This AD retains the requirements of AD 2019-11-08 and requires replacement of the MGB assembly and EEC software on engines that do not operate on ETOPS flights. This AD was prompted by multiple reports of in-flight engine shutdowns as the result of high-cycle fatigue causing fracture of certain parts of the MGB assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2020-04-21: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell Canada) Model 429 helicopters. This AD requires inspecting a certain part-numbered curvic coupling for proper engagement and depending on the inspection results, inspecting for play, inspecting the curvic coupling teeth, inspecting the flapping bearing teeth, replacing parts, performing a rigging check, and reporting information. This AD was prompted by a report of disengaged teeth of a curvic coupling due to improper installation. The actions of this AD are intended to address an unsafe condition on these products.
2008-04-04: We are adopting a new airworthiness directive (AD) for the products listed above. 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: There has been a reported case of failure of a bracket (P/N 85217732-108) of the over-centering spring assembly inside the translating door of the forward baggage compartment. * * * Failure of the bracket caused the eyebolt at the bottom of the spring assembly to become loose, resulted in damage of the support beam during normal door handle movement. Damage of the support beam, which is dormant, in combination with failure of a doorstop attached to any remaining undamaged support beam will degrade the structural integrity of the door, resulting in possible depressurization or loss of the door. We are issuing this AD to require actions to correct theunsafe condition on these products.
60-17-01: 60-17-01 AERO PRODUCTS: Amdt. 193 Part 507 Federal Register August 19, 1960. Applies to A6441FN-606 Propeller Installed On Lockheed 188 Series Aircraft. Compliance required as indicated. As a result of investigations, it has been determined that the following must be accomplished to minimize the possible occurrence of propeller roughness and/or failures: Not later than November 1, 1960, the thrust member thickness must be determined per Allison Propeller Bulletin 63-127. All blades that do not meet thrust member thickness as prescribed in Allison Propeller Bulletin 63-127 must be removed from service prior to further flight. Concurrently with this inspection all blades shall be classified aerodynamically per Allison Propeller Bulletin 63-125. (Allison telegram to all operators dated May 19, 1960, and Allison Propeller Bulletins Nos. 63-125 and 63-127 cover this same subject.)
82-14-01: 82-14-01 HUGHES: Amendment 39-4402. Applies to the Hughes Model 369 Helicopters with Chadwick C-20 Auxiliary Fuel System installed per Supplemental Type Certification SH129WE. Compliance is required as indicated, to provide early warning of auxiliary fuel transfer pump malfunction and the associated decrease in usable auxiliary fuel. Accomplish the following, unless already accomplished: 1. Within 30 days after the effective date of this AD, install a placard in accordance with Chadwick Service Bulletin 20-81-01 dated October 6, 1981, or FAA approved equivalent limiting usable auxiliary fuel to half the amount in the auxiliary tanks at takeoff. 2. Within 300 hours' time-in-service or 6 months from the effective date of this AD, whichever occurs first, install the C-20-FM Flow Monitoring Kit in accordance with Chadwick Service Bulletin 20-81-01 dated October 6, 1981, or FAA approved equivalent. The placard installed per Item 1 above may be removed, provided the revisedFlight Manual Supplement, Chadwick Auxiliary Fuel System C-20, dated October 21, 1981, is incorporated into the Rotorcraft Flight Manual. 3. Alternate modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 4. Special flight permits may be issued in accordance with Federal Aviation Regulation Part 21, Sections 21.197 and 21.199, to operate each helicopter to a base for the accomplishment of the modification required by this AD. This amendment becomes effective July 30, 1982.
79-02-05: 79-02-05 PIPER AIRCRAFT CORPORATION: Amendment 39-3394. Applies to Model PA-28-161, serial numbers 28-7816002 through 28-7816553, 28-7816554, 28-7816556 through 28-7816564, 28-7816566 through 28-7816597, 28-7816599 through 28-7816607, 28-7816609 through 28-7816634, 28-7816636 through 28-7816643; Model PA- 28R-201T, serial numbers 28R-7803002 through 28R-7803294, 28R-7803296 through 28R-7803308, 28R-7803310, 28R-7803311, 28R-7803315, 28R-7803317 through 28R-7803321, 28R-7803323 through 28R-7803325; and Model PA-28R-201, serial numbers 28R-7837002 through 28R-7837232, 28R-7837234, 28R-7837236, 28R-7837238 through 28R-7837241, 28R-7837243 through 28R-7837245, 28R-7837248 through 28R-7837250, 28R-7837253 through 28R-7837257, 28R-7837260, 28R-7837262 through 28R-7837264, 28R-7837266 through 28R-7837270, 28R-7837272 through 28R-7837275, airplanes certificated in all categories. \n\n\tCompliance is required within the next 25 hours time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent possible fuel flow interruption, accomplish the following: \n\n\t(a)\tRemove the top cowl or open the top left cowl as appropriate. \n\n\t(b)\tRemove the lower cowl attaching hardware on left side only and pull lower cowl outward to gain visual access to the fuel gascolator assembly. \n\n\t(c)\tCheck the gascolator installation to determine if the gascolator is installed with the ports oriented as shown in the accompanying figure. \n\n\t(d)\tIf the gascolator is installed in accordance with the accompanying figure, secure the cowling and make the appropriate maintenance record entry. \n\n\t(e)\tIf the gascolator is not installed in accordance with the accompanying figure, have the following accomplished by a person authorized by FAR 43.3: \n\n\t\t(1)\tRemove lower cowling. \n\n\t\t(2)\tPlace the fuel selector valve in the "OFF" position. \n\n\t\t(3)\tCut safety wire on the gascolator bowl bail. Remove the filter bowl, gasket and screen from the gascolator. Cleanany deposits that may be on the screen and/or the bowl. \n\n\t\t(4)\tCarefully spread the bail wire where it enters the housing until the bail can be removed. \n\n\t\t(5)\tSupporting the fittings in the gascolator housing with an open end wrench, remove the inlet and outlet "B" nuts. It will facilitate the removal and the re-installation of the gascolator assembly if the fuel line is loosened at the electric fuel pump inlet. \n\n\n\n\n\t\t(6)\tOn the PA-28-161 only, disconnect the primer line directly on top of the gascolator housing. \n\n\t\t(7)\tRemove the gascolator assembly from the attaching bracket and turn 180 degrees, positioning as shown in the accompanying figure. \n\n\t\t(8)\tIf the line assembly does not reach the inlet fitting, remove the forward left hand upholstery panel and inspect for, and correct, improper bends. \n\n\t\tCAUTION: Pulling the line into position with the "B" nut may cause damage to the flare. \n\n\t\t(9)\tRe-assemble the gascolator assembly and tighten all fuel line connections. \n\n\t\t(10)\tTurn on the aircraft power and the fuel boost pump and check for any fuel leaks. Correct any discrepancies found. \n\n\t\t(11)\tReinstall the cowling. \n\n\t\t(12)\tMake the appropriate maintenance record entry. \n\n\t(f)\tAn alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tThe checks in this AD may be accomplished by the pilot and appropriate maintenance record entries made in accordance with FAR 91.173. Installation correction must be accomplished by a person authorized by FAR 43.3. \n\n\tNOTE: Piper Service Bulletin 612 dated October 25, 1978, also pertains this subject. \n\n\tThis amendment becomes effective January 29, 1979.
2020-05-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, -232, and -271N airplanes, and Model A321-231 airplanes. This AD was prompted by a report of a production line inspection finding of damage on a main landing \n\n((Page 14790)) \n\ngear (MLG) side stay attachment outboard lug. This AD requires an inspection for discrepancies of the MLG side stay attachment outboard lugs, left-hand and right-hand sides, and applicable corrective action, 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.
2008-05-05: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, 737-700, 737-700C, 737-800, and 737-900 series airplanes. This AD requires an inspection of the vertical fin lugs, skin, and skin edges for discrepancies; an inspection of the flight control cables, fittings, and pulleys in section 48 for signs of corrosion; an inspection of the horizontal stabilizer jackscrew, ball nut, and gimbal pins for signs of corrosion; and corrective actions if necessary. This AD results from reports indicating that moisture was found within the section 48 cavity. We are issuing this AD to ensure that the correct amount of sealant was applied around the vertical fin lugs, skin and the skin edges. Missing sealant could result in icing of the elevator cables, which could cause a system jam and corrosion of structural and flight control parts, resulting in reduced controllability of the airplane.
82-25-06: 82-25-06 BRITISH AEROSPACE (formerly Hawker Siddeley): Amendment 39-4503. Applies to all H.S. 748 airplanes with Modifications 2743 or 5263 incorporated. Compliance is required as indicated unless already accomplished. To eliminate a heat source which may cause a fire in the cabin wiring accomplish the following within the next 100 hours time in service or 60 days, whichever occurs first, after the effective date of this AD: 1. Remove two cable assemblies (including resistors), Parts No. 2V19699 and 3V19699, for aircraft having Modification 6318 incorporated or, on aircraft without Modification 6318 incorporated, remove two resistor assemblies, Part No. 10V15130, in accordance with the Accomplishment Instructions of British Aerospace H.S. 748 Service Bulletin No. 21/106, dated March 23, 1981. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest MountainRegion. 3. 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 and/or modifications required by this AD. 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). This amendment becomes effective December 6, 1982.