Results
2017-19-04: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and/or airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2014-18-02: We are superseding Airworthiness Directive (AD) 2014-05-02 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2014-05-02 required repetitive inspections for cracking and corrosion of the aft pressure bulkhead, repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes. This AD requires the same actions as AD 2014-05-02, but revises a certain repetitive inspection interval to avoid a misunderstanding of the repetitive inspection interval for the aft pressure bulkhead. This AD was prompted by reports from operators expressing confusion regarding a certain repetitive inspection interval for the aft pressure bulkhead. We are issuing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.
58-23-01: 58-23-01 BELL: Applies to All 47B, B3, D, D1, G, G2 and H1 Helicopters. Compliance required as indicated. Service experience indicates numerous failures of the tail rotor pitch change control bearing, P/N R4AF4 and alternate P/N's SIRP and 7R4AXIC. Failures of this bearing have been partly attributed to the pitch change control shaft being bent. To preclude the possibility of losing tail rotor control, a service life of 100 hours' time in service has been established for the tail rotor pitch change bearings P/N's R4AF4, 47-641-146-1, SIRP, and 7R4AXIC. All bearings with 90 or more hours' time in service shall be retired within the next 10 hours' time in service after the effective date of this amendment, except that tail rotor pitch change bearings with 190 or more hours' time in service as of the effective date of this amendment shall be retired prior to the accumulation of 200 hours' time in service. The bearing service life of 100 hours is predicted by the maintenance of a concentric pitch change control shaft to within the allowable tolerances. To insure straightness of the pitch change control shaft, P/N 47-641-034 or P/N 47-641-045, a 600-hour inspection for runout is required. The shaft must be inspected at the next 600-hour inspection or not later than December 15, 1958, and every 600 hours thereafter. Inspect shaft for allowable runout as follows: 1. Remove shaft from tail rotor gear box in accordance with Bell Service Manual. 2. Mount shaft at acme screw thread end in collet. 3. Measure concentricity of bearing shaft diameter. This diameter must be concentric within 0.060 TIR. 4. If diameters are not concentric within 0.060, shaft must be straightened within this tolerance. (Manufacturers Urgent Action Maintenance and Overhaul Instructions, Nos. S58-41 thru S58-47, H58-10, H58-11 and H58-12, dated October 3, 1958, cover same subjects.) Revised September 21, 1961. Revised January 18, 1963.
2014-16-23: We are superseding Airworthiness Directive (AD) 2011-16-01 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-16-01 required adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and installing placards in the cockpit; replacing the frame of the emergency switch box; replacing certain horizontal stabilizer electronic control units (HSECU); revising the Limitations section of the airplane flight manual (AFM); and revising the maintenance program to incorporate a certain task. This new AD requires modifying the fly-by-wire (FBW) standard; and operational testing of the electric motors reversion relays and trim emergency command of the horizontal stabilizer trim system (HSTS), and repairs if necessary. This AD was prompted by an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane.
2014-17-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes; Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of rupture of the uplock springs of the nose landing gear (NLG) and main landing gear (MLG) doors and legs. This AD requires repetitive inspections of the uplock springs of the NLG and MLG doors and legs for broken and damaged springs, and corrective actions if necessary. We are issuing this AD to detect and correct improper free fall extension of the MLG or NLG, which could lead to possible loss of control of the airplane on the ground, and consequent damage to the airplane and injury to occupants.
74-23-08: 74-23-08 GRUMMAN AMERICAN CORPORATION: Amendment 39-2007. Applies to Grumman G-159 airplanes certificated in all categories. Compliance required within the next 200 hours time in service after the effective date of this airworthiness directive unless already accomplished. To provide dual electrical power for the fire extinguisher squib circuits accomplish the following or an equivalent rework approved by the Chief, Engineering and Manufacturing Branch, Southern Region. Remove the existing left and right engine fire extinguisher switches and left hand eyebrow circuit breaker panel nameplate. Install MS24524-21 switches, electrical wiring, 159SB10112-1 nameplate and check out system in accordance with Grumman Gulfstream I Aircraft Service Change 210. This amendment becomes effective November 15, 1974.
66-22-02: 66-22-02\tBOEING: Amdt. 39-285 Part 39 Federal Register September 7, 1966. Applies to Model 727 Series Airplanes Listed in Boeing Service Bulletin No. 29-22, Dated February 21, 1966.\n \n\tCompliance required within the next 700 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failure of the pneumatic brake system due to leaks between the control valve and the brake housing, modify the pneumatic brake system line installation in accordance with Boeing Service Bulletin No. 29-22, dated February 21, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective October 7, 1966.
2016-18-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300ER series airplanes. This AD requires replacing the low-pressure oxygen flex hoses with new non- conductive low-pressure oxygen flex hoses in the gaseous passenger oxygen system in airplanes equipped with therapeutic oxygen. This AD was prompted by a determination that the low-pressure oxygen flex hoses in the gaseous passenger oxygen system can potentially be conductive. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen flex hoses in the gaseous passenger oxygen system, which can cause the flex hoses to melt or burn, and a consequent oxygen-fed fire in the passenger cabin.
2014-16-26: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX airplanes. This AD was prompted by our determination to introduce a corrosion prevention control program, among other changes, to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to include the maintenance tasks and airworthiness limitations specified in the Airworthiness Limitations section of the airplane maintenance manual. We are issuing this AD to prevent reduced structural integrity and reduced controllability of the airplane.
2014-16-25: We are superseding Airworthiness Directive (AD) 2007-06-12 for certain Airbus Model A330-200 and A330-300 airplanes. This new AD reduces the compliance times for reinforcing the structure of the center fuselage. This AD was prompted by a new fatigue and damage tolerance evaluation that revealed the compliance time for an existing reinforcement of the fuselage has to be reduced. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
2014-16-05: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by reports of ``BLEED 1(2) LEAK'' messages displayed on the engine indication and crew alert system (EICAS), and indirect damage to components of the electrical wiring interconnection system (EWIS) in the engine pylon area. This AD requires inspecting the EWIS components for damage, and repair if necessary. This AD also requires installing pre-cooler deflectors on the left- and right-hand pylons, and applying silicone sealant. We are issuing this AD to prevent indirect damage to EWIS components near the engine bleed air pre-coolers, which could result in a dual engine roll back to idle and consequent dual engine power loss and reduced controllability of the airplane.
75-01-04: 75-01-04 BEECH: Amendment 39-2062. Applies to Models A23-19, 19A, M19A and B19 (Serial Numbers MB-1 through MB-520); Model B19 Sport 150 (Serial Numbers MB-521 through MB-616); Models 23, A23, A23A, B23 and C23 (Serial Numbers M-1 through M-1361); Model C23 Sundowner 180 (Serial Numbers M-1362 through M-1485); Models A23-24 and A24 (Serial Numbers MA-1 through MA-368); Model A24R (Serial Numbers MC-2 through MC-95); and Models A24R and B24R Sierra 200 (Serial Numbers MC-96 through MC-180) airplanes. Compliance: Required as indicated, unless already accomplished. A) To reduce the possibility of improper or unintentional movement of the fuel selector valve, within 50 hours' time in service after the effective date of this AD, replace the existing fuel selector valve guard with a P/N 169-920001-43 or P/N 169-920000-165 as applicable to the airplane. B) To prevent binding and assure complete shutoff of the P/N 169-920000-61-127 or -131 selector valve in the "Off" position, within 50 hours' time in service after the effective date of this AD, and thereafter at each annual, progressive or 100-hour inspection interval as required by Federal Aviation Regulation 91.169, check this valve for binding and shutoff characteristics in accordance with Beechcraft Service Instruction No. 0364-289, Rev. III, or later FAA-approved revision. If the valve does not meet the criteria contained in this Service Instruction, prior to further flight, replace it with an improved selector valve, P/N 169-380086-1, in accordance with Beechcraft Service Instruction No. 0622-289 or later FAA-approved revision. The above inspections are not applicable to the P/N 169-380086-1 selector valve and may be discontinued when it is installed. C) Equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. This amendment becomes effective January 7, 1975.
2014-16-18: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG). This AD requires revising the maintenance program by incorporating a new safe- life limitation for the NLG main fitting. We are issuing this AD to prevent collapse of the NLG, which could lead to degradation of direction control on the ground or an un-commanded turn to the left, and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants.
2014-16-21: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports that the pintle pins installed on a certain number of airplanes may be incorrectly protected against corrosion. This AD requires replacing certain pintle pins on the left- and right-hand main landing gear (MLG) with a serviceable part. We are issuing this AD to detect and correct pintle pins that have been incorrectly corrosion-protected, which could cause the pintle pins to shear under normal load and lead to the collapse of the MLG during take-off or landing.
2014-12-52: We are superseding emergency airworthiness directive (AD) 2014-12-52 for all Honeywell International Inc. TFE731-4, -4R, -5AR, - 5BR, -5R, -20R, -20AR, -20BR, -40, -40AR, -40R, -40BR, -50R, and -60 turbofan engines. Emergency AD 2014-12-52 was sent previously to all known U.S. owners and operators of these engines. AD 2014-12-52 required, before further flight, a review of the engine logbook maintenance records to determine if any affected engines are installed. AD 2014-12-52 also prohibited operation of an airplane with two or more affected engines that have 2nd stage low-pressure turbine (LPT2) blades with less than 250 operating hours since new. This AD retains the requirements of AD 2014-12-52 and clarifies the intent of the mandatory requirements. This AD was prompted by reports of LPT2 blade separations. We are issuing this AD to prevent LPT2 blade failure, multiple engine in-flight shutdowns, and damage to the airplane.
72-16-06: 72-16-06 SIKORSKY: Amendment 39-1496. Applies to all S61A, S61L, S61N and S61R type helicopters. Compliance required as indicated after the effective date of this Airworthiness Directive. To assure the proper electrical feeder wiring gage in the A.C. circuit breaker panel, accomplish the following: 1. Within the next 25 hours time in service from the effective date of the Airworthiness Directive comply with Sikorsky Service Bulletin 61B55-27A, Paragraph 2A or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 2. Within 250 hours time in service from the effective date of this Airworthiness Directive. (a) Conduct a conformity inspection in accordance with the aircraft drawing effectivity list shown in Sikorsky Service Bulletin 61B55-27A, Paragraph 2.B(5) or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (b) Conduct an inspection of all alterations performed on, or affecting the A.C. circuit breaker panel and substantiate feeder wire sizes affected are adequate for the alterations performed. Changes required as a result of this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (Ref. Sikorsky S.B. 61B55-27A dated 9 May 1972 for list of Sikorsky Service Bulletins which modified drawings all listed in Paragraph 2.B(5)). Upon request with substantiating data submitted through an FAA maintenance inspector, the Compliance times specified in this Airworthiness Directive may be increased by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. This amendment is effective 10 August 1972.
2010-24-08: 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: On two occurrences on Mystere-Falcon 50 aeroplanes in service, it was detected that two pipes of the emergency brake system 2 located near the nose landing gear bearing were swapped. The swapping of these two pipes implies that when the Left Hand (LH) brake pedal is depressed, the Right Hand (RH) brake unit is activated, and conversely, when the RH brake pedal is depressed, the LH brake unit is actuated. This constitutes an unsafe condition, which may go unnoticed as the condition is latent until the emergency brake system 2 is used. This condition, if not corrected, could ultimately lead to a runway excursion of the aeroplane. * * * * * ThisAD requires actions that are intended to address the unsafe condition described in the MCAI.
2020-22-17: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 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 movement of the aft fuel pipe within the coupling, which can cause damage to the O-rings and lead to a fuel leak, fuel fire or explosion, and consequent loss of control of the airplane. This AD requires replacing and prohibits installing affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2003-14-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200, -200C, -300, -400, and - 500 series airplanes. This action requires repetitive inspections for cracking of certain lap splices, and corrective action if necessary. This action is necessary to detect and correct fatigue cracks in the lap joints and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
2010-23-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Several power loss events have been reported, due to rail pressure control failures. Analyses have shown that high pressure (HP) fuel pumps failed as a result of pressure oscillations in the fuel supply line. We are issuing this AD to prevent engine power loss or in-flight shutdown, which could result in loss of control of the airplane.
2014-16-13: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. This AD requires revising the maintenance or inspection program, as applicable, to include the new life limits. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane.
2014-17-01: We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 airplanes. This AD results from 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 looseness of the horizontal stabilizer actuator mounting block in the forward-aft and side-to-side directions. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-17-02: We are superseding Airworthiness Directive (AD) 2013-18-09 for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) installed on various transport category airplanes. AD 2013-18-09 required various one-time general visual inspections of the ELT transmitter units (TUs), and corrective actions if necessary. This new AD corrects the manufacturer's name in the AD applicability and adds a source of approval for an installation. AD 2013-18-09 was prompted by a fire on a parked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. This new AD was prompted by the identification of an error in the applicability of AD 2013-18-09. We are issuing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an electrical short and possible ignition source.
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.