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2011-15-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2011-15-51, which was sent previously to all known U.S. owners and operators of the specified Bell Model 407 and 427 helicopters by individual letters. This AD requires inspecting certain hydraulic servo actuators to determine whether the shaft turns independently of the nut or the clevis assembly. If the shaft turns independently, this AD requires replacing the servo with an airworthy servo. If the shaft does not turn independently, the AD requires inspecting to determine the condition of the lock washers. Based on the condition of the lock washers, the AD requires either replacing the servo with an airworthy servo, or if any tab of the lock washer is not flush against a flat surface of the nut or clevis assembly, bending it flush against a flat surface. The AD also requires reidentifying the servo by metal-impression stamping or by vibro- etching ``67.01'' onto the modificationplate. Also, the AD requires before installing a servo with a part number or serial number identified in this AD, not identified by ``67-01'' on the modification plate, inspecting it by following the requirements of this AD. This AD is prompted by a report that a quality escape by a supplier has occurred and certain servos may have a loose nut, shaft, and clevis assembly due to improper lock-washer installation. An investigation after an accident revealed the clevis nut on the servo was loose. The actions specified by this AD are intended to prevent a malfunction of a servo in the flight control system and subsequent loss of control of the helicopter.
2011-18-16: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter model helicopters. This action requires inspecting the upper end fitting ball joints of the main rotor servocontrols for lateral play, and depending on the findings either repetitively inspecting the ball joint or replacing the servocontrol. This amendment is prompted by reports of noncompliant swaging of the end fitting ball joints on main rotor servocontrols. Investigation has shown that the swaging load applied to the ball joints was 1.3 metric tons instead of the specified 13 metric tons. The actions specified in this AD are intended to prevent failure of the upper end fitting ball joints of the main rotor servocontrols, failure of the upper end fittings, and loss of control of the helicopter.
71-16-03: 71-16-03 MORANE SAULNIER: Amdt. 39-1252. Applies to Morane Saulnier Model MS.894A airplanes. Compliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the electrovalve outlet and inlet fuel lines in the engine compartment, replace the electrovalve outlet fuel line, P/N 894.52.0.013, with a new outlet fuel line, P/N 894.52.0.047, and replace the electrovalve inlet fuel line and union assembly, P/N 804.52.0.011, with a new inlet fuel hose and adapter union, P/N 894.52.0.045, in accordance with SOCATA-Service Bulletin No. 81 (Gr. 28.11), dated October 1970, or an FAA-approved equivalent. This amendment becomes effective July 29, 1971.
2011-16-04: This amendment adopts a new airworthiness directive (AD) for Sikorsky Model S-92A helicopters. This action requires making pen and ink changes, inserting a copy of this AD, or inserting specified temporary revisions into the Limitations section of the Rotorcraft Flight Manual (RFM) limiting the maximum rolling groundspeed for a normal landing or takeoff from 65 knots to 50 knots for helicopters with a certain serial-numbered landing gear retract actuator (actuator). Instead of limiting the groundspeed, replacing the affected actuator with a modified actuator is terminating action for the requirements of this AD. This amendment is prompted by a report of a main landing gear that would not retract. The manufacturer reports that certain actuators were manufactured with down-lock keys that did not meet the specified minimum hardness requirements. This condition, if not corrected, could lead to a landing gear collapse following a roll- on landing that exceeds 50 knots groundspeed. These actions are intended to prevent collapse of a landing gear and subsequent loss of control of the helicopter.
2011-20-06: This amendment supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. This action retains the requirements in the existing AD and adds a daily check of the tailboom panels to detect bulging or deformation of the tailboom outer skin panels. If there is bulging or deformation, this AD requires a mechanic to do a tap inspection for debonding. If the debonded area exceeds a certain limit, this AD requires modifying the tailboom. Also, when an area of debond does not exceed the limits, this AD requires, before further flight, repairing the debonded area of the tailboom or replacing the tailboom. This action also adds a tap inspection for additional tailboom panels and requires the inspection on both sides of the tailboom. This amendment is prompted by the determination that more inspections are required and to limit the applicability only to those helicopters with tailboom assemblies that have not been modified. Modifying the tailboom assembly is terminating action for the requirements of this AD. The actions specified in this AD are intended to detect damage in the tailboom to prevent failure of a tailboom and subsequent loss of control of a helicopter.
51-28-02: 51-28-02 FRANKLIN: Applies to Model 6V4-178 Series Engines Prior to Serial Number 17690 and 6V4- 200 Series Engines Prior to Serial Number 26235. Compliance required as indicated. To preclude the possibility of oil pump failure, oil pump gears (P/N 10673 and 17736) must be inspected at each 300 hours of operation. Excessively galled gears must be replaced. If same part numbers are used for replacements, the 300-hour inspections will still apply. If carbonitrided oil pump drive gear, P/N 19377, and oil pump driven gear, P/N 19373, are installed, no further inspection is required. When these new carbonitrided gears are installed, suffix "P" must be stamped after the serial number of the engine on the nameplate - example: No. 1700P. (Franklin Service Bulletin No. 86, revised November 1, 1951, covers this same subject.) This supersedes AD's 51-22-02 and 51-11-03.
98-03-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 and CL-600-2A12 series airplanes, that requires replacement of the anti-noise filter on the standby and auxiliary power unit (APU) fuel pump assemblies with a new filter. 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 electrical arcing between the internal wiring and casing of the anti-noise filter on the standby and APU fuel pump assemblies, and consequent increased risk of fuel tank explosion or fire.
98-02-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. Model HC-E4A-3(A,I) propellers. This action requires replacing propeller blade counterweight clamp bolts with improved bolts. This amendment is prompted by reports of a manufacturing defect in the counterweight clamp bolts that resulted in the blade counterweight separating and causing damage to the propeller. The actions specified in this AD are intended to prevent counterweight clamp bolt failure, which can result in propeller blade counterweight separation and damage to the propeller and aircraft.
2011-20-05: This amendment adopts a new airworthiness directive (AD) for the Eurocopter Model EC225LP helicopters. This AD requires inspecting the dome fairing support for a crack at the dome fairing attachment point. If a crack is found, this AD requires replacing the dome fairing support and the associated coning stop support assembly before further flight. If no crack is found, this AD requires repetitive inspections and retorquing the screws at specified intervals. This AD is prompted by the discovery of two fatigue cracks in the dome fairing attachment on the dome fairing support. This condition, if not corrected, could lead to the loss of the dome fairing in flight, causing damage to the helicopter and injury to people on the ground.
86-05-03: 86-05-03 DeHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-5247. Applies to Model DHC-8-101 airplanes, serial numbers 1 through 24, certificated in any category. To assure structural integrity of the elevator and spring tab, accomplish the following within the next 200 flight hours or 30 days after the effective date of this AD, whichever comes first, unless already accomplished: A. For airplanes, serial numbers 1 through 14, accomplish Modification No. 8/0478 to the elevator mass balance weights as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-4, dated January 15, 1986. B. For airplanes, serial numbers 15 through 24, the limitation imposed by telegraphic AD T85-26-52, issued January 3, 1986, may be removed from the Airplane Flight Manual when Modification No. 8/0468 to the spring tab and elevator mass balance weights, as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-3, dated January 3, 1986, has been incorporated. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to deHavilland Aircraft of Canada, Ltd., Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This supersedes telegraphic AD T85-26-52, dated January 3, 1986. This amendment becomes effective March 24, 1986.