Results
98-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. (Agusta) Model A109C and A109K2 helicopters. This action requires a one-time inspection of each tail rotor blade (blade) for debonding, and if debonding exists which exceeds certain limits, replacement of the blade with an airworthy blade. This amendment is prompted by two incidents in which helicopters lost a blade tip fairing during ground run-up. The actions specified in this AD are intended to prevent loss of the tip fairing on a blade, which could result in increased vibrations, loss of the tail rotor assembly, and subsequent loss of control of the helicopter.
2015-08-07: We are adopting a new airworthiness directive (AD) for certain Zodiac Aerotechnics (formerly Intertechnique Aircraft Systems) oxygen [[Page 27082]] mask regulators. This AD was prompted by a report of a malfunctioning mask having an inflatable harness with a high premature rupture rate due to defective silicon. This AD requires inspecting and replacing defective harnesses with new or modified serviceable units. We are issuing this AD to detect and correct defective harnesses, which could lead, in case of a sudden depressurization event, to a harness rupture, thereby providing inadequate protection against hypoxia and possibly resulting in unconsciousness of the affected flightcrew member and consequent reduced control of the airplane.
2015-09-01: We are adopting a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This AD requires repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD requires, before further flight, repairing or replacing the blade with an airworthy part. This AD was prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The actions of this AD are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter.
75-08-14: 75-08-14 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2166 as amended by Amendment 39-2201 is further amended by Amendment 39-2627. Applies to Lockheed- California Company Model L-1011-385-1 series airplanes certificated in all categories. To prevent possible failures of the C-1, C-2, and C-3 cargo door hooks due to cracks, accomplish the following: (a) Within 275 additional flight hours after the effective date of this AD, unless already accomplished, perform the following per Lockheed Alert Service Bulletin 093-52-A079, Revision 1, dated March 26, 1975 or later FAA-approved revision. (1) An inspection of the C-1, C-2 and C-3 cargo door hooks for identification configuration and affixing of appropriate part numbers; (2) A dye penetrant inspection of all hooks for cracks; (3) Replace all cracked hooks prior to further flight. (4) Scrap hooks identified as P/N's 1517205-103/-105. (5) Check rigging of hooks and doors for usage, and rerigg, as required.(b) Perform a dye penetrant inspection for cracks at intervals not to exceed 1500 hours time in service, of the C-1 and C-2 cargo door hooks identified as P/N's 1517205-107/-109 (per the inspection of (a)(1), above). Replace all cracked hooks prior to further flight. (c) Within 3000 flight hours after the initial inspections performed per (a)(1) and (2), above, replace all hooks identified as P/N's 1517205-107/-109 with hooks identified as P/N's 1517205-111/-113 on the C-1 and C-2 cargo doors. (d) The repetitive inspections required by paragraph (b) of this AD may be discontinued after accomplishment of modifications and checks in accordance with FAA-approved Lockheed-California Company Service Bulletin 093-52-087, dated March 11, 1976, or later FAA- approved revisions or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (Reference: Paragraph (f), AD 76-09-03). (e) Equivalent inspections and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. Amendment 39-2166 became effective April 16, 1975. Amendment 39-2201 became effective May 19, 1975. This amendment 39-2627 becomes effective June 7, 1976.
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.