Results
54-01-01: 54-01-01 HAMILTON STANDARD: Applies to All Hamilton Standard Reversing Propellers Models 43D, 43E, 34D, 34E, 232 and 242. Compliance required as indicated. Subsequent to December 31, 1954, Hamilton Standard Model 67000 reverse solenoid valves shall not be used on civil aircraft. Analysis has shown that unwanted reversal of Hamilton Standard propellers could possibly occur with use of the Hamilton Standard Model 67000 reverse solenoid valve if any of the following malfunctions of the valve were experienced: 1. A broken plunger spring. This could cause the valve to open fully. 2. A film of oil between the armature and the valve body. This could cause the valve to remain fully open. 3. A foreign particle lodged between the valve and its seat. This could cause a pressure buildup in the reverse oil passage. Although there is no record of such malfunctions of this valve on civil aircraft, the potential hazards that exist indicate the desirability of precluding future use of this obsolete component.
2021-19-14: The FAA is adopting a new airworthiness directive (AD) for AERO Sp. z o.o. (AERO) Model AT-3R100 airplanes with an ELPROP 3-1-1P propeller. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as cracks in the propeller hub. The FAA is issuing this AD to address the unsafe condition on these products.
71-08-06: 71-08-06 AVCO LYCOMING: Amdt. 39-1192. Applies to all Avco Lycoming T5313A and T5313B turboshaft engines which incorporate part number 1-180-230-01 or -03 Overspeed Pickup Housing Assembly. Compliance required as follows: (a) To detect possible failure of the overspeed pickup gear bearings, perform the following inspection within the next 25 hours' time in service after the effective date of this AD and every 25 hours' time in service thereafter until item (b) is accomplished. Inspect Part Number 1-180-230-01 or -03 Overspeed Pickup Housing Assembly in accordance with the procedure given in Part 1 of Avco Lycoming Service Bulletin, Product Support, No. 0022, Rev. 1, dated 1 March 1971. (b) To prevent secondary failure of the power turbine (N2) accessory drive system as a result of failure of the overspeed gear bearings, accomplish the following within the next 200 hours time in service after the effective date of this AD. Replace Overspeed Pickup Housing Assembly P/N 1-180-230-01 or -03 with P/N 1-180-230-04 (Note: Part II of Avco Lycoming Service Bulletin, Product Support, No. 0022 provides information for modifying Part numbers 1-180-230-01 and -03 to the -04 configuration). The manufacturer's Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Avco, Lycoming Division, Avco Corp., 550 So. Main Street, Stratford, Conn. These documents may also be examined at the FAA, Eastern Region, Federal Building, J.F. Kennedy International Airport, Jamaica, New York and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and in the Eastern Region. This amendment is effective April 16, 1971.
2004-09-37: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier transport category airplanes, that currently requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. That AD also provides for two optional terminating actions for the detailed inspection(s). This action requires performing one or the other of the terminating actions. The actions specified by this AD are intended to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective June 11, 2004. The incorporation by reference of certain publications listed in the regulations was previously approved by the Director of the Federal Register as of May 8, 2003 (68 FR 19940, April 23, 2003).
2011-26-11: We are adopting a new airworthiness directive (AD) for the products listed above, with certain part number (P/N) high-pressure compressor (HPC) stages 2-5 spools installed. This AD was prompted by an aborted takeoff caused by liberation of small pieces from the HPC stages 1-2 seal teeth and two shop findings of cracks in the seal teeth. This AD requires eddy current inspection (ECI) or spot fluorescent penetrant inspection (FPI) of the stages 1-2 seal teeth of the HPC stages 2-5 spool for cracks. This AD only allows installation of either HPC stator stage 1 interstage seals that are pregrooved or previously worn seals with acceptable wear marks to prevent heavy rubs. We are issuing this AD to detect cracks in the HPC stages 1-2 seal teeth due to heavy rubs that could result in failure of the seal of the HPC stages 2-5 spool, uncontained engine failure, and damage to the airplane.
2021-19-12: The FAA is adopting a new airworthiness directive (AD) for MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports and a design review indicating that there could be possible corrosion on the main landing gear (MLG) outer cylinder at the interface with the gland nut on the shock strut installation and on the forward and aft trunnion pins in the MLG dressed shock strut assembly. This AD requires detailed inspections for corrosion on the MLG outer cylinder assemblies, certain MLG dressed shock strut assemblies, and the MLG outer cylinder at the gland nut threads, thread relief groove, and chamfer; a detailed inspection for the presence of corrosion-inhibiting compound (CIC) on the MLG forward and aft trunnion pins and grease adapter assemblies; applicable corrective actions; application of primer, paint, and CIC as applicable; re-identification of certain part numbers; and marking of the MOD STATUS field of the nameplate of certain parts. The FAA is issuing this AD to address the unsafe condition on these products.
72-21-01: 72-21-01 AERO COMMANDER DIVISION, NORTH AMERICAN ROCKWELL CORPORATION: Amdt. 39-1527. Applies to all Aero Commander (Intermountain) (CallAir) Models B-1 and B-1A series airplanes, S/N's 10,000 through 10,035. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failures of the landing gear shock struts, accomplish the following: (a) Remove main landing gear shock struts, P/N 18004-1 (left hand) and P/N 18004- 2 (right hand) and discard struts and all hardware except the wire cutters, P/N 18026. (b) Install replacement shock struts. P/N 18045-1 (left hand) and P/N 18045-2 (right hand). Attach these struts with the following hardware: (1) Upper strut attachment (2 required per strut): NAS 1306-26 Bolt AN 960-616 Washer AN 365-624 Nut (2) Lower strut attachment (1 required per strut): NAS 1306-38 Bolt AN 960-616 Washer AN 365-624 Nut(c) Replace the wire cutter, P/N 18026, on the new landing gear shock strut with two AN 3-6A bolts, two AN 960-10 washers, and two AN 365-1032 nuts. Repeat for the opposite strut. Aero Commander Service Bulletin A-23 pertains to this same subject. This amendment becomes effective October 6, 1972.
2004-09-16: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 and -300 series airplanes, that requires repetitive inspections of the bearing lugs of the rudder spring tab lever assembly for cracking, and corrective action if necessary. This action is necessary to prevent failure of the rudder flight control system due to such cracking, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2011-27-01: We are adopting a new airworthiness directive (AD) for Turbomeca Arriel 1B turboshaft engines. This AD results from 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 describes the unsafe condition as an increase in hot gas ingestion and an increase of temperature in the gas generator (GG) turbine rotor, potentially resulting in turbine damage and an uncommanded in-flight shutdown. We are issuing this AD to prevent over-temperature damage of the GG turbine, which could result in an uncommanded in-flight engine shutdown, and a subsequent forced autorotation landing or accident.
2021-19-13: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42-500 and ATR72- 212A airplanes. This AD was prompted by reports indicating that certain Thales global positioning system (GPS) satellite based augmentation system (SBAS) receivers provided, under certain conditions, erroneous outputs on aircraft positions. This AD requires replacing affected GPS SBAS receivers with new, improved receivers, 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.