Results
2003-13-13: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires a one-time inspection of the adjustable stop screws of the magnetic brake assembly; repairing, as appropriate, certain mechanical damage to the cyclic and collective flight control magnetic brake arm assembly (arm assembly), if necessary; and installing the stop screw with the proper adhesive, adjusting the arm assembly travel, and applying slippage marks. This amendment is prompted by reports that the magnetic brake adjustable screws have backed out, which limited travel of the arm assembly. The actions specified by this AD are intended to detect loose adjustable stop screws that could result in limiting the travel of the cyclic and collective arm assembly, and subsequent loss of control of the helicopter.
2014-16-19: We are superseding Airworthiness Directives (AD) 2006-21-08, AD 2007-14-01, AD 2008-25-02, AD 2010-04-09, AD 2011-01-02, and AD 2012-16-05, for certain Airbus Model A330 and A340 series airplanes. AD 2006-21-08, AD 2007-14-01, AD 2008-25-02, AD 2010-04-09, AD 2011-01-02, and AD 2012-16-05 required revising the maintenance program or inspection program to incorporate certain maintenance requirements and airworthiness limitations for fuel tank systems. This new AD requires a new maintenance or inspection program revision. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2014-15-51: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-500 airplanes. This AD was sent previously to all known U.S. owners and operators of these airplanes as an emergency AD. This AD requires an inspection and replacement as necessary of the barrel nuts at the horizontal stabilizer to vertical stabilizer attachment joint. This AD was prompted by 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 cracking of the barrel nuts at the horizontal stabilizer to vertical stabilizer attachment joint. We are issuing this AD to correct the unsafe condition on these products.
74-05-05: 74-05-05 BEECH: Amendment 39-1796 as amended by Amendment 39-1841. Applies to Models 60 and A60 (Serial Numbers P-3 through P-246) airplanes now having or subsequently accruing 27 months in service from the date of the original airworthiness certification, except those airplanes having Beech P/N 60-420013-59 or Beech P/N 60-420013-652 pilot's side window installed. Compliance: Required as indicated. To prevent rapid decompression caused by failure of the pilot's side window accomplish the following: A) Effective immediately, operation with the cabin pressurized is prohibited and prior to further flight (1) deactivate the pressurization system by securing the "TEST/DUMP" switch in the "Dump" position and install a placard on the control panel adjacent to the pressurized system controls reading: "CABIN PRESSURIZATION PROHIBITED" and (2) insert a copy of this AD in the limitation section of the airplane flight manual. B) In lieu of Paragraph A(1) and (2), and prior to operation with cabin pressurization, replace existing pilot's side window with Beech P/N 60-420013-59 or Beech P/N 60-420013-652 pilot side window in accordance with Beechcraft Service Instructions No. 0594- 110, or later approved revisions or any equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) Upon accomplishment of Paragraph B, reactivate the pressurization system and remove the placard and flight manual insertion required by Paragraph A. Amendment 39-1796 became effective March 8, 1974. This Amendment 39-1841 becomes effective May 17, 1974.
2009-19-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2009-19-51, which was sent previously to all known U.S. owners and operators of the Agusta Model AB139 and AW139 helicopters by individual letters. This AD requires inspecting the tail panels for debonding and, if the debonding area exceeds a certain limit, repairing the tailboom. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that while taxiing, the tailboom of a Model AW139 helicopter bent and collapsed. Also, EASA had received previous reports of evidence of debonding on some tailboom panels of the specified Agusta model helicopters. This condition, if not corrected, could result in failure of a tailboom and subsequent loss of control of the helicopter. DATES: Effective on February 8, 2010,to all persons except those persons to whom it was made immediately effective by Emergency AD 2009- 19-51, issued on September 16, 2009, which contained the requirements of this amendment. Comments for inclusion in the Rules Docket must be received on or before March 23, 2010.
2014-15-13: We are superseding Airworthiness Directive (AD) 2005-15-04 for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL- 601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. AD 2005-15-04 required operators to assign serial numbers or part numbers to certain landing gear parts; establish the number of landings on the parts, if necessary; and revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to reflect the new life limits of the landing gear parts. This new AD adds airplanes to the applicability, requires operators to assign serial numbers or part numbers to certain additional landing gear parts to establish the number of landings on the parts if necessary, and requires operators to record in all required airplane technical records and manuals the new part numbers, serial numbers, and landings assigned to these parts. This AD was prompted by reports that landing gear parts that have safe-life limits but do not have serial numbers or part numbers can be removed from one landing gear and re-installed on another, making tracking difficult. We are issuing this AD to prevent life-limited landing gear parts from being used beyond their safe-life limits, which could lead to collapse of the landing gear.
2013-13-13: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD was prompted by the revision of certain airworthiness limitation items (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program to incorporate the limitations section. We are issuing this AD to prevent fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane.
72-18-01: 72-18-01 BEECH: Amdt. 39-1505. Applies to Models 35, A35, B35 and C35 airplanes (Serial Numbers D-1 through D-2900) with a P/N 35-924065 fuel unit modified by the installation of Beech Kit No. 35-5030S (Serial Numbers 100 through 989) or any equivalent installation using a warning light with a dimming feature. (NOTE: Installation of either Beech Kit No. 35-5030S or P/N 35-924230 fuel unit is required by AD 69-18-01.) To prevent dimming of fuel selector valve disengagement warning light, unless already accomplished, accomplish the following: A) Effective immediately until Paragraph B has been accomplished, adjust the dimming lens on the fuel selector valve disengagement warning light to maximum bright. B) Within the next 25 hours' time in service after the effective date of this AD, either replace MS 25041-2 light indicator assembly with MS 25041-6 light indicator assembly or replace the dimming lens assembly of the MS 25041-2 light assembly with the non-dimming lens assembly from an MS 25041-6 light assembly. Any equivalent method of compliance must be submitted to and approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective August 29, 1972.
2021-05-21: The FAA is superseding Airworthiness Directive (AD) 2017-23-08 for Agusta S.p.A. (now Leonardo S.p.a.) Model AB139 and AW139 helicopters. AD 2017-23-08 required repetitively inspecting the main rotor (M/R) rotating scissors, removing certain lower half scissor spherical bearings (bearings) from service, replacing the removed bearings with a new bearing, and installing a special nut. This new AD retains the requirements of AD 2017-23-08 and requires replacing each affected bearing with a certain part-numbered bearing. This AD was prompted by investigation results determining that a quality control issue may have affected the production of the affected bearings. The actions of this AD are intended to address an unsafe condition on these products.
2014-16-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of in-flight uncommanded rudder movements. This AD requires revising the airplane flight manual (AFM) to incorporate an uncommanded yaw motion procedure. We are issuing this AD to prevent in- flight uncommanded rudder movements, which could lead to structural failure and subsequent loss of the airplane.