Results
2004-09-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This action requires repetitive inspections of the internal and external spring sleeves of the aileron artificial feel unit (AFU) for proper lubrication, and lubrication if necessary. This action is necessary to prevent ice accumulation due to water entering the AFU, which could restrict or jam the aileron, resulting in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2021-20-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by multiple reports of cracking of the main landing gear (MLG) shock strut lower pin. This AD requires repetitive lubrication and repetitive detailed visual inspections (DVI) and non- destructive test (NDT) inspections of the MLG shock strut lower pins, and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
70-17-01: 70-17-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1061. Applies to Model BAC 1-11 Series 401 Type AK airplanes. To prevent overheating of the heating elements fitted to the S8 and S9 right-hand and left-hand static vent plates located at Station 66, within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, accomplish one of the following: (a) Deactivate the static plate heaters in accordance with Part (B) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 30-PM4306 dated November 28, 1969, or a later ARB-approved issue or an FAA-approved equivalent; or (b) Modify the pitot/static plate heater circuit to provide a separate power supply for each circuit in accordance with Part (A) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 4306 dated November 28, 1969, or a later ARB-approved issue or an FAA-approved equivalent. This amendment becomes effective September 5, 1970.
98-13-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit the use of mach trim and to add speed restrictions if the autopilot is disengaged or inoperative. That AD also requires installation of an associated placard. This amendment adds requirements for replacement of the horizontal stabilizer trim control unit (HSTCU) with a new HSTCU, and reactivation of the mach trim engage/disengage switch/light (if deactivated). Accomplishment of these actions terminates the requirements of the existing AD. This amendment also limits the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent deficiencies of the HSTCU, which could result in a nose-up trim runaway when a single component in the mach trim circuit fails.
98-13-09: This amendment adopts a new airworthiness directive (AD) that applies to certain AERMACCHI S.p.A. (AERMACCHI) Models F.260, F.260B, F.260C, and F.260D airplanes. This AD requires marking the airspeed indicator to indicate the correct flap operation range and stall speed of the airplane. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent the airplane from stalling at an airspeed higher than anticipated, which could result in loss of control of the airplane.
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.