Results
71-11-08: 71-11-08 MCDONNELL DOUGLAS: Amdt. 39-1217. Pursuant to the authority of the Federal Aviation Act of 1958, delegated to me by the Administrator, the following airworthiness directive, applicable to all operators of Douglas DC-9 and Military C-9A airplanes, was effective immediately upon receipt of telegram dated May 10, 1971. \n\n\tBecause of repeated incidents of the pilot's or first officer's instrument panel assemblies sliding aft; and in one instance, producing control column interference, one of the following alternate actions is to be accomplished within 25 flight hours in service after receipt of this telegram: \n\n\t(1)\tInstall placard on captain and first officer instrument panel stating "Check panel security before takeoff." Or \n\n\t(2)\tIncorporate a check item in flight crew aircraft acceptance check list stating "Check security of captain and first officer instrument panels." Or \n\n\t(3)\tIn the maintenance program include security of captain and first officer instrument panel as a "required inspection item" whenever the panels are disturbed, subject to the approval of the assigned principal inspector. \n\n\t(4)\tSecondary safety latches may be installed in accordance with Douglas Service Bulletin 31-16, dated October 14, 1969, or later FAA approved revision. Accomplishment of this modification will constitute of itself compliance with this AD. \n\n\tEquivalent methods of compliance must be referred to the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated May 10, 1971.
2020-24-07: The FAA is superseding Airworthiness Directive (AD) 2018-26-02 for Airbus Helicopters (previously Eurocopter France) Model AS350B3, EC130B4, and EC130T2 helicopters. AD 2018-26-02 required inspecting the pilot's and co-pilot's throttle twist for proper operation. This new AD retains the requirements of AD 2018-26-02 and adds calendar time compliance times for the required actions. This AD was prompted by a public comment that prompted additional review. The actions of this AD are intended to address an unsafe condition on these products.
2009-23-04: We are adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive replacement of the internal electrical feed-through connectors of the boost pumps of the main fuel tank. This AD results from a report of cracking in the epoxy potting compound on the internal feed-through connector of the fuel boost pump in the area of the soldered wire connector lugs. We are issuing this AD to prevent a hazardous electrical path from the dry side to the wet side of the fuel boost pump through a cracked feed- through connector, or between pins or a pin and the shell on one side of the feed-through connector, which could create an ignition source on the wet side of the fuel boost pump or cause a fire in the fuel pump enclosure and lead to subsequent explosion of the fuel tank.
2003-25-01: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters with a Breeze 300-pound electric hoist (hoist) installed that requires modifying and re-identifying the hoist operator control unit and replacing certain fuses. This amendment is prompted by a test of a hoist that revealed an anomaly in the electrical control circuit. The actions specified by this AD are intended to prevent failure of the hoist pyrotechnic squib electrical control unit, lack of adequate current to activate the hoist pyrotechnic squib, an inability of the pilot to cut the rescue hoist cable in the event of cable entanglement or other emergency, and subsequent loss of control of the helicopter.
2009-23-02: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: During the Acceptance Test Procedure (ATP) of returned Inboard Flap Actuators * * * an excessive wear condition was identified regarding endplay between the flap actuator and ball screw. Excessive wear of the screw and ball nut could potentially lead to a flap system jam. * * * * * * * * The unsafe condition is a flap system jam, which could result in a skewed flap condition with consequent reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
67-02-05: 67-02-05 VICKERS: Amdt. 39-323 Part 39 Federal Register December 20, 1966. Applies to Viscount Models 744 and 745D airplanes. Compliance required as indicated. To prevent further failures of the flying control rod guide beam at Fuselage Station 399.25, accomplish the following: (a) Within the next 25 landings after the effective date of this AD, unless already accomplished within the last 225 landings, and thereafter at intervals not to exceed 250 landings from the last inspection until modified in accordance with (c) or repaired in accordance with (b), visually inspect the control rod guide beam attached to the bottom of the floor beam at Fuselage Station 399.25 for cracks at the top and bottom extremities of the vertical slot for the trim chains. (b) Repair cracked beams before further flight in accordance with British Aircraft Corporation PTL 261, Issue 1, or later ARB-approved issue, or an FAA-approved equivalent, and either inspect as specified in (a) at intervals not to exceed 500 landings from the last inspection until modified in accordance with (c) and repair in accordance with this paragraph if applicable, or modify cracked beams before further flight in accordance with (c). (c) Modify beams in accordance with British Aircraft Corporation Modification D.3179 within the next 1500 landings after the effective date of this AD. (d) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (e) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, Europe, Africa, Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This directive effective January 19, 1967.
2003-24-13: The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes that are equipped with a Honeywell KAP 140 autopilot computer system installed on the center instrument control panel near the throttle. This AD requires you to install an update to the operating software of the KAP 140 autopilot computer system, change the unit's part number, and change the software modification identification tag. This AD is the result of reports of inadvertent and undetected engagement of the autopilot system. We are issuing this AD to prevent unintentionally engaging the KAP 140 autopilot computer system, which could cause the pilot to take inappropriate actions.
2020-25-01: The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. (Textron) (type certificate previously held by Beechcraft Corporation) Models F90, 65-90, 65-A90, B90, C90, H90 (T-44A), E90, 65-A90-1 (JU-21A, U-21A, RU-21A, RU-21D, U-21G, RU- 21H), 65-A90-2 (RU-21B), 65-A90-3 (RU-21C), 65-A90-4 (RU-21E, RU-21H), 99, 99A, 99A (FACH), A99, A99A, B99, C99, 100, A100 (U-21F), and B100 airplanes. This AD was prompted by reports of fatigue cracks in the lower forward wing fitting. This AD requires a one-time inspection for the presence of washer part number (P/N) 90-380058-1 on the left-hand (LH) and right-hand (RH) lower forward wing bolt and, if applicable, removing washer P/N 90-380058-1, inspecting the wing fitting, bolt, and nut, replacing the wing fitting if it is cracked, and replacing the washer with washer P/N 90-380019-1. The FAA is issuing this AD to address the unsafe condition on these products.
95-09-04: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 and -300 series airplanes, that requires an inspection to verify the integrity of the shield grounds for the cable harness of the electronic engine control (EEC), and correction of any discrepancy. This amendment also requires measurement of the electrical resistance of certain shield grounds, and repair, if necessary. This amendment is prompted by a report of an engine flameout after a lightning strike, due to several shields for the cable harness of the EEC not being properly grounded to the airframe. The actions specified by this AD are intended to prevent engine flameout due to insufficient protection of the EEC.
59-24-03: 59-24-03 BROWN-LINE CORPORATION SAFETY BELT: Applies to All Model WB-2002-2 Safety Belts. Investigation of two recent accidents involving aircraft in which the subject model safety belts were installed, disclosed that the wearer could not free himself from the belt, thereby preventing his escape from the aircraft. The design of this belt buckle is such that it will not enable the wearer to quickly and easily release the belt from the buckle. Thus this belt does not conform with Section 4.1.2 of TSO-C22 (See NOTE) and compliance is considered essential to safety in cases of fire or emergencies involving landings in water. Accordingly, since this model safety belt does not meet the necessary safety requirements, it is not acceptable for installation in civil aircraft. Furthermore, all belts of this model that are in service must be replaced with acceptable safety belts within the next 25 hours of service time or the next periodic inspection whichever occurs first. NOTE: Section 4.1.2 of TSO-C22 states in part: ". . . . shall include an easily operable quick release mechanism which will enable the wearer to release himself easily under a load simulating the wearer hanging in the belt".
2003-24-14: 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. This action requires one-time inspections to detect discrepancies of electrical wiring installations in various areas of the airplane, and corrective action if necessary. The actions specified by this AD are intended to prevent smoke and fire in various areas of the airplane due to heat damage and/or electrical arcing of improperly installed wiring. This action is intended to address the identified unsafe condition.
2003-24-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell \nDouglas Model MD-11 series airplanes, that currently requires performing a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 integrated drive generator (IDG); repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG. This amendment revises the applicability of the existing AD by adding certain airplanes and removing certain other airplanes. The actions specified by this AD are intended to prevent chafing and arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. This action is intended to address the identified unsafe condition.
95-08-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires replacement of the currently installed door opening actuators of the emergency off-wing escape system with new, improved actuators. This amendment is prompted by reports indicating that the requirements of a previously issued AD do not adequately preclude leakage from these actuators. The actions specified by this AD are intended to prevent failure of the escape slide to deploy due to failure of the door opening/snubbing actuator, which could delay and possibly jeopardize successful emergency evacuation of an airplane.
2008-04-18 R1: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. 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 describes the unsafe condition as: It has been found that former revisions of the Maintenance Review Board Report (MRBR) of the EMB-120( ) aircraft do not fully comply with some Critical Design Configuration Control Limitations (CDCCL) and Fuel System Limitations (FSL). These limitations are necessary to preclude ignition sources in the fuel system, as required by RBHA-E88/SFAR-88 (Special Federal Aviation Regulation No. 88). * * * * * The potential of ignition sources, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. This AD requires actions that are intended to address the unsafecondition described in the MCAI.
2020-25-04: The FAA is superseding Airworthiness Directive (AD) 2016-24-08 for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211- Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model turbofan engines. AD 2016-24-08 required repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. This AD retains the requirements to perform repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. As a terminating action to these inspections, this AD also requires the modification of the engine upper bifurcation nose fairing assembly. The FAA is issuing this AD to address the unsafe condition on these products.
57-06-01: 57-06-01 COLONIAL: Applies to Model C1 Aircraft Serial Numbers 2 Through 10 Inclusive, and Serial Number 13. Compliance required by May 1, 1957. To prevent unwanted extension of the landing gear, a more positive lock must be installed for the landing gear selector valve lever in accordance with Colonial Service Bulletin No. 1 dated January 25, 1957.
95-08-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires repetitive inspections of the attachment bolts and nuts in the rear spar root joint attachment fittings at wing rib 2 for integrity of nuts, tightness of bolts, and/or fuel leaks; and repair, if necessary. That AD was prompted by fuel leaks from bolt positions on the rear spar attachment fitting at wing rib 2. This amendment provides for an optional terminating modification for the repetitive inspections, and expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent fuel leaks and a subsequent fire.
69-08-10: 69-08-10 AERO COMMANDER DIVISION, NORTH AMERICAN ROCKWELL CORPORATION: Amdt. 39-754. Applies to all Aero Commander Model 1121 series airplanes. Compliance required within the next 100 hours' time in service after the effective date of this A.D., unless already accomplished. To assure required trim capability at the approved aft center of gravity limit, accomplish the following: Modify the horizontal stabilizer trim system in accordance with Part II of Aero Commander Service Bulletin No. J-4B dated February 28, 1969, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southwest Region, Fort Worth, Texas. This amendment becomes effective May 24, 1969.
2009-22-09: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: A change in dimensions of the fuse blocks in the Auxiliary Power Unit (APU) Start Contactor Assembly (ASCA) box assembly can cause an incorrect interface between the bus bars and fuses. This condition can result in an increase in temperature, which could damage the ASCA box and/or compromise the availability of battery bus supply. The unsafe condition could result in the ignition of a fire in the ASCA box. We are issuing this AD to require actions to correct the unsafe condition on these products.
96-12-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires inspections to detect missing fasteners, cracked fitting angles, and elongated fastener holes in certain frames, and correction of discrepancies. It also provides an optional terminating action. This amendment is prompted by discrepancies found at the fitting angles on the frame at which a certain electronic rack is attached. The actions specified by this AD are intended to prevent damage propagation that could lead to failure of the rack-to-structure attachment points, and subsequently could result in loss of airplane systems, structural damage, and possible electrical arcing.
2003-24-12: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. This AD requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This AD is prompted by a report of a failed gearbox pressure tube that resulted in an engine fire. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.
2009-22-03: The FAA is superseding an existing airworthiness directive (AD) for Hartzell Propeller Inc. ()HC-()2Y()-() series propellers with non-suffix serial number (SN) propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines. That AD currently requires initial and repetitive eddy current inspections (ECIs) of the front cylinder half of the propeller hub for cracks and removing cracked hubs from service before further flight. In addition, that AD allows installation of an improved design propeller hub (suffix SN "A'' or "B'') as terminating action to the repetitive ECI. This ad requires the same actions but changes the affected propeller series designation to ()HC-()2Y(K,R)-() series propellers with non-suffix SN propeller hubs and suffix SN letter "E'' propeller hubs. This AD also expands the engine eligibility to include Lycoming LIO-, TO-, LTO-, AIO-, and TIO-360-series engines. This AD results from the need to make changes to the affected seriesdesignation of propellers, to expand the engine applicability, and to respond to comments received on AD 2006- 18-15. We are issuing this AD to prevent failure of the propeller hub causing blade separation and subsequent loss of airplane control.
95-06-53: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-06-53 that was sent previously to all known U.S. owners and operators of Boeing Model 737 series airplanes by individual telegrams. This AD requires identification of the part and serial numbers of the main rudder power control unit (PCU), and replacement of certain PCU's with serviceable parts, if necessary. This amendment is prompted by reports indicating that certain modified rudder PCU's malfunctioned and failed functional retesting. The actions specified by this AD are intended to prevent the rudder actuator piston and the rudder from operating with reduced force capability or moving in a direction opposite the intended direction due to malfunctioning of the rudder PCU; these conditions could result in reduced controllability of the airplane.
2009-22-04: We are adopting a new airworthiness directive (AD) for the specified ECF model helicopters. 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 freezing of the route display on the navigation display (ND) in the Sector mode occurs for flight plans that include procedures in the terminal zone (departure or arrival). The MCAI AD prohibits the use of the UNS-1D navigation system (also known as the Flight Management System (FMS)) for Standard Instrument Departure (SID), Standard Instrument Terminal Arrival Route (STAR), and instrument approach procedures. The actions are intended to prevent the flight crew from relying on a frozen route ND, unanticipated increases in flight crew workload, pilot confusion in the terminal airspace environment, and subsequent loss of control of the helicopter.
2003-24-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes. This action requires installation of ceiling panels and a protective pad in the tailcone emergency exit passageway. The actions specified by this AD are intended to prevent people on board the airplane from striking their heads on exposed metal frames in the tailcone area, which could cause injury and delay or impede their evacuation during an emergency. This action is intended to address the identified unsafe condition.