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55-05-02: 55-05-02 HAMILTON STANDARD: Applies to All 43E60 Propellers With 6903 Blades Installed on Lockheed 1049 Series Aircraft Powered by Wright 972TC-18DA Series Engines. Compliance required as indicated. Analysis of loadings and stresses in the Hamilton Standard 43E60/6903 propeller when installed as noted has shown that it is desirable to improve the strength characteristics of the propeller barrel assembly by shotpeening the barrel and spider in specified areas, and by substituting stronger barrel bolts. Therefore, in order to preclude any failures from this cause: At the earliest opportunity, but not later than the first overhaul subsequent to May 1, 1955, accomplish the rework of the hub barrels and spiders, and replace the barrel bolts as specified in Hamilton Standard Service Bulletin No. 316 dated September 10, 1954.
98-12-32: This amendment adopts a new airworthiness directive (AD), applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines, that requires a one-time eddy current inspection (ECI) for cracks or gouges in certain high pressure turbine rotor (HPTR) disks. This amendment is prompted by a report of a HPTR disk found to have a crack in a rim bolt hole during a routine shop manual ECI. The actions specified by this AD are intended to prevent the potential for an uncontained failure of the HPTR disk, which could result in an inflight engine shutdown, aborted takeoff, or damage to the aircraft.
69-11-06: 69-11-06 AVIONS MARCEL DASSAULT: Amdt. 39-770. Applies to all Fan Jet Falcon and Fan Jet Falcon Series D airplanes. Compliance required as indicated unless already accomplished. To prevent a power loss resulting from defective T2 aspirator hoses, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 75 hours' time in service from the date of the last inspection, visually inspect the T2 aspirator hose, P/N MY 20 510.001 or P/N MY 20 510.001A, in each nacelle to see if the hose is collapsed, if the fabric is loose from the hose coil, or if the hose is twisted. (b) If during the inspection required in paragraph (a) either hose is found to be defective, before further flight, replace the defective hose with a new hose of the same part number, or with either hose P/N MY 20 510.001/2 or hose P/N AWF 1.11.1.2.1. (c) The repetitive inspections required by paragraph (a)may be discontinued after the installation of either hose P/N MY 20 510.001/2 or hose P/N AWF 1.11.1.2.1 on each nacelle, in accordance with Avions Marcel Dassault Service Bulletin No. 374, Revision 1, dated March 27, 1969, or later SGAC-approved revision or an FAA-approved equivalent. This amendment becomes effective June 2, 1969.
2000-24-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Vulcanair S.p.A. (Vulcanair) Models P 68 "OBSERVER", P68 "OBSERVER 2", and P68TC "OBSERVER" airplanes. This AD requires you to inspect the nose landing gear (NLG) upper strut for evidence of cracking (cracks or crack beginnings), and replace the NLG upper strut if you find evidence of cracking. 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 failure of the NLG upper strut caused by cracking in the area of the seeger retaining ring groove, which could result in loss of control of the airplane.
88-24-05: 88-24-05 PRATT & WHITNEY: Amendment 39-6018. Applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, - 7AH, -7H, -7F, -7J, and -20 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent sixth stage turbine inner airseal (IAS) rupture that can cause uncontained engine failure, accomplish the following: (a) Modify sixth stage IAS Part Numbers (P/N) 751879, 660178, 661387, 667924, 677871, 704516, and 751881, in accordance with the Accomplishment Instructions contained in PW Service Bulletin 4835, Revision 5, dated September 27, 1983, as follows: (1) Sixth stage IAS installed with either honeycomb or microfin type shrouds where engine build records indicate seal knife edge to shroud diametrical clearance less than 0.153 inches in either the front or the rear knife edge, within the next 500 cycles in service after the effective date of this AD. (2) Sixth stage IAS installed with either honeycomb or microfin type shrouds whereengine build records indicate seal knife edge to shroud diametrical clearance equal to or more than 0.153 inches in both front and rear knife edges, at the next low pressure turbine (LPT) module shop visit after the effective date of this AD. (b) Wet abrasive blast, visually inspect, and fluorescent penetrant inspect (FPI) at the next LPT module shop visit after the effective date of this AD, in accordance with the requirements of paragraph 4E, Inspection 01, Section 72-52-06, of the Engine Manual P/N 646028, Revision 74, sixth stage IAS assemblies P/N's 774836, 774827, 774829, 774825, 774831, 774834, and 774838, that have been modified in accordance with the requirements of PW SB 4835, Revision 3, dated June 12, 1978, or earlier revisions of the SB. (c) Remove from service, prior to further flight, sixth stage IAS assemblies found cracked when accomplishing the requirements of paragraphs (a) or (b) above, and replace with serviceable parts. NOTES: (1) Modification of sixth stage seals in accordance with the requirements of PW SB 4835, Revision 4, dated May 21, 1981, constitutes an equivalent means of compliance with this AD. (2) For the purpose of this AD, an LPT module shop visit occurs when the LPT module rotor is removed from the case and vane assembly. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance times specified in this AD. PW SB 4835, Revision 5, dated September 27, 1983, and the PW Engine Manual P/N 646028, Section 72- 52-06, Inspection 01, Paragraph 4E, Page 817, dated December 1, 1986, and Figure 810, Page 818, dated August 1, 1984, identified and described in this document, 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 Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. These documents also may be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-38, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-6018, becomes effective on December 15,1988.
2003-06-02: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Hartzell Propeller Inc. model HC-C2Y(K,R)-1BF/ F8477-4 propellers with TKS (Aircraft De-icing) Ltd. anti-ice boots that were installed by SOCATA-Groupe AEROSPATIALE, the aircraft manufacturer, using TKS Ltd. Procedure P232, Specification for the Attachment of Propeller Overshoes. This amendment requires removal of the anti-ice boots, inspection and rework of the anti-ice boot area of the propeller blades, and installation of new anti-ice boots. This amendment is prompted by a report of TKS (Aircraft De-icing) Ltd. anti- ice boots on the blades of a model HC-C2Y(K,R)-1BF/F8477-4 propeller that were installed by SOCATA-Groupe AEROSPATIALE using processes that could lead to blade corrosion and failure. The actions specified by this AD are intended to prevent propeller blade separation, damage to the airplane, and possible loss of the airplane.
2018-04-01: We are adopting a new airworthiness directive (AD) for all Airbus Model A320-271N, A321-271N, and A321-272N airplanes. This AD requires de-pairing certain International Aero Engines (IAE) engines in order to continue to operate affected airplanes and discontinuing extended operations (ETOPS) for airplanes with at least one affected engine. This AD was prompted by reports of two engine in-flight shutdowns (IFSDs) and two rejected takeoffs. We are issuing this AD to address the unsafe condition on these products.
2012-03-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-600 series airplanes. This AD requires modifying the fire extinguishing system from a three-bottles solution with 4 flow metering compact unit into a two-bottles solution with 2 flow metering systems equipped with upgraded water absorbing filter elements. This AD was prompted by reports of partial blockage of a certain water absorbing filter element. We are issuing this AD to prevent partial blockage of a certain water absorbing filter element, which could lead to reduction of the halon outflow, which leads to incapacity to maintain fire extinguishing agent concentration. Combined with fire, this condition could result in an uncontrolled fire in the affected compartment.
2003-06-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain General Electric Aircraft Engines (GEAE) CT7 series turboprop engines. This amendment requires initial and repetitive inspections of the propeller gearbox (PGB) oil filter impending bypass button (IBB) for extension (popping), requires follow- on inspections, maintenance, and replacement actions if the PGB oil filter IBB is popped, and if necessary, replacement of the PGB with a serviceable PGB. In addition, this amendment requires replacement of certain left-hand and right-hand idler gears at time of overhaul of PGBs, and the replacement of certain SN PGBs before accumulating 2,000 flight hours. This amendment is prompted by an on-going investigation that concluded that low-time PGB removals are due to accelerated wear of the PGB idler gears, rather than improperly hardened PGB input pinions. The actions specified by this AD are intended to prevent separation of PGB left-hand and right-handidler gears, which could result in uncontained PGB failure and internal bulkhead damage, possibly prohibiting the auxiliary feathering system from fully feathering the propeller on certain PGBs.
68-09-01: 68-09-01 PRATT & WHITNEY AIRCRAFT: Amendment 39-591 as amended by Amendment 39-1581. Applies to Wasp, Jr., and R-985 Type Engines. Compliance required as indicated: To prevent further propeller blade failures as the result of excessive wear of the engine crankshaft flyweight and flyweight liners, accomplish the following: (a) For engines operated with Hartzell propeller models HC-93Z30, HC-B3Z30, and HC-B3W30. (1) With 1,150 hours' or more time in service after the last engine overhaul, within the next 50 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,200 hours' time in service from the last engine overhaul, replace the two engine crankshaft flyweight liners P/N 34461 with two new engine crankshaft flyweight liners P/N 34461; inspect and rework or replace engine crankshaft flyweights P/N's 34462 and 34463 in accordance with Pratt & Whitney Aircraft Service Bulletin No. 1758 Revision A dated November 18, 1964, or later FAA approved revision; (2) With less than 1,150 hours' time in service after the last engine overhaul accomplish the procedures of (a)(1) above prior to the accumulation of 1,200 hours' time in service after the last engine overhaul and thereafter at intervals not to exceed 1,200 hours' time in service from the last engine overhaul. (b) Engines operated with a combination of Hartzell propellers models HC-93Z30, HC-B3Z30, or HC- B3W30 and any other eligible propeller in excess of 1,150 hours' time in service since last engine overhaul must have engine flyweight liners replaced and the engine crankshaft flyweights inspected, reworked or replaced as required by paragraph (a)(1). (c) For engines operated with any other eligible propellers: (1) Engines with more than 1,550 hours' time in service after the last engine overhaul, within the next 50 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,600 hours' time in service from the last engine overhaul, replace the two engine crankshaft flyweight liners P/N 34461 with two new engine crankshaft flyweight liners P/N 34461, inspect and rework or replace engine crankshaft flyweights P/N's 34462 and 34463 in accordance with Pratt & Whitney Aircraft Service Bulletin No. 1758 Revision A dated November 18, 1964, or later FAA approved revision. (2) Engines with less than 1,550 hours' time in service after the last engine overhaul, accomplish the procedures of (c)(1) above prior to the accumulation of 1,600 hours' time in service after the last engine overhaul and thereafter at intervals not to exceed 1,600 hours' time in service from the last engine overhaul. (d) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the repetitive inspection intervals specified in this AD. (e) This supersedes AD 65-07-02. Amendment 39-591 became effective May 26, 1968. This Amendment 39-1581 becomes effective January 17, 1973.