Results
2012-13-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires inspecting parts or doing a records review to determine if certain trailing edge flap carriages are installed, doing repetitive inspections for corrosion, and flaking or missing thermal coating on suspect carriage spindles, and related investigative and corrective actions, if necessary; this AD also provides optional terminating action for the repetitive inspections. This AD was prompted by reports of corrosion found on carriage that are located on the outboard flaps. We are issuing this AD to detect and correct corrosion of the carriage spindle, which could result in a fracture; fracture of both the inboard and outboard carriage spindles, at the forward ends through the large diameters, on a single flap assembly, could adversely affect the continued safe flight and landing of the airplane.
2009-07-01 R1: We are rescinding an airworthiness directive (AD) for RRD BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. The existing AD resulted from the need to reduce the published life limits of high-pressure (HP) turbine stage 1 discs, part numbers (P/Ns) BRH20130 and BRH20131, and HP turbine stage 2 discs, P/Ns BRH19423 and BRH19427. We are rescinding the existing AD because RRD has revised the approved published life limits of these parts to the same or higher limits as originally certified.
68-08-03: 68-08-03 FAIRCHILD-HILLER: Amdt. 39-583. Applies to all F-27 type aircraft Serial Nos. 1 to 95 inclusive incorporating a combustion heater system. Compliance required as indicated unless already accomplished, or unless installed heaters are rendered electrically inoperative and heater controls are placarded to prohibit operation prior to compliance with this AD. To preclude the possibility of residual fuel fire in the heater outer air passage due to lack of adequate drainage, accomplish the following: (a) Within the next 400 operational heater hours after the effective date of this AD, incorporate a heater outer pass drain installation in accordance with Fairchild Service Bulletin No. 21-68 Revision No. 1 dated November 10, 1964, or later FAA-approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon the effective date of this AD heater operational hours will be logged until such time as the AD has been complied with. This amendment effective May 19, 1968.
99-04-03: This amendment adopts a new airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A5/-D5 series turbofan engines, that requires the removal from service of certain high pressure compressor (HPC) stage 9-12 drums prior to reaching the new reduced cyclic life limits, and replacement with serviceable parts. This amendment is prompted by the reduction of the life limit for certain IAE V2500 HPC stage 9-12 drums due to higher stresses in this part than originally predicted. The actions specified by this AD are intended to prevent high pressure compressor (HPC) stage 9-12 drum failure, which could result in an uncontained engine failure and damage to the aircraft.
99-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines, that requires a fluorescent penetrant inspection (FPI) of the rear skirt of the diffuser case for cracks, and, if necessary, blending down to minimum wall thickness to remove cracks and subsequent FPI to determine if cracks have been removed, polishing, and shotpeening. If the cracks are shown by subsequent FPI not to have been removed, this AD requires removing the diffuser case from service and replace with a serviceable part. This amendment is prompted by a report of a diffuser case rupture during takeoff roll that resulted in damage to the aircraft. The actions specified by this AD are intended to prevent diffuser case rupture due to cracks, which can result in an uncontained engine failure and damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the FederalRegister as of April 12, 1999.
2012-11-09: We are superseding an existing airworthiness directive (AD) for certain transport category airplanes. That AD currently requires either activating all chemical oxygen generators in the lavatories until the generator oxygen supply is expended, or removing the oxygen generator(s); and, for each chemical oxygen generator, after the generator is expended (or removed), removing or restowing the oxygen masks and closing the mask dispenser door. This new AD requires installing a supplemental oxygen system in affected lavatories, which terminates the requirements of the existing AD. This AD was prompted by reports that the current design of the oxygen generators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate a hazard that could jeopardize flight safety, and to ensure that all lavatories have a supplemental oxygen supply.
67-32-05: 67-32-05 VICKERS: Amdt. 39-524 Part 39 Federal Register December 12, 1967. Applies to Viscount Models 744, 745D and 810 Series Airplanes. Compliance required as indicated. To prevent failure of the hydraulic flexible hoses installed in the nose wheel steering system, accomplish the following: (a) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 7246-1, located on the top of the nose oleo in the nose steering system, with 6,500 or more hours' time in service or which have been installed for 4 1/2 or more years on the effective date of this AD with new hoses of the same part number within the next 8 months or 1,500 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (b) Replace hydraulic system flexible hoses P/N 70126-163, 70826-13, and 72426-1, located on the top of the nose oleo leg in the nose steering system, with less than 6,500 hours' time in service and which have been installed for less than 4 1/2 years on the effective date of this AD with new hoses of the same part number before the accumulation of 5 years or 8,000 hours' time in service, whichever occurs sooner after the effective date of this AD, and thereafter at intervals not to exceed 5 years or 8,000 hours' time in service, whichever occurs sooner from the last replacement. (British Aircraft Corporation Preliminary Technical Leaflets (PTLS) Nos. 268 (700 Series) and 131 (800 Series), Issue 1, dated June 22, 1967, pertain to this subject.) This amendment effective January 11, 1968.
99-04-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires inspecting the main landing gear hydraulic actuators to determine whether a certain Frisby Aerospace actuator is installed, and reworking or replacing any of these Frisby Aerospace actuators. This AD is the result of reports of fatigue cracks in the end cap of main landing gear hydraulic actuators manufactured by Frisby Aerospace and installed on the affected airplanes. The actions specified by this AD are intended to prevent the main landing gear from failing to lock down due to the hydraulic actuator cracking and separating, which could result in loss of control of the airplane during landing, taxi, or ground operations.
99-03-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -700IGW, and -800 series airplanes. This action requires repetitive inspections to detect discrepancies of the quick-disconnect coupling on the fuel hose, located at the fan case firewall; corrective action, if necessary; and installation of a clamp shell on the coupling to prevent separation of the coupling halves. This amendment is prompted by a report that a quick-disconnect coupling on the fuel hose on an in-service airplane was found loose and leaking fuel. The actions specified in this AD are intended to detect and correct excessive wear of the quick-disconnect coupling on the fuel hose, which could result in major fuel leakage, fire in the engine nacelle, and consequent loss of thrust from the affected engine.
2021-20-01: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st- stage blade retaining plate installed. This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life- cycle limits for each part. This AD requires removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is issuing this AD to address the unsafe condition on these products.
68-12-05: 68-12-05 AERO COMMANDER: Amdt. 39-611. Applies to Models 100 and 100A, and Volaire Models 10A and 10, Serial Numbers 001 through 250. Compliance required as indicated. To preclude failure of the left and right arms, P/N 35321, of the rudder control system, accomplish the following: NOTE: The arms are those to which the rudder system left and right cables and springs are attached, and extend forward from the cross-bar assembly supporting the rudder pedals. (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect and modify the left and right arms, P/N 35321, as follows: Clean to bare metal all surfaces of the web and flanges of each arm over an area extending from the center of the 3/16 inch diameter cable attach hole to a point 3/4 inch aft of the hole. Visually inspect the exposed areas of the webs for cracks using a 10-power magnifying glass, or in an equivalent manner approved by the Chief,Engineering and Manufacturing Branch, FAA Southern Region. Weld the 1/16 inch deep square notches which are located in the webs at the forward ends of the upper and lower flanges of each arm, completely filling the notches with weld metal. Weld all cracks detected during the inspection with full penetration welds over the full length of each crack. Recoat the exposed area with oxide primer or equivalent. (b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, modify the left and right arms, P/N 35321, in accordance with the instructions contained in Aero Commander Service Bulletin 1009, dated May 24, 1968, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective June 14, 1968.
99-03-06: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires a one-time visual inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary. 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 breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane.
2003-06-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-06-51 that was sent previously to all known U.S. owners and operators of certain Learjet Model 45 airplanes by individual notices. This AD requires an inspection to determine the part number of the horizontal stabilizer actuator assembly (A66), and replacement of any suspect horizontal stabilizer actuator assembly (A66) with a new or serviceable actuator assembly (A66). This action is prompted by a report of severe vibration followed by a rapid nose down pitch change on a Learjet Model 45 airplane. The actions specified by this AD are intended to prevent structural failure of the horizontal stabilizer actuator assembly, which could result in possible loss of control of the airplane.
2012-12-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus Model A340-200 series airplanes; and Airbus Model A340-300 series airplanes. This AD was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. This AD requires performing a detailed inspection of the outer skin rivets at the frame fork ends of the forward and aft cargo door for sheared, loose, and missing rivets; repairing the outer skin rivets, if necessary; and performing repetitive inspections. We are issuing this AD to detect and correct sheared, loose, or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door.
72-15-04: 72-15-04 CANADAIR: Amdt. 39-1485. Applies to Canadair Limited Type CL-215-1A10 airplanes, Serial Nos. 1005, 1006, 1010, 1011, 1013 through 1018, 1021, and 1023 through 1030. Compliance required within the next 125 hours' time in service, unless already accomplished, after the effective date of this AD. To reduce the risk of flame propagation in the event of a fire in the engine fire zone, modify the oil system and hydraulic system hoses in accordance with the instructions and effectivities listed in the following Canadair Service Bulletins or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (a) Canadair Service Bulletin CL-215-138 dated February 2, 1971, and revision "A" dated April 23, 1971 or later approved revision. (b) Canadair Service Bulletin CL-215-140 dated January 18, 1971 or later approved revision. Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective July 25, 1972.
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.