Results
2005-13-07: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with certain part numbers (P/Ns) and serial numbers (SNs) of low pressure (LP) 1st and 2nd stage turbine rotor discs initially installed. This AD requires replacement of those LP 1st and 2nd stage turbine rotor discs. This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and damage to the airplane.
74-20-05: 74-20-05 BELL: Amendment 39-1965. Applies to Bell Model 212 helicopters, serial numbers 30501 through 30593, certificated in all categories. Compliance required within the next 100 hours' time in service after the effective date of the A.D., unless already accomplished. To prevent possible failure of the synchronized elevator ribs with resulting loss of the elevator, modify the right and left elevators as specified in Part III of Bell Helicopter Company Service Bulletin No. 212-01-74-2 dated March 27, 1974, or later FAA approved revision. The manufacturer's specifications and procedures identified and described in this directive are 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 the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D. C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective October 21, 1974.
74-16-05: 74-16-05 SIKORSKY AIRCRAFT: Amendment 39-1910 is amended by Amendment 39-2033. Applies to S-64A, S-64E, and S-56 helicopters certificated in all categories. Compliance required as indicated. To prevent fatigue failures of the main rotor head spindle lock nut, accomplish the following: (a) Before the accumulation of 750 hours time in service on a main rotor head spindle lock nut, P/N S1510-23031-0, or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, replace the affected lock nut with a serviceable part of the same part number and thereafter repeat replacement at intervals not to exceed 750 hours time in service. (b) Before the accumulation of 10,500 hours time in service on a main rotor head spindle lock nut, P/N S1510-23031-1, or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, replace the affected lock nut with a serviceable part of the same part number and thereafter repeat replacement at intervals not to exceed 10,500 hours time in service. Amendment 39-1910 became effective August 15, 1974. This amendment 39-2033 becomes effective December 12, 1974.
51-15-02: 51-15-02 FRANKLIN: Applies to All Franklin 6A4-165-B3 Engines Serially Numbered 33046 and Below Incorporating Original Crankcase (Left Half No. 18305; Right Half No. 18306). These Two Parts Form Crankcase Assembly, P/N 18553. The Number of Each Crankcase Half is Located on Each Casting Below the Number 1 and 6 Cylinder Location. To be accomplished by July 15, 1951. Effective on and after this date, all applicable crankcases with 500 hours of operation since new or 250 hours since last overhaul should be inspected as follows: Remove crankcase cover and visually inspect the webbing near the main journal area for cracks. (1) Crankcases found to be free of cracks should be inspected at 250-hour intervals thereafter. In the event that the conditions described in (2) and (3) are detected, the provisions of (2) and (3) will apply. (2) Crankcases found with (a) surface indications, hairline cracks, or small wall cracks and (b) cracks starting at main bearing stud hole on the opposite side from main bearing support, may be operated further at the option of the owner. Such crankcases should be inspected at 50-hour intervals thereafter to determine progress of cracks. (3) Crankcases found fractured or with cracks that have progressed to the extent that they enter the main bearing supports (usually from back near (a) main bearing stud hole and (b) drilled oil hole) indicate that a complete break soon will occur. Such crankcases should be replaced with the reinforced crankcase assembly, P/N 18925, at which time no further inspection is required. Crankcase assembly P/N 18925 may be identified by casting No. 18905 appearing below No. 1 cylinder location and casting No. 18906 appearing below No. 6 cylinder location. (Franklin Service News No. 10 also covers this subject.)
2005-13-03: The FAA is adopting a new airworthiness directive (AD) for certain AvCraft Dornier Model 328-100 and -300 airplanes. This AD requires operators to install colored identification strips on the pulley brackets, fairlead bracket assemblies, operational assemblies, and flight control cables. This AD is prompted by a report that the flight control systems do not have elements that are distinctively identified. We are issuing this AD to prevent the incorrect re-assembly of the flight control system during maintenance, which could result in reduced controllability of the airplane.
67-03-08: 67-03-08 VICKERS: Amdt. 39-330 Part 39 Federal Register December 29, 1966. Applies to Viscount Models 744, 745D, and 810 Series Airplanes. Compliance required as indicated. To prevent further failures of the nose landing gear bracing structure, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, visually inspect the nose landing gear bracing structure for damage in accordance with British Aircraft Corporation (BAC) Ltd. Preliminary Technical Leaflet (PTL) No. 104, Issue 3 (800/810 Series), or No. 240, Issue 3 (700 Series), or later ARB-approved issue, and thereafter at intervals not to exceed 350 hours' time in service from the last inspection until modified in accordance with (e). (b) Within the next 350 hours' time in service after the effective date of this AD, unless already accomplished within the last 1,050 hours' time in service, conduct a radiographic inspection or disassemble and inspect by dye penetrant the upper and lower actuator beam members and center diaphragms of the actuator beam for cracks in accordance with applicable PTL specified in (a) of this AD or later ARB-approved issue and thereafter at intervals not to exceed 1,400 hours' time in service from the last inspection until modified in accordance with (e). (c) Conduct the visual inspection specified in (a) before further flight and the radiographic or dye penetrant inspection specified in (b) within the next 350 hours' time in service following any flight in which the nose landing gear is subjected to any of the high loadings discussed in the paragraph headed "The Cause" of the applicable PTL specified in (a) of this AD or later ARB-approved issue. (d) Repair or replace any parts found damaged or cracked during the inspections required by this AD before further flight in accordance with the applicable PTL specified in (a) of this AD or later ARB-approved issue or an equivalent approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region. (e) The repetitive inspections required by this AD may be discontinued after installation of BAC Modification D3147 (700 Series) or (800/810 Series) or an equivalent approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This directive effective January 28, 1967.
2005-12-20: The FAA is adopting a new airworthiness directive (AD) for certain The Lancair Company (Lancair) Model LC41-550FG airplanes. This AD requires both visual and dye penetrant inspections of the elevator torque tube assembly for cracks. If a crack is found, this AD requires replacement with a modified assembly that incorporates a steel doubler. This AD also requires replacement of the modified elevator torque tube assembly every 300 hours time-in-service or 18 months (whichever occurs first). This AD results from cracks found in the weld area of the elevator torque tube assembly. We are issuing this AD to detect and correct cracks in the elevator torque tube assembly, which could result in failure of the elevator torque tube assembly and subsequent loss of control of the airplane.
2016-07-26: We are superseding Airworthiness Directive (AD) 2010-23-02 for Eurocopter France (now Airbus Helicopters) Model SA-365N, SA-365N1, AS- 365N2, and AS 365 N3 helicopters. AD 2010-23-02 required amending the Limitations section of the Rotorcraft Flight Manual (RFM) to limit the never-exceed velocity (VNE) to 150 Knots Indicated Air Speed (KIAS) and to add a 1,500 ft/minute rate of descent (R/D) limitation beyond 140 KIAS. Since we issued AD 2010-23-02, a design change designated as modification (MOD) 0755B28 improved the dynamic behavior of the horizontal stabilizer such that AD actions are not required. This new AD retains the requirements of AD 2010-23-01 and revises the applicability to exclude helicopters with MOD 0755B28. We are issuing this AD to exclude certain helicopters from the applicability and restrict the VNE on other helicopters to prevent failure of the horizontal stabilizer and subsequent loss of control of the helicopter.
2005-12-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires inspecting the electrical connectors of the fire extinguisher bottles for the forward and aft baggage compartments and for the auxiliary power unit and engine nacelles to determine if they are connected correctly; and doing related investigative and corrective actions, if necessary. This AD is prompted by reports of the electrical connectors for the fire bottles in the forward and aft baggage compartments being cross connected. We are issuing this AD to detect and correct cross connection of the fire extinguisher bottles, which could result in failure of the fire bottles to discharge and consequent inability to extinguish a fire in the affected areas.
66-14-01: 66-14-01 AERO COMMANDER (SNOW): Amdt. 39-246 Part 39 Federal Register June 3, 1966. Applies to Models S-2A, S-2B, S-2C, and 600 S-2C Airplanes. Compliance required as indicated, unless already accomplished. To prevent fatigue cracks in the lower spar cap of the wing main spar, accomplish the following: (a) For Model S-2A airplanes with 1,400 or more hours' time in service on the effective date of this AD - (1) Comply with (k) within the next 100 hours' time in service and comply with (l) within the next 1,500 hours' time in service after complying with (k); or (2) Comply with (l) within the next 100 hours' time in service. (b) For Model S-2A airplanes with less than 1,400 hours' time in service on the effective date of this AD - (1) Comply with (k) before the accumulation of 1,500 hours' time in service and comply with (l) within the next 1,500 hours' time in service after complying with (k); or (2) Comply with (l) before the accumulation of 1,500 hours' time in service. (c) For Models S-2B and S-2C airplanes, Serial Number 1189 and below, powered by 450 hp. engines, with 900 or more hours' time in service on the effective date of this AD - (1) Comply with (k) within the next 100 hours' time in service and comply with (l) within the next 1,000 hours' time in service after complying with (k); or (2) Comply with (l) within the next 100 hours' time in service. (d) For Models S-2B and S-2C airplanes, Serial Number 1189 and below, powered by 450 hp. engines, with less than 900 hours' time in service on the effective date of this AD - (1) Comply with (k) before the accumulation of 1,000 hours' time in service and comply with (l) within the next 1,000 hours' time in service after complying with (k); or (2) Comply with (l) before the accumulation of 1,000 hours' time in service. (e) For Model S-2C airplanes, Serial Numbers 1190 through 1231, powered by 450 hp. engines, with 900 or more hours' time in service on the effective date of this AD, comply with (l) within the next 100 hours' time in service. (f) For Model S-2C airplanes, Serial Numbers 1190 through 1231, powered by 450 hp. engines, with less than 900 hours' time in service on the effective date of this AD, comply with (l) before the accumulation of 1,000 hours' time in service. (g) For Models S-2C and 600 S-2C airplanes, Serial Number 1189 and below, powered by 600 hp. engines, with 600 or more hours' time in service on the effective date of this AD - (1) Comply with (k) within the next 100 hours' time in service and comply with (l) within the next 700 hours' time in service after complying with (k); or (2) Comply with (l) within the next 100 hours' time in service. (h) For Models S-2C and 600 S-2C airplanes, Serial Number 1189 and below, powered by 600 hp. engines, with less than 600 hours' time in service on the effective date of this AD - (1) Comply with (k) before the accumulation of 700 hours' time in service and comply with (l) within the next 700 hours' time in service after complying with (k); or (2) Comply with (l) before the accumulation of 700 hours' time in service. (i) For Models S-2C and 600 S-2C airplanes, Serial Numbers 1190 through 1231, powered by 600 hp. engines, with 600 or more hours' time in service on the effective date of this AD, comply with (l) within the next 100 hours' time in service. (j) For Models S-2C and 600 S-2C airplanes, Serial Numbers 1190 through 1231, powered by 600 hp. engines, with less than 600 hours' time in service on the effective date of this AD, comply with (l) before the accumulation of 700 hours' time in service. (k) Install modified wing center splice in accordance with Snow Service Letter No. 29 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southwest Region. (l) Install wing lower steel spar caps in accordance with Snow Drawing No. 5-1089, Revision D, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southwest Region. (Snow Service Letter No. 36 pertains to this subject.) This directive effective July 5, 1966.