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63-22-03: 63-22-03 MARVEL-SCHEBLER: Amdt. 636 Part 507 Federal Register October 30, 1963. Applies to All MA4-5 Carburetors Not Having the One-Piece Combination Primary and Main Venturi and Used on the Following: Continental O-470 Series Engines Installed in Cessna 180 and 182 Series Aircraft; Continental GO-300 Series Engines Installed in Cessna 175 and P172 Series Aircraft; Lycoming O-540 Series Engines Installed in Aero Commander 500 Series Aircraft, Piper PA-23-250 Series Aircraft and Piper PA-24 Series Aircraft; Lycoming O-360 Series Engines Installed in Piper PA-24 Series Aircraft, Beech 95 Series Aircraft, and Mooney Mark 20 or 21 Series Aircraft; and Franklin 6A4-165 Series Engines Installed in Stinson 108 Series Aircraft. Compliance required at next carburetor removal or overhaul of either the carburetor or engine whichever occurs first after the effective date of this AD, on all carburetors not having the one-piece combination primary and main venturi installed. Carburetorshaving the one-piece combination primary and main venturi installed are identified by the letter "V" stamped on the nameplate. The primary venturi may become loose resulting in wear of the primary venturi support legs on the ends contacting the carburetor body and at the retaining clip area. As a result, the retaining clips may become dislodged or dislocated and wear may progress to the point the venturi becomes dislodged or dislocated. This can cause erratic engine operation or complete engine stoppage. To preclude this, accomplish the following: Replace the existing primary and main venturi with a one-piece combination primary and main venturi of the correct part number for the carburetor involved. When accomplished stamp the letter "V" on the carburetor nameplate below the serial number. (Marvel-Schebler Service Bulletin No. A4-63, Lycoming Service Bulletin No. 297, and Continental Motor Service Bulletin No. M63-18 cover this same subject.) This directive effective December 2, 1963.
63-20-01: 63-20-01 BELLANCA: Amdt. 620 Part 507 Federal Register September 19, 1963. Applies to All Model 14-13 Series Aircraft. Compliance required as indicated. Within 50 hours' time in service after the effective date of this AD, and at intervals thereafter not to exceed 50 hours' time in service from the last inspection, accomplish the following: (a) Inspect for cracks in the welds and the structure immediately adjacent to the area where the left and right brake-cylinder support brackets, P/N's 9811-17 and -21, are attached to the fuselage cross tube P/N 9802-47 (located directly aft of the firewall, below the cabin floor), using a dye penetrant and a 10-power glass or an FAA approved equivalent. Prior to inspection, all grease and dirt shall be removed from the surfaces involved. (b) If cracks are found, that part must be repaired in accordance with an FAA approved repair, or replaced by a part of the same part number, or an FAA approved equivalent part before further flight. This directive effective October 21, 1963.
2018-09-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-200B, 747-300, and 747-400 series airplanes. This AD requires replacing certain low-pressure oxygen flex- hoses with new non-conductive low-pressure oxygen flex-hoses in the gaseous passenger oxygen system in airplanes equipped with therapeutic oxygen. This AD also requires a general visual inspection of the low- pressure passenger oxygen system to ensure there is minimum clearance of the oxygen system components from adjacent structure and systems. This AD was prompted by reports of low-pressure flex-hoses of the flightcrew oxygen system that burned through due to inadvertent electrical current from a short circuit. We are issuing this AD to address the unsafe condition on these products.
2005-15-03: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes identified above. This AD requires repetitive functional tests for noisy or improper operation of the exterior emergency control handle assemblies of the mid, overwing, and aft passenger doors, and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive tests. This AD is prompted by a report that the exterior emergency control mechanism handles were inoperative on a McDonnell Douglas Model MD-11 airplane. We are issuing this AD to prevent failure of the passenger doors to operate properly in an emergency condition, which could delay an emergency evacuation and possibly result in injury to passengers and flightcrew.
86-20-13: 86-20-13 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORP. (ALLISON, formerly DETROIT DIESEL ALLISON): Amendment 39-5465. Applies to Allison Model 250-C28 and -C30 Series engines installed in, but not limited to, Bell Model 206L-1, Messerschmitt-Bolkow-Blohm GmbH BO 105 LS A- 1, Sikorsky Model S-76A, Bell Model 206L-1, modified to incorporate the Allison 250-C30 engine, Bell Model 206L-3, and McDonnell Douglas Helicopter Company (Hughes) Model 369F and 369FF aircraft. The following engine models and turbine serial numbers are affected: ENGINE MODEL TURBINE SERIAL NUMBER 250-C28B CAT 70001 thru 70802 and 70804 250-C28C CAT 28001 thru 28046 250-C30 Series CAT 90001 thru 95436 and 95438 EXCEPT existing Model 250-C28 and 250-C30 Series engines which have incorporated Allison Commercial Engine Alert Bulletin 250-C28/C30 CEB-A-72-2132/3146 dated October 1, 1985, or the following FAA approved equivalents: Allison Message THO-2639W-RFR-85 dated February 7, 1985Allison C28 Overhaul Manual Temporary Revision 72-7, Page 12 dated January 22, 1986 Allison C30 Overhaul Manual Revision dated July 1, 1985, Section 72-50-00, Paragraph (7), page 524 Allison Commercial Service Letter 250-C28/C30 CSL-2071/3073 dated June 1, 1985 Compliance is required as indicated unless already accomplished. To prevent excessive wear and/or fretting damage on the external splines of the turbine spline adapter or the aft splines of the turbine-to-compressor coupling shaft, which can progress to a disconnect and subsequent overspeed gas generator turbine failure/uncontained failure, accomplish the following: (a) Within the next five hours time-in-service after the effective date of this AD, but not later than December 20, 1986, for inservice engines, inspect the gas generator turbine spline adapter locknut torque in accordance with Allison Commercial Engine Alert Bulletin 250-C28/C30 CEB-A-72-2132/3146 dated October 1, 1985, or FAA approved equivalent.(b) Before initial flight, for uninstalled affected turbine assemblies, inspect the gas generator turbine spline adapter locknut torque in accordance with Allison Commercial Engine Alert Bulletin 250-C28/C30 CEB- A-72-2132/3146 dated October 1, 1985, or FAA approved equivalent. NOTE: The compliance requirements of this AD were previously published in Allison Commercial Service Letter 250-C28/C30 CSL-A-2084/3087, Revision 1, dated September 29, 1986, FAA approved by the Manager, Chicago Aircraft Certification Office. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Allison Commercial Engine Alert Bulletin 250-C28/C30 CEB-A-72-2132/3146 dated October 1, 1985, is 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 this document from the manufacturer may obtain copies upon request to Allison Gas Turbine Division, General Motors Corp., P.O. Box 420, Indianapolis, Indiana 46206-0420. This document also may be examined at the Office of Regional Counsel, FAA, ATTN: Rules Docket No. 86-ANE-41, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective December 3, 1986, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD No. 86-20-13, issued October 8, 1986, which contained this amendment.
2005-10-24: The FAA adopts a new airworthiness directive (AD) to supersede AD 2003-14-20, which applies to all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-14-20 requires you to repetitively inspect, using either dye penetrant or magnetic particle methods, the rudder control lever shafts for cracks; inspect (one-time) all lever shaft side plates by measuring the thickness; and if cracks or discrepancies in thickness are found, replace unserviceable parts with new or serviceable parts. Since AD 2003-14-20 was issued, we determined that the AD should also affect Model N22S airplanes. The manufacturer has also revised the service information to include a rudder control lever shaft part number (P/N) that was not part of AD 2003-14-20. Consequently, this AD retains the actions of AD 2003-14-20, adds Model N22S airplanes to the applicability, and adds rudder control lever shaft P/N 1/N-45-1102 to the inspection requirements. We are issuing this ADto detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane.
63-19-06: 63-19-06 SUD AVIATION: Amdt. 615 Part 507 Federal Register September 13, 1963. Applies to SE 3130 Alouette II Aircraft. Compliance required as indicated. To prevent fatigue failure in the top fillet radius area of the rotor shaft, P/N 68.00.001, the following shall be accomplished within 10 hours' time in service after the effective date of this AD: (a) Rotor shafts Serial Numbers 307 and 309 shall be replaced with new shafts and the replaced shafts damaged or marked in such a way as to preclude their further use in any helicopter. (b) Rotor shafts other than those covered in paragraph (a) shall be inspected and reworked or replaced in accordance with Sud Technical Instruction for SE 3130 Alouette II helicopters (Appendix to Service Bulletin 68.11.210A) by Sud or Republic Aviation, unless already accomplished. There is no life limit for shafts that incorporate this modification and are marked on the bottom with D12.13.394 or D12.13.424. Reworked or new rotor shaft may replace unreworked shafts when replacement is required. (Sud Service Bulletin AL II No. 68.11.210/A, including Appendix entitled "Technical Instruction", covers this subject.) This directive effective September 13, 1963.
2018-09-15: We are superseding Airworthiness Directive (AD) 2016-25-18, which applied to certain Bombardier, Inc., Model BD-700-1A10 and BD- 700-1A11 airplanes. AD 2016-25-18 required an inspection for discrepancies of the attachment points of the links between the engine rear mount assemblies, and corrective actions if necessary. This AD requires an inspection of certain attachment points, corrective action if necessary, and replacement of certain bolts and nuts in the engine rear mount assemblies. This AD also adds airplanes to the applicability. This AD was prompted by the determination that replacement of certain nuts and bolts in the engine rear mount assemblies is necessary. We are issuing this AD to address the unsafe condition on these products.
86-16-07: 86-16-07 SAAB-FAIRCHILD: Amendment 39-5381. Applies to Model SF-340A airplanes listed in Service Bulletin SF340-27-028, Revision 1, dated August 14, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent uncommanded pitch trim inputs, accomplish the following: 1. Modify the elevator pitch trim synchronizer in accordance with SAAB-Fairchild Service Bulletin SF340-27-028, Revision 1, dated August 14, 1985. 2. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. 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 document from the manufacturer, may obtain copies upon request to SAAB-Fairchild, Product Support, S-58188, Linkoping, Sweden. This document 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 amendment becomes effective September 10, 1986.
56-21-01: 56-21-01 BELL: Applies to All Models 47G, 47G2, and 47H1 Helicopters Except As Noted Below and All Spare Hydraulic Boost Power Cylinders Part Numbers 1090, 1190 and All 1270 Cylinders Prior to and Including Serial Number 733. Model 47G, Serial Numbers 1530 and 1687 and Up; Model 47G2, Serial Numbers 1494, 1505, 1506, 1508, 1617 and Up; and Model 47H1, Serial Numbers 1534 and Up Will be Modified Prior to Delivery. Compliance required as indicated. Malfunctioning of the hydraulic boost cylinder in service has necessitated the replacement of the hydraulic boost power cylinder barrels and clamps in the fore and aft and lateral cyclic boost power cylinder units and the establishment of a service life of 100 hours on the cylinders which have not been modified. These hydraulic boost cylinder barrels must be replaced by the time 100 hours service is obtained, except barrels that have already accumulated 100 hours service prior to the date of this directive may be used until 125hours are obtained or until December 1, 1956, whichever occurs first. (Detail procedures for installation of cylinder barrel P/N 1097 and clamps P/N 1029 are contained in Bell's Mandatory Service Bulletin No. 114 dated August 27, 1956.)