Results
2025-02-12: The FAA is superseding Airworthiness Directive (AD) 2023-20-03 for certain Austro Engine GmbH Model E4 and E4P engines. AD 2023-20-03 required repetitive engine oil analysis for aluminum content outside the acceptable limits and, if necessary, replacement of the pistons, piston rings, con-rods assembly, and crankcase or, as an alternative, replacement of the engine core. Since the FAA issued AD 2023-20-03, the manufacturer identified errors in the lists of affected engines and provided updated information, which prompted this AD. This AD retains the requirements of AD 2023-20-03, adds compliance times for additional affected engine serial numbers, and removes certain engine serial numbers from the applicability of the existing AD. The FAA is issuing this AD to address the unsafe condition on these products.
2025-02-14: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG Model Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C engines. This AD was prompted by reports of cracked intermediate pressure compressor (IPC) shaft assembly front air seals. This AD requires an inspection of the affected IPC shaft assembly for cracking and, depending on the results of the inspection, repetitive inspections or replacement of the IPC shaft assembly front air seals, 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.
2015-09-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787 airplanes. This AD requires a repetitive maintenance task for electrical power deactivation on Model 787 airplanes. This AD was prompted by the determination that a Model 787 airplane that has been powered continuously for 248 days can lose all alternating current (AC) electrical power due to the generator control units (GCUs) simultaneously going into failsafe mode. This condition is caused by a software counter internal to the GCUs that will overflow after 248 days of continuous power. We are issuing this AD to prevent loss of all AC electrical power, which could result in loss of control of the airplane.
2015-07-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by a determination that the forward lugs of the flap hinge box might not conform to engineering drawings, which could result in premature fatigue cracking. This AD requires revising the maintenance or inspection program to include new airworthiness limitations tasks; and measuring the forward lug edge distance of each flap hinge box, inspecting for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of each flap hinge box, and repairing any cracking or damage if necessary. We are issuing this AD to detect and correct non-conforming flap hinge box forward lugs, which could result in failure of the lugs and detachment of the flap hinge box and consequent detachment of the flap surface.
2015-08-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600 and -700 series airplanes. This AD was prompted by reports of cracking in the body station (STA) 727 bulkhead lower frame. This AD requires a detailed and open hole high frequency eddy current (HFEC) inspection of the left- and right-side lower frame webs and inner chords for cracking, and corrective actions and preventative modifications if necessary. This AD also provides for optional terminating action of the repetitive inspections, under certain conditions. We are issuing this AD to detect and correct cracking in a bulkhead lower frame web and inner chord, which could result in a severed frame and induced skin cracks, and could lead to rapid decompression of the fuselage.
72-13-07: 72-13-07 FAIRCHILD-HILLER: Amdt. 39-1465. Applies to Models 1100 and FH-1100 helicopters certificated in all categories. Compliance required after the effective date of this AD as follows: 1. For helicopters incorporating P/N 19E49-3A or -3B engine-to-transmission drive shaft assemblies, replace the assemblies within 15 hours in service with P/N 19E49-3C assemblies which have accumulated less than 350 hours on their diaphragm end packs, or with P/N 19E49-3E assemblies. 2. For helicopters incorporating P/N 19E49-3C engine-to-transmission drive shaft assemblies with 350 hours or more in service on their diaphragm end packs, replace the assemblies with P/N 19E49-3E assemblies within the next 50 hours in service. 3. For helicopters incorporating P/N 19E49-3C engine-to-transmission drive shaft assemblies with less than 350 hours in service on their diaphragm end packs, replace the assemblies with P/N 19E49-3E assemblies prior to the accumulation of 400 hours in service.4. Within the next 50 hours in service, unless already accomplished within the last 50 hours in service and every 50 hours in service thereafter, inspect horizontal and vertical alignment, and axial end play of each drive shaft assembly in accordance with Sections 24-21-4 and 24-21-5 of Fairchild-Hiller FH-1100 Service Manual revised 1 March 1972 or alternative method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. When alignment or axial end-play limits are exceeded, replace components and check engine and transmission rigging in accordance with the service manual instructions. 5. The repetitive inspections required by Item 4 above may be extended to 100-hour intervals when P/N 19E49-3E assembly is installed. These inspections shall be conducted whenever a hard landing is made, the engine, the engine-to-transmission drive shaft, engine transmission support strut, or transmission isolation mount is removed or replaced. (Fairchild-Hiller Service Bulletin FH-1100-24-4 pertains to this subject.) This amendment 39-1465 revokes AD 69-15-11. This amendment is effective June 27, 1972.
2015-08-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a report that during production, an incorrect clevis was used, resulting in improper installation onto the alternate release cable of the main landing gear (MLG). This AD requires a detailed visual inspection of the emergency release clevis of the MLG to determine if an incorrect clevis has been installed, and if necessary, replacing the clevis with a correct clevis and clevis pin. We are issuing this AD to detect and correct improper installation of the clevis, which could cause loss of the alternate release system and prevent the MLG from extending and retracting, and could consequently affect the airplane's continued safe flight and landing.
2015-06-10: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR72-212A airplanes. This AD requires inspection of the shock mount pick-up fittings and cone bolts, and replacement of certain shock mount pick-up fittings if necessary. This AD was prompted by reports of several cases of engine shock mount pick-up fittings with cracks or failure on the engine left- hand (LH) aft side attachment. We are issuing this AD to detect and correct an aft side attachment [[Page 21640]] pick-up fitting failure associated with a cone bolt failure that could reduce the structural integrity of the concerned engine nacelle, and possibly result in detachment of the engine and consequent reduced control of the airplane.
2023-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Austro Engine GmbH Model E4 and E4P engines. This AD is prompted by reports of piston failures and the determination that certain batches of pistons were manufactured with a dimensional deviation in the piston pin bore and piston diameter. This AD requires repetitive engine oil analysis for aluminum content outside the acceptable limits and, if necessary, replacement of the pistons, piston rings, con-rods assembly, and crankcase or, as an alternative, replacement of the engine core. The FAA is issuing this AD to address the unsafe condition on these products.
2015-07-05: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes, and Model Avro 146-RJ series airplanes. This AD was prompted by a report of a pressurization problem on an airplane during climb-out; a subsequent investigation showed a crack in the fuselage skin. This AD requires require repetitive external eddy current inspections on the aft skin lap joints of the rear fuselage for cracking, corrosion, and other defects, and repair if necessary. We are issuing this AD to detect and correct cracking, corrosion, and other defects, which could affect the structural integrity of the airplane.