Results
67-14-06: 67-14-06 MARTIN: Amdt. 39-406 Part 39 Federal Register April 28, 1967. Applies to Models 202, 202A, and 404 Series Airplanes. (a) Within the next 15 hours' time in service after the effective date of this AD unless already accomplished within the last 185 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, inspect the following areas in both outer wing panel front spars located at 25% of the wing chord for cracks using X-ray or dye penetrant with a glass of at least 10 power, or an FAA-approved equivalent inspection. (1) The lower spar cap in a region 3 inches long from the outer panel closing rib outboard. (2) The spar web inboard of the outer panel closing rib between the rib and the splice bolts. (3) The vertical angle that attaches this web to the outer panel closing rib. (b) If a crack is found, before further flight, replace the cracked part with a part of the same part number that has been inspected in accordance with (a) and found free of cracks or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Equivalent inspections may be approved by an FAA maintenance inspector. (d) All fuel must be drained before X-ray inspection because of lead in the gasoline. (e) Upon request of the operator, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may increase the compliance times specified in this AD if the request contains substantiating data submitted through an FAA maintenance inspector to justify the increase for that operator. This supersedes AD 59-26-05. This directive effective upon publication in the Federal Register for all person except those to whom it was made effective by telegram dated April 20, 1967.
2016-04-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracking at a central part of the structure. This AD requires repetitive inspections of the skin hidden by the upper and lower splice fittings on both sides of the fuselage, and corrective action if necessary. We are issuing this AD to detect and correct fatigue cracking of the hidden fuselage skin and cracking, corrosion, and other damage to the splice fittings and adjacent visible fuselage skin and structure that could lead to loss of a primary load path between the fuselage and the wing box, and consequent reduced structural integrity of the airplane.
2024-26-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160-B helicopters. This AD was prompted by a report of excessive axial play of the rotating scissors spherical bearings. This AD requires measuring the axial play of the rotating scissors spherical bearings and, depending on the results, accomplishing corrective action and reporting inspection results, 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.
2024-26-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by reports of broken main landing gear (MLG) shock absorber piston rod eye ends. This AD requires repetitively inspecting the MLG shock absorber piston rod eye ends, reporting the results of the inspection, and, depending on the results, replacing the MLG shock absorber assembly. It also prohibits installing certain MLG shock absorber assemblies unless specific requirements are met, 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.
2016-04-05: We are superseding an airworthiness directive (AD) 2014-03-18 for B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN- 2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B- 21, BN-2B-26, BN-2B-27, BN2A MK. III, BN2A MK. III-2, and BN2A MK. III- 3 airplanes. 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 damage of the cable sliding end assembly and installation of the incorrect end fitting on engine control cable assemblies. We are issuing this AD to require actions to address the unsafe condition on these products.
70-17-05: 70-17-05 MORANE SAULNIER: Amdt. 39-1067. Applies to Models MS. 880B, MS. 885, and MS. 894A airplanes. To prevent a possible fire resulting from contact between the terminal components of the battery cable and the battery box, within the next 100 hours' time in service after the effective date of this AD, unless already accomplished, accomplish the following: (a) Modify the battery box by installing an insulating plate in accordance with Socata Service Bulletin No. 68 dated November 1969 or later SGAC-approved issue or an FAA- approved equivalent. (b) Inspect the battery cables in the area of the battery box for damage due to wear against the battery box. (c) If the battery cable is found to be damaged during the inspection required by paragraph (b), before further flight replace the cable with a serviceable cable of the same part number. This amendment becomes effective September 12, 1970.
48-38-01: 48-38-01 AERONCA: Applies to Serial Numbers 15AC-1 to 15AC-227 Inclusive, or S15AC-1 to S15AC-227 Inclusive. Compliance required before operation at temperatures below freezing, but in any case not later than December 1, 1948. To prevent the possible loss of engine oil pressure and subsequent engine damage during cold weather starting, the present oil cooler installed on the suction side of the engine oil pump must be revised and installed on the pressure side of the pump. This change involves the following: 1. Installation of an oil cooler adapter assembly, Continental Motors Corp. Drawing 530536 and 530697, replacing pressure oil screen. This pressure oil screen is then used in adapter assembly. 2. Install new suction oil screen, Continental Motors Corp. P/N A20878. 3. Replace present oil cooler bypass spring with a 35 p.s.i. spring. 4. Replumb oil cooler with different fittings and line arrangement. (Aeronca Service Helps and Hints Bulletin No. 35 covers this same subject.)
2009-02-07: The FAA is superseding an existing airworthiness directive (AD) that applies to certain British Aerospace (Jetstream) Model 4100 series airplanes. The existing AD currently requires an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, and related investigative and corrective actions if necessary. This AD revises the applicability to include additional airplanes. This AD results from reports of exfoliation corrosion of the upper splice plate of the wing. We are issuing this AD to detect and correct such corrosion, which could result in reduced structural integrity of the airplane.
2016-03-06: We are superseding Airworthiness Directive (AD) 2012-18-05 for The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9- 50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes; equipped with a center wing fuel tank and Boeing original equipment manufacturer-installed auxiliary fuel tanks. AD 2012-18-05 required adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. Since we issued AD 2012-18-05, we have determined that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. This new AD allows certain actions as optional methods of compliance. This AD was prompted by our determination that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
71-11-01: 71-11-01 De HAVILLAND AIRCRAFT OF CANADA, LIMITED: Amdt. 39-1212. Applies to de Havilland Model DHC-6 Airplanes certificated in all categories. Compliance required within the next 500 hours time in service after the effective date of this AD unless already accomplished. To provide adequate protection for particular circuit wires, accomplish the following in accordance with the instructions contained in DHC Service Bulletin No. 6/245 dated October 9, 1970: (a) Alter airplanes, S/Ns 6 through 289, except S/Ns 176, 221, 233, 268 and 286, by incorporating DHC Modification No. 6/1369; (b) Alter airplanes, S/Ns 1 through 289, except S/Ns 176, 233, 268, and 286, by incorporating DHC Modification No. 6/1370; (c) Alter airplanes, S/Ns 6 through 289, except S/Ns 176, 221, 233, 268 and 286, by incorporating DHC Modification No. 6/1371. Modification No. 6/1371 is applicable only to those airplanes in which DHC Modification No. 6/1053 has been incorporated; (d) Alter airplanes, S/Ns 136 through 289, except S/Ns 176, 221, 233, 268, and 286, by incorporating DHC Modification No. 6/1372; (e) Alter airplanes, S/Ns 136 through 289, by incorporating DHC Modification No. 6/1389. Equivalent alterations may be used provided they are approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective May 19, 1971.