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2019-03-15: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-201, -202, and -203 airplanes, and Model A330- 301, -302, and -303 airplanes. This AD was prompted by reports of damaged drain pipes located above the lower aft pylon fairing (LAPF), caused by a contact between the drain pipe and the two u-shape ribs of the LAPF. This AD requires a special detailed inspection for damage, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
58-01-03: 58-01-03 CONVAIR: Applies to the Following Aircraft Equipped With PR-58E5-17 Carburetors in P&W Double Wasp CB16 and 17 Engines; Model 440 Serial 312 Through 420 and All Model 340 With Model 440 Nacelles. Compliance required by first engine overhaul after March 1, 1958, but not later than October 1, 1958. The PR-58E5-17 carburetor setting originally provided in the aircraft has an undesirable leaning tendency. To overcome this deficiency the PR-58E5-29 carburetor setting has been developed and must be incorporated in the above aircraft. Normal fuel metering in carburetors incorporating the PR-58E5-29 "Transport Setting" may result in powers lower than those employed for aircraft certification. This occurs in the high power range with the control in the Auto-Rich position in cases where the carburetor meters on the rich side of the allowable limits. The amount of power loss will vary with different carburetors. Performance information in the FAA approved Airplane Flight Manual is based upon the maximum certificated power ratings of the engine. To obtain full rated power at manifold pressure limits for maximum continuous power, it is necessary to adjust the fuel mixture by the mixture control (takeoff power is not adversely affected by use of the full rich mixture position). (P&WA Engine Operation Information Letter No. 28 covers this subject in further detail.) In order to insure obtaining the power used in aircraft certification, accomplish the following: 1. For MC power during one-engine out operation use Auto-Lean mixture setting. Insert revised pages in the pertinent Airplane Flight Manuals in accordance with Convair Service Bulletins Nos. 340-144A and 440-58. 2. Modify the PR-58E5-17 carburetor setting to the PR-58E5-29 carburetor setting in accordance with Bendix Aircraft Carburetor Service Bulletin No. 820. 3. The Auto-Lean mixture control position should be plainly marked and identified.
81-06-07: 81-06-07 GULFSTREAM AMERICAN CORPORATION (formerly Grumman American Corporation, Grumman Aerospace Corporation): Amendment 39-4054. Applies to Gulfstream American Model G-1159, serial numbers 1 through 258, and 775, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent improper functioning of the landing gear system, accomplish the following: Within the next 10 hours time in service after the effective date of this AD, inspect the landing gear selector valve to determine valve part number (Ref. Gulfstream II Illustrated Parts Catalog (IPC) Figure 32-23, Item 52). (a) If P/N 1159SCH216-1 or P/N 1159SCH216-5 is installed, no further action is required. (b) If P/N 1159SCH216-3 is installed, accomplish the following: (1) Before further flight, install placard adjacent to the landing gear selector handle. The wording of the placard shall be: "INTERRUPTION OF LANDING GEAR RETRACTION OR EXTENSION PROHIBITED",using letters of 1/8 inch minimum height. Concurrently, FAA Approved Flight Manual Supplement No. GII-81-01, dated February 6, 1981, must be added to the Airplane Flight Manual. The Flight Manual Supplement may be obtained from Gulfstream American Corporation, P.O. Box 2206, Savannah, Georgia 31402. (2) Within 60 landing gear operating cycles (one retraction and one extension) after effective date of this AD, replace P/N 1159SCH216-3 landing gear selector valves with either a P/N 1159SCH216-1 or a P/N 1159SCH216-5 valve. Remove the placard and the Airplane Flight Manual Supplement added in section (1) when either of the replacement valves is installed. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. NOTE: Information concerning replacement selector valves may be obtained from Gulfstream American Corporation Customer Bulletin No. 305, amendment No. 1, January 15, 1981. This amendment is effective March 27, 1981.
2019-03-08: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports of an overheat failure mode of the hydraulic engine-driven pump (EDP), and a determination that the affected EDP needs to be replaced with an improved EDP. This AD requires replacement of a certain EDP with an improved EDP. We are issuing this AD to address the unsafe condition on these products.
2019-03-21: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of corrosion and chromium layer chipping of the forward and aft pintle pins of the main landing gear (MLG) shock struts. This AD requires repetitive inspections for discrepancies of affected forward and aft pintle pins of the MLG shock struts, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
62-10-04: 62-10-04 PRATT & WHITNEY: Amdt. 432 Part 507 Federal Register April 26, 1962. Applies to All JT4A Series Turbojet Engines. Compliance required within the next 85 hours' time in service after the effective date of this directive and thereafter at periods not to exceed 85 hours' time in service from the last inspection. Inspect third stage turbine rotor blades, P/N 405903, 411803, or 411903, for looseness or rattling in accordance with Pratt & Whitney Aircraft telegraphic message of November 15, 1961. If any blade looseness or rattling is found, remove the engine for blade replacement prior to further flight, except that an operator conducting more frequent periodic inspections than at the 85-hour intervals may delay replacement of loose blades for one additional 15-hour period of time in service provided that time in service since a known no loose blade condition will not exceed 85 hours. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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 such operator. (Pratt & Whitney Aircraft telegraphic messages of November 15, 1961, and January 29, 1962, cover the same subject.) This directive effective April 26, 1962. (Revised June 14, 1962, for all persons except those to whom it was made effective immediately by individual telegrams dated May 14, 1962.)
2005-24-09: The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller assemblies, models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X. This AD requires, within 10 flight hours or 10 days after the effective date of this AD, whichever occurs first, removing certain serial number propeller hubs from service. This AD results from a report by the manufacturer that they manufactured and released 40 propeller hubs with improperly machined socket retention threads. We are issuing this AD to prevent cracked propeller hubs, which could cause failure of the propeller hub, blade separation, and loss of control of the airplane.
2002-19-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier-Rotax GmbH 912 F series and 912 S series reciprocating engines with fuel pump assembly part number (P/N) 996.596 installed. This action requires initial and repetitive visual inspections and tests of the fuel pump assembly for fuel leakage. This amendment is prompted by two reports of fuel pump assembly fuel leaks. The actions specified in this AD are intended to prevent in-flight fuel leaks of the fuel pump assembly, which could result in an engine fire.
2005-06-01: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC 155B1 helicopters that requires inspecting the chamfer of the stop on the cabin sliding doors (doors) and installing an airworthy stop if the chamfer exceeds a certain length; and prior to each flight, visually checking the door to determine if it is correctly locked in the open position before flying with the doors open, and checking the locking indicator light and the position of the door handles before flying with the doors closed. This amendment also requires revising the Limitations Section of the Rotorcraft Flight Manual (RFM) to prohibit the opening or closing of a cabin sliding door at airspeeds of 40 or greater knots indicated airspeed (KIAS). This amendment is prompted by a report of a door separating from a helicopter during flight. The actions specified by this AD are intended to prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter.
2005-24-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-300 series airplanes. This AD requires replacing the frequency converters used to supply power for medical and galley utility outlets with modified frequency converters, and related actions. This AD results from a report indicating that a hard short circuit condition between the output of certain frequency converters and their downstream circuit breakers will produce a continuous output current that could cause the undersized output wiring to overheat when the frequency converters fail to shut off. We are issuing this AD to prevent overheating of the output wiring of the frequency converters, which could result in the failure of a wire bundle and consequent adverse effects on other systems sharing the affected wire bundle.