Results
2018-02-08: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 helicopters with a Helicopter Technology Company (HTC) main rotor (M/R) blade installed. This AD requires cleaning and visually inspecting the M/R blades, and depending on the outcome of the inspection, repairing or replacing the M/R blades. This AD is prompted by a report of an M/R blade with a fatigue crack in the grip plate and doublers at the blade retention bolt hole. The actions of this AD are intended to correct an unsafe condition on these products.
98-16-24: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and certain Model Avro 146-RJ series airplanes, that requires a one-time inspection for "drill marks" and corrosion on the underside of the wing top skin, and corrective actions, 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 corrosion from developing on the underside of the top skin of the center wing, which could result in reduced structural integrity of the airplane.
2000-26-12: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 helicopters that requires inspecting the hydraulic line shielding hose (hose), replacing any unairworthy hose with an airworthy hose, and installing a nylon cable tie. This amendment is prompted by the tail rotor drive shaft Thomas coupling contacting and chafing the hose that shields the fenestron tail rotor hydraulic lines. The actions specified by this AD are intended to prevent damage to the hose, leaking of accumulated hydraulic fluid to an area with an ignition source, inflight fire, and subsequent loss of control of the helicopter.
2000-23-04: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-500 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a new revision of the "Time Limits" section of the ATR42-400/500 Maintenance Planning Document, which specifies new inspections and compliance times for inspection and replacement actions. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2007-10-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200 and -300 series airplanes. For certain airplanes, this AD requires repetitive inspections for discrepancies of the tube assemblies and insulation of the metered fire extinguisher system and the bleed air duct couplings of the auxiliary power unit (APU) located in the aft cargo compartment, and corrective actions if necessary. For certain other airplanes, this AD requires a one-time inspection for sufficient clearance between the fire extinguishing tube and the APU bleed air duct in the aft cargo compartment, and modification if necessary. This AD also requires an inspection for signs of chafing and to verify sufficient clearance between the fire extinguisher system and the bleed air duct couplings of the APU. This AD results from one report indicating that an operator found a hole in the discharge tube assembly for the metered fire extinguishing system; and another report indicating that anoperator found chafing of the fire extinguishing tube against the APU duct that resulted in a crack in the tube. We are issuing this AD to prevent fire extinguishing agent from leaking out of the tube assembly in the aft cargo compartment which, in the event of a fire in the aft cargo compartment, could result in an insufficient concentration of fire extinguishing agent, and consequent inability of the fire extinguishing system to suppress the fire.
2000-26-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747, 757, 767 and 777 series airplanes, that requires modification of certain drip shields located on the flight deck, and follow-on actions. This action is necessary to prevent potential ignition of the moisture barrier cover of the drip shield, which could propagate a small fire that results from an otherwise harmless electrical arc, leading to a larger fire. This action is intended to address the identified unsafe condition.
77-07-05 R1: 77-07-05 HILLER AVIATION: Amendment 39-2862 as amended by Amendment 39-2917. Applies to Hiller Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E UH-12E (4- place), (including military Models H-23A, H-23B, H-23C, H-23D, H-23F, OH-23G, HTE-1, HTE-2, and CH112) helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To detect cracks in the control rotor blade spar tube and cuff and to establish a service life of 6860 hours for Hiller P/N 36124 cuff used with unfaired paddles accomplish the following: (a) Within the next 100 hours time in service after the effective date this AD, unless already accomplished within the last 100 hours time in service and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect, replace or repair the control rotor blade spar tube and cuff in accordance with Hiller Aviation Service Bulletin No. 36-1, Revision 2, dated June 19, 1974, or later FAA-approved revisions. (b) After any repair is accomplished in accordance with Hiller Aviation Service Bulletin No. 36-1, Revision 2, dated June 19, 1974 or later FAA-approved revisions, the control rotor blade spar tube (faired and unfaired) and cuff must be retired before 2500 additional hours time in service after rework or when the current approved total service life (total service life before repair plus service life after repair) is reached, whichever comes first. (c) Fabric covered, metal covered, faired and unfaired control rotor blades are not interchangeable and must not be intermixed. (d) For Hiller P/N 36124 cuffs used with unfaired paddles (1) Cuffs with more than 6660 hours time in service, remove and replace with a serviceable part within 200 hours time in service after the effective date of this AD. (2) Cuffs with less than 6660 hours time in service, remove and replace with a serviceable part prior to 6860 hours time in service. (3) For cuffsfor which the prior service history cannot be documented, within the next 25 hours time in service, unless already accomplished within the last 25 hours time in service prior to the effective date of this AD and at intervals not to exceed 50 hours time in service, perform a dye penetrant inspection of the cuff per Hiller Aviation Service Bulletin, No. 36-1, Revision 2, dated June 19, 1974, or later FAA approved revisions. Remove cracked cuffs from service prior to further flight. Cuffs for which the prior service history cannot be documented cannot be used as a replacement part. Remove from service all cuffs prior to the accumulation of 225 hours total time in service since April 7, 1977. (e) Equivalent inspection procedures and repair procedures for Hiller P/N 36124 cuff when used only with unfaired paddles may be approved by the Chief,Aircraft Engineering Division, FAA Western Region. (f) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for accomplishment of the inspections required by this AD. Amendment 39-2862 superseded Amendment 39-1990 (39 F.R. 36855), AD 74-21-05. Amendment 39-2862 became effective April 7, 1977. This amendment 39-2917 becomes effective June 20, 1977.
2018-02-04: We are adopting a new airworthiness directive (AD) for certain Aerospace Welding Minneapolis, Inc. mufflers, part numbers A1754001-23 and A1754001-25, installed on airplanes. This AD was prompted by occurrences of cracks or broken welds in the connecting weld of the muffler body to muffler cuff that may allow carbon monoxide exhaust fumes into the cockpit heating system. This AD requires an inspection of the muffler for leaking to identify cracks and replacement of the muffler. We are issuing this AD to address the unsafe condition on these products.
2018-01-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes) airplanes. This AD was prompted by a revision of certain airworthiness limitation item (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2007-09-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as un-damped extension of the main landing gear (MLG), potentially leading to loss of side stay integrity and then MLG collapse. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-24-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: The manufacturer has advised of receiving a report of looseness of the drive arm of the mechanical elevator trim tab, found during an annual inspection. This kind of damage is likely caused by penetrated humidity over the years. If left uncorrected, this condition could lead to the separation of the drive arm which could result in flutter of the elevator and possible loss of control of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-26-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, and 767 series airplanes, that requires rework of certain duct assemblies of the environmental control system (ECS) or replacement of the duct assemblies with new or reworked duct assemblies. This action is necessary to prevent potential ignition of fiberglass insulation material installed on the outside of the ECS ducts, which could propagate a small fire and lead to a larger fire. This action is intended to address the identified unsafe condition.
99-19-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that currently requires inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. This amendment establishes repetitive inspection intervals for certain inspections required by the existing AD. This amendment also adds a requirement to modify Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. 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 fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane.
2000-25-09: This amendment supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that currently requires inspecting the exhaust ejector locking system, clamp, and dampers for each engine. The existing AD also requires verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment requires modifying the engine exhaust ejectors. This amendment is prompted by the development of a kit to modify the engine exhaust ejectors to provide terminating action from the requirements of the current AD. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, damage to the main or tail rotor system and subsequent loss of control of the helicopter.
2007-06-52: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2007-06-52 that was sent previously to all known U.S. owners and operators of Boeing Model 737- 800 series airplanes by individual notices. This AD requires inspecting spoilers to determine spoiler position after every landing and after any rejected takeoff maneuvers. For airplanes on which any spoiler is found in the up position with the speedbrake handle in the down position, this AD requires replacement of the flight spoiler actuator with a flight spoiler actuator having a certain part number. This AD also requires an operational test of the speedbrake control system after any maintenance actions that operate the spoiler system and replacement of the flight spoiler actuator if necessary. This AD also provides for optional terminating action for those requirements. In addition, this AD requires you to report to the manufacturer any spoiler panel that is found in the up positionwith the speedbrake handle in the down position. This AD results from a report of seven flight spoiler actuator jams on Model 737-800 Short Field Performance airplanes. We are issuing this AD to detect and correct any spoiler panel that is found in the up position with the speedbrake handle in the down position, which could result in a spoiler actuator hardover, and could cause the spoiler surface to jam in the fully extended position. Two or more hardover failures of the spoiler surfaces in the up direction on the same wing, if undetected prior to takeoff, can cause significant roll and consequent loss of control of the airplane.
2019-08-08: We are superseding Airworthiness Directive (AD) 2010-14-05, which applied to certain Bombardier, Inc., Model CL-600-1A11 (600), CL- 600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. AD 2010-14-05 required inspection for the part numbers of the system and brake accumulators, and repetitive replacement of affected accumulators. This AD adds requirements for relocating the accumulators and revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. This AD also adds optional terminating action for certain airplanes. This AD was prompted by reports of on-ground hydraulic accumulator screw cap or end cap failure that resulted in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. We are issuing this AD to address the unsafe condition on these products.
77-15-06: 77-15-06 MORANE SAULNIER (SOCATA): Amendment 39-2975. Applies to Model MS 892A150, MS 892E150, MS 893A, MS 893E, RALLYE 150T and RALLYE 150ST airplanes, certificated in all categories. Compliance is required as indicated. To prevent failure of engine mounts, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours time in service from the last inspection, visually inspect the engine mounts for cracks using dye penetrant in accordance with paragraphs 111-1-1 and 111-1-2 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. (b) If one or more cracks are detected as a result of any inspection required by paragraph (a) of this AD, repair as necessary in accordance with paragraph 111-1-3 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. (c) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, on airplanes with right angle engine mount brackets, modify the brackets in accordance with paragraph 111-2 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. This amendment becomes effective August 22, 1977.
2007-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as Several recent inspections have revealed that some spar wooden centre blocks have shown cracks. Investigation revealed that cracks are generated by the wood drying. Actions specified in this AD are intended to detect and correct any defects on the central wing spar block. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-26-11: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires replacing certain tail rotor blades with airworthy tail rotor blades. This amendment is prompted by a tail rotor blade (blade) failure that caused a high vibration level in the helicopter. Investigation revealed that the failure was due to a change in the manufacturing process for an identified production lot of blades. This condition, if not corrected, could result in a failure of a blade and subsequent loss of control of the helicopter.
2000-25-53: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-25-53, which was sent previously to all known U.S. owners and operators of Airbus Model A330 series airplanes by individual notices. This AD requires either repetitive detailed visual inspections or repetitive borescopic inspections to detect cracking or other damage of the barrel nuts of the engine aft mount; and replacement of any cracked nut and its associated bolt with a new nut and bolt, or replacement of all 4 nuts and their associated bolts if two or more nuts on the same engine mount are found cracked. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the aft engine mount nut, which could result in reduced structural integrity of the engine-to-pylon aft mount assembly, or, in the case of multiple cracked nuts, possible loss of an engine.
2013-25-08: We are superseding airworthiness directive (AD) 2009-24-09 for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2009-24-09 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installing new lock wire, and corrective actions if needed. This new AD expands the applicability, reduces the compliance time, changes torque values of the check valve tightening, and requires a repetitive inspection program for certain check valves in the [[Page 78695]] hydraulic systems on airplanes that have had a certain modification embodied during production or in-service. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to detect and correct such check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane.
2007-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 182 series airplanes that are equipped with Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI. This AD requires you to disconnect or remove the electrical cable between the forward ground power relay and the starter relay, install a placard, inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing, and replace the fuel line if chafing is found. This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment.
2021-26-24: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. (type certificate previously held by Agusta S.p.A.) Model A109A and A109A II helicopters. This AD was prompted by a report of internal corrosion on a main rotor (M/R) blade. This AD requires repetitively inspecting affected M/R blades and accomplishing film analysis and repair in accordance with certain approved methods. The FAA is issuing this AD to address the unsafe condition on these products.
75-20-06: 75-20-06 BELLANCA: Amendment 39-2372. Applies to Model 17-30, 17-30A (S/N 30263 through S/N 76-30811), 17-31, 17-31TC, 17-31ATC (S/N 30004, S/N 31004 through S/N 76-31124), 14-19-3A, and 17-31A (S/N 32-15 through S/N 76-32-163) airplanes certificated in all categories. Compliance required upon accumulation of 300 hours time in service or within the next 25 hours time in service from the effective date of this Airworthiness Directive (whichever occurs later) unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service from the last inspection until Bellanca Kit SK1234789-0004 is accomplished. To detect cracks in either vertical side fuselage tube (F. S. 7), which is adjacent to the horizontal stabilizer carry-through, in the area near the upper fuselage longeron, accomplish the following: A. Inspect the vertical tube for circumferential cracks at the upper weld, and between the upper weld and the horizontal stabilizer carry-throughtube, all around the tube. B. If cracks are found, repair and modify in accordance with Bellanca Kit SK1234789-0004 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region, before further flight, except that the airplane may be flown, in accordance with FAR 21.197, to a base where the repair can be performed. C. If no cracks are found, no further action is required until the next inspection. Bellanca Service Letter No. 85 or 85A pertains to this same subject. This amendment becomes effective September 26, 1975.
2007-08-09: 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: An analysis of the cable operated control system installed on the SD3 aircraft types that use MS 21260 type end fittings has identified a number of potentially unsafe conditions due to a combination of failures * * *. The failure of certain control cables could result in the loss of certain critical systems. For example, the loss of the low pressure (LP) fuel control cable in combination with a single failure of a fuel condition control cable on the same engine can cause the loss of the capability to shut down the engine in the event of an engine fire. This AD requires actions that are intended to address the unsafe condition described in the MCAI.