Results
99-07-09: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3201 airplanes. This AD requires replacing the nose landing gear downlock actuator, the flap actuator, the steering selector valve, the hydraulic reservoir, and the emergency selector valve. 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 prevent internal corrosion of the hydraulic components on airplanes where these components were exposed to water contamination, which could result in reduced or loss of control of the airplane.
2019-03-26: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of passenger service units (PSUs) becoming detached from the supporting airplane structure in several Model 737 series airplanes. This AD requires modifying the PSUs and life vest panels by replacing the existing inboard lanyard and installing two new lanyards on the outboard edge of the PSUs and life vest panels; measuring the distance between the hooks of the torsion spring of the lanyard assembly; replacing discrepant lanyard assemblies; and re-identifying serviceable lanyard assemblies. We are issuing this AD to address the unsafe condition on these products.
2006-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires replacing the existing vent float valve with a new, improved vent float valve. This AD results from reports of failure of the vent float valve in the left-hand outboard section of the trimmable horizontal stabilizer. We are issuing this AD to prevent, in the event of a lightning strike to the horizontal stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion.
98-04-44: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires replacement of the groove pins on the doors of the center main landing gear (MLG) with new pins, modification of the bolt head, installation of an antirotation plate, and modification of the hinge pins on the doors of the MLG by the installation of oversize bolts. 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 detachment of the center MLG door during flight, which could pose a hazard to persons or property on the ground.
2000-11-19 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 767-200 and -300 series airplanes. That AD currently requires repetitive inspections to detect wear or damage of the door latches and disconnect housings in the off-wing escape slide compartments, and replacement of any discrepant component with a new component. This new AD revises the applicability of the existing AD to refer to a later revision of the referenced service bulletin, which removes airplanes that are not subject to the identified unsafe condition. This AD results from reports of worn and damaged door latches and disconnect housings in the off-wing escape slide compartments. We are issuing this AD to ensure deployment of an escape slide during an emergency evacuation. Non-deployment of an escape slide during an emergency could slow down the evacuation of the airplane and result in injury to passengers or flightcrew. We are also issuing this AD to detect damaged disconnect housings in the off-wing escape slide compartments, which could result in unexpected deployment of an escape slide during maintenance, and consequent injury to maintenance personnel. \n\nDATES: The effective date of this AD is July 18, 2000. \n\n\tThe Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-25A0260, Revision 1, dated January 25, 2001; Boeing Service Bulletin 767-25A0260, Revision 2, dated August 26, 2004; Boeing Service Bulletin 767-25A0260, Revision 3, dated July 7, 2005; and Boeing Service Bulletin 767-25A0275, Revision 3, dated April 24, 2003; listed in the AD as of July 17, 2006. \n\n\tOn July 18, 2000 (65 FR 37015, June 13, 2000), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-25A0260, dated July 9, 1998.
2009-01-11: 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 cases of loss of internal components from the Hydro Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part number (P/N) 9 550 17 956 0 into the fuel system, have been reported on Arriel 2 engines. The loss of internal components from the low fuel pressure switch into the fuel system may lead to a rupture of the HP-LP pumps drive shaft shear pin, and thus to a possible uncommanded in-flight shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD results in an emergency autorotation landing and in certain conditions may lead to an accident. We are issuing this AD to prevent forced autorotation landing, or an accident.
2018-22-11: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran Helicopter Engines), ASTAZOU XIV B and H model engines with certain 3rd-stage turbine wheels installed. This AD requires initial and repetitive inspections of the 3rd-stage turbine wheels. This AD was prompted by a report that six 3rd-stage turbine wheels were returned to service after a repair that could result in exceedance of the allowable vibration threshold during operation. We are issuing this AD to address the unsafe condition on these products.
91-01-05: 91-01-05 BOEING: Amendment 39-6850. Docket No. 90-NM-155-AD. \n\n\tApplicability: Boeing Model 757 series airplanes, as listed in Boeing Service Bulletin 757-25-0061, Revision 2, dated June 29, 1989, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the potential for reduced passenger evacuation capability during an emergency, accomplish the following: \n\n\tA.\tModify the number 3 left and right emergency exit doors by replacing the door catch assembly support and performing an operational check, in accordance with Boeing Service Bulletin 757-25-0061, Revision 1, dated June 9, 1988, or Revision 2, dated June 29, 1989. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: Therequest should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6850, AD 91-01-05) becomes effective on January 31, 1991.
87-11-08 R1: 87-11-08 R1 AEROSPATIALE: Amendment 39-5628 as amended by amendment 39-5984. Applies to ATR-42 series airplanes, certificated in any category, unless the equivalent of Production Modification 1397 was installed prior to delivery. Compliance is required as indicated, unless previously accomplished. To prevent simultaneous loss of both pilots' primary attitude and heading information generated by Attitude and Heading Reference Systems (AHRS), accomplish the following: A. Within 15 days after June 8, 1987 (the effective date of Amendment 39-5628, AD 87-11-08), accomplish the following: 1. Isolate the pilots' AHRS (AHRS Number 1) from the System Avionics Standard Communications Bus (ASCB) in accordance with Aerospatiale Service Bulletin ATR- 42-34A-0016, dated March 23, 1987, and ensure that Electronic Flight Instrument System (EFIS) Symbol Generators having part number 700544-411, Mod-level U or subsequent, have been installed. 2. Insert the following intothe Airplane Flight Manual (AFM) Limitations Section 2. This can be accomplished by inserting a copy of this AD into the AFM and into the Flight Crew Operations Manual (FCOM), if used. a. "Disconnect autopilot at or above 200 feet above ground level (AGL)." b. "Approach operations are limited to Category I or higher weather minima." B. Replacement of the Attitude and Heading Reference Systems (AHRS) with a modified AHRS, and connection of four (4) wires between terminal blade 67VT1 and connector 1FP1-AA, in accordance with Aerospatiale Service Bulletin ATR42-34-340018, Revision 1, dated September 22, 1987, constitutes terminating action for the requirements of paragraph A., above. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAAPrincipal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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 39-5984 amends AD 87-11-08, Amendment 39-5628. This Amendment, 39-5984, becomes effective September 3, 1988.
87-23-03: 87-23-03 BRITISH AEROSPACE: Amendment 39-5757. Applies to all Model Viscount 700, 800, and 810 series airplanes which have accumulated more than 10,000 landings, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the wing due to cracking, accomplish the following: A. Before further flight: 1. Visually inspect the wing upper surface and end rib in accordance with applicable British Aerospace Preliminary Technical Leaflet No. 185 or No. 316, both dated October 23, 1986. Repeat this inspection at intervals not to exceed 25 landings. 2. Perform eddy current inspection of the wing in accordance with applicable British Aerospace Preliminary Technical Leaflet No. 185 or No. 316, both dated October 23, 1986. Repeat this inspection at intervals not to exceed 1,500 landings. B. Any cracks found as a result of the inspections required by paragraph A., above, must be repaired prior to further flight in a manner approved by the FAA. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Eddy current inspections may be deferred for 15,000 landings after incorporation of Modification D3292 or Modification FG2172 as applicable. All persons affected by this proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective December 9, 1987.