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2017-15-07: We are superseding airworthiness directive (AD) 2017-04-51 for all Safran Helicopter Engines, S.A., Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. AD 2017-04-51 required inspecting, wrapping, and replacing the affected drain valve assembly (DV) installed on these Arriel 1 engines. This AD requires inspecting and wrapping affected DVs and replacing those DVs found to be defective. This AD eliminates the terminating action that existed under AD 2017-04-51 and reduces the population of affected parts. This AD was prompted by reports of additional fuel leaks originating from the DV on certain Arriel engines. We are issuing this AD to correct the unsafe condition on these products.
50-32-01: 50-32-01 CONTINENTAL: Applies to All Airplanes Equipped With Continental Model E185-3 Engines Serially Numbered 4514-D and Below, E185-1 Engines Serially Numbered 4566-D and Below and E165-2 Engines Serially Numbered 10025 and Below. This Includes Navion, Beech Model 35 and Temco (Luscombe) Model 11A Airplanes. Compliance required each 10 hours of operation as indicated. AD 49-02-04 describes an inspection procedure to preclude the possibility of sudden oil pump failure (and almost immediate complete engine failure resulting therefrom) due to shearing of the square corners of the oil pump drive gear shaft. There have been a few recent oil pump failures which could have been avoided by continuation of periodic wear checks of the oil pump drive until the related parts are proven satisfactory by teardown inspection and/or replacement. Therefore, the following should be accomplished on all engines in the serial number ranges indicated above which have not already complied withContinental Service Bulletin No. M48-15: Remove tachometer drive cable and insert tapered flat end of Continental Drive Fit Indicator flat end of Continental Drive Fit Indicator (P/N 530757) in slot of tachometer drive shaft, tapping slightly to be sure it is tight in place. By holding the graduated indicator with one finger, and moving the bar with another, a reading (in degrees) of total backlash is obtained. Total backlash should not exceed 15 degrees. If total backlash does not exceed 15 degrees, the wear check should be repeated at 10-hour intervals until the engine is overhauled and oil pump parts are dimensionally inspected and/or replaced, to determine whether or not excessive wear is accumulating. An accumulation of an additional 5 degrees indicated wear in 20 hours, over the original reading, whether a total of 15 degrees is reached or not, is sufficient to warrant replacement of parts as hereafter noted. A reading of more than 15 degrees on the indicator indicates excessive wear, a potential failure, and requires immediate replacement of worn parts prior to further operation of the airplane. Parts affected include the oil pump drive gear, oil pump housing, accessory case, and cam gear. The cam gear need not be replaced if concentricity check shows total runout of square holes to be less than 0.004 inch. At the time of major overhaul (or first disassembly), oil pump drive parts as per Continental Service Bulletin No. M48-15, should be checked and replaced if necessary. These parts are the oil pump drive gear and cam gear. The wear check can be made at any Continental Authorized Service Station, and involves only a few minutes for accomplishment. (Continental Service Bulletins Nos. M48-14, with supplements Nos. 1 and 2, and M48-15, cover this same subject.) This supersedes AD 49-02-04.
87-16-11: 87-16-11 BEECH AIRCRAFT CORPORATION: Amendment 39-5709. Applies to Model 58 (S/N's TH-1389, TH-1396, TH-1397, TH-1403, TH-1407 through TH-1410, TH-1412, TH-1414, TH-1416, TH-1420 through TH-1423, TH-1425, TH-1427, TH-1430, TH-1434, TH-1438, TH-1440, TH-1442, TH-1443, TH-1445, TH-1447, TH-1451, TH-1452, TH-1456, TH-1457, TH-1459, TH-1462, TH-1463, TH-1466, TH-1468, TH-1472 through TH-1474, TH-1477, TH-1478, TH-1481, TH-1483, TH-1485, TH-1490, TH-1492, TH-1495 through TH-1497, TH-1499, TH-1500, TH-1502 and TH-1506) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless previously accomplished. To preclude the loss of stall warning capability in icing conditions, accomplish the following: (a) Within the next 25 hours time-in-service (unless the inspection and relay installation requirements of paragraph (c) have been accomplished): (1) Fabricate and install on the instrument panel in clear view of thepilot the following placard using letters of a minimum of 0.10 inch in height: "FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED". (2) Place a copy of this AD in the Limitation Section of Pilot's Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM). (3) Cover the airplane operating placard statement, "This airplane approved for flight in icing conditions" with opaque tape. (4) Operate the airplane in accordance with this limitation. (b) The requirements of paragraph (a) of this AD may be accomplished by the owner/operator on any airplanes which are not used under Part 121 or 135. The person accomplishing these actions must make the appropriate airplane maintenance record entry per FAR 43.9 and 91.173. (c) Within the next 100 hours time-in-service after the effective date of this AD, inspect and, if necessary, modify the stall warning heater circuit in accordance with the instructions in Beechcraft Mandatory Service Bulletin No. 2180,dated June 1987. (d) The requirements and limitations of paragraph (a) of this AD do not apply to airplanes that have been inspected and modified as required per paragraph (c) of this AD. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5709, becomes effective on September 1, 1987.
2017-15-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of uncommanded altitude display changes in the mode control panel (MCP) altitude window. This AD requires replacing the existing MCP with a new MCP having a different part number. We are issuing this AD to address the unsafe condition on these products.
2001-25-10: This amendment adopts a new airworthiness directive (AD) that supersedes Airworthiness Directive (AD) 99-19-32, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-19-32 currently requires you to inspect the flap actuator internal gear system for correct end-play and backlash measurements and accomplish any corrective adjustments, as necessary. Pilatus has identified modifications for the flap system and designed and manufactured a new flap control and warning unit (FCWU) that permits the flap power drive-unit circuit breaker to close during flight. This AD requires you to modify the flap control wiring and install a flap power drive-unit field control panel. The actions specified by this AD are intended to allow the flap power drive-unit circuit breaker to close during flight and prevent current surges in the flap control system. If the pilot cannot close the circuit breaker during flight, the flight control and warning unit (FCWU) would not sense a worn actuator. Current surges in the flap control system could decrease the electrical life of the flap power drive-unit motor contactor. Both conditions have the potential for flap system failure with consequent reduced or loss of control of the airplane.
2001-25-07: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model AS 332C, L, L1, and L2 helicopters. That AD requires conducting a filter clogging warning test, and, if necessary, replacing a jammed valve with an airworthy valve. This amendment requires the same actions as the existing AD but references a revision to the previously referenced service information; adds fuel filter part numbers to the applicability; and clarifies other provisions throughout the AD. This amendment is prompted by jammed fuel filter by-pass valves. The actions specified by this AD are intended to prevent power loss due to fuel starvation, engine flameouts, and a subsequent forced landing.
86-13-01: 86-13-01 WYTWORNIA SPRZETU KOMUNIKACYJNEGO: Amendment 39-5330. Applies to Model(s) PZL M18 (S/Ns up to and including 1Z012-40) airplanes, certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent loss of engine control, accomplish the following: (a) Before the first flight of each day: (1) Visually check the following parts for the absence of discernible deformation, corrugation and cracks in accordance with Wytwornia Sprzetu Komunikacyjnego, PZL-Mielec Mandatory Service Bulletin (MSB) No. E/02.064/84, dated April 1984: (i) The propeller pitch control system load carrying tube, P/N D65.250.00.2 (see the above S/B Sketch No. 1, sheet 1). (ii) The propeller pitch control system bracket, P/N D65.012.00.1 (see the above S/B Sketch No. 1, sheet 1). (iii) The throttle control system torque tube, P/N D65.210.00.1 (see the above S/B Sketch No. 1, sheet 2). (iv) The engine mounting frame struts (see the above S/B Sketch No. 2). (2) If no cracks, deformations, or corrugations are found, record compliance with paragraph (a)(1) of this AD in the aircraft maintenance records in accordance with FAR 91.173. (3) If any crack, deformation, or corrugation is found, replace the damaged part before the next flight as follows: (i) The propeller pitch control tube with a new serviceable part, or accomplish (iv). (ii) The propeller pitch control bracket with a new serviceable part, or accomplish (iv). (iii) The throttle control torque tube with a new serviceable part or an improved part in accordance with Mandatory Design Bulletin (MDB) No. K/02.067/84, dated July 1984, or accomplish (iv). (iv) The torque tube system with either the D65.300.00.4 propeller pitch control cable installation and the D65.310.00.4 throttle control cable installation in accordance with MDB No. K/02.060/83 dated October 1983, or alternatively replace both with the 56-3632-0062 cable installations in accordance with Mandatory Engineering Bulletin (MEB) No. K/02.070/84. (v) The engine frame struts with new serviceable units or with an improved engine mount P/N D64.100.00.5 in accordance with MDB No. K/02.060/83, dated October 1983. (b) The daily visual check required by paragraph (a)(1) of this AD may be performed by the holder of a pilot certificate issued under FAR Part 61 on any airplane which is not used for operations under FAR Part 121, 127, 129, or 135. (c) Within 50 hours time-in-service (TIS) after the effective date of this AD and every 50 hours TIS thereafter: (1) Visually inspect for cracks, using a 5X power (or greater) magnifying glass, the parts described in paragraphs (a)(1)(i) through (a)(1)(iv) of this AD in accordance with MSB E/02.064/84. (2) If any crack is found, prior to the next flight accomplish the corrective action described in paragraph (a)(3) of this AD. (d) The intervals between the repetitive 50 hour TIS inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance of the airplane. (e) Aircraft may be flown in accordance with FAR 21.197 to a location where paragraph (a)(3) and (c) of this AD can be accomplished. (f) The daily and 50 hour TIS repetitive inspections specified by this AD are no longer required after MDB No. K/02.060/83, dated October 1983, is accomplished. If MEB No. K/02.070/84 is accomplished prior to MDB No. K/02.060/83, the inspections specified by this AD on the propeller and throttle controls are no longer required. The engine frame inspection would still be required. (g) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Wytwornia Sprzetu Komunikacyjnego, PZL-Mielec, 39-301 Mielec, Poland, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on July 19, 1986.
2017-14-06: We are superseding airworthiness directive (AD) 93-17-13 for Schweizer Aircraft Corporation and Hughes Helicopters, Inc. (now Sikorsky Aircraft Corporation) (Sikorsky) Model TH55A, 269A, 269A-1, 269B, and 269C helicopters. AD 93-17-13 required installing tachometer markings and inspecting the lower coupling driveshaft (driveshaft). This new AD requires repetitive inspections of the driveshaft and expands the applicability to include Model 269C-1 helicopters. This AD is prompted by reports of accidents because of driveshaft failures. The actions of this AD are intended to prevent the unsafe condition on these products.
78-01-10: 78-01-10 AVIONS MARCEL DASSAULT-BREGUET AVIATION: Amendment 39- 3115. Applies to Model Falcon 10 airplanes, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent the loss of engine fire extinguishing system capability as a result of cracking in the discharge lines, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD, comply with paragraphs (a)(1) through (a)(4) of this paragraph and thereafter continue to comply with paragraphs (a)(1),(a)(2), and (a)(3) at intervals not to exceed 300 hours time in service until paragraph (b) is met: (1) Remove the engine fire extinguishing system lines, P/N's F10A791105 and F10A791115, and inspect for cracks using a dye penetrant method in accordance with paragraph 2C of Avions Marcel Dassault - Breguet Aviation Alert Service Bulletin F10-A-26- 002, AMD-BA F10-A-0141, dated April 4, 1977, or an FAA-approved equivalent (hereinafter referred to as "Alert Service Bulletin"). (2) If a crack is found in a line, replace the line with a line of the same part number or an FAA-approved equivalent that is found to be free of cracks. Mark cracked lines to identify them as unairworthy. (3) Comply with paragraph 2D of the Alert Service Bulletin when reinstalling lines. (4) Enlarge the diameter of the openings which permit passage of the fire extinguishing system lines through the fuselage skin between frames 29 and 30 in accordance with paragraph 2B of the Alert Service Bulletin. (b) The repetitive inspections required by paragraphs (a)(1) through (a)(3) of this AD may be discontinued after the following is accomplished: (1) Paragraph (a)(4) of this AD has been accomplished. (2) A clamp is installed at frame 29 in accordance with paragraph 2D of the Avions Marcel Dassault - Breguet Aviation Service Bulletin F10-26-002, AMD-BA-F10-0141, dated June 17, 1977, or an FAA-approved equivalent (hereinafter referred to as "June Service Bulletin"). (3) Lines, P/N F10 A 791105A2 and F10 A 791115A2, have been installed in accordance with the June Service Bulletin. (c) Airplanes may be flown in accordance with FAR 21.197 and FAR 21.199 to a maintenance base where the repairs and maintenance required by this AD are to be performed. (d) Upon request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, FAA, c/o American Embassy, Brussels, Belgium, may adjust the inspection interval specified in paragraph (a) of this AD or approve modifications equivalent to these specified in paragraph (b) of this AD provided that such requests are made through an FAA maintenance inspector and the request contains substantiating data to justify the request for that operator. This amendment becomes effective January 19, 1978.
91-22-01: 91-22-01 CESSNA: Amendment 39-8061. Docket No. 91-CE-64-AD. Applicability: Model 210 airplanes (serial numbers (S/N) 21059062 through 21064535, S/N T210-0393 through T210-0454, and S/N P21000001 through P21000760), certificated in any category. Compliance: Required within the next 50 hours time-in-service, unless already accomplished. To prevent fuel leakage caused by damaged fuel lines, which could result in an in-flight fire, accomplish the following: (a) Inspect the electrical wires in the nose gear tunnel area and the fuel line to the engine-driven fuel pump for cracks or chafing. (1) If any cracked or chafed electrical wire or fuel line is found, prior to further flight, replace with a new electrical wire or fuel line. Ensure that the electrical wires are bundled and route or clamp the wire bundle so there is a clearance of .25 inches between the wire bundle and fuel line to the engine-driven fuel pump. (2) If no cracked or chafed electrical wire or fuel line is found, ensure that the electrical wires are bundled and route or clamp the wire bundle so there is a clearance of .25 inches between the wire bundle and fuel line to the engine-driven fuel pump. NOTE: Cessna Service Information Letter SE82-32, dated July 23, 1982, includes a photo that highlights the inspection areas and clearance area that is referenced in this AD. This service information may be obtained from the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (d) Information that is related to this AD may be obtained from the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. This amendment (39-8061, AD 91-22-01) becomes effective on November 4, 1991.