Results
2017-08-12: We are adopting a new airworthiness directive (AD) for GROB Aircraft AG Models GROB G 109 and GROB G 109B gliders. 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 broken pivots of the tail wheel mounting bracket resulting from corrosion and damage due to wear. We are issuing this AD to require actions to address the unsafe condition on these products.
2001-22-08: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 series airplanes, that requires replacing the main landing gear (MLG) torque link dampers with modified and reidentified dampers. This action is necessary to prevent degradation of the dampers, which could result in MLG high amplitude oscillation in a lateral torsional mode, and consequent MLG damage or separation of the MLG from the airplane. This action is intended to address the identified unsafe condition.
2001-21-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires, for certain airplanes, revising the Airplane Flight Manual, and, for all airplanes, performing repetitive inspections for wear or damage of the inlet check valves and inlet adapters of the override/jettison pumps, and corrective actions, if necessary. This amendment applies to fewer airplanes than the existing AD and requires rework of certain components, which ends the repetitive inspection requirement. These actions are necessary to ensure that the flight crew is advised of the hazards of dry operation of the override/jettison pumps of the center wing fuel tank, and to prevent wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps, which could result in a fire or explosion in the fuel tank during dry (no fuel) operation. This action is intended to address the identified unsafe condition. \n\n\tTheincorporation by reference of Boeing Alert Service Bulletin 747-28A2212, Revision 2, dated May 14, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 24, 1998 (63 FR 42210, August 7, 1998).
2017-08-09: We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine modified with a fuel injection system following the instructions of Solo Kleinmotoren GmbH Technische Mitteilung (TM)/ Service Bulletin (SB) 4600-3 ``Fuel Injection System'' and identified as Solo 2625 02i. 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 possible in-flight engine shut-down and engine fire due to failure of the connecting stud for the two fuel injector mounts of the engine redundancy system. We are issuing this AD to require actions to address the unsafe condition on these products.
64-13-04: 64-13-04 WALTER KIDDE: Amdt. 749 Part 507 Federal Register June 18, 1964. Applies to Aircraft Incorporating Inflatable Escape Slides or Life Rafts Utilizing Walter Kidde Series 1 Actuating Valve P/N's 891771, 891178, 891178-01, 890881-01, 890683, and 890881 Which Have Had Their Seat Assemblies, Walter Kidde P/N 801906 Replaced or Modified With Parts Purchased Since April 1, 1963, and All Series 2 Actuating Valve P/N's 891771-01, 891178-02, 890881-02. Compliance required as indicated. During recent demonstrations of inflatable escape slides and life rafts, certain Walter Kidde inflation valves did not provide adequate inflation and required excessive pull forces to actuate the valve. Effective July 1, 1964, all Walter Kidde valves specified herein which are used in escape slides or life rafts installed in civil aircraft shall be modified as follows or in accordance with an FAA Western Region, Aircraft Engineering Division, approved equivalent: (a) Remove seat assembly Walter Kidde P/N 801906 and install a new nylon seat assembly Walter Kidde P/N 843045. (b) Functionally test the valve by installing it, along with anti-recoil fitting Walter Kidde P/N 6531, on an appropriately charged bottle and discharging the bottle. During this functional check, the pull load required to actuate the valve is to be determined and is not to exceed 30 pounds. Do not install valves which require a pull in excess of 30 pounds. (NOTE: If Walter Kidde P/N 6531 anti-recoil fitting is not available, the bottle should be adequately constrained.) (c) Reidentify the reworked valves in accordance with Walter Kidde Service Bulletin No. 168 dated May 8, 1964. NOTE: Walter Kidde valve P/N's 891771, 891178, 891178-01, 890881-01, 890683 and 890881 which have not had seat assemblies replaced or modified with parts purchased since April 1, 1963, are not affected by the provisions of this AD. (Walter Kidde Company Service Bulletin No. 168 dated May 8, 1964, withAddendum No. 1 dated May 15, 1964, and Addendum No. 2 dated June 2, 1964, and Boeing Alert Service Bulletins Nos. 2000 dated May 11, 1964, and 2000A dated May 15, 1964, cover this same subject. Note that where the applicability specified in these Bulletins is not the same as that in the AD, the applicability specified in the AD applies.) This directive effective June 18, 1964.
2001-22-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires an inspection to find discrepancies of the hydraulic pipelines to the 7P panel and adjacent electrical wiring harnesses, and corrective action, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing between the hydraulic lines and adjacent wiring, and a potential fire. This action is intended to address the identified unsafe condition.
92-03-11 R1: 92-03-11 R1 SAAB-SCANIA: Amendment 39-8248. Docket No. 92-NM-73-AD. Revises AD 92-03- 11, Amendment 39-8166. Applicability: Model SF-340A series airplanes, serial numbers 004 through 021, 023 through 028, 030 through 035, 037 through 049, and 051 through 159; and Model SAAB 340B, serial numbers 160 through 169, and 171 through 219; equipped with a forward or aft lavatory; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a possible wire overload and resultant smoke and/or fire in the cabin, accomplish the following: (a) Within 3 months after the effective date of this AD, replace the lavatory circuit breaker, 1MG (1OA size), with circuit breaker, 1MG (7.5A size), and perform an operational test, in accordance with SAAB-SCANIA Service Bulletin 340-25-181, dated March 7, 1991. (b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with SAAB-SCANIA Service Bulletin 25- 181, dated March 7, 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 16, 1992 (57 FR 4847, February 10, 1992). Copies may be obtained from SAAB-SCANIA AB, Product Support, S-581.88, Link ping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on May 6, 1992.
96-09-16: This amendment adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft SA226 and SA227 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2023-02-04: The FAA is adopting a new airworthiness directive (AD) for certain Mooney International Corporation Model M20C, M20D, M20E, M20F, and M20G airplanes. This AD was prompted by reports of the hybrid material elevator balance weight cracking. This AD requires inspecting to determine whether a certain elevator balance weight is installed. If installed, this AD requires inspecting each affected elevator balance weight for corrosion and cracking, and depending on the findings, either replacing each affected elevator balance weight with a non- hybrid (lead) elevator balance weight or repetitively inspecting each affected elevator balance weight. This AD also prohibits the installation of an affected elevator balance weight on any airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2001-22-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B2 and B4 series airplanes. This action requires determining the part and amendment numbers of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions, if necessary. This action is necessary to prevent failure of both spring boxes of the VLA due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.