Results
2009-26-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900, and 747-400 series airplanes; and Model 757, 767, and 777 airplanes. This AD requires modifying the static inverter by replacing resistor R170 with a new resistor and relocating the new resistor. This AD results from evaluation of the carbon resistor, which revealed a failure mode that can cause the resistor to ignite, involving adjacent capacitors as well. We are issuing this AD to prevent a standby static inverter from overheating, which could result in smoke in the flight deck and cabin and loss of the electrical standby power system.
2009-24-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Zinc-coated starter ring gears installed on Solo 2625 01 and 2625 02 engines have shown to be prone to cracking. For that reason, AD 2009-0169-E has been published in July 2009. From that date, collected in-service data have been revealed that painted starter ring gears with lightening holes are also subject to cracks. The reason for these cracks is still unknown at the present time. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
64-21-04: 64-21-04 FAIRCHILD: Amdt. 814 Part 507 Federal Register September 11, 1964. Applies to Model F-27 Aircraft, Serial Numbers 1 through 97, and 99. Compliance required as indicated. There have been cracks found in the rib caps and stringers in the vertical stabilizer where the rib at water line 201.575 attaches to the hat and zee section stringers. To preclude the condition from developing in other such aircraft, accomplish the following: (a) On aircraft with less than 1,000 hours' time in service on the effective date of this AD, comply with (c) prior to the accumulation 1,050 hours' time in service, unless already accomplished within the last 200 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection. (b) On aircraft with 1,000 or more hours' time in service on the effective date of this AD, comply with (c) within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and at intervals thereafter not to exceed 200 hours' time in service from the last inspection. (c) Inspect for cracks in the skin, rib and stringers on both sides of the vertical stabilizer along and directly adjacent to water line 201.575, from the trailing edge of the stabilizer, forward, to the auxiliary spar (located directly aft of the stabilizer leading edges). Use X-ray or dye penetrant in conjunction with at least a 10-power glass, or FAA-approved equivalent inspection. If cracks are found accomplish (d). (d) Repair cracked parts in accordance with an FAA-approved repair or replace cracked parts with a part of the same part number or an FAA approved equivalent before further flight except that a ferry flight may be made in accordance with the provisions of CAR 1.76. (e) The repetitive inspection intervals specified in (a) and (b) may be increased from 200 hours' time in service to 800 hours' time in service from the last inspection on aircraft that are modified in accordance with Fairchild Service Bulletin No. 55-4 dated March 1, 1963, or an FAA approved equivalent. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Fairchild Service Bulletins 55-4 dated March 1, 1963, and 55-5 dated March 1, 1963, cover this subject.) This supersedes AD 63-10-2. This directive effective September 12, 1964.
2021-23-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that during re- engineering of galley G5, a 9G forward full scale qualification test was performed, and the door of the waste compartment opened before the required load was reached. This AD requires modifying the waste compartment door of each affected galley, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference The FAA is issuing this AD to address the unsafe condition on these products.
88-11-10 R1: 88-11-10 R1 AIRBUS INDUSTRIE: Amendment 39-5931 as amended by Amendment 39- 6005. Applies to Model A300 series airplanes, equipped with General Electric CF6-50 engines, without a secondary latching system on core cowl doors, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent structural damage to the airplane due to engine core cowl door separation, accomplish the following: A. Within 10 days after the effective date of this AD, check the core cowl door latches of each engine once each day, and re-check after each core cowl door is opened and subsequently closed. 1. If the latch is open, before further flight, properly close the latch. 2. If the latch will not engage, adjust the latch, in accordance with the A300 maintenance manual. 3. If the latch cannot be properly adjusted, replace the latch prior to further flight. B. The checks required by paragraph A., above, may be discontinued after a secondary latching system is installed, in accordance with Airbus Industrie Service Bulletin A300- 71-053, Revision 2, dated January 6,1987. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 the modification required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD revises AD 88-11-10, Amendment 39-5931. This amendment, 39-6005, becomes effective September 6, 1988.
60-23-04: 60-23-04 PRATT & WHITNEY: Amdt. 215 Part 507 Federal Register November 4, 1960. Applies to Turbo Wasp JT3C-7 Turbojet Engines Prior to Serial Number P632425B and all JT3C-6 Turbojet Engines. Compliance required at first engine overhaul after December 15, 1960. To prevent failure of the bevel accessory drive gearshaft and resultant loss of engine power, replace P/N 350460 gearshaft with P/N 401493 gearshaft.
92-15-05: 92-15-05 FOKKER: Amendment 39-8299. Docket No. 92-NM-39-AD. Applicability: Model F28 Mark 0100 series airplanes, serial numbers 11340 through 11348 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent wire burnthrough or meltdown, that could render the fire detection system ineffective in detecting fire in the engine, accomplish the following: (a) Within 30 days after the effective date of this AD, remove existing engine fire detection wires and replace them with fire resistant ones, in accordance with Fokker Service Bulletin SBF100-26-004, dated August 23, 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, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. 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 removal and replacement shall be done in accordance with Fokker Service Bulletin SBF100-26-004, dated August 23, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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 September 8, 1992.
90-12-10: 90-12-10 AIRBUS INDUSTRIE: Amendment 39-6624. Docket No. 90-NM-100-AD. Applicability: Model A320 series airplanes, as listed in Airbus Industrie Service Bulletin A320-28-1024, Revision 1, dated February 20, 1990, certificated in any category. Compliance: Required within 100 landings after the effective date of this AD, unless previously accomplished. To ensure proper operation of the fuel quantity indicating system and to prevent the possibility of a spark in the fuel system in the event of a lightning strike, accomplish the following: A. Verify the clearance between fuel probes 23QT1, 23QT2, and 28QT1, and the adjacent structures; install an insulating sleeve on the vent pipe bonding lead; and adjust fuel probe clearance, in accordance with Airbus Industrie Service Bulletin A320-28-1024, Revision 1, dated February 20, 1990, or All Operators' Telex (AOT) 28/89/03, dated November 20, 1989. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 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 information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6624, AD 90-12-10) becomes effective on June 20, 1990.
71-10-02: 71-10-02 AEROSTAR: Amdt. 39-1206. Applies to all Model 600 and 601 airplanes certificated in all categories. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To assure all over-voltage relays are properly grounded, accomplish the following: A. On S/N 61-0001 and 60-0001 through 60-0005: (1) Inspect each overvoltage relay installation and assure that the overvoltage relay base and the aircraft structure are in direct contact. (2) If the installation appears satisfactory from the inspection, use an ohmmeter to determine that low resistance continuity of less than one (1) ohm exists between the base of each overvoltage relay and the airplane structure. (3) If a satisfactory ohmmeter indication is not achieved, ground the overvoltage relay base to the aircraft structure using good aircraft grounding practice. B. On all others; (1) Inspect each installation of thecrimp wire terminal which connects to the overvoltage relay base and assure that the crimp terminal and relay base are in contact. (2) If the results of the inspection are not satisfactory, rearrange the components as follows: (a) Install the nylon bearing from the bottom side of the overvoltage relay base so that it isolates the overvoltage relay base from the aircraft structure. (b) Install the crimp wire terminal over the nylon bearing so that it is in electrical contact with the overvoltage relay base. (c) Install the AN960 washer over the nylon bearing so it is in contact with the crimp wire terminal. (d) Install the two nylon washers on top of the AN960 washer and insert the NAS221 screw through the two nylon washers and the nylon bearing, and tighten the screw into the nut-plate provided. (e) Assure that the nylon bearing is seated properly to prevent electrical contact of the crimp wire terminal, the AN960 washer, and the overvoltage relay base with the NAS221 screw and the aircraft structure. (f) Repeat the above procedure for the opposite side of each overvoltage relay except for elimination of the crimp wire terminal. (3) Using an ohmmeter, determine that low resistance continuity of one (1) ohm or less exists between the base of each overvoltage relay and the airplane structure with the respective alternator switch in the "on" position. Low resistance continuity should not exist with the respective alternator switch in the "off" position. (4) If the existing installation of either overvoltage relay will not give a satisfactory check and cannot be changed as described above, accomplish an equivalent FAA approved modification. If Aerostar Aircraft Corporation Service Bulletin No. S.B. 600-24 dated November 23, 1970, or later FAA approved revision, has been compiled with and an appropriate entry made in the airplanes' permanent maintenance record, the requirements of this AD will be considered satisfied. This amendment becomes effective on May 14, 1971.
2021-23-07: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Support and Services Model SAAB 340B airplanes. This AD was prompted by a report that the circuit breaker for the emergency cabin lighting tripped without fault in the system. This AD requires replacing a certain circuit breaker with a part having a higher rating, 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.