Results
98-20-38 R1: The FAA adopts a new airworthiness directive (AD) to revise AD 98-20-38, which applies to all Beech 200 series airplanes. AD 98-20-38 requires you to revise 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. Part of the applicability of AD 98-20-38 includes the Raytheon Models B200 and B200C airplanes. AD 96-09-13 already requires AFM revisions on this subject for these airplane models. Consequently, FAA is revising AD 98-20-38 to remove the Models B200 and B200C from the applicability and add clarification that AD 96-09-13 affects these airplanes. We are issuing this AD to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations.
80-02-06: 80-02-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 3656. Applies to Fan Jet Falcon Series D, E and F airplanes, Serial numbers 1 through 404, certificated in all categories. Compliance is required as indicated, unless already accomplished. To reduce the possibility of flexible line failure in the engine fire extinguisher system, within the next 100 hours time in service after the effective date of this AD, unless already accomplished, in each engine fire extinguisher system, modify the rigid tubing and install a new flexible line in accordance with paragraph 2, "Accomplishment Instructions," of Avions Marcel Dassault, Service Bulletin No. 632, dated July 18, 1979, or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region. This amendment becomes effective January 24, 1980.
2023-12-24: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) (type certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model M601E-11AS, M601E-11S, H75-100, H80-100, and H85-100 engines. This AD is prompted by reports of multiple failures of the needle bearing installed in propeller governors having part numbers (P/Ns) P-W11-1 or P-W11-2, caused by self-generated debris from the needle bearing, which led to oil contamination. This AD requires replacement of the affected propeller governors with a redesigned propeller governor and prohibits installation of the affected propeller governors, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
97-04-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pacific Scientific Company, HTL/Kin-Tech Division, fire extinguisher bottle cartridges (squibs), which may be installed on various transport category airplanes. This action requires a one-time inspection of the electrical receptacle of these fire extinguisher bottle cartridges and their mating connectors to detect the presence of aluminum foil in the area of the pins of the cartridges and the connectors, and removal of any aluminum foil that is present. This amendment is prompted by a report of failure of a fire extinguisher bottle cartridge to discharge as a result of the presence of aluminum foil in the cartridge, which caused electrical shorting of the pins. The actions specified in this AD are intended to prevent such shorting, which could result in failure of the fire extinguisher bottle to discharge when commanded.
2000-12-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment requires revising the compliance thresholds for the inspection and requires that the inspections be repeated at reduced intervals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
2014-19-04: We are superseding Airworthiness Directive (AD) 2004-03-19, which applies to certain Airbus Model A320-111, -211 and -231 series airplanes. AD 2004-03-19 required repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. AD 2004-03-19 also provided for an optional terminating modification for the repetitive inspection requirements. This new AD requires accomplishing the modification by installing washers between the transition pick-up angle and the pin nuts, and doing related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability of AD 2004-03-19. This AD was prompted by a determination that the optional terminating modification must be required in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could resultin reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
97-04-13: This amendment adopts a new airworthiness directive (AD) that applies to Mitsubishi Heavy Industries, Ltd., (Mitsubishi) MU-2B series airplanes. This AD requires removing the vent check valve assembly from the bulkhead between the fuel tanks. This AD results from an incident where both engines on an affected airplane failed near the end of a flight because of lack of fuel to the engines. The incident is attributed to the fuel filler caps on the top of the wings not sealing correctly. The actions specified by this AD are intended to prevent the inability of both engines to utilize the entire fuel supply because of the outboard fuel not transferring to the center tank, which could result in an uncommanded engine shutdown.
79-15-01: 79-15-01 CESSNA: Amendment 39-3517. Applies to: Model 205 (210-5) Series (Serial Numbers 641, 205-0001 through 205-0577) airplanes; Model 206 (Serial Numbers 206-0001 through 206-0275) airplanes; Model U206/TU206 Series (Serial Numbers U206-0276 through U206-1444, U20601445 through U20604287, U20604289, U20604290, U20604292 through U20604335, U20604337 through U20604389, U20604391 through U20604787, U20604789 through U20604894, U20604896 through U20604906, U20604908 through U20604911, U20604913 through U20604958, U20604960 through U20604963, U20604965 through U20604973, U20604975 through U20604977, U20604980 through U20604985, U20604987 through U20604990, U20604992, U20604993, U20604995 through U20604998, U20605000 through U20605018, U20605020 through U20605058, U20605060, U20605061, U20605063, U20605066, U20605069, U20605071 through U20605073, U20605075, U20605077, U20605078, U20605083, U20605085, U20605086, U20605088, U20605095, U20605097, U20605100, U20605102, U20605105, U20605107 and U20605110) airplanes; Model P206/TP206 Series (Serial Numbers P206-0001 through P206-0603, P20600604 through P20600647) airplanes; Model 207/T207 Series (Serial Numbers 20700001 through 20700530) airplanes; Model T210 Series (Serial Numbers T210-0001 through T210-0454) airplanes; Model 210/T210 Series (Serial Numbers 21057841 through 21063013, 21063015 through 21063086, 21063088 through 21063228, 21063230 through 21063287, 21063289 through 21063298, 21063300 through 21063324, 21063326 through 21063389, 21063391 through 21063393, 21063396 through 21063399, 21063401, 21063403 through 21063407, 21063412, 21063413, 21063419, 21063424 and 21063426) airplanes; Model P210 Series (Serial Numbers P21000001 through P21000255, P21000257 through P21000273, P21000275 through P21000279, P21000281 through P21000283, P21000287, P21000290 and P21000292) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To provide instructions for recognition of fuel system vapor blockage and operating procedures to restore normal fuel flow, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) On Model 205 (210-5) series (Serial Numbers 641, 205-0001 through 205-0555); Model 206 (Serial Numbers 206-0001 through 206-0137); Model 210 (Serial Numbers 21057841 through 21058351) airplanes, examine the airplane and its maintenance record to determine whether Cessna Service Kit SK 205-5 or SK 206-2 has been installed. If neither of these kits is installed, make an entry in the maintenance records indicating this AD is not applicable to the airplane and no further action is required. If Cessna Service Kit SK 205-5 or SK 206-2 has been installed, accomplish Paragraphs B) 1 and 2 of this AD. B) On affected (see Applicability Statement) Model 205 (210-5) series airplanes having serial numbers between 205-0556 through 205-0577 inclusive, Model 206 series airplanes having serial numbers between 206-0138 through 206-0275 inclusive, Model U206/TU206 series airplanes having serial numbers between U206-0276 through U206-1444 inclusive and U20601445 through U20604649 inclusive, Model P206/TP206 series airplanes having serial numbers between P206-0001 through P206-0603 inclusive and P20600604 through P20600647 inclusive, Model 207/T207 series airplanes having serial numbers between 20700001 through 20700482 inclusive, Model 210/T210 series airplanes having serial numbers between 21058352 through 21062954 inclusive, Model T210 series airplanes having serial numbers between T210-0001 through T210-0454 inclusive and Model P210 series airplanes having serial numbers between P21000001 through P21000150 inclusive; 1. Install Cessna P/N 1205252-2 placard next to the fuel flow indicator which reads as follows: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP - ON, ADJUST MIXTURE. 2. SELECT OPPOSITE TANK. 3. WHEN FUELFLOW STEADY, RESUME NORMAL OPERATIONS. SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." 2. Place Cessna special procedure card P/N D1189-13 in the airplane at a location accessible to the pilot at all times when he is in the pilot's seat and revise the aircraft Equipment List by adding this card as a required item of equipment. C) On affected (See Applicability Statement) Model U206/TU206 series airplanes having serial numbers between U20604650 and U20605110 inclusive, Model 207/T207 series airplanes having Serial Numbers between 20700483 through 20700530 inclusive, Model 210/T210 series airplanes having Serial Numbers between 21062955 through 21063426 inclusive and Model P210 series airplanes having Serial Numbers between P21000151 through P21000292 inclusive; 1. Install Cessna P/N 1205252-1 placard next to the fuel flow indicator which reads as follows: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP - ON, ADJUST MIXTURE.2. SELECT OPPOSITE TANK. 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS. SEE P.O.H. FOR EXPANDED INSTRUCTIONS." 2. Revise the Pilot's Operating Handbook for the following airplanes by inserting the revision specified below: Airplane Model Revision Cessna Part Number U206G Rev 1 22 May 1979 D1147R1-13PH TU206G Rev 2 22 May 1979 D1148R2-13PH 207A Rev 1 22 May 1979 D1149R1-13PH T207A Rev 2 22 May 1979 D1150R2-13PH 210N Rev 3 22 May 1979 D1151R3-13PH T210N Rev 3 22 May 1979 D1152R3-13PH P210N Rev 3 22 May 1979 D1153R3-13PH D) The modification required by this AD may be accomplished by owner/operator authorized to perform preventative maintenance under FAR 43. An entry should be made in the aircraft maintenance record indicating compliance; i.e., "AD 79-15-01 complied with by installing placard P/N 1205252-2 and Special Procedure Card P/N D1189-13 this date _________" or "AD 79-15-01 complied with by installing placard P/N 1205252-1 and Pilot's Operating Handbook Rev _____ dated _______, Cessna P/N _______ this date ___________." E) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. F) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, 601 E. 12th Street, Kansas City, Missouri 64106. Cessna Service Letter SE 79-25, dated April 30, 1979, and Supplement No. 1 thereto dated June 4, 1979, pertains to the subject matter of this Airworthiness Directive. Cessna Aircraft Company has mailed copies to all owners of record. Additional copies may be obtained from: Cessna Aircraft Co., Marketing Division, Attn: Customer Service Department, Wichita, Kansas 67201; Telephone (316) 689-9111. This Amendment becomes effective July 26, 1979.
2014-19-01: We are superseding an airworthiness directive (AD) 2013-22-20 for Embraer S.A. Model EMB-505 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks beyond acceptable limits in the carbon discs of the left hand (LH) and right hand (RH) brake assemblies. We are issuing this AD to require actions to address the unsafe condition on these products.
2005-01-19: The FAA is adopting a new airworthiness directive (AD) to supersede Airworthiness Directive 2004-10-15, which applies to certain GTX 330 and GTX 330D Mode S transponders that are installed on airplanes. AD 2004-10-15 currently requires you to install GTX 330/330D Software Upgrade Version 3.03, 3.04, or 3.05. This AD applies to certain GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S transponders that are installed on airplanes and is the result of observations that the GTX 33/33D/330/330D may detect, from other airplanes, the S1 (suppression) interrogating pulse below the minimum trigger level (MTL) and, in some circumstances, not reply. The GTX 33/33D/330/330D should still reply even if it detects S1 interrogating pulses below the MTL. Consequently, this AD would require you to install a GTX 33/33D/330/ 330D Software Upgrade to at least Version 3.06. No additional action is necessary for those airplanes that have transponders Software Upgrade 3.03 installed. Software Upgrade Versions 3.03 and 3.06 correct a TAS, TCAD, and TCAS I system "whisper-shout" problem that could potentially lead to the aircraft not being visible at certain ranges. TCAS II systems are not affected. We are issuing this AD to prevent interrogating aircraft from possibly receiving inaccurate replies due to suppression from aircraft equipped with the GTX 33/33D/330/330D Mode S transponders when the pulses are below the MTL. The inaccurate replies could result in reduced vertical separation.