Results
2007-16-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200B, 747-300, and 747-400 series airplanes. This AD requires doing repetitive detailed inspections for cracking of the aft tension tie channels from body station (BS) 1120 to BS 1220 and from BS 880 to BS 1100, and corrective actions if necessary. This AD results from cracks found in the aft tension tie channels at four station locations, on a Model 747-200B series airplane that had been modified to a special freighter. We are issuing this AD to detect and correct cracking of the aft tension tie channels; failure of more than one tension tie could result in rapid depressurization of the airplane.
2022-11-16: The FAA is adopting a new airworthiness directive (AD) for all British Aerospace (Operations) Limited Model Jetstream Model 3101 airplanes and British Aerospace Regional Aircraft Model Jetstream Model 3201 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as stress corrosion cracking of the primary flight control cable terminals. This AD requires repetitively inspecting the turnbuckle type control cable terminals in the rudder and elevator primary flight control circuits for corrosion, pitting, and cracking and, depending on the inspection results, replacing an affected cable assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2007-16-13: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 757-200, -200PF, and -200CB series airplanes. The existing AD currently requires repetitive inspections of the shim installation between the vertical flange and bulkhead, and repair if necessary. This new AD adds, for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary. This AD results from reports of cracking in the pylon under bolts that appear to be undamaged during the existing AD inspections. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut- to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
2022-11-06: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109S and AW109SP helicopters. This AD was prompted by a report of a protective sheath, installed around a fixed flight control rod, which should have been removed during assembly. This AD requires borescope inspecting certain parts, and removing any foreign object if detected, 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.
2007-16-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-100 and A320-200 series airplanes. This AD requires repetitive inspections of the wing-tank fuel pumps, canisters, and wing fuel tanks for detached identification labels, and corrective action if necessary. This AD also requires modification of the fuel strainers at the fuel pump and suction bypass intakes, which would end the repetitive inspections. This AD results from several incidents of detached plastic identification labels found floating in the wing fuel tanks. We are issuing this AD to prevent plastic identification labels being ingested into the fuel pumps and consequently entering the engine fuel feed system, which could result in an engine shutdown.
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.