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83-08-06: 83-08-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4636. Applies to Lockheed Model L-1011-385-3 series airplanes, certificated in all categories. Compliance is required as indicated, unless previously accomplished. To minimize the potential for a total loss of the Active Control System (ACS) inflight, accomplish the following by June 30, 1983: A. Modify the aircraft wiring in accordance with Part 2, Accomplishment Instructions, in Lockheed-California Company L-1011 Service Bulletin 093-22-147 dated August 17, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Los Angeles 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also 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. This amendment becomes effective June 2, 1983.
82-26-01: 82-26-01 BOEING: Amendment 39-4514. Applies to all Boeing Model 747 Series airplanes equipped with a dual channel autopilot with a Monitor and Logic (M & L) Unit, Boeing Part Number 60B00013-452, -453, -454, and on, listed in Boeing Service Bulletin 747-22-2130, Fail- Passive Autopilot Stabilizer Trim Bias and Automatic Disconnect Modification. \n\n\tCompliance required as indicated. To prevent no-flare automatic landings with excessive sink rates, accomplish the requirements of paragraph A and either paragraph B or C below within 180 days after the effective date of this AD: \n\n\tA.\tIncorporate the following limitations as appropriate in "Section 1 - Certification Limitations" of the Airplane Flight Manual: \n\n\t\t1.\tOn airplanes equipped with an operating Autoland Bias Control System, incorporate the following limitation: "Autopilot - Autopilot use below 50 feet AGL is prohibited except when Boeing Service Bulletin 747-22-2127 FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent is installed and one of the following conditions is met: \n\n\t\t\t(a)\tAt flaps 25 - the ground speed on final approach is less than 187 kts.\n \n\t\t\t(b)\tAt flaps 30 - the ground speed on final approach is less than 173 kts." \n\n\t\t2.\tOn all other airplanes incorporate the following limitation: "Autopilot - Autopilot use below 50 feet AGL is prohibited except when Boeing Service Bulletin 747-22- 2127 FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent is installed and one of the following conditions is met: \n\n\t\t\t(a)\tAt flaps 25 - the ground speed on final approach is less than 180 kts. \n\n\t\t\t(b)\tAt flaps 30 - the ground speed on final approach is less than 163 kts." \n\n\tB.\tInstall a placard on the autopilot flight director mode select panel which reads: "DO NOT USE AUTOPILOT BELOW 50 FT. AGL." \n\n\tC.\tAccomplish Boeing Service Bulletin 747-22-2127, FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent. Install a placard on the autopilot flight director mode select panel which reads: "DO NOT USE AUTOPILOT BELOW 50 FT AGL EXCEPT PER FLIGHT MANUAL LIMITATIONS." \n\n\tD.\tAccomplishment of Boeing Service Bulletin 747-22-2130 provides terminating action and allows removal of the placard and flight manual limitations required by paragraphs A, B, and C above. \n\n\tE.\tAlternate means of compliance with this 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\tF.\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 inspections and/or modifications required by this AD. \n\n\tThe 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). \n\n\tThis amendment becomes effective January 17, 1983.
2016-13-02: We are superseding Airworthiness Directive (AD) 2016-09-04 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2016-09-04 required replacement of incorrectly calibrated angle of attack (AOA) transducers. This new AD requires the same actions as AD 2016-09-04. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2016-09-04. We are issuing this AD detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
72-10-03: 72-10-03 HAWKER SIDDELEY: Amendment 39-1443. Applies to DeHavilland Model D.H. 104 Series 7A, 7AXC, 8A, 8AXC airplanes modified per STC SA1747WE certificated in all categories. (Also known as "Carstedt Jet Liner C-600"). Compliance required prior to further flight after the effective date of this AD as indicated, unless already accomplished. To prevent fatigue failure of a wing main spar lower attach fitting or of a wing center section lower spar boom, accomplish the following: (a) Replace each wing lower spar attach fitting P/N CPD 2004 installed under STC SA1747WE at or before 1800 hours' time in service, and at intervals thereafter not to exceed 1800 hours' time in service, with a new attach fitting (Strato Engineering Co., Inc. Part No. CPD 2004). (b) Replace the wing center section lower spar boom at or before 1800 hours' time in service, and at intervals thereafter not to exceed 1800 hours' time in service, in accordance with DeHavilland Aircraft Company drawing number 4-Z-13775, or another replacement modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) If aircraft are further modified in accordance with STC SA2438WE, or an alternate acceptable modification approved by the Chief, Aircraft Engineering Division, Western Region, replacement of the parts as specified in (a) and (b) above, may be discontinued. This amendment becomes effective June 7, 1972.
2024-19-16: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH Model 328-100 and 328-300 airplanes. This AD was prompted by reports of a broken attachment eyebolt in a Collins Aerospace JB6 Commuter Class passenger seat. This AD requires a one- time detailed inspection of each affected part, and applicable corrective actions, and limits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2024-19-05: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) (type certificate previously held by Turbomeca, S.A.) Model Makila 1A, Makila 1A1, and Makila 1A2 engines. This AD is prompted by a determination that the accumulated service life of certain critical parts was underestimated. This AD requires determining the recalculated service life of certain critical parts, replacing if necessary, and also specifies conditions for installing the 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.
2004-01-10: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model MBB-BK-117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters with a certain tail rotor (TR) transmission or intermediate (INT) gearbox installed. This action requires inspecting the magnetic plug of the TR transmission and INT gearbox for metal particles before the first flight of each day. Replacing an unairworthy TR transmission, INT gearbox, or bearings with airworthy parts is also required within 30 days after the effective date of this AD. This amendment is prompted by a report of production-related cracks on the cage of bearings installed in certain TR transmissions and INT gearboxes. This condition, if not corrected, could result in cracking and separation of the bearing cage, failure of a bearing, failure of the TR transmission or INT gearbox, and subsequent loss of control of the helicopter.
2024-19-09: The FAA is superseding Airworthiness Directive (AD) 2016-08-08 for all SOCATA (type certificate now held by DAHER) Model MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235C, and Rallye 235E airplanes. AD 2016-08-08 required doing repetitive detailed visual inspections of the intersection between the axle radius and the nose landing gear (NLG) fork area for chafing; doing repetitive dye penetrant inspections on the NLG wheel axle for cracks, distortion, and nicks or wear; doing corrective actions if necessary; and replacing the NLG wheel axle attachment screws with new screws. This AD is prompted by the introduction of a new inspection method and a new design for the affected NLG wheel axle that provides terminating action for the repetitive inspections, as specified in updated service information published by the manufacturer. This AD requires preparing, inspecting, replacing, reconditioning the NLG wheel axle, and prohibiting affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2003-26-14: The FAA adopts a new airworthiness directive (AD) for certain Kidde Aerospace P/N 898052 hand-held halon fire extinguishers that are utilized on aircraft. This AD requires you to remove the affected fire extinguishers from service and would prevent you from using them in the future. This AD is the result of information that shows that the discharge time of the affected fire extinguishers exceeds the maximum allowable discharge time. The problem is due to incomplete crimping of the siphon tube. We are issuing this AD to remove from service fire extinguishers that had this incomplete crimping of the siphon tube. If not removed from service, these fire extinguishers could function at diminished levels and compromise the level of safety in an emergency situation.
2003-26-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires identification of the valves installed on the engine struts as hydraulic supply (fire) shutoff valves for the engine-driven pump, corrective action if necessary, and eventual replacement of discrepant valves with serviceable parts. This action is necessary to prevent leakage of hydraulic (flammable) fluid into an engine fire, which could result in an uncontrolled fire. This action is intended to address the identified unsafe condition.