Results
80-15-02: 80-15-02 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 3839. Applies to Partenavia Model P.68 and P.68B airplanes serial numbers 1 through 165, except serial number 40, certificated in all categories, which have rudder cable pulley brackets P/N 2.3097-1 installed. Compliance required as indicated, unless already accomplished. To prevent the loss of proper rudder cable tension and rudder control system failure, accomplish the following: (a) For airplanes which have more than 500 hours time in service on the effective date of this AD, within the next 50 hours time in service after the effective date of this AD, accomplish paragraph (c) or paragraph (e) of this AD. (b) For airplanes which have less than 500 hours time in service on the effective date of this AD, before accumulating a total of 500 hours time in service, or within the next 50 hours time in service after the effective date of this AD, whichever occurs later, accomplish paragraph (c) or paragraph (e) of this AD. (c) Inspect the rudder pedal interconnecting bell crank bracket for cracks with special attention to the lower bracket and the rear face of aircraft frame number 3 for cracks and loose rivets in the area of the rudder cable pulley bracket attachment in accordance with PART II "Instructions" of Partenavia Service Bulletin 40, dated September 9, 1978, or an FAA-approved equivalent. If no cracks are found, repeat the inspection at intervals not to exceed 50 hours time in service since the last inspection until paragraph (e) of this AD is accomplished. (d) If as a result of an inspection required by paragraph (c) of this AD, cracks or loose rivets are found, before further flight, except as provided in paragraph (g) of this AD, (1) repair cracks in frame number 3 by stop drilling; (2) remove any loose rivets and replace with new rivets; and (3) replace any cracked brackets, P/N 2.3097-1, by compliance with paragraph (e) of this AD. Uponcompliance with subparagraphs (1), (2) and (3) of this paragraph, the repetitive inspections required by paragraph (c) are no longer required. (e) Replace the rudder pedal interconnecting bell crank bracket, P/N 2.3097-1, with a new bracket, P/N 2.3111-1, in accordance with PART III "Instructions" of Partenavia Service Bulletin No. 40, dated September 9, 1978, or an FAA-approved equivalent. (f) Equivalent means of compliance specified in this AD must be approved by the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. (g) Aircraft may be flown in accordance with FAR 21.197 and 21.199 to a location where the repairs and replacement can be performed. This amendment becomes effective July 21, 1980.
2018-02-18: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes and Model A321-111, -112, -131, -211, -212, -213, -231, -232 airplanes. This AD requires revising the airplane flight manual (AFM) to provide guidance to the flight crew for emergency procedures when erroneous airspeed indications are displayed on the back-up speed scale (BUSS). This AD was prompted by a determination that, when two angle of attack (AoA) sensors are adversely affected by icing conditions at the same time, data displayed on the BUSS could be erroneous. We are issuing this AD to address the unsafe condition on these products.
78-26-03: 78-26-03 GRUMMAN: Amendment 39-3369. Applies to Models G-164, G-164A and G-164B aircraft, certificated in all categories, that have been in service for either more than 500 hours or six months. Compliance is required as indicated: To detect corrosion of the lower wing attachment fittings, P/N's A1050-1, -3, -4, -101, -102, -103, -104, -13, -19, -20, -411, -412 and 3050-13, -14, -15, -16, accomplish the following: (a) Within the next 25 hours in service and thereafter at intervals not to exceed 500 hours in service or six months, whichever comes first, since the last inspection, visually inspect the lower wing panel attachment fittings for corrosion. (b) If surface corrosion (corrosion which is evidenced by dulling, pitting, blistering, scaling, roughness, or localized discoloration of the metal surface) is found on the attachment fittings, remove the wing and the corrosion. If it is required to clean up corrosion of the rear fittings follow the procedure below: 1. Press wing attachment bolt bushing below corroded surface. Do not fully remove the bushing. 2. Remove corrosion. 3. Equalize the amount the bushing extends from each surface of the fitting. 4. Measure gap in fuselage fitting. 5. Fabricate shims for both sides of fitting so that total width of fitting does not exceed gap of fuselage and bushing does not exceed width of fitting by more than .020". If the front or rear wing attachment fitting dimensions are found to be in excess of the minimum limits specified in paragraph (c), (d), or (e), protect the surface from further corrosion in accordance with FAA Advisory Circular 43.13-1A, Paragraph 250(b) or equivalent. (c) For G-164 aircraft S/N's 001 thru 400: If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than the .231", or the distance from the edge of the fitting is found to be less than .290", install an unused fitting of the same part number or an equivalent.(d) For G-164A aircraft S/N's 401 and up. If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than .220", or the distance from the edge of the hole to the edge of the fitting is found to be less than .340", install an unused fitting of the same part number or an equivalent. (e) For G-164B aircraft S/N's 001 and up. If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than .230", or the distance from the edge of the hole to the edge of the fitting is found to be less than .515", install an unused fitting of the same part number or an equivalent. Equivalent parts and corrosion protection must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The aircraft may be flown in accordance with FAR 21.197 to a location where the AD can be accomplished. Grumman Service Bulletin No. 65 dated October 16, 1978, covers this same subject. This amendment is effective December 20, 1978.
2002-25-09: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-250, AT- 300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-401A, AT-402, AT-402A, AT-501, AT-502, and AT-502A airplanes. This AD requires you to install an overturn skid plate in the cockpit area. This AD is the result of reports of foreign material entering the cabin area during an overturn skid of the affected airplanes. The actions specified by this AD are intended to minimize the possibility of dirt or mud penetrating the cockpit in case of an aircraft overturn. Such mud and dirt penetration into the cockpit could lead to pilot asphyxia or injury.
2024-12-05: The FAA is superseding Airworthiness Directive (AD) 2021-25-12 and AD 2022-11-11, which applied to certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and -402 airplanes. AD 2021-25-12 required repetitive lubrications of the trailing arm of the nose landing gear (NLG). AD 2021-25-12 also required revising the existing maintenance or inspection program to include new and revised airworthiness limitations. AD 2022-11-11 required a modification to the NLG shock strut assembly. This AD continues to require the actions specified in AD 2021-25-12 and AD 2022-11-11 and requires replacement of the pivot pin and tow fitting assembly with a new, improved pivot pin and tow fitting assembly and prohibits the installation of affected parts. This AD was prompted by a determination that the pivot pin and tow fitting assembly of the NLG must be replaced. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires a one-time inspection of all gland nuts supplied with certain shock struts of the center landing gear (CLG) to verify that the gland nuts have the correct thread profile, and replacement of any defective gland nut with a new gland nut. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the failure of the CLG, and subsequent damage to the airplane structure or injury to airplane occupants.
2002-25-08: This amendment supersedes three existing airworthiness directives (AD's), that are applicable to GE CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines. Those AD's currently require specific handling of the GE CF6 series high pressure compressor rotor (HPCR) stage 3-9 spools during a fluorescent penetrant inspection process, and initial and repetitive ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This amendment removes the AD that requires special handling of the spools during fluorescent- penetrant inspection, and adjusts and combines the initial and repetitive inspection requirements, currently listed in two AD's, into one AD for the HPCR stage 3-9 spool. This amendment aligns repetitive inspection requirements with the more stringent initial inspection requirements mandated by AD 2000-16-12, Amendment 39-11868 (65 FR 50623, August 21, 2000) and terminates AD 95-18-14, Amendment 39-9361 (60 FR 46216, September 6, 1995) that is no longer necessary. The actions specified by this AD are intended to prevent cracks, which can cause separation of the HPCR stage 3-9 spool and possible uncontained engine failure.
2024-13-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by a report of sparking due to damaged wire insulation in the fueling adapter. This AD requires inspecting the electrical wires attached to the airplane connector located behind the fuel scupper for damage, and all applicable related investigative and corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
98-09-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301 series airplanes. This action requires a one-time visual inspection to measure clearances between the engine forward feed pipe and shroud sleeve in the engine pylon; and repetitive operational tests for fuel leakage, and replacement of the shroud sleeve with a new improved part, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fuel from leaking into the pylon primary structure and into the engine nacelle core zone, which could result in a fire in the engine.
96-06-09: This amendment adopts a new airworthiness directive (AD) that is applicable to three Boeing Model 767 series airplanes, serial numbers 26847, 27048, and 27049. This action requires a functional check of the trailing edge flap drive bypass valve, and eventual replacement of the control valve module for the trailing edge flaps with an improved module. This amendment is prompted by reports of failure of the bypass valve motor in the control valve module of the trailing edge flaps due to hydraulic fluid contamination. The actions specified in this AD are intended to prevent such failure, which could result in loss of shutdown protection for the trailing edge flap drive; this condition could result in reduced controllability of the airplane in the event of uncommanded or asymmetrical flap motion.
2024-12-03: The FAA is adopting a new airworthiness directive (AD) for certain CFE Company (CFE) Model CFE738-1-1B engines. This AD was prompted by a manufacturer investigation that revealed certain high- pressure turbine (HPT) stage 1 and stage 2 disks were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of affected HPT stage 1 and stage 2 disks with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2024-10-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by a report of abnormal oscillatory behavior during automated glide slope approaches, due to sealant on the glide slope (G/S) antenna coaxial connectors. This AD requires visually inspecting certain G/S antennas and G/S antenna coaxial connectors for the presence of any sealant; cleaning parts and removing any sealant; performing an external G/S acceptance test procedure (ATP); and taking corrective actions if necessary. This AD would also prohibit installing certain G/S antennas and G/S antenna coaxial connecters. These requirements are 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.
2002-25-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. (RR) Olympus 593 Mk. 610-14-28 turbojet engines, installed in BAe/SNIAS Concorde Type 1 airplanes that have been modified in accordance with Airbus Concorde service bulletins No.'s SST 57-078, SST 57-079, SST 57-080, and SST 57-082. This action requires initial and repetitive engine fuel filter inspections and fuel sample analysis. This amendment is prompted by a report of fuel tank liner materials found in and partially through an engine fuel filter. The actions specified in this AD are intended to prevent contamination of any or all of the four airplane engine fuel control units, causing power loss or one or more engines to shutdown.
2002-25-02: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331-3, -5, -6, -8, -10, and -11 series turboprop and TSE331-3 series turboshaft engines. This amendment requires removing weld repaired first stage compressor impellers from service. This amendment is prompted by an uncontained TPE331-11U turboprop engine failure and an in-flight shutdown due to the separation of the first stage Ti 6-4 compressor impeller. The actions specified by this AD are intended to prevent uncontained engine failures, in-flight shutdowns, and secondary damage.
98-24-20: This amendment adopts a new airworthiness directive (AD) that applies to certain Grob Luft-und Raumfahrt (Grob) Models G 109 and G 109B sailplanes. This AD requires inspecting the radius of the landing gear retaining bars, installing additional supportive parts, and replacing the retaining bars if the retaining bars chamfer radius is less than 3.0 millimeters (mm). This AD also requires inspecting the landing gear legs for cracks and proper thickness, and either polishing out the cracks or replacing the landing gear legs with parts of improved design depending on the crack length. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct fatigue cracking of the landing gear legs, which could result in landing gear failure with consequent loss of control of the sailplane during landing operations.
2024-12-07: The FAA is adopting a new airworthiness directive (AD) for The Boeing Company Model 757-200 airplanes modified by particular supplemental type certificates. This AD was prompted by reports of cracking in the structure in and around the lavatory service panel. This AD requires repetitively inspecting the lavatory service panel, access pan, and attaching structure for cracks; reinforcing the attaching structure; and if necessary, replacing the access pan or repairing cracked parts. The FAA is issuing this AD to address the unsafe condition on these products.
2002-25-05: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman (Pilatus Britten-Norman) Limited BN-2 and BN2A Mk. III series airplanes. This AD requires you to inspect the universal joints on the pilot's and co-pilot's control column to determine the diameter of the shaft and replace any universal joint that is the wrong size. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to correct the installation of universal joints that have the wrong- sized shaft, which could result in failure of the pilot's and/or co- pilot's control column. Such failure could lead to loss of control of the airplane.
99-23-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of a flight attendant panel and modification of its associated wiring. 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 the disabling of the "Fasten Seat Belt" and "No Smoking" signs when they are required to be illuminated. Such disabling could result in the inability to instruct the passengers to extinguish their cigarettes and fasten their seat belts when required, which may contribute to passenger injury should a hard landing or in-flight turbulence be experienced.
97-12-06: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-12-06, which was sent previously to known U.S. owners and operators of certain Cessna Aircraft Company (Cessna) Model 172R airplanes. This AD requires checking the clearance between both the gascolator and cowling area and the tailpipe and cowling area, and modifying these areas immediately if any evidence of rubbing at either location is found or modifying the gascolator to cowling area within a certain time period if no evidence of rubbing at either location is found. This AD results from an occurrence of fuel loss on a Cessna Model 172R airplane, which was severe enough to force an emergency landing. Investigation of the occurrence reveals that the cowling knocked the gascolator drain valve off the gascolator. The actions specified by this AD are intended to prevent the cowling from rubbing against the gascolator drain valve or the tailpipe, which could result in fuelloss and engine stoppage.
2002-25-03: This amendment supersedes Airworthiness Directive (AD) 97-14- 01, which currently applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2A and BN2A Mk. III series airplanes. AD 97-14-01 requires repetitively inspecting the left-hand rudder bar assembly for cracks, measuring the slider tube unit wall thickness, and modifying the rudder bar assembly by installing a slider tube unit of improved design as a terminating action for the repetitive inspections. AD 97-14-01 resulted from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. Reports of cracks being found on the right-hand rudder bar assembly and the inadvertent omission of requiring inspection of the rudder pedal beams prompted this action. This AD retains the requirements of AD 97-14-01 and requires inspections of the right-hand rudder bar assembly and each rudder pedal beam. The actions specified by this AD are intended to prevent failure of the pilot's and co-pilot's rudder bar assemblies, which could result in loss of control of the airplane during landing operations.
2024-08-05: The FAA is superseding Airworthiness Directive (AD) 2014-15- 09, AD 2020-15-09, and AD 2022-16-07. AD 2014-15-09 applied to all Airbus SAS Model A330-200 Freighter, A330-200 and -300, and A340-200, - 300, -500, and -600 series airplanes. AD 2020-15-09 applied to all Airbus SAS Model A330-941 airplanes. AD 2014-15-09 and AD 2020-15-09 required repetitive operational tests of the hydraulic locking function on certain spoiler servo-controls (SSCs) and replacement if necessary. AD 2022-16-07 applied to certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2022-16-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by the determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2014-15-09, AD 2020-15-09, and AD 2022-16-07 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), which is incorporated by reference. This AD also removes Model A340-200, -300, -500, and -600 series airplanes from the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2000-03-19 REM: This amendment removes Airworthiness Directive (AD) 2000-03-19, which currently applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with pneumatic deicing boots. AD 2000-03-19 requires revising the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. Since FAA issued AD 2000-03-19, I.A.M. has shown the language currently included in the AFM and the airplane configuration are satisfactory to address the conditions identified in AD 2000-03-19. Therefore, this action removes AD 2000-03-19.
2024-10-09: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a determination that a more restrictive airworthiness limitation is necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a more restrictive airworthiness limitation, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-24-09: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN2T and BN2T-4R series airplanes. This AD requires you to repetitively inspect the left and right engine-mounting frame for cracks and replace the frame if cracks are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the left and right engine- mounting frame, which could lead to engine mount failure. Such failure could result in separation of the engine from the airplane.
2002-24-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Deutschland Ltd. & Co KG (RRD), Model Tay 620-15 and 650-15 turbofan engines. This action requires initial and repetitive inspections of certain low pressure (LP) fuel tubes. This amendment is prompted by a dual-engine flameout. The actions specified in this AD are intended to prevent a dual-engine flameout due to fuel exhaustion, which could lead to forced landing and possible damage to the airplane.