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73-13-01: 73-13-01 PIPER: Amendment 39-1665 as amended by Amendment 39-1936 is further amended by Amendment 39-1964. Applies to all Piper Model PA-34-200 "Seneca" airplanes, S/Ns 34-E4, 34-7250001 and up. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, determine the rudder trim tab "free play" as follows: (1) Adjust rudder trim tab to neutral position with rudder trim wheel. (2) Index tab to rudder. Use straight edge at trailing edge, making marks on rudder and tab that coincide. (3) Hold light finger pressure against rudder tab in one direction and measure distance between marks. (4) Reverse direction of finger pressure on rudder tab and measure distance between marks. (5) "Free play" of the rudder tab is the sum of the distances measured in (3) and (4) above and should not exceed .125 inches. (b) If rudder tab "free play" exceeds .125 inches, check the travel control arm assembly, P/N 96220-00 (Ref. Fig. 60, PA-34 parts catalog), for wear at the center bolt and at the bolt attaching the rudder trim rod assembly to the control arm. Replace the arm assembly and associated hardware if there is any noticeable wear or elongation of the bolt holes. (c) Also check for end play in the rudder trim barrel, P/N 96596-00 (Ref. Fig. 34, PA-34 parts catalog). If end play exists, shim between the forward barrel mount support assembly and barrel. Reduce end play to the minimum amount attainable without causing excessive system friction. Note: Shim (P/N 62833-18V) is a laminate made of 10 pieces of .002 inch brass shim stock, although it appears to be one solid piece. The proper thickness of shim material may be obtained by pealing off layers as required. (d) Upon completion of any adjustments, re-check "free play" in accordance with the procedures of (a)(3), (a)(4), and (a)(5) to ascertain that travel is less than .125 inches.(e) Repeat the above inspection every 100 hours time in service after the initial inspection. Piper Service Bulletin No. 390A pertains to this same subject. When the airplane is modified with Piper Rudder Trim Mechanism Kit, Piper P/N 760800V, the repetitive inspections of (e) are no longer required. Piper Service Letter No. 714 pertains to this same subject. Amendment 39-1665 became effective June 18, 1973. Amendment 39-1936 became effective August 30, 1974. This Amendment 39-1964 becomes effective September 30, 1974.
2002-06-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to replace the metered connector and oxygen tubing and related components in the rear seat bench. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to correct the potential for insufficient oxygen quantity that is available to occupants of the rear seat bench in some emergency conditions. This condition could result in reduced occupant safety at the rear bench seat location.
2023-05-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS 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). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-05-17: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-76B, GE90-85B, GE90-90B, and GE90-94B model turbofan engines. This AD was prompted by a commanded in-flight shutdown (IFSD) due to cracking and rockback of the high- pressure turbine (HPT) stage 2 nozzles resulting in blade liberation, severe rotor imbalance, and liberation of the exhaust centerbody. This AD requires initial and repetitive borescope inspections (BSIs) of the forward platforms of the HPT stage 2 blades or the leading edges of the HPT stage 2 nozzles and, depending on the results of the inspections, removal and replacement of the HPT stage 2 nozzles with parts eligible for installation. As a mandatory terminating action to the repetitive BSIs of the forward platforms of the HPT stage 2 blades or the leading edges of the HPT stage 2 nozzles, this AD requires replacing the HPT stage 2 nozzles. The FAA is issuing this AD to address the unsafe condition on these products.
2023-05-05: The FAA is superseding Airworthiness Directive (AD) 2021-10-09 for certain CFM International, S.A. (CFM) CFM56-5B and CFM56-7B model turbofan engines with a certain high-pressure turbine (HPT) inner stationary seal installed. AD 2021-10-09 required removal, inspection, and replacement of the affected HPT inner stationary seal and, depending on the findings, replacement of the rotating air HPT front seal, HPT rotor blades, and No. 3 ball bearing. This AD was prompted by cracks found in the rotating air HPT front seal. After the FAA issued AD 2021-10-09, the manufacturer notified the FAA that the service information incorrectly lists the year of certain honeycomb repairs and that affected HPT inner stationary seals could potentially be installed on CFM CFM56-5C model turbofan engines. This AD requires removal, inspection, and replacement of the affected HPT inner stationary seal and, depending on the findings, replacement of the rotating air HPT front seal, HPT rotor blades, and No. 3 ball bearing. This AD also revises the applicability to add CFM CFM56-5C model turbofan engines. The FAA is issuing this AD to address the unsafe condition on these products.
2002-06-08: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Rolls-Royce Corporation (formerly Allison Engine Company) 250-C28 series engines. This amendment requires removal of third stage turbine wheels, part number (P/N) 6899383, with certain serial numbers (SN's), from service before exceeding new, reduced life limits. This amendment also establishes a drawdown program to require the removal of those turbine wheels that exceed the new lower limits. This amendment is prompted by the potential to experience uncommanded shutdown caused by fractures of third stage turbine blade tips and shrouds. The actions specified by this AD are intended to prevent uncommanded shutdown of the engine due to fractures of third stage turbine blade tips and shrouds.
2023-05-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-8, 737-9, and 737-8200 airplanes. This AD was prompted by a determination that new airworthiness limitations are necessary to require periodic replacement; or testing, and replacement if necessary; of the oxygen sensor of the nitrogen generation system (NGS). This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate the new airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2002-06-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300; A300-600; and A310 series airplanes. This action requires certain inspections of the airplane (including the vertical stabilizer, horizontal stabilizer, pylons, wing, and fuselage areas) following an in-flight incident resulting in extreme lateral loading. This action is necessary to detect and correct reduced structural integrity of the airplane following any future event. This action is intended to address the identified unsafe condition.
2002-03-09 R1: This amendment revises an existing airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. The existing AD will become effective on March 27, 2002, and requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires the same inspections, and in addition, allows installation of impellers that pass those inspections. This revision to the existing AD is prompted by an inadvertent omission in the existing AD to include allowance of installation of impellers that pass inspections required by the AD. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
2002-03-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-03-52, sent previously to all known U.S. owners and operators of Eurocopter France (ECF) helicopters by individual letters. This AD requires checking for a gap between the adhesive bead and the metal bushing bonded on each STARFLEX star arm end (arm end) and, if a gap is found, replacing the STARFLEX with an airworthy part. This AD is prompted by reports of bonding failure between the metal bushing and the arm end that led to severe vibrations resulting in several emergency landings. The actions specified in this AD are intended to detect bonding failure between the metal bushing and each arm end, severe lateral vibrations, and subsequent loss of control of the helicopter.