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87-21-09: 87-21-09 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 5747. Applies to all Model AS 332C and L helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loss of the AC electrical generation system, accomplish the following: (a) Within the next 50 hours' time in service or the next 30 days after the effective date of this AD, inspect the electrical cable bundles connecting each AC generator to its regulating card in accordance with the instructions given in paragraph BBA of Aerospatiale Telex Service No. 05.12, transmitted by Aerospatiale Telex No. 10084, dated January 16, 1987. (b) The aircraft can be returned to operational service if the insulation values measured are greater than 2 megohms. (c) If the insulation values measured are less than 2 megohms, the installation is to be modified in accordance with the instructions given in Aerospatiale AS 332 Service Bulletin No. 24.10,paragraph 2, "Accomplishment Instructions." (d) Within 400 hours' time in service following the inspection or before December 31, 1987, whichever occurs first, modify the aircraft in accordance with the instructions given in AS 332 Service Bulletin No. 24.10, paragraph 2, "Accomplishment Instructions." (e) An alternate means of compliance which provides an equivalent level of safety may be used if approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, Fort Worth, Texas 76193-0100. This amendment becomes effective November 12, 1987.
2018-16-08: We are adopting a new airworthiness directive (AD) for Leonardo S.p.A. (Leonardo) Model A109E, A109S, and AW109SP helicopters with an oil cooler fan assembly (fan assembly) installed. This AD requires inspecting each oil cooler system pulley assembly (pulley assembly) bearing and replacing each fan assembly. This AD is prompted by reports of degraded pulley assembly bearings. The actions of this AD are intended to correct an unsafe condition on these products.
65-28-03: 65-28-03 MACCHI: Amdt. 39-167 Part 39 Federal Register December 14, 1965. Applies to Models AL 60 and AL 60-B Airplanes. Compliance required as indicated. To prevent further failures of the threaded shank of the eyebolt, Heim Company P/N M44-14, located at the elevator center hinge, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, visually, or by use of other FAA-approved methods, inspect the threaded shank of the eyebolt, Heim Company P/N M44-14. (b) If no cracks are found, repeat the inspection specified in (a) at intervals not to exceed 25 hours' time in service from the previous inspection. (c) If cracks are found, replace the eyebolt. If the replacement eyebolt is of the same part number, the repetitive inspections required by (b) must be continued. (d) The repetitive inspection required by (b) may be discontinued when Aermacchi Modification No. AL60/24, installation of eyebolt Heim Company P/N MD46-15, or an FAA- approved equivalent is accomplished. (Aeronautical Macchi Service Bulletin No. AL60/11 and Modification Bulletin No. AL60/24 covers this subject.) This directive effective January 13, 1966.
48-02-06: 48-02-06 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43018; 43025; 43055 Through 43057; 43062 Through 43064; and 43105. \n\n\tCompliance required by March 1, 1948. \n\n\tAs a fire protection measure, close off the dead air space between the upper and lower wing surfaces within the engine nacelle by installing cover plates over the open access hole in the lower surface of the wing in the right and left inboard nacelles between center and front spars and between Stations 130 and 167. \n\n\t(Douglas Service Bulletin DC-6 No. 92 covers this same subject.)
65-24-01: 65-24-01 AIR CRUISERS: Amdt. 39-149, Part 39 Federal Register October 13, 1965. Applies to Emergency Evacuation Slides, P/N 15D22129, Installed on Boeing Model 727 Series Airplanes. \n\n\tCompliance required within the next 1,000 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent ripping of Air Cruisers emergency evacuation slides, P/N 15D22129, rework and reinforce each slide in accordance with the Accomplishment Instructions specified in Air Cruisers Service Bulletin SB-114-65-1, Revision A, dated March 19, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. \n\n\tThis directive effective November 12, 1965.
65-21-03: 65-21-03 DOUGLAS: Amdt. 39-133 Part 39 Federal Register September 4, 1965. Applies to Model DC-8 Airplanes. \n\n\tCompliance required as indicated. \n\n\tTo prevent further failures of the main landing gear strut piston due to cracking in the radius of the torque link lug, accomplish the following on landing gear strut piston assemblies, Douglas P/N's 5598229, 5598343, 5719155, 5773028, 5773029, and 5773030: \n\n\t(a)\tUnless already accomplished, rework assemblies having 4,000 or more hours' time in service on the effective date of this AD - \n\n\t\t(1)\tIn accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD; or \n\n\t\t(2)\tIn accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, within 500 hours' time in service after the effective date of this AD and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD. \n\n\t(b)\tUnless already accomplished, rework assemblies having less than 4,000 hours' time in service on the effective date of this AD - \n\n\t\t(1)\tIn accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service; or \n\n\t\t(2)\tIn accordance with Douglas TWX MIS-108/DJW dated January 28, 1963, before the accumulation of 4,500 hours' time in service and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service. \n\n\t(c)\tInspect assemblies with 4,000 or more hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 500 hours' time in service after the effective date of this AD unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection. \n\n\t(d)\tInspect assemblies with less than 4,000 hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 4,500 hours' time in service unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection. \n\n\t(e)\tReplace any part having a crack 0.040 inch or more in depth with an undamaged part before further flight. Replace any part having a crack less than 0.040 inch in depth with an undamaged part before further flight or rework it in accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before further flight. \n\n\t(f)\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust therepetitive 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. \n\n\tThis directive effective October 4, 1965.
2018-15-07: We are adopting a new airworthiness directive (AD) for certain Costruzioni Aeronautiche Tecnam srl Model P2006T 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 an incorrect part number for the rudder trim actuator is referenced in the Airworthiness Limitations section of the FAA-approved maintenance program (e.g., maintenance manual) and the life limit for that part may not be properly applied in service. We are issuing this AD to require actions to address the unsafe condition on these products.
85-03-04 R2: 85-03-04 R2 GULFSTREAM AEROSPACE (ROCKWELL): Amendment 39-5003 as amended by Amendment 39-5587. Applies to Models 112 (S/N' s 1 through 499); 112TC (S/N's 13000 through 13149); and 114 (S/N's 14000 through 14149) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To improve seat retention and passenger restraint during crash landing or accident impact, accomplish the following: (a) Within the next 100 hours time-in-service, or one calendar year after the effective date of this AD, whichever comes first, modify the front seats and belt attachments in accordance with one of the following modifications: (1) Rockwell Service Bulletin Nos. SB-112-45A or SB-114-5A, both dated April 7, 1977, as applicable, or (2) Gulfstream Aerospace Service Bulletin Nos. SB-1l2-70A, Revision 1, or SB-114-21A, Revision 1, both dated February 23, 1987, as applicable. NOTE: The modification specified in paragraph (a) (1) above is the modification referenced in AD 77-16-09. The modification specified in paragraph (a) (2) above is the modification referenced in AD 85-03-04 R1. (b) The airplane may be flown in accordance with FAR 21.197 to a location where the repair can be performed. (c) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76101; Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box 22500, Oklahoma City, Oklahoma 73123; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5003 superseded AD 77-16-09 which was effective March 25, 1985. Effective date of Amendment 39-5003 was suspended July 2, 1985. This amendment, 39-5587, becomes effective April 27, 1987.
70-10-02: 70-10-02 PRATT & WHITNEY: Amdt. 39-984. Applies to all Pratt & Whitney Aircraft R-985 and Wasp Jr. type engines altered in accordance with Supplemental Type Certificate No. SE1-391 incorporating Simmonds Precision Part No. 580047, fuel injector. Compliance required as indicated. To prevent engine power loss as the result of failure of the gerotor pump drive pin or the plugging of the fuel injector filter, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD and thereafter at intervals of 100 hours time in service inspect and clean the fuel injector filter P/N 580436. (b) Overhaul the fuel injector P/N 580047 prior to the accumulation of 600 hours time in service. For injectors with more than 550 hours time in service on the effective date of this AD overhaul the injector within the next 50 hours time in service. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineeringand Manufacturing Branch, FAA Eastern Region may adjust the repetitive inspection intervals specified in this AD. This amendment is effective June 9, 1970.
2018-15-08: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL 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 airplane sound insulation materials attached to the aft face of the firewall not complying with the applicable burn testing criteria for materials on the cabin side of the firewall. We are issuing this AD to require actions to address the unsafe condition on these products.