Results
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.
2018-25-06: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-223F and Model A330-243F airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both left- hand (LH) and right-hand (RH) sides, and applicable related investigative and corrective actions. We are issuing this AD to address the unsafe condition on these products.
2018-25-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that, for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant was not applied between all surfaces of the joint parts. This AD requires modification of the hybrid joints of the passenger doors by applying additional corrosion protection to the hybrid joints of the passenger door frame fittings. We are issuing this AD to address the unsafe condition on these products.
78-25-07: 78-25-07 CESSNA: Amendment 39-3371. Applies to Models A150M (Serial Numbers A1500654 through A1500734) and A152 (Serial Numbers A1520735 through A1520833) airplanes. COMPLIANCE: Required as indicated, unless already accomplished. To assure necessary structural integrity of the vertical fin attachment to the airplane, in accordance with the instructions contained in Cessna Single Engine Service Letter SE78-62, dated October 13, 1978, or later revisions, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) Replace the two existing Part Number 0431009-3 vertical fin attach brackets with two new Part Number 0431009-3 attach brackets obtained from Cessna. B) Return the two brackets removed from each airplane to the Cessna factory for metallurgical examination. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective December 22, 1978.
2018-25-03: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that debris from the parking brake shut off valve (PBSOV) could create a partial blockage of the restrictor check valve in the hydraulic return line of the PBSOV. This AD requires replacing the restrictor check valve with an improved valve that has a filter screen. We are issuing this AD to address the unsafe condition on these products.
83-09-01: 83-09-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4644. Applies to Model N24A Nomad airplanes (all serial numbers) certificated in any category. Compliance: Required within the next 50-hours time-in-service, unless already accomplished. To ensure Aircraft Flight Manual (AFM) one engine inoperative climb performance is achieved, accomplish the following: (a) Fabricate and install a placard on the instrument panel in plain view which reads as follows: "REDUCE WEIGHT OBTAINED FROM WEIGHT/ALTITUDE/TEMPERATURE CHARTS BY 200 LBS and operate the airplane in accordance with this placard. (b) The placard required by paragraph (a) may be installed by the pilot. NOTE: A maintenance record entry as prescribed by FAR 91.173 is required when complying with this AD. (c) The placard required by paragraph (a) may be removed when DOA AFM General Amendment G8 dated March 17, 1983, has been incorporated in the AFM. (d) An equivalent means of compliance with thisAD may be used if approved by the Manager, Honolulu Aircraft Certification Field Office, Room 7108, Prince Kuhio Federal Building, 300 Ala Moana Boulevard, Honolulu, Hawaii 96850. This amendment becomes effective on May 16, 1983.