Results
78-02-01: 78-02-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3124 as amended by amendment 39-3460. Applies to model PA-31T airplanes, serial numbers 31T-7400002 through 31T-7820077, and Model PA-31T1 airplanes, serial numbers 31T-7804001 through 31T-780-4006, certificated in all categories. Compliance required within the next fifty hours in service after the effective date of this AD, unless already accomplished. (a) To preclude possible failure of the main landing gear actuating cylinder rod end bearing assemblies, accomplish the inspection and replacement where required, described in the "Instruction" portion of Piper Aircraft Corporation Service Bulletin No. 57A, dated August 30, 1978. (b) Equivalent alterations or methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon submission of substantiating data by an owner or operator, 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. Amendment 39-3124 was effective January 18, 1978. This amendment 39-3460 is effective May 9, 1979.
84-12-51: 84-12-51 WESTLAND HELICOPTERS LIMITED: Amendment 39-4904. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent possible hazards in flight associated with cracking of the main rotor blades, accomplish the following: (a) Before the next flight and thereafter before the first flight of each day, visually inspect the main rotor blades in accordance with Westland Service Bulletin W30-05-23 dated July 16, 1984, or FAA-approved equivalent. (b) Within 15 hours after the effective date of this AD, unless already accomplished, conduct an eddy current inspection of the main rotor blade and thereafter at intervals not to exceed every 15 hours time in service since the last inspection in accordance with Westland Service Bulletin W30-05-23, or FAA-approved equivalent. (c) Remove from service any main rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with the AD may be used when approved by the Manager, Brussels Aircraft Certification Office, Federal Aviation Administration, c/o American Embassy, APO New York 09667. This amendment becomes effective September 11, 1984, as to all persons except those person to whom it was made immediately effective by telegraphic AD T84-12-51, issued June 5, 1984, which contained this amendment.
64-25-01: 64-25-01\tBOEING: Amdt. 39-1 Part 507 Federal Register November 6, 1964. Applies to Models 707 and 720 Series Aircraft Equipped With Pratt & Whitney JT3D Engines. \n\n\tCompliance required as indicated.\n \n\tThere have been a number of engine fires in service due to fuel accumulation in the aft thrust reverser sleeve and the side cowl panel as a result of false starts.\n \n\tTo correct this condition, unless already accomplished, provide additional fluid drainage in the left-hand side cowl panel and aft thrust reverser sleeve on each engine in accordance with either (a) or (b) or an equivalent approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tWithin 3,100 hours' time in service after the effective date of this AD accomplish the following: \n\n\t\t(1)\tDrill or cut four 1/2 inch-diameter holes through lower skin of the aft thrust reverser sleeve at Station 222.30 as shown on page 5 of Boeing Service Bulletin No. 1908. \n\n\t\t(2)\tDrill or cut two 1/4 inch-diameterholes through lower skin of aft thrust reverser sleeve at Station 222.30, one hole outboard of each channel section E-E and F-F at the locations shown on page 6 of Boeing Service Bulletin No. 1908. \n\n\t\t(3)\tDrill or cut two 1/2-inch diameter holes through lower skin of the aft thrust reverser sleeve at Station 241.75 as shown on page 4 of Boeing Service Bulletin No. 1908. \n\n\t\t(4)\tDrill or cut two 1/4 inch-diameter holes, one hole outboard of each rib, through lower skin on the aft thrust reverser sleeve, 1.3 inches outboard and 0.1 inch forward of each hole drilled in accordance with (a)(3). \n\n\t\t(5)\tDrill or cut two 1/2 inch-diameter holes through lower skin on left-hand side cowl nacelle Station 197.51 and bend trailing edge of each hole as shown on page 8 of Boeing Service Bulletin No. 1908. \n\n\t(b)\tWithin 3,100 hours' time in service after the effective date of this AD, drill or cut additional 1/2 inch-diameter drain holes in the aft thrust reverser sleeve and in the left sidecowl panel in accordance with Boeing Service Bulletin No. 1908. \n\n\tNOTE. - American Airlines, Inc. Fleet Campaign Directive No. 810B is an equivalent which has been approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(Boeing Service Bulletin No. 1908 dated January 16, 1964, covers this same subject.) \n\n\tThis directive effective December 7, 1964.
2020-05-16: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115 airplanes; Model A320-214, -216, - 232, -251N, and -271N airplanes; and Model A321-211, -231, -251N, - 251NX, -253N, -271N, -271NX, and -272N airplanes. This AD was prompted by reports of incomplete installations of the over wing panel lug attachments in the production assembly line. This AD requires a one- time detailed inspection of certain attaching points on the left-hand and right-hand wings for the correct installation of certain hardware, and, depending on findings, accomplishment of applicable corrective actions, 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.
79-05-11: 79-05-11 PIPER AIRCRAFT CORPORATION: Amendment 39-3433. Applies to Model PA-44-180, serial numbers 44-7995001 through 44-7995144, 44-7995146 through 44-7995180, 44-7995182 through 44-7995186, 44-7995190, 44-7995192, 44-7995193, 44-7995195, and 44-7995197 airplanes certificated in all categories. \n\n\tCompliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent loss of engine power control due to a damaged or binding throttle control cable or restricted carburetor throttle arm movement, on both engines, accomplish the following: \n\n\t(a)\tRemove upper and lower cowling. \n\n\t(b)\tDisconnect the throttle cable at the carburetor end and inspect the throttle control cable movement for full and free travel. If the throttle control cable movement exhibits stiffness or binding, replace the cable assembly with a serviceable unit. \n\n\t(c)\tInspect the carburetor throttle arm movement for full and free travel. If the throttle arm movement exhibits stiffness or restricted movement, take the necessary corrective action. \n\n\tNOTE: Marvel-Schebler/Tillotson Service Bulletin A2-78, dated October 1978, pertains to this condition. \n\n\t(d)\tRemove both left and right engine throttle control supports, and modify the part as shown in Figure No. 1 (dimensions are in inches). Re-mark the modified part as Part No. 86574-04. \n\n\t(e)\tReinstall the modified support as shown in Figure No. 1 (dimensions are in inches). Apply torque in accordance with the Piper Maintenance Manual. \n\n\t(f)\tRe-rig the throttles in accordance with Figures No. 2 and No. 3 (dimensions are in inches). \n\n\t(g)\tReinstall upper and lower cowling. \n\n\t(h)\tAdjust the throttle quadrant gear warning micro switch in accordance with Piper's Maintenance Manual. \n\n\t(i)\tMake an appropriate maintenance record entry. \n\n\t(j)\tAn equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tNOTE: Piper Service Bulletin 639, dated January 10, 1979, pertains to this subject. \n\n\tThis amendment becomes effective March 15, 1979.
97-24-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, -2A12, and -2B16 series airplanes. This action requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking in the pressure bulkhead at frame station (FS) 409.00, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
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.
89-06-03: 89-06-03 BOEING, McDONNELL DOUGLAS, AND AIRBUS: Amendment 39-6154.\n\n\tApplicability: Boeing Model 747 series airplanes equipped with General Electric CF6-45/50 series engines, as listed in Boeing Alert Service Bulletin 747-73A2048, dated June 9, 1988; Boeing Model 747 series airplanes equipped with Rolls Royce RB211-524 engines, as listed in Boeing Alert Service Bulletin 747-73A2049, dated December 8, 1988; McDonnell Douglas Model DC-9 series airplanes, including Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (Military) airplanes, as listed in McDonnell Douglas Service Bulletin A73-10, Revision 1, dated June 22, 1988; McDonnell Douglas Model DC-10 series airplanes and KC-10 (Military) airplanes, as listed in McDonnell Douglas Alert Service Bulletin A73-21, dated June 23, 1988; Airbus Industrie Model A300 series airplanes, as listed in Airbus Industrie Service Bulletin A300-73-009, dated September 30, 1988; Airbus Model A300-600 series airplanes equipped with General Electric CF6-80C2 engines, as listed in Airbus Industrie A300-73-6008, dated October 11, 1988; and Airbus Model A310 series airplanes equipped with Pratt & Whitney (P&W) 4000 series engines, as listed in Airbus Industrie Service Bulletin A310-73-2011, Revision 1, dated September 27, 1988; certificated in any category.\n\n\tCompliance: Required as indicated, unless previously accomplished.\n\n\tTo prevent engine compartment fires due to fuel leakage from degraded hose assemblies, accomplish the following:\n\n\tA.\tWithin 30 days after the effective date of this amendment, inspect the main fuel and vapor recovery hose assembly for fuel leakage and determine the cure date code contained on both the main fuel supply hose and the vapor recovery hose, in accordance with Boeing Alert Service Bulletin 747-73A2048, dated June 9, 1988 (for Model 747 series airplanes equipped with General Electric CF6-45/50 series engines); Boeing Alert Service Bulletin 747-73A2049, dated December 8, 1988 (for Boeing Model 747 series airplanes equipped with Rolls Royce RB211-524 engines); McDonnell Douglas Service Bulletin A73-10, Revision 1, dated June 22, 1988 (for Model DC-9 and DC-9-80 series airplanes, and Model MD-88 airplanes); McDonnell Douglas Service Bulletin A73-21, dated June 23, 1988 (for Model DC-10 series airplanes); Airbus Industrie Service Bulletin A300-73-009, dated September 30, 1988 (for Model A300 series airplanes); Airbus Industrie A300-73-6008, dated October 11, 1988 (for Model A300-600 series airplanes); or Airbus Industrie Service Bulletin A310-73-2011, Revision 1, dated September 27, 1988 (for Model A310 series airplanes).\n\n\n\nThe affected hose assemblies are Aeroquip Part Number (P/N): \nAE1006944H0140\nAE704313-1\nAE703400-3\nAE704312-2\nAE703402-2\nAE704314-1\nAE1000100H0072\nAE705348-1\nAE703630-1\nAE700064-2\nAE703651-1\nAE703402-2 or RBSL0010-503\n601000-8-0304\nAE704312-5\nAE703650-1\nAE704312-7 or 221D4020-501\nAE703652-1\nAE704312-4 or 221D0041-1\nAE703653-1\n\nAE1006944H0144\n\n\n\tThe affected main fuel supply hoses contain cure date codes of 3Q84 through 2Q87. The affected vapor recovery hoses contain cure date codes of 2Q84 through 3Q87. The affected bulk 601 hose contains a CAGE code of 50556 (regardless of cure date code).\n\n\t\t1.\tIf fuel leakage is detected, prior to further flight, replace the hose(s) with a serviceable hose not containing the cure date codes or CAGE code specified above, in accordance with the applicable service bulletin identified above.\n\n\t\t2.\tIf the affected hoses are installed, but fuel leakage is not detected, repetitively inspect the hoses for evidence of fuel leakage in accordance with the schedule specified in the applicable service bulletin.\n\n\tB.\tAfter the effective date of this amendment, bulk 601 hose with CAGE code of 50556 shall not be installed on any airplane.\n\n\tC.\tReplacement of main fuel supply and vapor recovery hoses with serviceable hoses that do not contain the cure date codes or CAGE code specified in paragraph A., above, constitutes terminating action for the requirements of this AD.\n\n\tD.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Chicago Aircraft Certification Office, FAA, Central Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Chicago Aircraft Certification Office.\n\n\tE.\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\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124; McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60); or Airbus Industrie, Product Support Division, Avenue Didier Daurat, 31700 Blagnac Cedex, France. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Central Region, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois.\n\n\tThis amendment (39-6154, AD 89-06-03) becomes effective March 30, 1989.
2020-06-01: The FAA is adopting a new airworthiness directive (AD) for all CFM International S.A. (CFM) LEAP-1B21, -1B23, -1B25, -1B27, -1B28, - 1B28B1, -1B28B2, -1B28B2C, -1B28B3, -1B28BBJ1, and -1B28BBJ2 model turbofan engines. This AD was prompted by reports of two new unsafe conditions and the need to supersede corrective actions for two previously addressed unsafe conditions. This AD supersedes AD 2018-25- 09 and AD 2019-12-01, which apply to the affected LEAP-1B model turbofan engines. This AD requires revising the Airworthiness Limitations Section (ALS) of the applicable CFM LEAP-1B Engine Shop Manual and the operator's approved continuous airworthiness maintenance program. The FAA is issuing this AD to address the unsafe conditions on these products.
78-26-06: 78-26-06 PIPER: Amendment 39-3378. Applies to Model PA-38-112, Serial Numbers 38-78A0001 thru 38-78A0652, 38-78A0653, 38-78A0655, 38-78A0656, 38-78A0658, 38- 78A0660, 38-78A0661, 38-78A0664 thru 38-78A0672, 38-78A0674, 38-78A0676, 38-78A0677, 38-78A0680 thru 38-78A0682, 38-78A0686, 38-78A0690, 38-78A0693, 38-78A0701, 38-78A0702, 38-78A0708, 38-78A0711, 38-78A0717, 38-78A0723, 38-78A0729, 38-78A0734 and 38-78A0749 certificated in all categories. To avoid possible hazards in flight associated with a crack in the vertical fin forward spar attachment plate accomplish the following within the next five hours in service unless previously accomplished. a. Remove the dorsal fin fairing P/N 77607-02 and inspect the forward bend radius of the vertical fin forward spar attachment plate P/N 77553-5 for cracks using a dye penetrant inspection method. b. If a cracked plate is found, replace with an undamaged part of the same part number before further flight, except a ferry flight to a place of repair may be authorized in accordance with FAR 21.197 with prior approval of the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 628A refers to this same subject.) This amendment is effective December 26, 1978.
2008-03-18: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) * * * [which] required * * * [conducting] a design review against explosion risks. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
78-25-03: 78-25-03 THE DEUTSCH COMPANY, METAL COMPONENTS DIVISION: Amendment 39-3363. Applies to P/N 94B0100004F0160 and 94F0100004F0166 hose assemblies marked with identification 4Q77 or 1Q78 which may be installed on various aircraft but which are known to be installed on Piper Models PA-23-250, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31-TI, PA-31-T, PA-34-200T, and PA-44-180 aircraft. NOTE 1: Hose P/N and manufacturing date codes (e.g. 4Q77 and 1Q78) are shown on a metal tag attached to the hose assemblies. a) Deutsch P/N 94B0100004F0160 is Piper P/N 17766-27, TSO C-53a Type A. b) Deutsch Part No. 94F0100004F0166 is Piper P/N 63901-41, TSO C-53a Type C. Compliance required as indicated, unless already accomplished. To prevent an unsafe condition in the various aircraft systems in which these hoses may be installed, accomplish the following: A. Within the next ten hours time in service after the effective date of this (AD), inspect to determine if hose assembly P/N 94B0100004F0160 or 94F0100004F0166 with manufacturing date 4Q77 or 1Q78 is installed. B. If the hose assemblies as in A above are not installed no further action is required by this (AD). C. If the hose assemblies in A above are installed, prior to further flight, (1) Remove and replace hose assemblies. (2) Check system for contamination. Purge system if evidence of contamination is found. NOTE 2: Piper Service Bulletin No. 611 refers to purging procedures for Piper Models PA -28, -34, and -44. Piper Service Bulletin No. 629 refers to purging procedures for Piper Models PA-31 and PA-23. NOTE 3: The following is a list of Piper Model, Serial Nos. and hose application which are believed to have suspect hoses installed. Possible hose application is not limited to this list. Model Serial Number Application Qty. of hoses PA-23-250 Aztec F 27-7854007 thru 27-7954018 Pressure nose gear cylinder up and pressure anti-retract valve 2 PA-28R-180 Possible Retrofit NLG actuating cylinder 2 PA-28R-200 Possible Retrofit NLG actuating cylinder 2 PA-28R-201 78-37105 thru 78-37317 NLG actuating cylinder 2 PA-28R-201T 78-03154 thru 78-03372 NLG actuating cylinder 2 Manifold pressure at left hand rear of engine 1 PA-31 31-1 thru 31-7812122 and 31-5001 thru 31-7852166 Main landing gear actuating cylinders 2 PA-31-300 Possible Retrofit Main landing gear actuating cylinders 2 PA-31-325 Navaho C/H 31-7812016 thru 31-7912004 Main landing gear actuating cylinders 2 PA-31-350 & PA-31-P Possible Retrofit Main landing gear actuating cylinders 2 PA-31TI Cheyenne I 31T-7804001 thru 31T-7904006 Main landing gear actuating cylinders 2 PA-31T Cheyenne, Cheyenne II 31T-77200069 thru 31T-7920012 Main landing gear actuating cylinders 2 PA-34-200T 78-70100 thru 78-70474 Fuel drains 4 PA-44-180 79-95001thru 79-95127 Engine oil pressure line at filter 2 D. Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for the accomplishment of the inspection required by paragraph A of this AD. E. Equivalent inspections and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. F. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Engineering Division, FAA Western Region may adjust the compliance time for hose replacement. This amendment becomes effective January 15, 1979, for all persons except those to whom it was made effective by priority message dated October 27, 1978.
63-23-03: 63-23-03 VICKERS: Amdt. 641 Part 507 Federal Register November 9, 1963. Applies to All Viscount Model 810 Series Aircraft. Compliance required as indicated. Fatigue failures have been reported on flap beams in the areas shown in Figure 1 of Preliminary Technical Leaflet No. 107 (800/810 Series). To preclude further failures accomplish the following on Nos. 2 and 3 flap units: (a) Within 500 flights* after the effective date of this AD, on aircraft which have accumulated 10,000 or less flights, unless already accomplished within the past 1,000 flights, conduct dye penetrant or FAA approved equivalent inspection for cracks in accordance with PTL 107. If no cracks are found, reinspect at intervals not exceeding 1,500 flights until the aircraft accumulates between 10,000 and 11,000 flights during which time the aircraft must be reinspected. Thereafter, the aircraft must be reinspected at intervals not exceeding 600 flights until a total of not more than 12,000 flightsare accumulated, at which time either of the following or FAA approved equivalent must be incorporated. (1) Modification FG.1946, or (2) The repair/reinforcing scheme defined in the referenced PTL. (b) Within 100 flights after the effective date of this AD on aircraft which have attained over 10,000 flights, unless already accomplished within the past 500 flights, conduct the inspection of paragraph (a). If no cracks are found, reinspect at intervals not exceeding 600 flights until reinforcing scheme (a)(1) or (a)(2), or FAA approved equivalent, has been incorporated. Incorporate the reinforcing scheme within 2,000 flights after the effective date of this AD. (c) Cracked flap beams may be considered serviceable for a further 500 flights provided that the cracks are confined to one doubler plate each side of the beam only, and extend no further than the bolt hole, per Figure 1 of PTL 107, and provided that the area is reinspected in accordance with (a) within every100 flights to ensure that no crack propagation has occurred. Incorporate repair/reinforcing scheme paragraph (a)(1) or (a)(2), or FAA approved equivalent, as follows: (1) Within 10 flights from the time of crack detection for aircraft with unacceptable cracks, and within 10 flights for aircraft with cracks that are found to propagate in length. (2) On or before the completion of 500 flights from the time of crack detection for aircraft with acceptable cracks. (d) After incorporating the modification of (a)(1) or (a)(2), or FAA approved equivalent, the special inspection in this AD may be discontinued. (Vickers-Armstrongs PTL No. 107 (800/810 Series) and Modification FG. 1946 cover this subject.) This directive effective December 11, 1963. *This will require operators to maintain a record of flights to ascertain compliance with this AD. If past records are unavailable the number of flights prior to this AD may be estimated.
85-16-08: 85-16-08 SHORT BROTHERS LTD.: Amendment 39-5101. Applies to Model SD3-60 airplanes as listed in Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984, certificated in any category. Compliance is required within twelve months after the effective date of this AD, unless previously accomplished. To prevent structural failure under ditching conditions, accomplish the following: A. Install Cherrymax rivets in the bottom section of fuselage frame 475 in accordance with Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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. This amendmentbecomes effective August 22, 1985.
99-19-40: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a detailed visual inspection to detect damage to the terminal lugs on the 12XC and 15XE connectors and the mounting lugs on the 15XE connector; and repair or replacement of the terminal lugs or the 15XE connector with new parts, if necessary. This amendment is prompted by the issuance of a mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct broken terminal and mounting lugs on the 15XE and 12XC connectors in the 101VU panel in the avionics compartment, which could result in loss of electrical power from the standby generator.
2020-04-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-941 airplanes. This AD was prompted by reports indicating premature aging of certain chemical oxygen generators. This AD requires repetitively removing the affected chemical oxygen generators and replacing them with serviceable parts, 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.