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87-25-52: 87-25-52 MCDONNELL DOUGLAS: Amendment 39-5843. Applies to McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, as listed in McDonnell Douglas Alert Service Bulletin A32-222, dated December 10, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo eliminate the potential for decreased braking performance or loss of braking capability during landing or rejected takeoff, accomplish the following: \n\n\tA.\tWithin 10 days after the effective date of this AD, inspect the Brake/Anti-Skid Control Unit in accordance with Paragraph B of the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A32-222, dated December 10, 1987, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. If correct Brake/Anti-Skid Control Unit is installed, no further action is necessary. \n\n\tB.\tIf incorrect Brake/Anti-Skid Control Unit is installed, before further flight, remove the incorrect anti-skid control unit, reconfigure the keying rack and electrical connector, and install the correct anti-skid control unit, in accordance with Paragraphs D, E, and F of the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A32-222, dated December 10, 1987, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\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 inspection requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis AD was effective earlier to all recipients of telegraphic AD T87-25-52, issued December 11, 1987. \n\n\tThis amendment 39-5843 becomes effective March 7, 1988.
2017-01-11: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, - 214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. This AD requires identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-17-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of a missing pintle fuse pin in the left-hand (LH) main landing gear (MLG) discovered during scheduled maintenance. This AD requires doing an inspection of the MLG pintle housing assembly to verify that the pintle fuse pins are present and correctly installed, and corrective actions if necessary, as specified in a Transport Canada Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-01-12: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Model DA 42 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 an uncommanded engine shutdown during flight due to failure of the propeller regulating valve caused by hot exhaust gases escaping from fractured engine exhaust pipes. We are issuing this AD to require actions to address the unsafe condition on these products.
98-01-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of the main landing gear (MLG) uplocks with new or modified MLG uplocks. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the MLG to lock in the stowed position due to ice accumulation on the uplock hook and roller assembly, which could result in the inadvertent deployment of the MLG during flight.
2021-09-05: The FAA is superseding Airworthiness Directive (AD) 2016-08-20 for certain Airbus Helicopters (previously Eurocopter France) EC130B4 and EC130T2 helicopters. AD 2016-08-20 required repetitively inspecting the tail boom to Fenestron junction frame (junction frame) for a crack. This new AD continues to require inspecting the junction frame with the horizontal stabilizer removed, and expands the applicability, revises the compliance time and the inspection procedures for inspecting the junction frame, adds inspection procedures for certain helicopters, allows repair of the junction frame, and requires modifying and then repetitively inspecting the junction frame and reporting certain information. This AD was prompted by additional cracks and the availability of a design change that modifies the junction frame. The actions of this AD are intended to address an unsafe condition on these products.
2017-01-10: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model C-212 airplanes. This AD was prompted by multiple reports of damaged and cracked rudder torque tube shafts. This AD requires various repetitive inspections, and corrective actions if necessary. This AD also provides a modification which terminates the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
78-09-09: 78-09-09 DETROIT DIESEL ALLISON: Amendment 39-3207. Applies to 501-D13/501-D13A/501- D13D/501-D13E, and 501-D13H engines equipped with third stage turbine wheel P/N's 6788833, 6842143, 6841223, and 6846553 or fourth stage turbine wheel P/N's 6738424 and 6843014 installed in aircraft certificated in all categories. Compliance required as follows unless previously accomplished: To preclude possible engine failure resulting from third or fourth stage turbine wheel failure: Remove and classify all third and fourth stage turbine wheels with unknown carbide precipitation classifications in accordance with the compliance times specified in (a) and (b) below, and the procedures specified in Detroit Diesel Allison Commercial Overhaul Information Letter No. 349 Rev. 1 or later FAA approved revision. Wheels both newly and previously classified with carbide precipitation classifications of "Heavy" must be removed from service in accordance with the maximum life limits specified in (a) and (b) below. Wheels both newly and previously classified with carbide precipitation classifications of "Medium Heavy" must be removed from service in accordance with the maximum life limits specified in (c) through (h) below. Wheels of all other classifications may be returned to service and operated in accordance with the existing hourly life limits. (a) For wheels of "Heavy" and unknown carbide precipitation classification which exceed 8000 total cycles upon the effective date of this AD, compliance is required within 300 cycles. (b) For wheels of "Heavy" and unknown carbide precipitation classification which do not exceed 8000 total cycles upon the effective date of this AD, compliance is required prior to reaching 8300 total cycles. (c) For wheels of "Medium Heavy" carbide precipitation classification which exceed 16,000 total cycles upon effective date of this AD, compliance is required within 200 cycles. (d) For wheels of "Medium Heavy" carbide precipitation classification which have from 14,000 to 16,000 total cycles upon the effective date of this AD, compliance is required within the next 400 cycles or prior to exceeding 16,200 cycles whichever occurs first. (e) For wheels of "Medium Heavy" carbide precipitation classification which have from 10,500 to 14,000 total cycles upon the effective date of this AD, compliance is required within the next 1000 cycles or prior to exceeding 14,400 total cycles whichever occurs first. (f) For wheels of "Medium Heavy" carbide precipitation classification which have from 8000 to 10,500 total cycles on the effective date of this AD, compliance is required within the next 2000 cycles or prior to exceeding 11,500 total cycles whichever occurs first. (g) For wheels of "Medium Heavy" carbide precipitation classification which have from 7000 to 8000 total cycles on the effective date of this AD, compliance is required prior to exceeding 10,000 cycles. (h) For wheels of "Medium Heavy" carbide precipitation classification which do not exceed 7000 total cycles upon the effective date of this AD, compliance is required prior to exceeding 8000 cycles. NOTE: For purposes of this airworthiness directive a cycle is defined as one takeoff. The Detroit Diesel Allison Commercial Overhaul Information Letter identified in this directive is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). The Detroit Diesel Allison Commercial Overhaul Information Letter incorporated herein may be obtained upon request to Detroit Diesel Allison, Division of General Motors Corporation, P.O. Box 894, Indianapolis, Indiana 46206. This document may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and the Great Lakes Region. (Detroit Diesel Allison Commercial Service Letter 501-D13 CSL-253 also pertains to this subject.) This amendment becomes effective May 12, 1978.
76-02-04: 76-02-04 BRITTEN NORMAN LTD: Amendment 39-2499. Applies to BN-2A and BN-2A Mark III airplanes, all series, certificated in all categories, equipped with engine mounting frames P/N's NB-20-D-5209, NB-20-G-1901, NB-20-G-5231, or NB-51-H-1021. Compliance is required as indicated. To prevent failure of the engine mounting frame and possible physical separation of the engine, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the welds on the engine mounting frame around the periphery of the mounting pads for cracks and the mounting pads for conformance to the dimensions set forth in the first paragraph of the section entitled "Inspection" of Britten Norman Service Bulletin No. BN-2/SB.72, dated March 27, 1974, or an FAA-approved equivalent. (b) As a result of the inspection required by paragraph (a) of this AD, if two or more of the engine mounting pads are foundnot to conform to all of the dimensions specified in Britten Norman Service Bulletin No. BN-2/SB.72, dated March 27, 1974, prior to further flight, replace the engine mounting frame in accordance with paragraph (e) of this AD. (c) As a result of the inspection required by paragraph (a) of this AD, if one of the engine mounting pads is found not to conform to all of the dimensions specified in Service Bulletin No. BN-2/SB.72, visually inspect the welds around the periphery of the mounting pads prior to the first flight of each day, until the engine mounting frame is replaced in accordance with paragraph (e) of this AD. (d) If a crack is found as a result of an inspection required by paragraphs (a) or (c) of this AD, before further flight, replace the engine mounting frame in accordance with paragraph (e) of this AD. (e) Where required or authorized by paragraph (b), (c), or (d) of this AD, replace the engine mounting frame with a serviceable engine mounting frame of the same part number that has been inspected and found to have no cracks in the welds around the periphery of the mounting pads and found to conform to all of the dimensions specified in the "Inspection" paragraph of Britten Norman Service Bulletin No. BN-2/SB.72 dated March 27, 1974, or an FAA-approved equivalent. This amendment becomes effective January 30, 1976.
77-17-08: 77-17-08 AVCO LYCOMING: Amendment 39-3019 as amended by Amendment 39-3165. Applies to all Avco Lycoming T53 series engines. Compliance for P/Ns 1-170-240-52, 1-170-240-58, and 1-170-240-59 is required by September 15, 1977. Compliance for remaining part numbers listed below is required by May 1, 1978. To preclude possible failure of the fuel regulator P1 multiplier lever resulting in flameout of the engine, perform the following in accordance with Avco Lycoming Service Bulletin No. 0048, Revision 1, dated March 15, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region: 1. Fill the fuel regulator P1 multiplier cavity with silicone oil, General Electric P/N SF96-100, or equivalent. 2. Reidentify the fuel regulator, from P/N 1-170-240-52 to P/N 1-170-240-61, or from P/N 1-170-240-58 to P/N 1-170-240-60, or from P/N 1-170-240-59 to P/N 1-170-240-62. From P/N To P/N 1-160-840-01 1-160-840-15 1-160-840-02 1-160-840-14 1-160-840-03 1-160-840-13 1-160-840-09 1-160-840-11 1-160-840-10 1-160-840-12 1-160-950-02 1-160-950-16 1-160-950-04 1-160-950-15 1-160-950-05 1-160-950-17 1-160-950-06 1-160-950-18 1-160-950-08 1-160-950-19 1-160-950-10 1-160-950-13 1-160-950-12 1-160-950-14 1-170-240-01 1-170-240-68 1-170-240-03 1-170-240-69 1-170-240-04 1-170-240-70 1-170-240-05 1-170-240-71 1-170-240-06 1-170-240-72 1-170-240-08 1-170-240-73 1-170-240-09 1-170-240-74 1-170-240-12 1-170-240-75 1-170-240-17 1-170-240-76 1-170-240-19 1-170-240-77 1-170-240-20 1-170-240-78 1-170-240-21 1-170-240-64 1-170-240-25 1-170-240-79 1-170-240-26 1-170-240-80 1-170-240-27 1-170-240-81 1-170-240-30 1-170-240-82 1-170-240-45 1-170-240-63 1-170-240-46 1-170-240-83 1-170-240-47 1-170-240-84 1-170-240-48 1-170-240-67 1-170-240-49 1-170-240-65 1-170-240-57 1-170-240-66 The manufacturer's Service Bulletin identified and described in this directive is 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 Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06497. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at New England Region. Amendment 39-3019 became effective August 31, 1977. This amendment 39-3165 becomes effective March 30, 1978.