Results
2020-02-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that during inspection of the installation of oxygen containers, certain fasteners of the oxygen containers and adjacent panels in the passenger supply channels (PSCs) were found damaged or unlocked, which could result in insufficient clearance between the oxygen container and adjacent panels. This AD requires a one-time inspection of the oxygen containers and adjacent panels and applicable corrective actions, 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.
71-06-06: 71-06-06 MAULE: Amendment 39-1169. Applies to M-4-180C serial numbers 3001C through 3004C and M-4-220C serial numbers 2044C through 2060C. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To detect seat track and seat track guide spacing that could allow the seat to become free from the guides, accomplish the following: a. Remove front bucket seats. b. Determine the distance between the inner edges of the horizontal flanges of the seat tracks for each front seat (measure at front and rear of tracks and use maximum dimension). The seat tracks are the L-shaped flanges welded to the bottom of the seat frame. c. Determine the distance between the outside edges of the vertical flanges of the seat track guides. The seat track guides are the L-shaped clips welded to the fuselage. d. If the distances measured in b. and c. differ by 3/32" or less, no further action is required. e. If the difference in these dimensions is greater than 3/32", accomplish one of the following: 1. Bend one of the seat tracks inward so that the above distance requirement is satisfied. A vertical cut must be made adjacent to the front end piece of the seat track to allow the necessary bending. After bending, secure in place and reweld on the inside of track, using at least 3/4" welds at the three existing tack welds attaching the track to seat frame. Also, reweld the saw cut and check for the proper dimensions. 2. Weld an extension strip to the full length of the seat track to meet the above distance requirement using 4130 steel, Condition N sheet, .060 inches thickness and check for proper dimensions. The minimum strip width must be 1/8". 3. Any other FAA approved equivalent method. f. A seat which has to be modified in accordance with (e) above is to be reported to the Chief, Engineering and Manufacturing Branch, SO-210, FAA Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. The report should include the airplane serial number and the distances determined in (b) and (c). (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174.) The checks required by this AD in paragraphs (a), (b), (c) and (d) may be performed by the pilot. Maule Service Letter No. 21 pertains to this same subject. This amendment becomes effective March 16, 1971.
94-10-10: This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 747-100, -200, and -300 series airplanes, that requires modification of the thrust reverser control system by installing a solenoid-operated shut-off valve. This amendment is prompted by incidents of deployment of the engine fan thrust reverser during flight. The actions specified by this AD are intended to prevent such deployment, which could result in reduced controllability of the airplane.
2007-25-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 206A and 206B helicopters, serial numbers (S/N) 0004 through 3906, with two-piece vertical stabilizer (fin) supports (fin supports) installed, that requires inserting a revision into the applicable maintenance manual, verifying the torque on the fin support attachment hardware, inspecting the fin support bracket and fins for paint or gaps, and inspecting the fin support bracket for cracking, and if a crack is found, replacing the two-piece vertical fin support with a one-piece casting support. This amendment is prompted by an accident in which the fin supports failed. The actions specified by this AD are intended to detect improper torque of the fin supports' attachment hardware, gaps between the fin support bracket and the doubler, painted mating surfaces of the fin supports, vertical fin, and vertical fin inserts (fin inserts), and cracking in the fin supports, toprevent the vertical fin from rotating into the tail rotor, separation of the tail rotor, and subsequent loss of control of the helicopter.
2020-01-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, - 114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by the absence of a requirement to remove a certain Emergency Procedure in the existing Aircraft Flight Manual (AFM) after accomplishing a certain modification or replacement. This AD requires, for airplanes on which a certain modification or replacement is done, revising the AFM by removing a certain Emergency Procedure in the AFM, 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.
2001-10-04 R1: This amendment revises AD 2001-10-04, which concerns certain Air Tractor, Inc. (Air Tractor) AT-400, AT-500, and AT-800 series airplanes. AD 2001-10-04 superseded AD 2000-14-51 and lowers the safe life for the wing lower spar cap on these airplanes. The AD was the result of numerous reports of cracks in the 3/8-inch bolthole of the wing lower spar cap on the affected airplanes. We inadvertently included certain AT-800 series airplanes in the Applicability of this AD. Those AT-800 series airplanes that are equipped with the factory-supplied part number 80540 computerized fire gate should not be affected by AD 2001-10-04. This action revises the AD to reflect this change and to provide information for applying for an alternative method of compliance with this AD. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if notdetected and corrected, could result in the wing separating from the airplane during flight.
79-10-04: 79-10-04 CANADAIR: Amendment 39-3459. Applies to Models CL-44D4, and CL-44J aircraft. Compliance required within the next 1700 hours in service and, if applicable, upon application for U.S. registration and airworthiness certification, after the effective date of this AD unless already accomplished. 1) (Docket No. 78-EA-82) In order to fireproof the engine fire extinguishing system fittings in inboard and outboard nacelles, accomplish the following: a. Wrap the fittings with asbestos tape and then coat them with a suitable end dip as described in Paragraphs "2" and "3" of Canadair Service Bulletin No. CL-44D4-480, dated December 11, 1972, or an equivalent alteration. 2) (Docket No. 78-EA-85) To minimize the chance of over-pressurizing the outer auxiliary fuel tanks during pressure refueling, and to eliminate wear caused by possible interference between float arm and valve casing, accomplish the following: a. Alter the modulator and shut-off pilot valves by riveting a fabricated angle to the float, re-identify them; re-identify the fuel level control valve assembly; and functionally check the altered valves all in accordance with the "Modification Procedure" of Canadair Service Bulletin No. CL-44-485, dated April 5, 1978. 3) (Docket No. 78-EA-86) In order to reduce the probability of flammmable fluid fires within the engine cowling areas and reduce the risk of damaging engine oil and fuel drain lines located on the engine bottom cowls, accomplish the following: a. Alter the engine cowling and drain lines in accordance with the "Modification" paragraph of Canadair Service Bulletin No. CL-33D4-486 dated May 12, 1978, or an equivalent alteration. Any equivalent method of compliance 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 time may be changed 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. Compliance with this AD must be noted in the logbook of the aircraft by referencing the AD number and the specific item complied with: ex. AD 79-10-04 (2) if item (2) is being accomplished. This amendment becomes effective May 9, 1979.
94-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires dye penetrant inspections and proof pressure testing to detect cracks or ruptures of the crossover pneumatic duct, and repair or replacement, as necessary. This amendment also requires stress relieving of the crossover pneumatic duct assembly. This amendment is prompted by reports of ruptured engine bleed air crossover ducts. The actions specified by this AD are intended to prevent failure of the engine bleed air crossover duct, which could result in loss of pneumatics and damage to adjacent structure.
2007-25-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires repetitive inspections for cracking of the station (STA) 1241 bulkhead fittings just above the canted pressure deck; a one-time determination of the edge margin at seven fastener positions on each side of the airplane; and related investigative/corrective actions if necessary. This AD results from a report that an operator found a 1.65- inch crack on the STA 1241 bulkhead fitting on the left side of a Boeing Model 747-200F series airplane that had accumulated 17,332 total flight cycles. We are issuing this AD to detect and correct cracking in the STA 1241 bulkhead fittings, which could result in reduced structural integrity of the airplane.
2001-10-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Britax Sell Gmbh & Co. OHG water boilers, coffee makers, and beverage makers. This action requires inspecting the wiring for indications of overheating or electrical arcing, and if indications are found, replacing the wiring. This amendment is prompted by reports of discolored and partially melted wires. The actions specified in this amendment are intended to prevent a fire in the galley compartment due to inadequate crimping of the electrical terminal contact pins, which could result in smoke in the cockpit and cabin and loss of control of the airplane.