Results
2012-23-11: We are adopting a new airworthiness directive (AD) for Erickson Air-Crane Incorporated (Erickson) Model S-64F helicopters. This AD requires inspecting for cracking or working rivets in each left and right splice fitting (transition fitting), the pylon bulkhead assembly-canted (bulkhead assembly), and the pylon steel strap (strap). This AD was prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and the pylon. The actions specified by this AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter.
2012-24-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires ensuring that lockwire is installed correctly on the engine fuel feed manifold couplings. This AD also requires inspecting the assembly of the engine fuel feed manifold rigid and full flexible couplings. This AD was prompted by reports of fuel leaks due to improperly assembled engine fuel feed manifold couplings. We are issuing this AD to detect and correct improperly assembled couplings, which could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire.
47-41-05: 47-41-05 BELL: (Was Mandatory Note 17 of AD-1H-2.) Applies to All Models in 47B Series, Through Serial Number 78. Compliance required at next 100-hour inspection. In order that the bearings will be securely locked in the gimbal ring, the fiber bearing seals should be replaced with steel bearing seals, P/N 27-120-127-1. This alteration is covered by Bell Service Bulletin 47C30 dated July 10, 1947.
99-22-10: 99-22-10 GENERAL ELECTRIC AIRCRAFT ENGINES: Amendment 39-11388. Docket 98-ANE-62-AD. Issued October 18, 1999. Applicability: General Electric Aircraft Engines (GEAE) Models CF34-1A, -3A, -3A1, and -3A2 turbofan engines, installed on but not limited to Canadair aircraft models CL-600-2A12, -2B16, and -2B19. NOTE 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent high pressure compressor (HPC) spool and disk cracking, which could result in an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Remove from service the following HPC spools and disks prior to accumulating cycles in service beyond new, reduced cyclic life limits, and replace with a serviceable part, as follows: (1) For forward HPC spools, part number (P/N) 6078T56P01, which have accumulated fewer than 6,000 cycles since new (CSN) on the effective date of this AD, remove prior to accumulating 6,000 CSN. (2) For forward HPC spools, P/N 6078T56P01, which have accumulated 6,000 or more CSN on the effective date of this AD, remove at the next shop visit after the effective date of this AD, but prior to accumulating 12,000 CSN. (3) For the purpose of this AD, engine shop visit is defined as engine disassembly that includes separation of the compressor section from the fan section front frame and from the combustion section combustion chamber frame. (4) For stage 9 HPC disks, P/N 6087T01P03 or 6087T01P04, remove prior to accumulating 20,000 CSN. (5) For rear HPC spools, P/N 5087T46P01 or 5087T46P02, remove prior to accumulating 17,000 CSN. (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, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance withsections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on December 27, 1999.
2012-23-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack found in the fuselage skin under the aft drain mast. This AD requires a detailed inspection for cracking and corrosion of the channel and fillers adjacent to the drain mast bolts, an inspection to determine the location of the bonding strap, a measurement of the washers under the drain mast bolts, and related investigative actions and repair if necessary. We are issuing this AD to detect and correct cracking in the fuselage skin and internal support structure, which could result in uncontrolled decompression of the airplane.
2012-24-01: We are adopting a new airworthiness directive (AD) for certain serial number (S/N) Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 620- 15 turbofan engines. This AD requires initial and repetitive general inspections and ultrasonic inspections (UI) of low-pressure compressor (LPC) fan blades for cracks. If any fan blade is found cracked, this AD requires replacement of the LPC fan blade set and the LPC fan disc. This AD was prompted by a report of an LPC fan blade separation. We are issuing this AD to detect cracks in the LPC fan blades, which could lead to uncontained failure of the LPC fan blades and LPC fan disc, and damage to the airplane.
47-10-40: 47-10-40 LUSCOMBE: (Was Mandatory Note 11 of AD-694-4.) Applies to Model 8 Series Aircraft Serial Numbers 1934 to 2200 Inclusive. Compliance required prior to May 1, 1947. Determine if the attachment of the rudder control arm to the torque tube has been reinforced by a steel strap that extends completely around the torque tube and is securely welded to both the fore and aft flanges of the rudder control arms and the torque tube. If the reinforcing steel strap is not properly located and welded to both flanges, a repair should be made. (Luscombe Service Bulletin No. 4-46 covers this same subject.)
2002-15-04: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) T5313B, T5317 series and former military T53 series, turboshaft engines having certain serial number centrifugal compressor impellers, installed. This amendment requires for T53 series engines, a revised operating cycle count (prorate) for those compressor impellers if installed, and initial and repetitive inspections, with eventual compressor impeller replacement. In addition, this amendment requires the marking of those compressor impellers. This amendment is prompted by a report from the supplier that four centrifugal compressor impellers may have been inadvertently misidentified. The actions specified by this AD are intended to prevent premature failure of the impellers from being operated beyond their design service life, which could result in an uncontained engine failure, in-flight shutdown, or damage to the helicopter.
2021-18-14: The FAA is adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-808C and DG-1000T gliders. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as damaged fuel hoses due to environmental and fatigue deterioration. This AD requires inspecting the polyurethane (PU) fuel hoses, replacing the PU fuel hoses if there is damage, and establishing a life limit for the PU fuel hoses. The FAA is issuing this AD to address the unsafe condition on these products.
74-04-05: 74-04-05 CANADAIR: Amdt. 39-1788. Applies to all CL-44D4 and CL-44J airplanes with more than 20,000 hours' time in service. To detect cracks in the main landing gear uplock attachment fitting, P/N 44-10162 and -1, accomplish the following: 1. Within the next 100 hours' time in service after the effective date of this AD, unless accomplished within the last 400 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service, inspect the main landing gear uplock attachment fitting, P/N 44-10162 and -1 at the four corners of the lug for cracks using a dye penetrant inspection with a glass of at least 10-power or an approved equivalent inspection. 2. Cracked parts must be replaced before further flight, or repaired before further flight as specified in paragraphs 1(a) and (b) of the Inspection Procedure of Canadair's Service Information Circular 374-CL-44 or with an approved equivalent repair. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector. 4. Equivalent inspections, parts or repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective February 20, 1974.