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88-19-07: 88-19-07 EMPRESA BRAZILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-6008. Applicable to all Model EMB-120 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To reduce the potential for flap asymmetry that could lead to loss of control of the airplane in a critical phase of flight, accomplish the following: A. Within 15 days after the effective date of this AD, revise the FAA-approved Airplane Flight Manual (AFM) to include Revision 9 (for EMB-120RT AFM 120/794) or Revision 14 (for EMB-120 AFM 120/624), as applicable. B. Within 90 days after the effective date of this AD accomplish the following: 1. Replace the flap actuator solenoid valves with new valves equipped with new filters, in accordance with Embraer Service Bulletin 120-027-0050, dated April 13, 1988; 2. Replace the inlet filter fitting of the flap actuators, in accordance with Embraer Service Bulletin 120-027-0042, dated February 10, 1988; and 3. Install in-line filters to the flap control hydraulic plumbing, in accordance with Embraer Service Bulletin 120-027-0038, dated November 16, 1987. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for an alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Embraer, 276 S.W. 34th Street, Fort Lauderdale,Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment supersedes AD 87-11-03, Amendment 39-5663. This amendment, 39-6008, becomes effective October 7, 1988.
82-22-51: 82-22-51 FAIRCHILD REPUBLIC: Amendment 39-4543. Applies to Fairchild Republic Models F-27 and FH-227 airplanes certificated in all categories. To prevent moisture separator assembly shell failure, accomplish the following: A. Prior to accumulating 100 landings or within 20 days, whichever occurs first, unless accomplished within the last 12 months, inspect the aircraft's moisture separator assembly P/N's 890469, 890469-01, 890469-02, 891572, or 891572-01, as applicable (two per aircraft), for the following: 1) Any of the above separator assemblies having upper shell assemblies P/N 841665 or 841665-01 which have been in service for three years or 20,000 cycles, whichever occurs first, must be immediately removed from service and replaced with a serviceable shell assembly. 2) Any shell assembly P/N 841665 or 841665-01 confirmed to have been installed less than three years or 20,000 cycles accumulated service, whichever comes first, which has not had the annualfluorescent penetrant inspection of shell assembly specified by the Walter Kidde Maintenance and Overhaul Manual F-41024B must be removed from service for the inspection and overhaul specified. Strict compliance with the crack and corrosion detection criteria of the Walter Kidde Manual is mandatory. 3) Any shell assembly P/N 841665 or 841665-01 with manufacturing dates stamped on the top of the shell housing prior to September 1979 which have never been in service must be inspected in accordance with Kidde Manual F-41024B before being put in service. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England 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 inspections and/or modifications required by this AD. This amendment becomes effective February 3, 1983, and was effective earlier to those recipients of Telegraphic AD T82-22-51 dated October 27, 1982.
2004-25-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes. This action requires various repetitive inspections for cracking of the drag and shear angles that attach the nacelle to the wing, and related corrective action. This action also requires eventual modification of the drag and shear angles, which would end the repetitive inspections. This action is necessary to prevent fatigue cracking of the drag and shear angles, which could result in reduced structural integrity of the nacelle attachment to the wing. This action is intended to address the identified unsafe condition.
2023-07-11: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1B engines. This AD was prompted by a report of multiple aborted takeoffs and air turn- backs (ATBs) caused by high-pressure compressor (HPC) stall, which was induced by high levels of non-synchronous vibration (NSV). A subsequent investigation by the manufacturer revealed that wear on the No. 3 bearing spring finger housing can lead to high levels of NSV. This AD requires repetitive calculations of the oil filter delta pressure (OFDP) data and, depending on the results of the calculation, replacement of the No. 3 bearing spring finger housing. This AD also prohibits installation of an engine with an affected No. 3 bearing spring finger housing onto an airplane that already has one engine with an affected No. 3 bearing spring finger housing installed. The FAA is issuing this AD to address the unsafe condition on these products.
2014-12-09: We are adopting a new airworthiness directive (AD) for Agusta Model AB412 helicopters. This AD requires inspecting the main transmission lubricating system oil outlet hose (hose) for damage, and, if required, replacing the hose. This AD is prompted by reports of damage found on the hose. These actions are intended to prevent loss of main gear box (MGB) lubrication, which could lead to failure of the MGB and subsequent loss of control of the helicopter.
83-14-02: 83-14-02 PILATUS BRITTEN-NORMAN, LTD.: Amendment 39-4682. Applies to BN-2A MK. III Trislander Series (S/Ns 1001 thru 1042, 1048 thru 1054, 1057 thru 1061, 350, 360, 361 and 363) airplanes certificated in any category. Compliance: Required within the next 500 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent defects in the wing attachment pins which can adversely affect the safe life of the wing-to-fuselage attachments, accomplish the following: (a) Remove the wing attachment pins, one at a time, in accordance with the instructions contained in the "ACTION" section of the Pilatus Britten-Norman, Ltd., Service Bulletin No. BN2/SB 146, Issue 1, dated December 31, 1980 (hereinafter referred to as the SB), or an FAA-approved equivalent. (b) Visually inspect the wing attachment pins for corrosion, fretmarks, file/grinding marks and thread binding of the inboard nut in accordance with the instructions contained in the "ACTION" section of the SB, and if defects are found, before further flight, replace the defective wing attachment pins with new attachment pins. NOTE: Refer to SB and Trislander Illustrated Parts Catalog (Pub. Ref. PC/2, Sec. 3.5./1). (c) Visually inspect the wing joint gaps to ensure shim washers fill the gaps, and before further flight, replace shim washers as required to fill the wing joint gaps. NOTE: Refer to SB and Trislander Maintenance Manual (Pub. Ref. MM/2). (d) Reinstall wing attachment pins in accordance with the instructions contained in the "ACTION" section of the SB. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomeseffective on August 19, 1983.
2004-25-51: The FAA is adopting a new airworthiness directive (AD) for all Raytheon Aircraft Company (Raytheon) Beech Models 45 (YT-34), A45 (T- 34A, B-45), and D45 (T-34B) airplanes. This AD requires you to perform an inspection and/or modification program approved specifically for this AD by the FAA Wichita Aircraft Certification Office (ACO). This AD is the result of a total of three accidents on the affected airplanes, including a recent accident where the wing separated from the airplane in flight. We are issuing this AD to detect and correct cracking in the wing structure of the affected airplanes, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
2008-21-07R1: We are revising airworthiness directive (AD) 2008-21-07 for certain Dowty Propellers model R408/6-123-F/17 propellers. AD 2008-21- 07 required initial and repetitive inspections of the blade bonded metallic leading edge (L/E) guards for correct bonding until they accumulate more than 1,200 flight hours (FH) time-in-service. This AD requires the same inspection and replacement requirements of AD 2008- 21-07. This AD also provides an optional terminating action to those requirements. This AD was prompted by updated service bulletins that identify terminating action to the requirements of AD 2008-21-07. We are issuing this AD to prevent the loss of the bonded metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel.
2023-07-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 airplanes. This AD was prompted by reports the overwing emergency exit door (OWEED) escape line may be incorrectly routed. This AD requires inspecting the OWEED escape line and correcting the routing if required, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-07-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.