Results
2016-26-09: We are superseding an airworthiness directive (AD) 2016-06-01 for B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN- 2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B- 21, BN-2B-26, BN-2B-27, BN-2T-4R, BN-2T, BN2A MK. III, BN2A MK. III-2, and BN2A MK. III-3 (all models on Type Certificate Data Sheets A17EU and A29EU) 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 describes the unsafe condition as cracks in the inner shell of certain pitot/static pressure heads. This AD changes model applicability due to errors found in AD 2016-06-01. We are issuing this AD to require actions to address the unsafe condition on these products.
2016-26-04: We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44, R44 II, and R66 helicopters. This AD requires inspecting the main rotor blade (MRB). This AD was prompted by a determination that some MRBs may have reduced blade thickness due to blending out corrosion. The actions are intended to prevent the unsafe condition on these products.
2024-14-08: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by a manufacturing quality escape concerning some overheat detection system (ODS) sensing elements. This AD requires inspecting the ODS sensing elements and performing applicable corrective actions, and prohibits the installation of affected parts, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
81-07-03: 81-07-03 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39-4069. Applies to Model P68 and P68B series airplanes, serial numbers 1 to 160 inclusive, certificated in all categories, which have a Woodward propeller governor installed but do not have a ball joint end, P/N 7.5077-1, installed on the pitch control flexible cable. Compliance is required as indicated, unless already accomplished. To preclude failure of the propeller pitch control system, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, or within 50 hours time in service since the last inspection, whichever occurs later, and every 50 hours time in service thereafter, inspect the propeller pitch control system for play between the ball joint, P/N 7.5021-3, and the joint end, P/N 7.5021-1, in accordance with Partenavia Service Bulletin 37, Revision 2, dated November 22, 1978, or an FAA-approved equivalent. (b) If play is not found during the inspection required in paragraph (a) of this AD, return airplane to service. (c) If play is found during the inspection required in paragraph (a) of this AD, adjust the propeller pitch control system as necessary in accordance with Part I, "Instructions", of Partenavia Service Bulletin 37, Revision 2, dated November 22, 1978, or an FAA-approved equivalent, or install a new joint end, P/N 7.5021.1, and return to service. (d) The inspections required by this AD are no longer required with the installation of Partenavia Kit P/N 68-005 installed in accordance with Partenavia Service Instruction No. 2, dated July 14, 1978, or an FAA-approved equivalent. (e) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Partenavia Costruzioni Aeronautiche S.p.A., Via Cava, Casoria - Naples, Italy. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, DC 20591. This amendment becomes effective April 2, 1981.
2024-14-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports that certain engine bleed air system (EBAS) T-Ducts may not conform to the type design due to a quality escape not detected during the manufacturing process on Rolls-Royce Trent XWB-75, Trent XWB-84, and Trent XWB-97 engines. This AD requires replacement of affected EBAS T-Ducts and limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2016-25-31: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; Model A330-200 Freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of chafed wiring at the upper left corner of the cockpit door. The affected wire bundle was not grounded on the cockpit door frame. This AD requires modifying the cockpit door frame structure, installing bonding-leads to the upper cockpit door frame, and modifying the upper cockpit door plate cover. We are issuing this AD to address the unsafe condition on these products.
2016-25-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports of the accumulation of very fine particle deposits in the power control unit (PCU) electro-hydraulic servo valves (EHSVs) used in the flight control system; this accumulation caused degraded performance due to reduced EHSV internal hydraulic supply pressures, resulting in the display of PCU fault status messages from the engine indication and crew alerting system (EICAS). This AD requires installing markers to limit the hydraulic system fluid used to a specific brand, doing hydraulic fluid tests of the hydraulic systems, replacing hydraulic system fluid if necessary, and doing all applicable related investigative and corrective actions. We are issuing this AD to address the unsafe condition on these products.
96-23-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-1A10 series airplanes. This action requires a one-time inspection of the three DC generators to ensure that the extra unconnected bare copper wire is properly stowed. This amendment is prompted by reports indicating that unconnected bare copper wire, which was fitted inside of some DC generators installed on these airplanes, could cause a short circuit. The actions specified in this AD are intended to prevent a fire hazard that would be posed if a short circuit were to occur at this area in the presence of a combustible fuel-air mixture.
97-01-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321 series airplanes. This action requires repetitive inspections to detect cracking and delamination of the doors that contain the left and right emergency evacuation slides located at certain emergency exits; and repair or replacement, if necessary. This action also requires the accomplishment of a modification that serves as terminating action for the repetitive inspections. This amendment is prompted by a report indicating that a slide aboard an airplane deployed during flight and consequently separated from the airplane. The actions specified in this AD are intended to prevent the loss of these slides during flight, which could make certain exits unusable in the event of an emergency, and also damage the empennage.
2016-25-26: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports of stick shaker activation at airspeeds that were above the stall protection system's stick shaker schedule. This AD requires installing angle-of-attack (AOA) sensor external case heaters on the existing AOA sensors, installing additional wires, and doing a functional test and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
89-20-07: 89-20-07 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6327. (Docket No. 89-NM-165-AD) Applicability: All Model L-1011 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent fuel leaking in the pylon leading to premature fuel exhaustion or fire, accomplish the following: A. Within 500 hours time-in-service after the effective date of this AD, unless already accomplished within the last 1,600 hours time-in-service, and thereafter at intervals not to exceed 2,100 hours time-in-service from the last inspection, accomplish the following: 1. Visually inspect the fuel feed line in Number 1 and Number 3 pylons between pylon stations PS89 and PS166 for clearance and chafing, as follows: a. The fuel line must have no evidence of chafing, and a minimum of 0.25 inch clearance must exist between it and the hydraulic lines. b. If there is less than 0.25 inch clearance between the fuel line and the hydraulic lines, reposition to obtain a minimum of 0.25 inch clearance prior to further flight. c. If the fuel line has evidence of chafing, repair or replace the line prior to further flight. A minimum of 0.25 inch clearance between the fuel line and the hydraulic lines is required. B. An 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, Los Angeles Aircraft Certification Office, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. C. Special 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. This amendment (39-6327, AD 89-20-07) becomes effective on October6, 1989.
76-06-07: 76-06-07 MORANE SAULNIER (SOCATA): Amendment 39-2543. Applies to all MS 760B Paris II airplanes certificated in all categories, all serial numbers. Compliance is required as indicated, unless already accomplished. To prevent a possible inflight fire caused by overpressure in the auxiliary fuel tanks accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, install an operating limitation placard on the instrument panel in full view of the pilot that reads as follows: FUEL TRANSFER SYSTEM OPERATING LIMITATIONS 1. Ground test PROHIBITED 2. Takeoff and climb TIP TANK OPEN LEADING EDGE CLOSED 3. Cruise LESS THAN 200 L. IN MAIN TANKS LEADING EDGE OPEN ONLY DURING TRANSFER 4. Descent LEADING EDGE OPEN (b) Within the next 10 hours' time in service after the effective date of this AD, visually inspect the wing leading edge electric spot welds for proper weld integrity. (c) If a weld is found to be defectiveduring the inspection required by paragraph (b) of this AD, before further flight, repair the wing leading edge associated with the defective welds. (d) Within the next 100 hours' time in service after the effective date of this AD - (1) Visually inspect the engine bleed apertures for proper diameter; and (2) Inspect the auxiliary fuel tank overpressure valve for proper valve opening pressure. (e) If, during the inspection required by paragraph (d)(1) of this AD, an engine bleed aperture diameter is found not to be as follows, replace the engine bleed overpressure valve with a serviceable valve of the same part number or an FAA-approved equivalent: (1) For aircraft equipped with neither pneumatic deicers nor pneumatic gyros, 2 mm in diameter; (2) For aircraft equipped with pneumatic gyros only, 3 mm in diameter; (3) For aircraft equipped with pneumatic deicers with or without pneumatic gyros, 6 mm in diameter. (f) If, during the inspection required by paragraph (d)(2) of this AD, the auxiliary fuel tank overpressure valve is found not to begin opening at a fuel pressure of 250 +20 or -10 grams/cm (squared), replace the valve with a serviceable valve of the same part number or an FAA-approved equivalent. (g) For aircraft equipped with pneumatic deicers, within the next 100 hours' time in service after the effective date of this AD, install a 2.8 mm restrictor, P/N TN-0176-56.4.093, in the union at the entrance of the pressure reducing valve. (Socata Service Bulletin No. 14/1 dated July 1971 pertains to this AD.) This amendment becomes effective March 25, 1976.
2024-14-02: The FAA is superseding Airworthiness Directive (AD) 2023-02- 13, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. AD 2023-02-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2023-02- 13, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023-02-13 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.
2016-25-29: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by a report of a fire in the bilge area of the cargo compartment that burned through the insulation blankets that were intended to prevent smoke from migrating behind the cargo compartment sidewall liners and upward into the main cabin. This AD requires replacing the cargo compartment insulation blankets on the left and right sides with new insulation blankets that incorporate fire stops. We are issuing this AD to address the unsafe condition on these products.
2024-14-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD 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 proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
85-10-02: 85-10-02 CESSNA: Amendment 39-5064. Applies to Models 206, U206, U206A, U206B, U206C, U206D, U206E, U206F, and U206G (R/Ns 206-0001 thru U20606065); P206, P206A, P206B, P206C, P206D, and P206E (S/Ns P206-0001 thru P20600647); 207 and 207A (S/Ns 20700001 thru 20700681); 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, and 210N (S/Ns 21058221 thru 21064226) airplanes certificated in any category which are equipped with Continental Model IO-520-( ) engines. Compliance: Required within 100 hours time-in-service after the effective date of this AD and each 100 hours time-in-service thereafter, until modified in accordance with paragraph (b) of the AD. To eliminate the possibility of engine power reduction due to ingestion of pieces of a failed engine induction airbox outboard duct, accomplish the following: (a) Visually inspect the engine induction airbox outboard duct lower skin for cracks. (b) If cracks are found, prior to further flight, either replace theinduction airbox outboard duct with a Cessna Part Number 1250705-8 duct or repair the skin of the existing duct in accordance with the repair procedures of FAA Advisory Circulars AC 43.13-1A and AC 43.13-2A using material at least .040 inches thick. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. Cessna Single Engine Customer Care Service Information Letter SE84-20 dated November 2, 1984, covers the subject matter of this AD. This amendment becomes effective on June 20, 1985.
2024-13-07: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a notice from a supplier reporting that torque wrenches used to install the air driven generator (ADG) downlock cam nut were out of calibration, which resulted in a higher torque level setting than required during the initial production installation of the affected cam nut. This AD requires replacement of the affected ADG locking cam screw and cam nut, 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.
2016-25-20: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC130B4, EC130T2, AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires inspecting each bi- directional suspension cross-bar (cross-bar). This AD was prompted by two reports of cracks in a cross-bar. These actions are intended to prevent the unsafe condition on these products.
2023-25-07: The FAA is superseding Airworthiness Directive (AD) 2023-04- 10, which applied to all Dassault Aviation Model MYSTERE-FALCON 900 airplanes. AD 2023-04-10 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 the actions in AD 2023-04- 10, 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.
2016-25-28: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS355NP helicopters. This AD requires removing and installing the fire extinguishing system pipes. This AD is prompted by the discovery that the left-hand and right-hand fire extinguishing discharge systems were incorrectly connected. The actions of this AD are intended to correct the unsafe condition on these products.
2016-25-21: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports of electrical shorts of the motor stator wiring burning a hole through the housing of the motor of the cabin air compressor (CAC). This AD requires installing modified inboard and outboard CAC modules on the left-hand (LH) side and right-hand (RH) side cabin air conditioning and temperature control system (CACTCS) packs. We are issuing this AD to prevent the unsafe condition on these products.
2016-25-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of two cases where the main landing gear (MLG) failed to fully extend; it was determined that interference between the MLG door and the MLG fairing seal prevented the MLG door from opening fully. This AD requires repetitive inspections of the MLG fairing, fairing seal, door, and adjacent structures; and replacement or repair of affected parts and fasteners, or removal of the MLG door, if necessary. This AD also requires installation of a safety guide in the MLG fairing and an increase of the spacing between the MLG door and the fairing, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
86-15-05: 86-15-05 DEHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-5357. Applies to Model DHC-7 airplanes, serial numbers 1 through 14 inclusive, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To assure proper crew warning in the event of the loss of the 400 Hz AC electrical power system, accomplish the following: 1. Modify the 400 Hz AC system in accordance with DeHavilland Service Bulletin 7-24-13, Revision A, dated September 10, 1982. 2. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. Special 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. All persons affected by this directive, who have not already received the appropriate service bulletin from the manufacturer, may obtain copies upon request to DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario M3K 1Y5, Canada. 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. This amendment becomes effective September 4, 1986.
89-03-16: 89-03-16 CESSNA: Amendment 39-6162. Final copy of Priority Letter AD issued February 7, 1989. Applicability: Model 650 series airplanes, serial numbers 650-0067 through 650-0165, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent non-restorable loss of all avionics power, accomplish the following: A. Within 25 hours time-in-service after the effective date of this Airworthiness Directive (AD), perform an operational check of the avionics bus relays, in accordance with the Accomplishment Instructions of Cessna Alert Service Letter SLA650-24-14, dated February 3, 1989. If the wiring of the avionics bus relays is not correctly installed, prior to further flight, modify that wiring in accordance with the referenced service letter. B. Within 5 days after accomplishing the check required by paragraph A., above, submit a report, in writing, of any incorrectly installed avionics bus relay wiring identified,to: Manager, Wichita Aircraft Certification Office, FAA, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. C. An 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, Wichita Aircraft Certification Office, FAA, Central Region. NOTE: If appropriate, the request should be forwarded through an FAA Principal Maintenance Inspector (PMI) who may add any comments and then send it to the Manager, Wichita Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 or 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not received copies of the service information from the manufacturer, may obtain copies upon request to Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas. This AD was effective earlier to all recipients of Priority Letter AD 89-03-16 issued February 7, 1989. This amendment (39-6162, AD 89-03-16) becomes effective April 5, 1989.
92-25-02: 92-25-02 FOKKER: Amendment 39-8417. Docket No. 92-NM-96-AD. Applicability: All Model F28 Mark 0100 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent false indications to the crew that the landing gear is not down and locked, accomplish the following: (a) Within 120 days after the effective date of this AD, identify the serial number on the nameplate of the main landing gear downlock actuator, part number 201218001 or 201218002. (1) If the serial number identified on the nameplate is not one of the following serial numbers, no further action is required by this AD: Part Number 201218001 Part Number 201218002 CWDD/DRG/1/88 to CWDD/DRG/20/88 CWDD/DRG/1/88 to CWDD/DRG/19/88 CWDD/DRG/1/89 to CWDD/DRG/25/89 CWDD/DRG/1/89 to CWDD/DRG/32/89 CWDD/DRG/1/90 to CWDD/DRG/42/90 CWDD/DRG/1/90 to CWDD/DRG/34/90 CWDD/DRG/1/91 to CWDD/DRG/13/91 CWDD/DRG/1/91 to CWDD/DRG/10/91 (2) If the serial number identified on the nameplate is one of the affected serial numbers specified in paragraph (a)(1) of this AD, and if "F100-32-45" is identified on the nameplate, no further action is required by this AD. (3) If the serial number identified on the nameplate is one of the affected serial numbers specified in paragraph (a)(1) of this AD, and if "F100-32-45" is not identified on the nameplate, prior to further flight, replace the downlock actuator with one that has "F100-32-45" identified on the nameplate, or one that is not one of the affected serial numbers specified in paragraph (a)(1) of this AD, in accordance with Fokker Service Bulletin SBF100-32-052, dated May 1, 1991. (b) As of the effective date of this AD, no main landing gear downlock actuator, part number 201218001 or 201218002, having a serial number that is specified in paragraph (a)(1) of this AD, shall be installed on any airplane unless "F100-32-045" is identified on the nameplate. (c)An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The replacement shall be done in accordance with Fokker Service Bulletin SBF100-32- 052, dated May 1, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on December 23, 1992.