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2016-11-19: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of chafing of the feeder cable at the pylon- wing junction due to vibration; one report revealed that the cable loom plastic support bracket of the G-route was broken due to vibration; and another report revealed wire chafing due to clamp damage. This AD requires modifying the cable loom support bracket of the G-route of the inboard pylons at the pylon-wing junction. We are issuing this AD to prevent chafing of the wiring in the pylon-wing area, which could result in an electrical short circuit near a flammable fluid vapor zone, and consequent fire or fuel tank explosion.
77-12-05: 77-12-05 CHAMPION SPARK PLUG COMPANY: Amendment 39-2923 as amended by Amendment 39-3208. Applies to Part Numbers CH48108 and CH48109 oil filters as installed in aircraft certified in all categories, identified by the following manufacturing date codes, 1A7E and 2A7C for the Part Number CH48108 filters, and 1A7G and 1A7I for the Part Number CH48109 oil filters, except for those affected filters which are identified with the symbol "Insp OK 5G7A" stamped adjacent to the manufacturing date code. The manufacturing date code is located on the outside of the filter housing adjacent to the filter installation instructions. Champion Spark Plug Company Aviation Sales Bulletin No. 77-13 also pertains to this subject. Compliance required before further flight, unless already accomplished, except that the airplane may be flown in accordance with FAR 21.197 to a base where the removal can be performed. To preclude possible oil filter malfunction resulting from internal bypass valve failure, remove all applicable filters from service. Amendment 39-2923 became effective June 24, 1977. This amendment 39-3208 becomes effective May 12, 1978.
2003-26-02: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; that requires either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators. This action is necessary to prevent jamming of a thrust reverser door during operation, or inadvertent deployment of a thrust reverser door in-flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-21-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-8, -10N, and -12B turboprop engines with certain electronic engine controls (EEC's) installed. This AD requires revising the Emergency and Normal Procedures section of the applicable Airplane Flight Manual (AFM) until the existing EEC's are replaced. This amendment is prompted by a report of an engine experiencing an uncommanded full power increase during an approach while both engine power levers were at the flight idle gate. The actions specified in this AD are intended to minimize exposure to flight and ground operations that could lead to the loss of control of the airplane due to asymmetric thrust and an uncommanded torque increase.
2024-19-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-8 and Model 737-9 airplanes. This AD was prompted by a Boeing review of the standby power system control unit (SPCU) design where a single point of failure exists internal to the SPCU. This AD requires installing four diodes and changing wire bundles in the P5 panel, as well as performing installation and power tests and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes equipped with certain Litton air data inertial reference units (ADIRU). This AD requires modifying the shelf (floor panel) above ADIRU 3, and, for certain airplanes, modifying the polycarbonate guard that covers the ADIRUs, and the ladder located in the avionics compartment, as applicable. This action is necessary to prevent failure of ADIRU 3 during flight, which could result in loss of one source of critical attitude and airspeed data and reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
2016-12-05: We are superseding Airworthiness Directive (AD) 2014-15-04 for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. AD 2014- 15-04 required deactivating the potable water system, or alternatively filling and activating the potable water system. This new AD requires inspecting the in-line heater for correct brazing and corrective action if needed, and installing a shrinkable tube on the water line and a spray shield on the in-line heater. This AD was prompted by a report of rudder pedal restriction which was the result of water leakage at the inlet tubing of an in-line heater in the lower part of the forward fuselage. This AD was also prompted by the development of a modification that would address the unsafe condition. We are issuing this AD to prevent rudder pedal restriction due to the pitch control mechanism becoming frozen as the result of water spray, which could prevent disconnection of the pitch control mechanism and normal pitch control, and consequently resultin reduced controllability of the airplane.
92-18-09: 92-18-09 BRITISH AEROSPACE: Amendment 39-8353. Docket No. 92-NM-97-AD. Applicability: Model BAe 125-800A series airplanes; post-mod 259404B (Turbomach auxiliary power unit) and post-mod 258706 (Garrett auxiliary power unit); certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a short circuit, arcing, and an electrical fire, accomplish the following: (a) Within 120 days after the effective date of this AD, modify the auxiliary power unit wiring, in accordance with British Aerospace Service Bulletin 49-37-25A253A&B, dated October 28, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send itto the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 modification shall be done in accordance with British Aerospace Service Bulletin 49-37-25A253A&B, dated October 28, 1991. (NOTE: The issue date of that service bulletin is indicated only on "page 1 of 10"; no other page of the document is dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.
49-11-01: 49-11-01 NAVION: Applies to Airplanes Equipped With Carter Fuel Pumps Continental P/N 530509 (Carter M687-S and M688-S) or Continental P/N 50375. To be accomplished as soon as possible but not later than April 15, 1949. Due to Carter fuel pump lower diaphragm failures, caused by diaphragm deterioration due to excessive pump temperatures when pumps are run dry, the two Carter pumps should be connected in series to insure that fuel will be continuously flowing both pumps and that the pumps will not overheat. It is therefore required that all parallel Carter pump fuel systems be converted to the series pump arrangement, or, as an alternative, that either an approved Ryan fuel system incorporating an Adel electric booster pump or an equivalent approved fuel system be installed. Ryan Navion Field Service Bulletin No. 7 also covers this subject and describes means for connecting the fuel pumps in series. In addition, the daily inspections for looseness of the pump lower bowl, which are specified in section II of Ryan's Bulletin No. 7, should be continued. This supersedes AD 48-40-01.
2003-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-622R and A300 F4-622R airplanes, and Model A310-324 and -325 series airplanes, that are equipped with Pratt & Whitney PW4000 series engines. This AD requires replacement of the existing flexible hose assembly that connects the oil pressure transmitter to the main oil circuit, with a new improved tube assembly. This action is necessary to prevent failure of the oil pressure indicator and low-oil-pressure warning in the event of an engine fire, which could result in an unannounced shutdown of the engine. This action is intended to address the identified unsafe condition.