Results
2000-12-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney PW4000 Series Turbofan Engines, that currently requires revisions to the Time Limits Section of the manufacturer s Engine Manuals (EM s) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2003-11-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires inspections of the linear variable differential transducers (LVDTs) of the autopilot for discrepancies, and follow-on actions if necessary. This amendment is prompted by information from the manufacturer advising that certain LVDTs were delivered with an undersize nylok element on the threaded extension. The actions specified by this AD are intended to prevent failure of the LVDTs, which could result in an automatic pitch trim malfunction or an autopilot disconnect, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2025-05-06: The FAA is superseding Airworthiness Directive (AD) 2022-01-02, which applied to certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. AD 2022-01-02 required inspecting for corrosion of the nacelle to wing rear spar attachment pins, and the nacelle to landing gear attachment pins, and doing all applicable corrective actions. This AD was prompted by a determination that some operators were unable to identify the airplanes subject to each requirement. This AD continues to require the actions specified in AD 2022-01-02, clarifies the affected airplanes for each required action, and revises the applicability by removing Model DHC-8-400 airplanes; as specified in Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-08: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW118A, PW118B, PW119B, PW119C, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD was prompted by reports of fractures of the first-stage power turbine (PT) blade. This AD requires inspection of the first-stage PT blades and the removal from service of those blades that fail the inspection or their replacement with blades eligible for installation. We are issuing this AD to prevent fracture of the first-stage PT blade, possible engine fire, and damage to the airplane.
97-03-17: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 and 757 series airplanes, that requires repetitive visual inspections to detect discrepancies of the wire terminal assembly, electrical connector, and wire insulation on the fuel pump; and replacement of the fuel pump with a new fuel pump, if necessary. This amendment also requires repetitive insulation resistance tests of the fuel pump wiring. This amendment is prompted by reports of fuel leaks at the fuel boost and override/jettison pumps due to corrosion. The actions specified by this AD are intended to prevent such a fuel leakage, which could result in a fire at the location of the affected fuel pump.
73-24-02: 73-24-02 SEMCO: Amendment 39-1746 is further amended by Amendment 39-2741. Applies to Model 30-AL, Serial Numbers SEM C1, SEM C2, SEM 11 to SEM 118 inclusive, Model TC-4A, Serial Numbers SEM 81 to SEM 118 inclusive, and Model "Model T," Serial Numbers SEM 28, SEM 60, SEM 61, SEM 62, SEM 64 through SEM 73, SEM 76, SEM 77 and SEM 78 to SEM 118 inclusive balloons certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent fuel leakage accomplish either 1 or 2 below: 1. (a) Remove the Amflo quick change female coupler part number C-2 from the lower end of the Imperial fuel hose Part Number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Install an Amflo quick change male plug Part Number CP-2 or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, on the lower end of the Imperial fuel hose Part Number Y905. (c) Remove the Amflo quick change male plugs Part Number CP-1 from the fuel tank 1/4" brass tee. (d) Install an Amflo quick change female coupler Part Number C-1 or an equivalent part approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the fuel tank 1/4" brass tee. 2. (a) Remove the Amflo quick change female coupler Part Number C-2 from the lower end of the Imperial fuel hose part number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Remove the Amflo quick change male plug, Part Number CP-1, from the fuel tank 1/4" brass tee. (c) Install an AN 901-2 coupling and the Amflo quick change male plug part number CP-1 which was removed in step (b) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, onto the lower end of the Imperial fuel hose Part Number Y905. (d) Install an AN 911-2 nipple and the Amflo quick change female coupling Part Number C-2 which was removed in step (a) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the 1/4" brass tee at the fuel tank. Amendment 39-1746 became effective November 26, 1973. This amendment 39-2741 becomes effective October 20, 1976.
2025-05-04: The FAA is superseding Airworthiness Directive (AD) 2019-05- 02, which applied to certain Rolls-Royce Deutschland Ltd & Co KG (RRD) (type certificate previously held by Rolls-Royce plc) Model RB211-Trent 970-84 and RB211-Trent 972-84 engines. AD 2019-05-02 required repetitive inspections of the drains mast for any crack and replacement or repair of the drains mast if necessary. Since the FAA issued AD 2019-05-02, the manufacturer has developed a modification (improved drains mast and drains support bracket), which the FAA has determined mitigates the unsafe condition. This AD was prompted by cracks found in the transition duct area of the drains mast. This AD requires modification with improved drains mast and drains support bracket. The FAA is issuing this AD to address the unsafe condition on these products.
2013-16-06: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-105C, BO- 105LS A-1, BO-105LS A-3, and BO-105S helicopters. This AD requires inspecting for debonding of the erosion protective shell (abrasion strip) on the leading edge of each main rotor blade. This AD was prompted by the discovery of abrasion strip debonding during an inspection on one Model BO-105 helicopter and also by an incident on a second Model BO-105 helicopter that lost its abrasion strip in-flight. The actions of this AD are intended to detect debonding of the main rotor blade abrasion strip, which could lead to an unbalanced main rotor, high vibrations, damage to the tail boom or tail rotor, and loss of control of the helicopter.
73-16-03: 73-16-03 BELL: Amdt. 39-1695. Applies to Model 205A-1 helicopters certificated in all categories equipped with float landing gear kit, P/N 205-706-050-1, with 200 hours or more total service time on the float gear. Compliance required as indicated: To detect possible cracks in the forward and aft cross tubes of the float landing gear, accomplish the following inspections specified in Bell Helicopter Company Service Bulletin 205- 02-73-1 dated February 16, 1973 or later approved revision or in accordance with an equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (a) Within the next 10 hours time in service after the effective date of this A.D., unless already accomplished, conduct the inspections specified in Part I, paragraphs 3 and 4 of Bell Service Bulletin 205-02-73-1. (b) At each 25 hours interval after the initial inspection, conduct the inspection specified in Part I, paragraph 6 of Bell Service Bulletin 205-02-73-1. (c) At each 100 hours interval after the initial inspection, conduct the inspection specified in Part I, paragraph 7 of Bell Service Bulletin 205-02-73-1. (d) The repetitive inspections specified herein, with the exception of the one-time inspection in (e), are no longer required after friction dampers, P/N 205-050-127-3 and 205-050- 127-5 have been installed. (e) If friction dampers have been installed on helicopters with float kit, P/N 205- 706-050-1, with cross tubes which had 200 hours or more service time at the time of damper installation, conduct the inspections specified in Part II, paragraph 1 of Bell Service Bulletin 205- 02-73-1 within 10 hours time in service, after the effective date of this A.D., unless already accomplished. (f) If a crack is found in a cross tube, replace the cross tube prior to next flight. This amendment becomes effective August 13, 1973.
2013-13-16: We are superseding airworthiness directive (AD) 2005-07-04 for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2005-07-04 required repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary; repetitive inspections for discrepancies of the ball screw assembly, and corrective action if necessary; repetitive greasing of the THSA ball nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ball nut assembly, which ends certain repetitive inspections. This new AD removes certain inspections, revises certain actions, and adds airplanes to the applicability. This AD was prompted by several reports of [[Page 47538]] disconnection of the transfer tube from the ball nut of the THSA. We are issuing this AD to prevent degraded operation of the THSA, which could result in reduced controllability of the airplane.
2013-16-02: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD requires incorporation of a new procedure into the airplane flight manual (AFM). This AD was prompted by a report of a runway excursion caused by failure of the nose landing gear position feed-back assembly. We are issuing this AD to detect and correct an incorrect angle signal causing an un-commanded nose wheel deflection, which could result in reduced controllability of the airplane.
2013-13-12: We are superseding airworthiness directive (AD) 2000-06-13 R1, which applied to certain The Boeing Company Model 737-200, -200C, -300, and -400 series airplanes. AD 2000-06-13 R1 required repetitively inspecting for cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions if necessary. AD 2000-06-13 R1 also required modifying the aft cargo door, which terminates the repetitive inspections. This new AD adds airplanes to the applicability, adds inspections and related investigative and corrective actions, revises certain inspection types, and reduces a certain compliance time for modifying the doors. This AD was prompted by reports of cracking in the forward and aft corner frames of the aft cargo door and in the lower cross beam. We are issuing this AD to prevent fatigue cracking of the corners of the door frame and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane.
2024-06-12: The FAA is superseding Airworthiness Directive (AD) 2021-24- 20, which applied to all Airbus SAS Model A350-941 and -1041 airplanes, and AD 2023-03-05, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-24-20 required repetitive water drainage and plug cleaning of the left- and right-hand slat geared rotary actuators (SGRAs) having a certain part number installed on slat 5 track 12 with certain functional item numbers. AD 2023-03-05 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2021-24-20 and AD 2023-03-05 and 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.
2013-14-06: We are adopting a new airworthiness directive (AD) for certain CFM International, S. A. (CFM) model CFM56-5 and CFM56-5B series turbofan engines. This AD was prompted by corrosion of the delta-P valve in the hydro-mechanical unit (HMU) fuel control caused by exposure to type TS-1 fuel. This AD requires cleaning, inspection, and repair of affected HMUs. We are issuing this AD to prevent seizure of the HMU, leading to failure of one or more engines and damage to the airplane.
2021-26-28: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by significant changes, including new or more restrictive requirements, made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention and the nitrogen generation system. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2013-14-11: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440), CL- 600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD requires revising the airplane flight manual (AFM) by incorporating an emergency procedure for uncommanded yaw motion. This AD was prompted by reports of airplanes experiencing uncommanded rudder movements while in flight. We are issuing this AD to advise the flightcrew of procedures to address a possible failure of the voltage regulator inside the yaw damper actuator that could lead to uncommanded yaw movement and consequent loss of the ability to control the airplane.
76-05-02: 76-05-02 TRANSPORT CATEGORY AIRPLANES: Amendment 39-2534. Applies to all transport category airplanes equipped with side-facing seats that could be used by required flight attendants, including, but not limited to, the following: Boeing Models 707-320B and 727-100 and Lockheed Model L-188 airplanes. \n\n\tCompliance is required within 30 days after the effective date of this AD, unless already accomplished. \n\n\tTo prevent injuries to flight attendants, to insure their ability to perform required duties under emergency conditions, and to insure occupant access to emergency exits, remove each side-facing flight attendant seat from the airplane. For purposes of this AD a side-facing flight attendant seat is a side-facing seat that may be used by a flight attendant during takeoff and landing. Side-facing seats which are prohibited from being used by a flight attendant, during takeoff and landing, by placard, operating limitation, or other approved method, are not side-facing flightattendant seats. \n\n\tNOTE: A flight attendant may occupy a passenger seat. However, Section 121.318(b), 121.319(b), and 121.391(d) contain equipment, location, and distribution requirements for flight attendants required for operations under Part 121. In addition, Section 121.291(a)(2)(ii) contains emergency evacuation demonstration requirements that might be applicable depending upon the extent of change in the cabin interior configuration. \n\n\tThis amendment becomes effective April 1, 1976.
86-16-06: 86-16-06 BOEING: Amendment 39-5380. Applies to all Model 747 airplanes, certificated in any category, listed in Boeing Alert Service Bulletin 747-25A2696, Revision 1, dated January 31, 1986, that are equipped with the cool gas generator inflation systems. To ensure that the escape slide inflation system operates properly, accomplish the following, unless already accomplished: \n\n\tA.\tWithin three months after the effective date of this AD, inspect the escape slide inflation system to verify the installation of acceptable self-locking nuts and replace defective nuts, if necessary, in accordance with Boeing Alert Service Bulletin 747-25A2696, Revision 2, dated May 2, 1986, or later FAA-approved revisions. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 10, 1986.
85-22-03: 85-22-03 McDONNELL DOUGLAS: Amendment 39-5154. Applies to McDonnell Douglas Model DC-10-10, -15, -30, and KC-10A (Military) series airplanes, and to Airbus Industrie Model A300 series airplanes, certificated in any category, equipped with Walter Kidde fire extinguishing containers, part number (P/N) 895240.\n\n\tCompliance required as indicated unless previously accomplished.\n\n\tTo preclude potential failures of fire extinguishing containers, P/N 895240, to discharge on command, accomplish the following unless already accomplished:\n\n\tA.\tWithin fifteen (15) days after the effective date of this AD, if both fire extinguisher containers in any one engine position have been replaced since June 20, 1985, determine the date of manufacture or rework of each fire extinguisher container (Walter Kidde P/N 895240) in accordance with McDonnell Douglas DC-10 Alert Service Bulletin A26-41, dated September 12, 1985, or later revisions approved by the Manager, Los Angeles Aircraft CertificationOffice, FAA, Northwest Mountain Region.\n\n\tB.\tIf any one fire extinguisher container (Walter Kidde P/N 895240) has been replaced since June 20, 1985, accomplish the determination specified in paragraph A., above, within thirty (30) days after the effective date of this AD.\n\n\tC.\tIf the determination made pursuant to paragraph A. or B., above, establishes that any fire extinguisher container (Walter Kidde P/N 895240) was manufactured or reworked between June 20, 1985, and December 31, 1985, and there is not a "-R" after the serial number of the fire extinguisher container, before further flight, remove the fire extinguisher container and replace it with a serviceable unit, unless it is determined that the container was manufactured or reworked using a disc from other than Lot Number 006.\n\n\tD.\tAfter the effective date of this AD, no fire extinguisher container (Walter Kidde P/N 895240) manufactured or reworked between June 20, 1985, and December 31, 1985, may be installed unless there is a "-R" after the serial number of the fire extinguisher container.\n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\tF.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.\n\n\tThis Amendment becomes effective November 4, 1985.
73-07-06: 73-07-06 PITTS AVIATION ENTERPRISES, INC.: Amdt. 39-1607 as amended by Amendment 39-1620. Applies to Pitts Model S-2A series airplanes, S/N 2001 through 2044. Compliance required as indicated. (a) Within the next 5 hours time in service after the effective date of this AD, unless already accomplished, inspect the horizontal stabilizer, P/N 2-3100, front and rear tubes, and the horizontal stabilizer support tubes, front (P/N 2-2123) and rear (P/N 2-2100-109) for cracks. (1) Disassemble the stabilizers (right and left) in accordance with instructions in Pitts Service Bulletin No. 6, Step 1, or the instructions of paragraph (a)(1) of AD 72-19-05. Also remove horizontal stabilizer root fairing. (2) Thoroughly clean the exposed portions of all tubes noted above with solvent. Dye-check the tubes in the vicinity of the AN3 bolt holes, and visually inspect for cracks. (i) If cracks are found, contact AEROTEK, INC., P.O. Box 547, Afton, Wyoming, 83110, for approved repair or repair in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, Atlanta, Georgia. (ii) If no cracks are found, reassemble in reverse order of disassembly. CAUTION: Use care on reassembly to insure that the AN365-1032 nuts on the AN3 bolts, which secure the horizontal stabilizer to the support tubes, are tight enough to prevent any axial movement of the bolt, without having any pre-load or crushing action on the tubes. (b) Repeat the inspection in paragraph (a) above every 50 hours time in service after initial inspection or until the aircraft has been modified in accordance with Pitts Service Bulletin Number 7, dated March 12, 1973. Modification in accordance with Service Bulletin Number 7 eliminates the need for repetitive inspection. Amendment 39-1607 became effective April 3, 1973, for all persons except those to whom it was made effective upon receipt of the air mail letter dated March 9, 1973, which contained this amendment. This amendment 39-1620 becomes effective April 17, 1973.
2018-06-02: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440), Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600- 2D15 (Regional Jet Series 705), and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by development of a modification to prevent uncommanded rudder movement during flight. This AD requires modifying the wiring harness of the yaw damper control system. We are issuing this AD to address the unsafe condition on these products.
2013-15-03: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters with a single hydraulic system and a certain hydraulic pump drive installed. This AD requires inspecting the hydraulic pump drive pulley bearing (pulley bearing) for leaks, rust, overheating, and condition. This AD is prompted by six reports of hydraulic pump drive belt failure caused by seizure of the pulley bearing. These actions are intended to prevent hydraulic pump drive belt failure, loss of hydraulic servo assistance, and subsequent loss of control of the helicopter.
2003-11-01: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires periodic inspections and cleaning of the drainage system cavity of the canted pressure deck, aft of the wing center section. This amendment adds new repetitive tests and inspections for discrepancies of the drainage system of the canted pressure deck; and corrective actions, if necessary. This amendment also terminates the requirements of the existing AD. The actions specified by this AD are intended to prevent ice accumulation on the lateral flight control cables and/or components due to water entering the wheel well of the landing gear and freezing, which could restrict or jam control cable movement, resulting in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2013-14-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by reports of cracks on the elevator rear spar stiffener assembly. This AD requires repetitive detailed inspections for cracking of the elevator rear spar stiffener assembly, and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the elevator rear spar stiffener assembly, which could adversely affect elevator structural stiffness, which could lead to elevator vibration and possible interference with the tab control rod. These conditions could result in flutter and consequent loss of control of the airplane.
2013-14-07: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by a report that the fire barrier seal on the external baggage door does not seal the surrounding door structure due to incorrect positioning of the barrier. This AD requires modifying the fire seal on the baggage door, including doing inspections of the fire seal for correct contact and corrective action if necessary. We are issuing this AD to prevent improper sealing of the baggage door, which could increase the risk of an uncontained fire in the baggage compartment.