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56-16-03: 56-16-03 SIKORSKY: Applies to All Model S-55 Helicopters With S14-10-2000-1, -2, - 3, -4, and -5 Main Rotor Blades Bearing Serial Numbers 100-3700 Inclusive, and All Model S-51 Helicopters With S10-10-2065 Series Main Rotor Blades Bearing Serial Numbers 100-3700 Inclusive. Compliance required as indicated. Main rotor blades of the S10-10-2065 Series on the S-51 and of the S14-10-2000-1, -2, - 3, -4 and -5 Series on the S-55 have been found with fine cuts on the spar beneath the edges of the pockets. These cuts are believed to be a result of repairs to blade pockets and constitute serious stress raisers which may materially affect the service life of the blades. Inspections are to be accomplished as indicated below. The necessary preparations for inspections, the inspections, the finishing of serviceable blades and the rework of salvable blades are to be in accordance with the procedures recommended in Sikorsky Service Information Circular No. 676 for the S-51 and 1410-669 for the S-55. 1. All blades with less than 500 hours service since manufacture or complete rebuilding prior to May 1953, should be inspected as soon as practicable but prior to the accumulation of 500 hours. 2. All blades with 500 hours or more service since manufacture or complete rebuilding prior to May 1953, should be inspected as soon as practicable but not later than August 15, 1956. 3. Blades found to have no cuts may be returned to service after refinishing. 4. S-55 blades with less than 1,200 hours service and S-51 blades with less than 1,000 hours service and found to have cuts on the top or bottom may be salvaged. 5. Blades found to have cuts on the back are to be returned to the manufacturer for evaluation. 6. S-55 blades with 1,200 hours or more service and S-51 blades with 1,000 hours or more service and found to have cuts on the top, bottom or back are to be returned to the manufacturer for evaluation.
56-16-02: 56-16-02 LOCKHEED: Applies to All Models 49, 149, 649, 749 and 1049 Series Aircraft Equipped With Bendix Eclipse-Pioneer Type PB-10 Series Automatic Pilot Installations. Compliance required as indicated. Numerous instances of fatigue failures have been reported in the side webs of the Bendix Eclipse-Pioneer Type DQ-15 Series servo disconnect mounting brackets in the primary flight control system. Since complete failure could result in disabling the flight control system, the following must be accomplished as indicated: 1. The rudder and elevator servo disconnect mounting bracket installations in the primary flight control system must be inspected by dye penetrant or equivalent method, at 125-hour intervals until item 2 is accomplished. Defective servo mounting brackets must be discarded. 2. To be accomplished as soon as possible but not to exceed next overhaul period after parts become available. The rudder and elevator servo must be reinforced by installation of a secondary servo support bracket to provide additional support and vibration dampening. (Bendix Eclipse-Pioneer Service Bulletin No. 858 and Lockheed Service Bulletins Nos. 49-864 and 1049-2830 also cover this subject.)
69-05-06: 69-05-06 SCHLEICHER: Amdt. 39-733. Applies to Schleicher Model Ka6E gliders, Serial Nos. 1 through 4232 except Serial No. 4226. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the failure of the thermos-bottle mounting brackets, install new mounting clamps with rubber insert, in accordance with Schleicher Technical Note No. 17, dated September 10, 1968, or later LBA-approved issue or an FAA-approved equivalent. This amendment becomes effective April 6, 1969.
2000-15-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for damage or cracking of the aft pressure bulkhead, and cracking of the bulkhead web-to-Y-ring lap joint area and the upper segment of the bulkhead web. That AD also requires certain follow-on actions, if necessary. This amendment requires that a currently required one-time inspection to detect cracking of the upper segment of the bulkhead web be accomplished repetitively, and adds additional repetitive inspections to detect cracking of the upper and lower segments of the aft bulkhead web. The actions specified by this AD are intended to detect and correct fatigue cracking of the bulkhead web, which could result in rapid depressurization of the airplane, and consequent reduced controllability of the airplane.
94-09-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Allied-Signal Inc., Garrett Engine Division, TPE331 series turboprop and Model TSE331-3U turboshaft engines. This action requires inspection of certain third stage turbine stator assemblies, and replacement, if necessary, with serviceable assemblies. This amendment is prompted by reports of six third stage turbine stator assemblies assembled with inner seal supports made of incorrect material that results in a significantly reduced cyclic life. The actions specified by this AD are intended to prevent an uncontained failure of the third stage turbine wheel.
94-19-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the autopilot disconnect switches with modified units. This amendment is prompted by several incidents in which the flight crew did not depress both halves of the autopilot disconnect switch during the LAND 2 or LAND 3 approach and, as a result, one autopilot remained engaged. This condition resulted in unanticipated movements of the stabilizer trim and higher than anticipated control forces of the flight controls. The actions specified by this AD are intended to prevent the flight crew from inadvertently disconnecting only one autopilot when both autopilots are engaged, which could result in unanticipated control surface movements.
92-12-05: 92-12-05 TEXTRON LYCOMING: Amendment 39-8265. Docket No. 91-ANE-48. Applicability: Textron Lycoming O-320 series, IO-320 series, LIO-320 series, AIO-320 series, AEIO-320 series, O-340 series, O-360 series, LO-360 series, HO-360 series, VO-360 series, IVO-360 series, IO-360 series, AIO-360 series, HIO-360 series, LHIO-360 series, LIO-360 series, AEIO-360 series, TO-360 series, LTO-360 series, TIO-360 series, O-480 series, GSO-480 series, IGSO-480 series, IGO-480 series, GO-480 series, O-540 series (excluding models O-540-J and O-540-L), VO-540 series, IO-540 series (excluding model IO-540-W), HIO-540 series, AEIO-540 series, IGSO-540 series, IGO-540 series, TVO-540 series, TIVO-540 series, IVO-540 series, TIO-540 series, LTIO-540 series, TIO-541 series, TIGO-541 series, and IO-720 series opposed piston engines; and in addition those engine models and serial numbers listed in Textron Lycoming Service Bulletin (SB) No. 501, Revision B, dated November 15, 1991; installed on but notlimited to Cessna 172 and Piper PA-28 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent piston pin failure, or piston release, and engine failure, accomplish the following: (a) For engines with serial numbers listed in Textron Lycoming SB No. 501, Revision B, dated November 15, 1991, with more than 75 hours time in service (TIS) since new, since remanufacture, or since factory overhaul on the effective date of this AD, remove all piston pins, Part Number (P/N) LW-14077, within 25 hours TIS after the effective date of this AD, and replace with serviceable parts. (b) For engines with serial numbers listed in Textron Lycoming SB No. 501, Revision B, dated November 15, 1991, with 75 hours or less TIS since new, since remanufacture, or since factory overhaul on the effective date of this AD, remove all piston pins, P/N LW-14077, within 100 hours TIS since new, since remanufacture, or since factory overhaul and replace with serviceable parts. (c) For engines not listed in Textron Lycoming SB No. 501, Revision B, dated November 15, 1991, accomplish the following: (1) Within 15 days after the effective date of this AD, conduct a search and review of maintenance and purchase records to determine if piston pin, P/N LW-14077, had been purchased from Textron Lycoming or a Textron Lycoming distributor from June 18, 1991, through August 5, 1991. (2) For installed piston pins, P/N LW-14077, purchased from Textron Lycoming or a Textron Lycoming distributor from June 18, 1991, through August 5, 1991, accomplish the following: (i) For engines with more than 75 hours TIS since piston pin installation on the effective date of this AD, remove all piston pins, P/N LW-14077, purchased from Textron Lycoming or a Textron Lycoming distributor from June 18, 1991, through August 5, 1991, within 25 hours TIS after the effective date of this AD, and replace with serviceable parts. (ii) For engines with 75 hours or less TIS since piston pin installation on the effective date of this AD, remove all piston pins, P/N LW-14077, purchased from Textron Lycoming or a Textron Lycoming distributor from June 18, 1991, through August 5, 1991, within 100 hours TIS since piston pin installation and replace with serviceable parts. (d) Piston pins, P/N LW-14077, purchased from Textron Lycoming or a Textron Lycoming distributor from June 18, 1991, through August 5, 1991, that are not installed in engines are considered unairworthy and shall not be placed in service. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (f) 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. (g) The identification of certain engines to which this AD is applicable shall be done in accordance with the following Textron Lycoming service document: DOCUMENT NO. PAGES REVISION DATE SB No. 501 1-3 Rev. B Nov. 15, 1991 Total pages: 3 This incorporation was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Textron Lycoming, 652 Oliver Street, Williamsport, PA 17701. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. (h) This amendment becomes effective on July 10, 1992.
95-07-06: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires inspections of the bearings of the aileron control system, and correction of discrepancies. This amendment is prompted by a report indicating that an operator experienced difficulties wherein considerable pressure was required to manually input roll control due to seized bearings in the aileron control system. The actions specified by this AD are intended to prevent such seizure of bearings, which could reduce the pilot's ability to initiate roll control during critical phases of flight.
99-04-21: This amendment adopts a new airworthiness directive (AD) that applies all British Aerospace Jetstream Model 3101 airplanes that have a certain wheel assembly incorporated and all Jetstream Model 3201 airplanes that are equipped with Dunlop AH54450 brake units. This AD requires inspecting the main landing gear brake units for correct setting of the wear indicator pins, and re-setting the pins if incorrect. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the main landing gear brakes because the wear indicator pins present a false indication of the remaining wear of the brake units, which could result in loss of control of the airplane during takeoff, landing, or taxi operations.
91-19-03: 91-19-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-8030. Docket No. 91-ANE-23. Applicability: TCM Models IO-360, L/TSIO-360, IO-346, L/I/O-470, TSIO-470, IO-520, L/TSIO-520, 6-285, IO-550, and GTSIO-520 series engines, which are installed on, but not limited to, certain Beech Bonanza models C33, E33, F33, S35, V35, A36, 36, A36TC, and B36TC; Musketeer model A23, Baron models C55, D55, E55, 58, and 58TC series airplanes; and on certain Cessna models R172K, 180 (Serial Numbers (S/N) 53087 and up), 182(S/N 67042 and up), F182(S/N 00130 and up), 185(S/N 03852 and up), 188(S/N 03474 and up), T188(S/N 03474 and up), 206(S/N 05030 and up), 207(S/N 05227 and up), T207 (S/N 05227 and up), 210 (S/N 63373-63375 and up), T210(S/N 63373-63375 and up), P210(S/N 278 and up), T303, 310, 320, P337, T337, 340, 401, 402, 414 series airplanes; and on certain Mooney Aircraft Corp. models M20K and M20K-252TSE series airplanes; and on certain Piper Pawnee model PA-36, Arrow model PA-28R-201T,Dakota model PA-28-201T, Malibu model PA-46-310P, and Seneca models PA-34-200T and PA-34-220T series airplanes; certificated in any category. Compliance: Required as indicated unless previously accomplished. To prevent operation with collapsed oil filter elements, which can result in loss of oil pressure, engine power loss or engine failure, and possible aircraft damage, accomplish the following prior to September 30, 1991: (a) Inspect the engine oil filter and determine if the filter is a Champion Part No. (P/N) CH48108 or CH48109. If the filter is so identified, proceed to paragraph (b) of this AD. (b) Inspect the engine oil filter and determine the date code of the filter printed on the side of the exterior. Remove any filter bearing any of the following date codes prior to further flight: Date codes: All three-digit date codes with "9" as the third-digit, or date codes 3J8, 4J8, 1K8, 2K8, 3K8, 4K8, 2L8, 1M8, 3M8, 1A0, or 2A0 (c) Filters identified with any of the date codes listed in paragraph (b) of this AD are not serviceable and cannot be returned to service. (d) Replace any removed filter with Champion filter P/N CH48108 or CH48109 having date codes other than those listed in paragraph (b) of the AD, or with any other FAA approved filter that is eligible for the applicable engines. (e) 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. (f) Upon submission of substantiating data by an owner or operator through an FAA Inspector, (maintenance, avionics, operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments of the compliance times specified in this AD may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. (g) All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request from Champion Aviation Products, 330 Pelham Road, Suite 200, Building B, Greenville, South Carolina 29615 or Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601. This information may be examined at the FAA, New England Region, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts. This amendment (39-8030, AD 91-19-03) becomes effective on September 29, 1991.