Results
2004-11-07: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, that requires implementation of a program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This action is necessary to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
2012-09-12: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and - 233 airplanes; and Model A321-111, -112, and -131 airplanes; equipped with an additional center tank (ACT). That AD currently requires identifying the part number of the ACT and, for certain ACTs, replacing the outer ACT manhole cover and seal. This new AD requires modifying certain ACTs by replacing the manhole seal with a new seal; adding certain ACT equipped airplanes to the applicability; and removing Model A320-111 airplanes from the applicability. This AD was prompted by reports that the modification required by the current AD was not fully effective. We are issuing this AD to prevent fuel and/or vapor leakage, which could result in a combustible fuel vapor/air mixture in the cargo compartment, and consequent fire risk.
2021-23-16: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD was prompted by 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 identifies the unsafe condition as chafing of the engine fuel feed line hoses. This AD requires inspecting the engine fuel feed line hoses and the electrical wiring and rerouting all fuel lines. The FAA is issuing this AD to address the unsafe condition on these products.
98-21-15: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires modifying the oxygen generators. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent failure of the oxygen generators caused by misalignment of the firing pin, which could result in crew incapacitation and loss of the airplane.
2004-11-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A (including C- 29A and U-125 variant) and 800B airplanes; and Model Hawker 800 (including U-125A variant) and 800XP airplanes; that requires a functional test of the engine fire extinguishing wiring for the appropriate installation; verification of the correct wiring connector installation; correction of wiring if necessary; and installation of new marker bands. This action is necessary to prevent incorrect wiring of the engine fire extinguisher bottles, which could result in one or both fire extinguisher bottles being discharged into the wrong engine nacelle. This action is intended to address the identified unsafe condition.
2021-23-19: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. 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 identifies the unsafe condition as insufficient separation of ground terminations for individual power sources and static grounds. This AD requires inspecting and separating, if applicable, the battery and generator common ground connections on the airframe. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-09: The FAA is superseding Airworthiness Directive (AD) 2015-16-07 R1, which applied to certain Reims Aviation S.A. (type certificate now held by ASI Aviation) Model F406 airplanes. AD 2015-16-07 R1 required inspecting the left-hand and right-hand rudder control pedal torque tubes and replacing with a serviceable part as necessary. Since the FAA issued AD 2015-16-07 R1, the European Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD retains the requirements of AD 2015-16-07 R1, expands the applicability, and requires repeating the inspections using updated procedures. The FAA is issuing this AD to address the unsafe condition on these products.
73-07-08: 73-07-08 PRATT & WHITNEY: Amendment 39-1616 as amended by Amendment 39-1630. Applies to all Pratt & Whitney JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3 and JT3D-3B model engines containing fuel control to fuel return line elbow P/N 424790 and jam nut P/N 217477. Compliance required within the next 500 hours time in service after the effective date of this AD and every 1000 hours in service thereafter, or until modified in accordance with the service bulletin referenced in paragraph (b)(2) or equivalent method approved by the Chief, Engineering and Manufacturing Branch, New England Region. To prevent the possibility of fuel leakage due to loosening of fuel control to fuel pump return tube elbow P/N 424790, and jam nut P/N 217477, check jam nut torque value. (a) If found to be a minimum of 285 in-lbs., continue in service operation. (b) If the jam nut is found to be less than 285 in-lbs., break the connection and examine the mating threads of the elbow P/N 424790 and fuel control cover P/N 704972-1 on their loaded sides for wear. NOTE: The loaded side will be on the fuel side (inside) rather than the air side (outside) of the cover. (1) If the threads are not worn remake the fitting according to the instructions given in the Overhaul Manual, P/N 411568, Section 72-00, Fits and Clearances. (2) If the threads of the elbow. P/N 424790, or fuel control cover P/N 704972-1, are found worn replace with new or serviceable parts of same part number or with P/N 483848 elbow and associated hardware in accordance with Pratt & Whitney Service Bulletin No. 1511 Revision 4, dated June 20, 1969, or later FAA approved revision. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust repetitive inspection intervals specified in this AD. Amendment 39-1616 became effective April 11, 1973. This amendment 39-1630 becomes effectiveupon publication in the Federal Register.
96-12-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 800A and Model Hawker 800 airplanes, that requires modification of the airframe structure in the lower area of the fuselage aft of the wing rear spar. For certain airplanes, this amendment also requires a functional test to determine if a particular bolt fouls the flap control system. This amendment is prompted by reports of restricted control of the aileron due to water accumulation that froze in the area around an aileron pulley located in the lower area of the fuselage aft of the wing rear spar. The actions specified by this AD are intended to prevent such water accumulation, which could freeze and result in restricted control of the ailerons; subsequently, this could reduce the pilot's ability to initiate roll control during critical phases of flight.
2004-11-02: This amendment adopts a new airworthiness directive (AD), [[Page 31001]] applicable to certain Saab Model SAAB SF340A and Model SAAB 340B series airplanes, that requires inspections of the internal and external structure of the nacelles for cracks, deformations, or other damage, and corrective actions if necessary. This action is necessary to prevent fatigue cracks in the outer flange of the nacelle frame, which could result in reduced structural integrity of the nacelle supporting structure. This action is intended to address the identified unsafe condition.