Results
2018-02-03: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by an erroneous radio altimeter reading, which caused certain systems to respond in a way that led to loss of speed. We are issuing this AD to address the unsafe condition on these products.
2007-10-02: 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: * * * Corrosion on the bearings with propagation to the bracket- hinge of the rudder. This corrosion has been discovered after rudder removals. This condition, if left uncorrected, could result in the loss of the rudder control on the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
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.