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2016-12-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and Model EC225LP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD immediately prohibits flight of all Model AS332L2 and EC225LP helicopters. This AD is prompted by an accident involving an EC225LP helicopter in which the main rotor hub (MRH) detached from the main gearbox (MGB). These actions are intended to prevent failure of the main rotor system and subsequent loss of control of the helicopter.
2016-13-11: We are superseding Airworthiness Directive (AD) 2008-05-06 for certain The Boeing Company Model 737-100, -200, -300, -400, and -500 series airplanes. AD 2008-05-06 required repetitive inspections for fatigue cracking in the longitudinal floor beam web, upper chord, and lower chord located at certain body stations, and repair if necessary. This new AD requires, for certain airplanes, an inspection to determine if tapered fillers are installed, and related investigative and corrective actions if necessary. This AD was prompted by reports of cracks in the center wing box longitudinal floor beams, upper chord, and lower chord. We are issuing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure. \n\n((Page 43476))
2024-21-01: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by a report of cracks found in the rear spar lower cap forward leg and lower aft skin of the right wing, during investigation of a fuel leak. This AD requires repetitive inspections for any fuel leak or crack of the lower aft skins, external doublers, and rear spar lower caps of the left and right wings, and corrective actions and inspection reports if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2016-13-07: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS 365 N3 helicopters. This AD requires inspecting the cabin and cockpit for labels, placards, or markings that provide jettison procedure instructions for cabin doors, removing any labels, placards, or markings that are in an incorrect location, and installing placards where they are missing. This AD is prompted by the determination that placards had not been installed according to specifications on newly manufactured helicopters. The actions are intended to provide exit procedures during an emergency.
2004-01-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes. This AD requires a one-time general visual inspection of the left and right sides of the pedestal side cover adjacent to the rudder pedal on the cockpit floor for proper installation of the attachment bracket, and corrective actions if necessary. This action is necessary to prevent restricted movement of the rudder pedal due to a loose pedestal side cover causing interference, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
69-17-01: 69-17-01 MCDONNELL DOUGLAS DC-9 and BOEING 737: Amdt. 39-819. Applies to DC-9 airplanes equipped with AiResearch Model GTCP85-98D Auxiliary Power Unit (APU) Serial Numbers listed in AiResearch Telegraphic Bulletin No. 49A1761 dated July 1, 1969, or later FAA approved revision, and to Boeing 737 airplanes equipped with AiResearch Model GTCP85-129 APU serial numbers listed in AiResearch Telegraphic Bulletin No. 49A1760 dated July 1, 1969, or later FAA approved revision. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tBecause of possible failure of the second stage impeller blades, the auxiliary power unit shall not be used as an alternate electric power source in place of a main engine driven generator until deficient impellers have been replaced. Pending replacement of the auxiliary power unit impeller, accomplishment of the following is required. \n\n\t1.\tWithin 10 hours time in service after the effective date of this Airworthiness Directive, install a placard in full view of the pilot to read: \n\n\tBoth main engine driven generators must be operative for takeoff. Only during in-flight emergency may the auxiliary power unit be used as an alternate electric power source. \n\n\t2.\tThis placard may be removed when the APU is replaced with an APU having satisfactory impeller blades, or when the APU is modified to incorporate an impeller with satisfactory impeller blades in accordance with the above AiResearch Telegraphic Service Bulletins. \n\n\tNOTE: Compliance with the inspection and speed reduction adjustments in these bulletins is optional. \n\n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated July 3, 1969.
2016-13-06: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of ruptured horizontal stabilizer de-icing boots. This AD requires a revision of the applicable airplane flight manual (AFM), repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. We are issuing this AD to detect and correct damage of the de- icing boot; such damage could lead to a ruptured boot, severe vibrations, and possible reduced control of the airplane.
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.