Results
2012-12-07: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of cracks underneath the passenger door in a butt-joint on the forward fuselage of a Model F.28 Mark 0100 airplane. This AD requires repetitive low frequency eddy current inspections of the forward fuselage butt-joints for cracks, and if necessary, a temporary repair followed by a permanent repair. We are issuing this AD to detect and correct cracking of the butt-joint on the forward fuselage, which could result in explosive decompression and consequent loss of control of the airplane.
99-02-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 2000 airplanes (commonly referred to as Beech Model 2000 airplanes). This AD requires inspecting the stainless steel fuel line, part number (P/N) 3035737, for evidence of chafing and a minimum clearance between the fuel line and power lever bracket, P/N 122-940028-1; and replacing the fuel line and modifying the power lever bracket, as necessary. This AD is the result of chafing found on the stainless steel fuel line on several of the affected airplanes. The actions specified by this AD are intended to prevent fuel line chafing caused by interference with the power lever bracket, which could result in fuel leakage and cause a fire in the engine compartment.
99-02-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time visual inspection to detect discrepancies of the components of the torque link apex joint and shimmy damper attachments of the main landing gear (MLG), and repair or replacement of any discrepant component with a new or serviceable component. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent heavy vibration and possible damage to the components of the MLG, and consequent reduced controllability of the airplane during takeoff and landing.
2012-12-22: We are adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by a report of a crack found on the left-hand sidewall well on the nose landing gear (NLG). This AD requires performing a repetitive high frequency eddy current inspection of the stiffeners on the left-hand sidewall on the NLG bay for cracks, and repair or replace the sidewall if necessary. We are issuing this AD to detect and correct failure of the sidewall, which could result in consequent in-flight rapid decompression of the cabin and injury to the passengers.
74-12-07: 74-12-07 MCDONNELL DOUGLAS: Amendment 39-1861 as amended by Amendment 39-1923. Applies to Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, and DC-10-40 airplanes certificated in all categories. \n\n\tCompliance required on or before December 1, 1974. \n\n\tTo assure that in-flight depressurization will not occur as a result of the opening of a lower cargo door, accomplish the following McDonnell Douglas DC-10 Service Bulletins, in accordance with each service bulletin affectivity, or equivalents approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tService Bulletin 52-98, "Doors - Cargo - Modify Vent Doors," dated May 13, 1974, or later FAA-approved revision. \n\n\t(b)\tService Bulletin 52-99, "Doors - Cargo - Replace Lock Mechanism Viewing Window," Revision 1, dated April 19, 1974, or later FAA-approved revision. \n\n\t(c)\tService Bulletin 52-102, "Doors - Cargo - Revise Lower Cargo Door Markings," Revision 1, dated April 12, 1974, or later FAA-approved revision. \n\n\t(d)\tService Bulletin 52-106, "Doors - Cargo - Revise Electrical Wiring for Forward, Center, and Aft Cargo Doors Latch Actuators" dated April 25, 1974, or later FAA-approved revision. \n\n\t(e)\tService Bulletin 53-69, "Fuselage-Aerodynamic Fairings - Add View Port to Wing - To - Fuselage Fillet Panel Assembly on Center Cargo Door," dated May 6, 1974, or later FAA-approved revision. Only applies to Model DC-10-30, -30F and -40 airplanes. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herewith and made a part hereof, pursuant to 5 U.S.C. 552(a)(i). All persons affected by this directive who have not already received these documents may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90801. These documents may also be examined at FAA Western Region, 15000 Aviation Boulevard, Hawthorne, California. \n\n\tAmendment 39-1861 became effective July 6, 1974.This Amendment 39-1923 becomes effective August 22, 1974.
99-02-02: This amendment supersedes an existing airworthiness directive (AD), applicable to RHC Model R22 helicopters, that currently requires an initial and repetitive inspections of the forward flexplate (flexplate) at specified time intervals. This amendment also supersedes an existing priority letter AD that requires, within 25 hours time-in-service (TIS) or 15 calendar days, whichever occurs first, replacing the flexplate with an airworthy flexplate. This amendment requires the same replacement as the priority letter AD. This amendment is prompted by an accident in which the flexplate failed, causing loss of main rotor drive and rupture of the fuel tank. The actions specified by this AD are intended to prevent failure of the flexplate, which could result in failure of the main rotor drive system and subsequent loss of control of the helicopter.
2018-05-02: We are adopting a new airworthiness directive (AD) for certain AgustaWestland S.p.A. (AgustaWestland) Model AW189 helicopters. This AD requires replacing the seal and filler wedges of all emergency exit windows. This AD was prompted by a report that some windows were improperly glued when installed. The actions of this AD are intended to correct an unsafe condition on these products.
75-10-01: 75-10-01 HILLER: Amendment 39-2193. Applies to all UH-12D (Mil. H-23D, OH- 23D), UH-12E (Mil. H-23F, OH-23F, OH-23G), UH-12E-L, UH-12L and UH-12L4 helicopters certificated in all categories except those helicopters modified to incorporate Allison 250 series engines in accordance with Supplemental Type Certificate No. SH177WE or SH178WE. Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished. In order to prevent power loss due to slippage of the mercury clutch in the rotor drive system: (a) Remove the existing placard reading "No further flight if clutch engagement time exceeds 25 seconds." (b) Install decal placard, part number 81426-7, on the instrument panel in accordance with Hiller Service Letter 21-4 dated April 3, 1975. The placard is to read, "No further flight if clutch engagement time exceeds 20 seconds." (c) Incorporate the Hiller Rotorcraft Flight Manual Revision dated April 15, 1975in the applicable rotorcraft flight manual. Equivalent modifications may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. This supersedes Amendment 39-1462 (37 F.R. 11857), AD 72-13-4. This amendment becomes effective May 8, 1975.
2003-08-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes, and Model ATR72-102, -202, -212, and -212A series airplanes, that requires replacement of insulation blankets constructed of metallized polyethyleneteraphthalate (MPET) located from sections 11 through 16 of the fuselage with new insulation blankets constructed of Terul 18TM. This amendment is prompted by reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets constructed of MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead to a much larger fire. This action is intendedto address the identified unsafe condition.
2012-12-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters, with Aviation Specialties Unlimited, Inc. (ASU), Night Vision Imaging System (NVIS) lighting modified by Supplemental Type Certificate SR01383SE (STC). This AD requires determining the date of STC installation, determining if the aircraft has an unfiltered turbine outlet temperature (TOT) internal over-temperature warning light, and based on those findings, installing an NVIS filter. This AD was prompted by the finding that an unfiltered TOT indicator over-temperature warning light, when illuminated, created glare and reflections that could degrade the pilot's view while using night vision goggles thereby creating an unsafe condition. The actions of this AD are intended to modify any unfiltered TOT indicator unit over-temperature warning light by installing a filter to prevent degradation of the pilot's vision while using night vision goggles and to prevent subsequent loss of control of the helicopter.