Results
2013-26-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model 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 was prompted by a report that traces of oil could be found in the crew oxygen system due to the use of incorrect pressure testing procedures during manufacturing. This AD requires cleaning the crew oxygen system. We are issuing this AD to detect and correct oil contaminants, which could cause an ignition and result in a fire in the oxygen system.
2013-26-03: We are superseding airworthiness directive (AD) 2011-24-09 which applied to certain Airbus Model A340-200 and A340-300 series airplanes. AD 2011-24-09 requires inspections to verify electrical bonding for the water drain system and ventilation intake system, and modification if necessary. This new AD requires revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations, and adds additional airplanes to the applicability. This AD was prompted by a determination that existing maintenance requirements are not adequate to address the unsafe condition. 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.
97-18-02R1: This amendment revises an existing airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. ( )HC-( )(2,3)(X,V)( )-( ) series and HA-A2V20-1B series propellers with aluminum blades. That AD currently requires initial and repetitive dye penetrant and eddy current inspections of the blade and an optical comparator inspection of the blade retention area, and, if necessary, replacement with serviceable parts. In addition, that AD currently requires initial and repetitive visual and magnetic particle inspection of the blade clamp, dye penetrant inspection of the blade internal bearing bore, and, if necessary, replacement with serviceable parts. Also, for all HC-(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, that AD currently requires an additional initial and repetitive visual and magnetic particle inspection of the hub, and, if necessary, replacement with serviceable parts. This amendment revises that AD by permitting the replacement of affected propellers with Hartzell Propeller Inc. model "MV" series propellers as an optional terminating action for the initial and repetitive inspections of that AD. This amendment is prompted by type certification approval of the Hartzell "MV" series propellers that are direct replacements for the affected propellers, and service bulletin approval to allow modification of affected propellers to the "MV" type design configuration. The actions specified by this AD are intended to prevent blade separation due to cracked blades, hubs, or blade clamps, which can result in loss of control of the airplane.
2013-25-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires, depending on airplane configuration, replacing fuel pump power control relays with new relays having a ground fault interrupter (GFI) feature, installing ground studs and a bonding jumper, doing certain bonding resistance measurements, and changing the GFI relay position. This AD also requires revising the maintenance program to incorporate certain airworthiness limitations. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2013-25-11: We are superseding Airworthiness Directive (AD) 2010-24-07 for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. AD 2010- 24-07 required repetitive inspections of the 80VU rack lower lateral fittings for damage, repetitive inspections of the 80VU rack lower central support for cracking, and corrective action if necessary. AD 2010-24-07 also specified optional terminating action for the repetitive inspections. This new AD reduces the inspection compliance time, adds an inspection of the upper fittings and shelves of the 80VU rack, and adds airplanes to the applicability. This AD was prompted by reports of worn lower lateral fittings of the 80VU rack. We are issuing this AD to detect and correct damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers, and if occurring during a critical phase of flight, could result in reduced control of the airplane.
2013-24-05: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires a one-time inspection of the free turbine (FT) module (M04) for the affected Turbomeca S.A. Arriel 1 engines and, if a discrepancy is found, repair of the affected module. This AD was prompted by a ``chip illumination event'' in flight on a Turbomeca S.A. Arriel 1 engine. We are issuing this AD to prevent a loss of FT bearing lubrication, resulting in FT module failure, damage to the engine, and damage to the aircraft.
2013-24-19: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires visually inspecting each jettisonable emergency exit window panel (window) for sealant, and removing any sealant that exists in the window's extruded sections. This AD was prompted by jettison tests during routine maintenance inspections that showed the windows failed to jettison. The actions of this AD are intended to prevent failure of the windows to jettison, so helicopter occupants can exit the aircraft during an emergency.
2025-05-03: The FAA is superseding Airworthiness Directive (AD) 2024-06-06 for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent7000-72 and Trent7000-72C engines. AD 2024-06-06 required revising the airworthiness limitations section (ALS) of the operator's existing approved engine maintenance or inspection program, as applicable, to incorporate new or more restrictive tasks and limitations and associated thresholds and intervals for life-limited parts. Since the FAA issued AD 2024-06-06, the manufacturer has revised the engine time limits manual (TLM) to introduce new or more restrictive tasks and limitations and associated thresholds and intervals for life-limited parts, which prompted this AD. This AD requires revising the ALS of the existing approved engine maintenance or inspection program, as applicable, to incorporate new or more restrictive tasks and limitations and associated thresholds and intervals for life-limited parts, 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.
2013-24-18: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-200B, -200C, -200F, -300, and 747SR series airplanes. This AD was prompted by reports of cracks of both lower chords and web on certain outboard struts. This AD requires repetitive inspections for cracking of the lower spar chords and web, web lower spar chord modification, which includes inspections for cracking of the lower spar chords, and repetitive post modification inspections for cracking of the lower spar web and chord; and applicable corrective actions. We are issuing this AD to prevent cracked chords and web on certain outboard struts, which, if the chord severs, could result in reduced structural integrity of the diagonal brace load path and of the strut-to-wing attachment, and \n\n((Page 76048)) \n\nconsequent separation of a strut and engine from the airplane during flight.
2013-24-09: We are adopting a new airworthiness directive (AD) for certain EADS CASA (Type Certificate Previously Held by Construcciones Aeron[aacute]uticas, S.A.) Model C-212-CB, C-212-CC, C-212-CD, C-212- CE, and C-212-DF airplanes. This AD was prompted by a report of the propeller pitch control (PPC) lever becoming disconnected from the engine due to a missing bolt. This AD requires modifying the PPC lever attachment system. We are issuing this AD to prevent PPC shaft disconnection, which could lead to a loss of propeller pitch control, possibly resulting in uncommanded change to the engine power settings and consequent reduced controllability of the airplane.
2013-24-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by a report that the seat track attachment of body station 520 flexible joint is structurally deficient in resisting a 9g forward emergency load condition in certain seating configurations. This AD requires replacing the pivot link assembly on certain seats, modifying the existing seat track link assembly fastener on certain seats, or replacing the seat track link assemblies on certain seats. Also, for certain airplanes, this AD requires installing a new seat track link assembly or modifying the seat track link assembly. For certain other airplanes, this AD requires inspecting, changing, or repairing the seat track link assembly. We are issuing this AD to prevent seat detachment in an emergency landing, which could cause injury to occupants of the passenger compartment and affectemergency egress.
2013-23-18: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and -115B turbofan engines. This AD was prompted by multiple events of a leaking variable bypass valve (VBV) actuator fuel supply tube. This AD requires replacement of this VBV actuator fuel supply tube with a part eligible for installation. We are issuing this AD to prevent failure of the affected fuel supply tube, fuel leakage, engine fire, and damage to the airplane.
2000-24-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, and Model A300-600 series airplanes, that requires repetitive inspections to detect chafing and the existence of repairs of the harness of the high-level sensor of the fuel surge tanks, and to detect chafe marks on the support canisters of the magnetic level indicators; and follow-on corrective actions, if necessary. This amendment also requires modification of the harness for the high-level sensor of the outer wing fuel tanks, which terminates certain repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing of the harness of the high-level sensor, which could result in a short circuit and consequent fuel ignition source inside the outer wing fuel tanks.
75-08-02: 75-08-02 DE HAVILLAND: Amendment 39-2149. Applies to de Havilland Model DHC- 6 Series Twin Otter Aircraft, Serial Nos. 1 through 135 inclusive. Compliance required as indicated. To preclude the hazard created by the failure of the right hand aileron control cable through contact with DC electrical power cable coded 2P66A8, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this A.D., alter the attachment of terminal block TB-17 and the routing of the cable harness to terminal block TB-17 and TB-18 in accordance with de Havilland Service Bulletin No. 6/304, Revision B, dated June 28, 1974, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA inspector, the compliance time specified in this A.D. may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective April 7, 1975.
2013-24-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes; and Model 720 and 720B series airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the left- and right-hand wing fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, and to replace any door with an impact-resistant access door if necessary. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. This AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire.
2013-24-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of fractured rudder pedal tubes installed on the pilot-side rudder bar assembly. This AD requires repetitive inspections for cracking and damage of both pilot-side rudder pedal tubes, and replacement of affected pilot-side rudder bar assemblies if necessary. We are issuing this AD to detect and correct cracking of both pilot-side rudder pedal tubes, which could result in loss of pilot rudder pedal input causing reduced yaw controllability or a runway excursion.
2000-02-28: This document adopts a new airworthiness directive (AD) that applies to all AeroSpace Technologies of Australia Pty Ltd. (AeroSpace Technologies) Models N22B and N24A airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle
71-24-02: 71-24-02 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1334. Applies to Model 1100 and FH-1100 Type Helicopters certificated in all categories. Compliance required as indicated. To preclude fatigue failure of the transmission mount strut, P/N 24-28031, due to internal corrosion, accomplish the following: Within the next 30 days after the effective date of this AD, unless already accomplished replace P/N 24-28031 left side, lateral, adjustable transmission strut with P/N 24-28031-11 strut in accordance with Section 28 of the FH-1100 Service Manual or an alternate method approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. Upon installation of MS-21252 fork fitting apply RTV-102 sealant or equivalent to the threads of fitting and under AN316-5R retaining nut. This amendment is effective November 24, 1971.
2018-07-15: We are adopting a new airworthiness directive (AD) for XtremeAir GmbH Model XA42 airplanes equipped with an engine mount part number XA42-7120-151. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking of the diagonal strut of the engine mount frame. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-24-08: We are superseding airworthiness directive (AD) 2006-06-14 for certain Airbus Model A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200 series airplanes, and A321-100 and A321-200 series airplanes. AD 2006-06-14 required operators to review the airplane's maintenance records to determine the part numbers of the magnetic fuel level indicators (MFLIs) of the wing fuel tanks, and perform related investigative and corrective actions if necessary. This new AD also requires an inspection (improved method) to determine the part numbers of the MFLIs, and, if necessary, replacement of the MFLI or repair. This AD was prompted by information that the related investigative actions of AD 2006-06-14 are not fully effective and that an affected MFLI could still be installed on airplanes on which the [[Page 71993]] related investigative actions were accomplished. We are issuing this AD to prevent an ignition source in the wing fuel tank in the event of a lightning strike, which could result in a fire or explosion.
2003-12-15: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. This amendment requires introducing an alternative technique to ultrasonically inspect installed fan blades on-wing using a surface wave ultrasonic probe. This action also adds the application of Metco 58 blade root coating as an optional terminating action. This amendment is prompted by the discovery of cracks on LPC fan blade roots during an engine overhaul. The actions specified by this AD are intended to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
75-17-12: 75-17-12 SLINGSBY SAILPLANES: Amendment 39-2314. Applies to Slingsby T59D Kestrel gliders certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent dive brake retraction failure, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, install a placard on the instrument panel in full view of the pilot reading: "AIR BRAKE EXTENSION LIMITATION FINAL APPROACH 50% FLAREOUT ON LANDING 100% CRUISE NONE (0%)" (b) Within the next 50 hours' time in service after the effective date of this AD, replace the dive brake control mechanism with the linear type dive brake control mechanism, P/N 59A-45-717, in accordance with Slingsby Sailplanes Technical Instruction No. 75 dated May 21, 1975, or an FAA approved equivalent. (c) The placard required by paragraph (a) of this AD may be removed after the work specified in paragraph (b) of this AD has been accomplished. This amendment becomes effective August 18, 1975.
2013-24-01: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 747-8 and 747-8F series airplanes and Model 787-8 airplanes powered by GEnx engines. This AD requires revising the airplane flight manual to advise the flight crew of potential ice crystal icing (ICI) conditions at high altitudes, and to prohibit operation in moderate and severe ICI conditions. This AD also requires inspecting the engine after any ICI event is detected by the flight crew. This AD was prompted by reports of engine damage and thrust loss events as a result of flying in high altitude ICI conditions. We are issuing this AD to ensure that the flight crews have operating instructions to avoid flight into ICI conditions that can lead to engine damage and thrust loss events; unrecoverable thrust loss on multiple engines can lead to a forced landing.
2013-23-12: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 turbofan engines. This AD requires replacement or repair of the low-pressure (LP) compressor fan blade set before reaching a specified number of flight cycles since new (FCSN) or flight cycles since last leading edge profile blade repair (FCSLR). This AD was prompted by reports of erosion of the leading edge profile of the LP compressor blade set contributing to fan blade flutter. We are issuing this AD to prevent failure of the LP compressor blades, which could lead to an uncontained engine failure and damage to the airplane.
67-08-05: 67-08-05 FAIRCHILD-HILLER: Amdt. 39-365 Part 39 Federal Register March 11, 1967. Applies to Model F-27 Series Airplanes Incorporating Stewardess Seat Assembly, Fairchild Drawings No. 27-770633 and 27-770634. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent injury to occupants of stewardess seat assemblies, accomplish the following: (a) Conspicuously post in the vicinity of the stewardess seat and in full view of the seat occupant a placard reading as follows: "Do not occupy stewardess jump seat during take-off or landing." (b) The placard required in (a) may be removed when there has been incorporated into the seat assembly a modification approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. This directive effective March 11, 1967.