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87-10-07: 87-10-07 ALEXANDER SCHLEICHER: Amendment 39-5603. Applies to Model ASK 21 gliders serial numbers 21001 through 21312 certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent the failure of the rudder pedal support fitting P/N 99.000.2173 which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the rudder pedal support fitting P/N 99.000.2173 using a 10 power or greater magnifying glass, for cracks. (b) If a cracked fitting is found during the inspection required by paragraph (a) of this AD, before further flight, replace the rudder pedal support fitting with a serviceable fitting, P/N 99.000.2174, in accordance with the action instructions of Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986. (c) Prior to July 15, 1987, replace any rudder pedal support fitting not replaced in accordance with paragraph (b) of this AD, with a serviceable fitting, P/N 99.000.2174, in accordance with Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o America Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium; telephone number 513.38.30 ext. 2710 or the Manager, New York Aircraft Certification Office, Federal Aviation Administration, New England Region, Aircraft Certification Division, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone number 516-791-6680. Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office or Manager, New York Aircraft Certification Office may adjust the compliance time specified in this AD. Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986, identified and described in this document is 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 this document from the manufacturer may obtain a copy upon request to Eastern Sailplanes, Heath Stage Route, Shelburne Falls, Massachusetts 01370. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment 39-5603 becomes effective May 13, 1987.
2022-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 series airplanes, Model A300 B4-600, B4- 600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracking in the main landing gear (MLG) support rib 5 lower flange. This AD requires a one-time detailed inspection (DET) of the affected area, and applicable corrective actions, 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.
2007-16-03: We are adopting a new airworthiness directive (AD) to supersede AD 98-19-15 R1 and AD 2000-03-17, which apply to M7 Aerospace LP SA226 and SA227 series airplanes equipped with certain pitch trim actuators. AD 98-19-15 R1 currently requires you to incorporate changes into the Limitations Section of the FAA-approved airplane flight manual (AFM) if certain part number (P/N) pitch trim actuators are installed. AD 2000-03-17 requires repetitive inspections and repetitive replacements of the pitch trim actuator. The repetitive inspection and repetitive replacement times vary depending on the combination of airplane model and pitch trim actuator P/N installed. Since we issued AD 98-19-15 R1 and AD 2000-03-17, we have determined that reliance on critical repetitive inspections on aging commuter-class airplanes carries an unnecessary safety risk when a design change exists that could eliminate or, in certain instances, reduce the number of those critical inspections. Consequently, thisAD retains all of the actions of the previously referenced ADs, places life limits on certain P/N pitch trim actuators, and requires the replacement of certain P/N pitch trim actuators with one of an improved design. Once installed, the improved design pitch trim actuator will terminate the AFM limitations in this AD and reduce the repetitive inspection and repetitive replacement requirements. We are issuing this AD to detect excessive freeplay or rod slippage in the pitch trim actuator, which, if not detected and corrected, could result in pitch trim actuator failure. We are also issuing this AD to lessen the severity of pitch upset if a pitch trim actuator mechanical failure occurs. These conditions could lead to possible loss of control. DATES: This AD becomes effective on September 7, 2007. As of April 10, 2000 (65 FR 8037, February 17, 2000), the Director of the Federal Register approved the incorporation by reference of the following Fairchild Aircraft service information listed in this AD: Fairchild Aircraft SA226 Series Service letter (SL) 226- SL-005, Revised: August 3, 1999; Fairchild Aircraft SA227 Series SL 227-SL-011, Revised August 3, 1999; Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued: August 12, 1999; Fairchild Aircraft SA226 Series SL 226-SL-014, Revised: February 1, 1999; Fairchild Aircraft SA227 Series SL 227-SL-031, Revised: February 1, 1999; and Fairchild Aircraft SA227 Series SL CC7-SL-021, Revised: February 1, 1999.
2022-09-10: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 model turbofan engines. This AD was prompted by findings during engine overhaul of corrosion on the low-pressure compressor (LPC) front case assembly. This AD requires inspection of the LPC front case assembly and, depending on the result of the inspection, accomplishment of the applicable corrective action(s), 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.
2007-15-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model ATP airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures; to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs); and to revise life limits for certain equipment and various components. This new AD requires revising the ALS of the ICA to include revised requirements. This AD results from the determination that additional and revised inspections of the fuselage are needed. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane.
2022-06-06: The FAA is superseding Airworthiness Directive (AD) 2017-14- 13, which applied to certain The Boeing Company Model 737-600, -700, - 700C, -800, -900, and -900ER series airplanes. AD 2017-14-13 required a torque check of the screws in the cover assembly of the heel rest for both the captain's and the first officer's rudder pedals, and corrective action if necessary. This AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly, and subsequent reports of loose rudder pedal cover fasteners on airplanes on which the actions required by AD 2017-14-13 were done and on additional airplanes that were not included in the applicability of AD 2017-14-13. This AD requires modifying the rudder pedal cover and shroud assemblies, and applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes and Model 737-8 and 737-9 airplanes. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2007-14-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes. This AD requires inspecting to identify the part number and serial number of the selector valves of the nose landing gear (NLG) and the nose gear door, and doing related investigative and corrective actions if necessary. This AD results from reports of uncommanded partial retractions of the NLG. We are issuing this AD to prevent internal leakage of the selector valve, which, under certain conditions, could result in an uncommanded retraction of the NLG with consequent damage to the airplane and possible serious injury to ground personnel.
2022-10-04: The FAA is adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. This AD was prompted by a manufacturer investigation that revealed certain stages 7-9 compressor rotor spools were manufactured from a billet of material suspected of having foreign material embedded. This AD requires the replacement of the affected stages 7-9 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.
2007-14-04: We are adopting a new airworthiness directive (AD) for the products listed above. 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: To prevent the rudder trim tab upper pivot hole in the rudder rib flogging out, which may lead to aerodynamic flutter and possible loss of aircraft control * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2022-08-16: The FAA is superseding Airworthiness Directive (AD) 2020-20-07 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C model turbofan engines. AD 2020-20-07 required initial and repetitive borescope inspections (BSIs) or visual inspections of the intermediate-pressure compressor (IPC) shaft assembly and, depending on the results of the inspection, replacement of the IPC shaft assembly. This AD was prompted by the manufacturer providing optional terminating actions for the required repetitive inspections and alternative inspection instructions. This AD continues to require initial and repetitive BSIs but allows modification of the engine in accordance with RRD service information as a terminating action to these inspections, 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.