Results
2006-20-10: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect the attach angles on the firewall mounted hopper rinse tank shelf for damage and/or cracks and replace damaged and/or cracked attach angles with steel attach angles. Replacing the attach angles with steel attach angles terminates the repetitive inspection requirement. Reports of an uncommanded change in the engine power setting caused by separation of the hopper rinse tank shelf from the firewall prompted this AD. We are issuing this AD to detect and correct damage and/or cracks in the attach angles on the firewall mounted hopper rinse tank shelf, which could result in failure of the attach angles. This failure could lead to shelf movement under maneuver load and shifting of the engine power cables, which could result in an uncommanded engine power setting change.
98-04-25: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company Model 2000 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2006-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires an inspection to determine if the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, and repair if necessary. This AD results from cases of girt bar disengagement from the floor fitting during deployment tests of slide rafts at the forward passenger doors. We are issuing this AD to prevent disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane.
2019-08-01: We are adopting a new airworthiness directive (AD) for certain RECARO Aircraft Seating GmbH & Co. KG (RECARO) Model 3510A and 3510D passenger seats. This AD requires modification and re-identification of all affected RECARO model passenger seats. This AD was prompted by an analysis that the affected RECARO model passenger seats contain a seat pan assembly design that can trap a person using the seat to assist during an emergency evacuation. We are issuing this AD to address the unsafe condition on these products.
87-16-06: 87-16-06 AIRBUS INDUSTRIE: Amendment 39-5692. Applies to Airbus Industrie Model A300 and A310 airplanes listed in Airbus Industrie Service Bulletins A300-32-374, Revision 1, dated July 15, 1986, and A310-32-2023, Revision 2, dated February 20, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent collapse of the nose landing gear due to failure of the drag strut upper attachment pin, accomplish the following: A. Prior to the accumulation of 16,000 landings or within the next 2,000 landings, whichever occurs later, replace the nose landing gear drag strut upper attachment pin in accordance with Airbus Industrie Service Bulletin A300-32-374, Revision 1, dated July 15, 1986 (applicable to Model A300 airplanes), or A310-32-2023, Revision 2, dated February 20, 1987 (applicable to Model A310 airplanes). B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level ofsafety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 Airbus Industrie, Airbus Support Division, Centreda, Avenue Didier Daurat, 31700 Blagnac, 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 becomes effective September 3, 1987.
76-12-07: 76-12-07 BELL: Amendment 39-2640 as amended by Amendment 39-3569. Applies to tail rotor pitch control chains, P/N 204-001-739-3, installed on all Bell Model 204B helicopters and on Bell Model 205A-1 helicopters, S/N 30001 through 30228, certificated in all categories (Airworthiness Docket No. 76-SW-19). Compliance required for Model 204B helicopters within 25 hours' time in service after July 19, 1976, and thereafter, at intervals not to exceed 25 hours' time in service from the last inspection. Compliance required for Model 205A-1 helicopters within 10 hours' time in service after October 29, 1979, and thereafter, at intervals not to exceed 10 hours' time in service from the last inspection, until Bell Service Bulletin 205-78-5 dated May 16, 1978, is incorporated per paragraph (f) of this AD. To detect cracks in the tail rotor pitch change chain link segments and to prevent possible failure of the tail rotor pitch change chains, accomplish the following repetitive inspections on chains, Part Number 204-001-739-3. (a) Remove the cover, if installed, from the chain assembly. (b) Inspect each chain assembly for cracks in the link segments using a 10-power or higher magnifying glass. Particular attention should be placed on the portion of the chain that travels over the sprocket and that extends six inches each side of this area or portion. (c) Remove chains with cracked or broken links or segments before further flight in accordance with the applicable maintenance manual or an equivalent FAA approved procedure. (d) Install chains with uncracked segments in accordance with the applicable maintenance manual and rig the controls as specified in the applicable maintenance manual or an equivalent FAA approved procedure. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (f) Within 100 hours' time in service after October 29, 1979, modify Bell Model 205A-1 aircraft in accordance with Bell Service Bulletin 205-78-5 dated May 16, 1978, as appropriate. This, in part, requires removal of the chain and cable control system and installation of the push-pull control system in conjunction with use of the Model 212 type of tail rotor. (g) Aircraft may be flown in accordance with FAR 21.197 to a location where modification required by paragraph (f) of this AD may be accomplished. (h) Equivalent means of compliance with paragraph (f) of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, Fort Worth, Texas. Amendment 39-2640 became effective July 19, 1976. This Amendment 39-3569 becomes effective October 29, 1979.
86-22-10: 86-22-10 COLLINS AVIONICS DIVISION/ROCKWELL INTERNATIONAL: Amendment 39-5462. Applies to Collins Model DME-42, P/N 622-6263-002, Distance Measuring Equipment. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent display of erroneous DME-42 information, accomplish the following: (a) For aircraft with Collins Model DME-42 Distance Measuring Equipment installed, within the next 25 hours time-in-service after the effective date of this AD: (1) Visually inspect all installed DME-42 equipment to determine if Part Number (P/N) 622-6263-002 transceivers are installed. (2) If installed, prior to further flight remove the transceiver(s), and tag the unit(s) unserviceable until the modification specified in paragraph (b) of this AD is accomplished. (b) For all affected DME-42 transceivers, P/N 622-6263-002, not installed in an aircraft, prior to further use modify and reidentify the transceiver inaccordance with the instructions contained in Collins Service Bulletin DME-42 SB-6, dated October 15, 1986. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. All persons affected by this directive may obtain copies of the documents(s) referred to herein upon request to Collins Avionics Division/Rockwell International, 400 Collins Road, N.E., Cedar Rapids, Iowa 52498; or the FAA, Rules Docket, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on November 17, 1986.
2000-01-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires the replacement of fuse pins in the attachment fittings and support fittings of the main landing gear with new, improved fuse pins. This amendment is prompted by a report of corrosion of a fuse pin of a similar design on the main landing gear of a Boeing Model 767 series airplane. The actions specified by this AD are intended to prevent corrosion and subsequent fracture of the fuse pins, which could result in collapse of the main landing gear and the loss of the inboard flap and spoilers.
2006-19-10: We are adopting a new airworthiness directive (AD) that supersedes AD 2005-17-19, which applies to certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. AD 2005-17-19 currently requires you to measure and adjust the crew seat break-over bolts and to replace the crew seat recline locks on both crew seats. Since we issued AD 2005-17-19, CDC developed new crew seat break-over pins to replace the old crew seat break-over bolts. Consequently, this AD retains the action from AD 2005-17-19 of replacing the crew seat recline locks on both seats and adds the action of replacing the crew seat break-over bolts with the new crew seat break-over pins on both seats. We are issuing this AD to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury. DATES: This AD becomes effective on October 24, 2006. As of October 24, 2006 the Director of the Federal Register approved the incorporation by reference of CirrusDesign Corporation Service Bulletin SB 2X-25-17 R1, Issued: December 15, 2005, Revised: January 20, 2006. As of October 13, 2005 (70 FR 51999, September 1, 2005), the Director of the Federal Register previously approved the incorporation by reference of Cirrus Design Corporation Service Bulletin SB 2X-25-06 R4, Issued: August 13, 2004; Revised: May 5, 2005.
96-07-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspection(s) to verify that the position indicator of the fuel balance transfer valve (FBTV) is in the closed position, and closing the FBTV, if necessary; and deactivation of the fuel balance transfer system (FBTS). This amendment is prompted by a report that, under certain failure conditions, the actuator of the FBTV could remain in the open position without a flight deck indication. The actions specified by this AD are intended to ensure that the FBTV is not in the open position during flight, which could lead to the reduction of fuel supply to the engines during cross-feed operation and consequent engine fuel starvation.