Results
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.
98-20-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This amendment requires a one-time inspection for different data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This action also adds airplanes to the applicability of the existing AD. This amendment is prompted by a report of the failure of a hose assembly in the fire extinguisher system of the engine nacelle due to cracks, caused during manufacture of the hose assemblies, in the swaged ferrule that attaches the hose to the end fitting. The actions specified by this AD are intended to prevent failure of hose assemblies, which could prevent theproper distribution of fire extinguishing agent within the engine nacelle in the event of a fire.
98-19-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires modifying the sliding surface of the door 1 left and door 1 right evacuation slide/rafts. This amendment is prompted by a report of injuries to evacuees using the slide/raft to exit the airplane; the evacuees were unable to achieve adequate initial sliding speed and adequate momentum to carry them expeditiously down the slide/raft. The actions specified by this AD are intended to prevent evacuee overload of the slide/rafts, and consequent impeded evacuation and injury to the evacuees.
2002-16-17: This amendment adopts a new airworthiness directive (AD) that applies to certain Barry Aviation, LLC Model PZL-Krosno KR-03A "Peregrine" (Puchatek) sailplanes. This AD requires you to inspect to ensure that the correct horizontal stabilizer attachment fittings are installed, install the correct fittings if necessary, and incorporate a "NO LIFT" placard to the vertical stabilizer. This AD is the result of reports of cracks in the horizontal stabilizer attachment fittings on the affected sailplanes. Analysis of these incidents reveals that incorrect fittings were installed. The actions specified by this AD are intended to prevent such cracks in the horizontal stabilizer attachment fittings, which could result in the horizontal stabilizer separating from the sailplane with consequent loss of control of the sailplane.
2018-24-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 airplanes. This AD was prompted by reports that filters, which are integral to certain T-unions in the landing gear hydraulic control system, disconnected from their housing and, in some cases, migrated. This AD requires replacing certain T- unions with an integral filter with T-unions without an integral filter. We are issuing this AD to address the unsafe condition on these products.
98-18-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and Model 737 series airplanes, that requires replacement of the actuator of the engine fuel shutoff valve and the fuel system crossfeed valve with an improved actuator. This amendment is prompted by a report indicating that, during laboratory tests, the actuator clutch on the engine fuel shutoff and crossfeed valves failed to function properly. The actions specified by this AD are intended to prevent improper functioning of these actuators, which could result in a fuel imbalance due to the inability of the flightcrew to crossfeed fuel; improperly functioning actuators also could prevent the pilot from shutting off the fuel to the engine following an engine failure and/or fire.
48-29-01: 48-29-01 NAVION: Applies to All Airplanes Employing Carter Engine Driven Fuel Pumps Not Presently Equipped With Vent Drain Lines. To be accomplished as soon as possible but not later than October 15, 1948. Several instances of rupture of the main diaphragm of Carter fuel pumps have occurred. This is considered a fire hazard, since fuel can then squirt from the pump breather hole onto the engine. To correct this condition the pump breather should be provided with an overboard drain to carry fuel clear of the airplane if the diaphragm ruptures. Before installing the drain line, the fiber screen and snap ring must be removed from the pump breather opening. The drain line should vent into a low pressure area so that any fuel leaving this drain will not be in the proximity of any engine or cabin heater exhaust and will not contact the airplane or enter any air intake line, in ground or flight operation. (Ryan Navion Service Letter No. 47 covers this same subject.)
2002-16-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model 717-200 airplanes. This action requires repetitive tests to detect failure of the solenoid operated shut-off valve (SOV) of the inboard and outboard spoiler actuator assemblies, and corrective action if necessary. This action is necessary to detect and correct conditions associated with high electrical resistance in the solenoid, which, in combination with the failure of a spoiler actuator, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
93-14-19R1: We are removing Airworthiness Directive (AD) 93-14-19, which applied to certain The Boeing Company Model 767-200 and -300 series airplanes. AD 93-14-19 required inspections for disbonding of the trailing edge wedge of the leading edge slat; and repair, if necessary. We issued AD 93-14-19 to prevent the loss of a trailing edge wedge, which could result in reduced maneuver margins, reduced speed margins to stall, and unexpected roll before stall warning, all of which would adversely affect the controllability of the airplane. Since we issued AD 93-14-19, an updated stability and control analysis showed that the worst-case scenario of a trailing edge wedge disbond in-flight would not adversely affect the controllability of the airplane. Accordingly, AD 93-14-19 is removed.
2018-22-13: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a technical issue detected on the inboard aileron electro-hydrostatic actuators that caused potential erroneous monitoring of those actuators. This AD requires revising the airplane flight manual to provide the flightcrew with updated procedures related to inboard aileron fault operations. We are issuing this AD to address the unsafe condition on these products.
94-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that requires inspections to detect cracking in the No. 2 engine pylon lower spar forward mount and thrust link fitting attach bolts, replacement of cracked bolts, and the eventual replacement of all bolts made of H-11 material with bolts made of Inconel. This amendment is prompted by reports of failures of these attach bolts due to stress corrosion. The actions specified by this AD are intended to prevent failure of the attach bolts, which could reduce the fail-safe capability of the attachment assembly.
2005-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB 2000 airplanes. This AD requires modifying the manual feather-and-unfeather system for the propellers to make the design of the system more robust. This AD results from reports of in- flight engine shutdown caused by uncommanded operation of the feather pump of the propeller. We are issuing this AD to prevent uncommanded feathering of the propeller, which could result in the shutdown of an engine during flight and consequent reduced controllability of the airplane.
68-02-01: 68-02-01 BRISTOL SIDDELEY: Amendment 39-542. Applies to deHavilland Model Gipsy Queen Series 70 Engines with Crankshafts with Modifications 1399 (R.155), 1609 (R.259), 2289 (R.155 and R.259), 2931 (R.563 and R.564), or Repair Schemes R.155 and R.259 incorporated. Compliance required as indicated, unless already accomplished. To prevent failure of the crankshaft front end that could result in loss of the propeller, accomplish the following: (a) Within the next 400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, visually inspect the crankshaft for cracks, in accordance with Bristol Siddeley Technical News Sheet (TNS) G.Q. 70 No. 105, dated August 14, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (b) If cracks are found during the inspections required by paragraph (a), replace cracked crankshaft before further flight with an uncracked crankshaft, or incorporate Gipsy Modification 2925 (R.550). If Gipsy Modification 2925 (R.550) is not incorporated, inspect the replacement crankshaft in accordance with paragraph (a). (c) If no cracks are found during the inspections required by paragraph (a), incorporate Modification 2925 (R.550), or an FAA-approved equivalent, at next overhaul. (d) The repetitive inspections required by paragraph (a) may be discontinued after the incorporation of Gipsy Modification 2925 (R.550). This amendment becomes effective February 16, 1968.
2002-19-52: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, -700C, -800, and - 900 series airplanes; Model 747 series airplanes; and Model 757 series airplanes, that currently requires revision of the FAA-approved airplane flight manual (AFM) to advise the flight crew of certain operating restrictions for maintaining minimum fuel levels; prohibits use of the horizontal stabilizer tank on certain airplanes, and prohibits the installation of certain fuel pumps. This amendment requires concurrent removal of the currently required AFM revisions and insertion of new AFM revisions; requires installation of placards to alert the flightcrew to the operating restrictions; and prohibits installation of any uninspected pumps. This amendment permits the AFM revision and placard to be removed under certain conditions. The actions specified in this AD are intended to prevent fuel vapors from coming into contact with an ignition source inthe center wing fuel tank, horizontal stabilizer fuel tank, center auxiliary fuel tank (body tank), or auxiliary fuel tanks 1 and 4, which could result in fire/ explosion.
2018-20-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-300 series airplanes. This AD was prompted by reports indicating that a certain emergency exit door could not be opened during maintenance. This AD requires a detailed inspection of the ball bearings of an emergency exit, replacement of bearings if necessary, application of corrosion inhibiting compound (CIC), and revision of the maintenance or inspection program, as applicable. We are issuing this AD to address the unsafe condition on these products.
2005-23-03: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires replacement of the spherical accumulator for the main hydraulic system with a new cylindrical accumulator. For certain airplanes, this AD also requires modification of the accumulator pressure gauge. This AD results from reports of the failure of two thrust reverser accumulators (which are similar to the main hydraulic system's spherical accumulator) and fatigue cracks found on four thrust reverser accumulators. We are issuing this AD to prevent failure of the spherical accumulator for the main hydraulic system, due to fatigue cracking on the threads, which could result in the loss of hydraulic power, damage to the surrounding airplane structure, and loss of airplane control. The failure of the accumulator could also result in injury to any persons in the surrounding area. The loss of hydraulic fluid could also leak onto a potential source of ignition and result in a consequent fire.
81-13-51: 81-13-51 CANADAIR: Amendment 39-4268. Applies to all Canadair CL-600 series airplanes certified in all categories. To detect dragging wheel brakes, unless already accomplished, accomplish the following prior to further flight. A. Inspect and replace, if necessary, wheel brake assembly P/N 600-85083-55 with wheel brake assembly P/N 600-85083-57 in accordance with Canadair Alert Service Bulletin A600-0045, Revision 1, dated June 15, 1981. B. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197. C. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective December 7, 1981 and was effective earlier to those recipients of Telegraphic AD T81-13-51 dated June 19, 1981.