Results
2018-25-15: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the inboard lower flange and adjacent web near the forward attachment of the outboard flap track at a certain position on a Model 737-300 airplane. The flap tracks of Model 737-300 airplanes are similar to the flap tracks of Model 727 airplanes. This AD requires repetitive detailed inspections and surface high frequency eddy current (HFEC) inspections of each outboard flap track at certain positions for any crack and discrepancy, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
98-19-20: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-7B and -7B/2 series turbofan engines. This action requires initial and repetitive inspections of certain hydromechanical unit (HMU) overspeed governor (OSG) spool valves for out-of-specification conditions or the presence of heavy contact or galling on the spool valve, and optional installation of an improved HMU as a terminating action to the inspections. This amendment is prompted by a report of a flameout that occurred on a flight test engine due to a failed HMU OSG spool valve shaft. The actions specified in this AD are intended to prevent failure of the HMU OSG spool valve shaft, and subsequent engine flameout.
80-24-04: 80-24-04 HUGHES HELICOPTERS: Amendment 39-3979. Applies to Model 369 Series Helicopters, certified in all categories, equipped with Automatic Engine Reignition System. Compliance is required as indicated unless already accomplished. To prevent the possibility of the middle front seat occupant accidentally deactivating the Automatic Engine Reignition System and also from blocking the crew's view of the automatic reignition "ARMED" and "RE-IGN" advisory lights, accomplish the following: (a) Within thirty (30) consecutive calendar days or prior to flight in falling and/or blowing snow, whichever comes first, after the effective date of this AD, install a placard in close proximity to the Automatic Engine Reignition Arming switch and in plain view of the pilot which states "Middle front seat is not to be occupied during flight in falling and/or blowing snow" or equivalent words. (b) Special flight permits may be issued in accordance with FAR 21.197 and .199 to operate aircraft to a base for the accomplishment of modification required this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective December 4, 1980.
2005-23-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires an accelerated schedule of repetitive testing of the elevator servo control loops, and corrective actions if necessary. This AD results from reports of failed elevator servo controls due to broken guides. We are issuing this AD to ensure proper functioning of the elevator servo controls. Failure of the elevator servo controls during certain phases of takeoff could result in an unannounced loss of elevator control and consequent reduced controllability of the airplane.
2018-25-13: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 airplanes. This AD was prompted by a report of chafing of a wire bundle located at the bottom of the right hand (RH) electrical cabinet. This AD requires a one-time general visual inspection of the wiring bundle for damage, measurement of the clearance between the metallic plate and the wiring bundle, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-25-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of inadequate clearance between the thermal protection system (TPS) insulation blankets and the electronic engine control (EEC) wiring, which resulted in damaged wires. This AD requires repetitive inspections of the EEC wire bundles and clips, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
83-19-06: 83-19-06 BOEING: Amendment 39-4736. Applies to Boeing Model 767 series airplanes equipped with Pratt and Whitney JT9D-7R4D engines certificated in all categories. In order to minimize the possibility of engine stall conditions during low power (idle) descent accomplish the following, unless already accomplished: \n\n\tA.\tWithin 30 days after the effective date of this AD, perform the airplane circuit modifications detailed in Boeing Alert Service Bulletin 767-73A7, dated September 2, 1983, or later FAA approved revisions. \n\n\tB.\tWithin 120 days after the effective date of this AD install Package B type hydromechanical fuel controls in accordance with Pratt & Whitney Aircraft Service Bulletin JT9D-7R4-73-4, dated May 3, 1983, or later FAA approved revisions. \n\n\tNOTE: Engine idle speeds associated with these modifications are not intended to replace or eliminate the requirement for proper observance of existing engine anti-ice limitations when operating in icing conditions, including selection of engine anti-ice "ON" and establishment of correct fan speeds prior to entering icing conditions. \n\n\tC.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tAirplanes may be flown in accordance with FAR 21.197 to a maintenance base to accomplish the above. \n\n\tThis amendment becomes effective October 11, 1983.
2005-23-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all Model A300 F4-605R airplanes. That AD currently requires repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. This new AD revises certain inspection thresholds and intervals. This new AD also adds inspections to detect cracks of additional attachment holes. This AD results from reports of cracks found before the inspection thresholds in the existing AD and cracks found in nearby areas not inspected by the existing AD. We are issuing this AD to prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame. DATES: This AD becomes effective December 19, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 19, 2005. On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
84-09-01: 84-09-01 BEECH: Amendment 39-4847. Applies to Models and Serial Numbers of 33, 35, 36, 50, 55, 56, 58 (except 58P), 58TC, and 95 series airplanes listed below with seating capacity for more than five occupants. MODELS SERIAL NUMBERS E33, F33, G33 CD-1119 through CD-1304 E33A, F33A CE-180 through CE-918, CE-920 through CE-922, CE-924, CE-926 and CE-928 E33C, F33C CJ-1 through CJ-155 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC, V35B and V35B-TC D-1 through D-10347, D-10349 through D-10352, D-15001 and D-15002 36, A36 E-1 through E-1421, E-1423 through E-1550, E-1552 through E-1568, E-1570 through E-1580, E-1582 through E-1593 A36TC EA-1 through EA-20, EA-22 through EA-27, EA-29 through EA-32 50 H-1 through H-11 B50, C50 CH-12 through CH-360 D50, D50A, D50B, D50C, D50E DH-1 through DH-347 E50 EH-1 through EH-70 F50 FH-71 through FH-93, FH-95 and FH-96 G50 GH-94, GH-97 throughGH-119 H50 HH-120 through HH-149 J50 JH-150 through JH-176 95-55, 95-A55, 95-B55, 95-B55A TC-1 through TC-349, TC-351 through TC-2339, TC-2341 through TC-2354 95-C55, 95-C55A, D55, D55A, E55, E55A TC-350, TE-1 through TE-1151, TE-1153 throughTE-1180 95-B55B (T42A) TF-1 through TF-70 56TC, A56TC TG-2 through TG-94 58, 58A TH-1 through TH-1026, TH-1028 through TH-1061, TH-1063 through TH-1066, TH-1068 through TH-1079 58TC, 58TCA TK-1 through TK-106, TK-109 95, B95, B95A, D95A, E95 TD-2 through TD-721 Compliance: Required as indicated, unless already accomplished. To assure adequate emergency egress provisions, within the next 100 hours time-in- service after the effective date of this AD, accomplish the following: (a) Visually inspect the openable window installation located on the side opposite the entry door to determine: (1) That Beech P/N 96-534051-61 or equivalent release pin has a red handle. (2) That any curtain bars and/or curtains installed are attached to the openable window and not on the window frame so that they will not restrict egress in the event of an emergency. (3) That the tab on the handle assembly does not catch on the back of the hooks on the window. (b) If, as the result of the inspection required by Paragraph a), any deficiencies in the above mentioned requirements are noted, prior to further flight: (1) Paint the handle of the existing release pin red. (2) Either remove the curtains and curtain bars or modify the curtain installation by attaching the bars to the openable window. (3) Trim tab on the back of the handle assembly as required so it doesn't catch on the back of the hooks on the window. (c) Replace existing placard with either Beech placard P/N 58-530258-1 (screwed- on type) or 58-530258-3 (adhesive back) as required which reads as follows: "EMERGENCY EXIT LIFT LATCH-PULL PIN PUSH WINDOW OUT." Locate placard below openable window on the molding. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. This AD supersedes AD 76-04-07, Amendment 39-2525. This amendment becomes effective on May 25, 1984.
2002-16-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires replacement of certain symbol generator units (SGUs) in the electronic flight instrument system with new, improved SGUs, and modification of associated equipment and wiring. This action is necessary to ensure that the flightcrew has adequate flight information by preventing temporary loss of data from the primary flight and navigation displays. Inadequate flight information could result in reduced situational awareness for the flightcrew, which could contribute to loss of control or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.