Results
2012-16-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by chafing on high pressure fuel lines due to improper installation of an expandable pin on the lower cowl assembly. This AD requires installing spring clips and repositioning the lanyard attachment points at the forward end and the forward firefloor of the lower cowl. We are issuing this AD to prevent chafing of the high pressure fuel lines, which if not corrected, could cause fuel leakage in a fire zone.
75-04-12: 75-04-12 BELLANCA: Amendment 39-2093. Applies to Model 8GCBC Airplanes, Serial Numbers 1-74 through 119-74, 120-75 through 153-75 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this airworthiness directive, unless already accomplished. To prevent possible resonant vibratory conditions with McCauley Model 1A200/HFA fixed pitch propellers installed on Lycoming 0-360-C2A, or -C2E type engines, accomplish the following in accordance with Bellanca Service Letter Number 115 and Bellanca Service Kit Number 245. (a) Remove existing markings on the tachometer instrument glass and affix Mylar decal, Bellanca P/N 1-10443. The decal is properly affixed when: a green arc extends from 500 to 1700 RPM; a yellow arc from 1700 to 2100 RPM; a green arc from 2100 RPM to 2700 RPM; and a red radial is positioned at 2700 RPM. (b) Install Bellanca P/N 1-10437, placard "AVOID 1700-2100 DURING DESCENT", on thetachometer instrument glass below the hour meter. (c) Accomplish Revision Number 1 to existing FAA Approved Airplane Flight Manual (AFM) in accordance with AFM revisions page. This amendment becomes effective February 21, 1975.
2012-16-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600 series airplanes and Model A310-203, -204, - 221, and -222 airplanes. This AD was prompted by a report of a capacitive density condensator (cadensicon) coil overheating during testing. This AD requires an inspection to determine if a certain fuel quantity indication computer (FQIC) is installed, replacement of identified FQICs, and modification of the associated wiring. We are issuing this AD to detect and correct potential overheating of the cadensicon coil, which could create an ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
67-18-03: 67-18-03 LOCKHEED: Amendment 39-423 as amended by Amendment 39-1601. Applies to Model 382 and 382B series airplanes, serial numbers 3946 and 4101 through 4196. Compliance as indicated. (a) For airplanes with 2350 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (b) For airplanes with less than 2350 hours' total time in service on the effective date of the AD comply with Paragraph (c) before the accumulation of 2400 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (c) Inspect all eight affected engine mount truss assemblies in accordance with the tooling and inspection instructions given in Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, Section 1f and 2a through 2e, respectively, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (1) Cracked parts shall be replaced with new parts having the same part number, or with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision. Replacement truss assemblies shall be installed according to the replacement instructions given in Section 2h through 2aa in the above Service Bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (2) Replacement of cracked trusses shall be accomplished before further flight, except that one flight may be made for the purpose of obtaining the necessary replacements in accordance with the provisions of FAR 21.197. (d) When a particular truss assembly is replaced with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153dated December 1, 1966, or later FAA approved revision, the repetitive inspection of that truss as required by this AD may be discontinued. Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966, covers this same subject. Amendment 39-423 became effective June 25, 1967. This Amendment 39-1601 becomes effective March 12, 1973.
2018-05-06: We are superseding Airworthiness Directive (AD) 2016-09-12, which applied to certain The Boeing \n\n((Page 9689)) \n\nCompany Model 787-8 and 787-9 airplanes. AD 2016-09-12 required repetitive inspections of the bilge barriers located in the forward and aft cargo compartments for disengaged decompression panels, and reinstalling any disengaged panels. This AD retains the actions required by AD 2016-09-12 and requires replacing the existing decompression panels with new panels and straps, which terminates the repetitive inspections. This AD also removes airplanes from the applicability. This AD was prompted by a terminating modification developed to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.
2003-09-06: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This amendment requires removal from service of eight serial number (SN) low-pressure turbine (LPT) stage 1 disks, part number (P/N) 9061M21P03, at the next engine shop visit. This amendment is prompted by a report of the potential for iron-rich inclusions introduced during manufacture in the affected disks. The actions specified by this AD are intended to prevent LPT stage 1 disk cracking, due to iron-rich inclusions introduced during manufacture, leading to uncontained disk failure.
65-13-04: 65-13-04 GRUMMAN: Amdt. 39-80 Part 39 Federal Register June 12, 1965. Applies to Model G-159 Aircraft Equipped with Bendix Nose Gear Strut Assembly, P/N 1722-40 or 2570890. Compliance required as indicated. To prevent failure of the nose gear trunnion, accomplish the following: (a) Inspect the nose gear trunnion, Bendix P/N 171467 in accordance with (c) within the next 20 hours' time in service after the effective date of this AD unless replaced within the next 20 hours' time in service after the effective date of this AD, or unless already inspected within the last 80 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) Within the next 20 hours' time in service after replacement of a nose gear trunnion, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the replacement trunnion in accordance with (c). (c) Inspect the retract shaft attachment lugs on the nose gear trunnion forward flanges for cracks in the radii above and below the area where the retract shaft attachment lugs blend into the trunnion flanges, using the dye penetrant method with a 10 power or greater glass or an FAA-approved equivalent. (d) Replace cracked trunnions with a trunnion of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight except that the aircraft may be flown in accordance with the provisions of FAR 21.197, after approval by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, to a base where the repair can be made. This directive effective June 12, 1965.
75-06-01: 75-06-01 UNITED AIRCRAFT OF CANADA LIMITED and PRATT & WHITNEY AIRCRAFT: Amendment 39-2118 as amended by Amendment 39-2182, 39-2208 and 39-2574 is further amended by Amendment 39-2858. Applies to all PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28, and -34 series turboprop engines. Compliance required as indicated unless previously accomplished. To ensure the early detection of reduction gearbox deterioration which could result in an engine failure and provide for improved blade containment accomplish the following: (a) Within the next 50 hours in service after effective date of this AD, unless previously accomplished, remove the main engine oil filter element and visually inspect the element for magnetic and non-magnetic metal particles. (1) If the inspection reveals less than 40 non-magnetic metal and no magnetic metal particles, clean oil filter and reinspect after every 50 hours in service. (2) (i) If the inspection reveals more than 40 non-magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (ii) If the reinspection, in accordance with paragraph (a)(2) (i) reveals less than 40 non-magnetic metal particles, clean oil filter and reinspect after every 50 hours in service thereafter. (iii) If the reinspection, in accordance with paragraph (a)(2) (i) reveals more than 40 non-magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (iv) If the reinspection, in accordance with paragraph (a)(2) (iii) reveals more than 40 non-magnetic metal particles, the engine must be removed from service for an overhaul inspection. (v) If the reinspection in accordance with paragraph (a)(2) (iii) reveals less than 40 non-magnetic metal particles, clean oil filter and reinspect after every 50 hours in service thereafter. (3) (i) If the inspection reveals less than 40 magnetic metal particles clean oil filter and reinspect after 10 hours in service. (ii)If the reinspection in accordance with paragraph (a)(3) (i) reveals the presence of similar quantity of magnetic metal particles, the engine must be removed from service for an overhaul inspection. (iii) If the reinspection in accordance with paragraph (a)(3) (i) reveals the presence of lesser quantity of magnetic metal particles clean oil filter and reinspect every 50 hours time in service thereafter. (4) (i) If the inspection reveals more than 40 magnetic metal particles, clean oil filter, drain and change oil, perform a ground run for one hour and reinspect oil filter. If the inspection after one hour ground run reveals more than 40 magnetic metal particles, the engine must be removed from service for an overhaul inspection. (ii) If the inspection after one hour ground run reveals less than 40 magnetic metal particles, clean oil filter and reinspect after 10 hours in service. (iii) If the reinspection after 10 hours in service reveals a similar quantityof magnetic metal particles, the engine must be removed from service for an overhaul inspection. (iv) If the reinspection after 10 hours in service reveals a lesser quantity of magnetic metal particles, clean oil filter and reinspect every 50 hours in service thereafter. (b) For the PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28 and 34 engines, within the next 8000 hours in service after the effective date of the AD, alter part number 3010548, power turbine shaft housing assembly in accordance with paragraph 2, accomplishment instructions in United Aircraft of Canada Limited Engine Service Bulletin No. 1138 or approved equivalent, or replace said assembly with any other power turbine shaft housing assembly listed as eligible in the engine parts catalog. (c) For the PT6A-6, -6A, -6B, -6/C20, -20, -20A and -20B engines within the next 2000 hours in service after the effective date of this AD alter all the power turbine blades in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1233, or approved equivalent alteration. (d) For the PT6A-27, -28 and -34 engines, within the next 4000 hours in service after the effective date of this AD install the improved power turbine containment ring in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1220 or approved equivalent alterations and modified combustion chamber liner and related parts in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1216, or approved equivalent alterations. (e) For the PT6A-20, -20A, and -20B, -6/C20 engines within the next 4000 hours in service after the effective date of this AD install the improved power turbine containment ring in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1246 or approved equivalent alterations and modified combustion chamber liner and related parts in accordance with paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada Limited Engine Service Bulletin No. 1245 or approved equivalent alterations. The main oil screen inspection requirements of this AD are no longer required when the engines have been modified as required by paragraph (b), (c), (d), and (e) as applicable. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this Airworthiness Directive. All equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. Amendment 39-2118 was effective March 10, 1975. Amendment 39-2182 was effective April 28, 1975. Amendment 39-2208 was effective May 20, 1975. Amendment 39-2574 was effective April 14, 1976. This amendment 39-2858 is effective April 1, 1977.
48-03-06: 48-03-06 BELL: Applies to All 47B Series Through Serial Number 78. Compliance required at next 25-hour inspection. If the play between the two bolts which connect links 47-612-048, to the side and aft sprag systems and the adapter plate, exceeds 0.010 inch, bushing 78B6-8-11 should be added to the tube assembly fittings and the clevis end of the link; bushings 75B6-8-11-5 should be added to the opposite end of the link; and bushings 75B6-8-8, 47-612-053-1 or 47-612-053-2 should be installed in the adapter plate. (Bell Service Bulletin 47C62 dated December 2, 1947, covers this subject and gives more detailed reaming and dimensional information.)
2012-16-03: We are adopting a new airworthiness directive (AD) for all HPH s. r.o. Models 304C, 304CZ, and 304CZ-17 sailplanes. 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 the lack of a drain hole in the elevator control rod, which may allow water to accumulate in the control rod and lead to possible corrosion. This condition could cause the elevator control rod to fail, which could result in loss of control of the sailplane. We are issuing this AD to require actions to address the unsafe condition on these products.