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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.)
72-18-09: 72-18-09 BRITISH AIRCRAFT CORPORATION: Amendment 39-1514. Applies to Vickers Viscount, Model 744, 745D and 810 airplanes. Compliance is required as indicated. To reduce the vulnerability of control rods, electrical systems, and structure located in the underfloor electrical system bay to fire and overheat damage, accomplish the following: (a) For Models 744, 745D and 810 airplanes with nickel-cadmium batteries in the primary electrical system, within the next 250 hours' time in service after the effective date of this AD, unless already accomplished, replace the control rods in accordance with paragraph (e) and replace the electrical panel guard covers in accordance with paragraph (f). (b) For Models 744 and 745D airplanes with nickel-cadmium batteries in the primary electrical system, within the next 250 hours' time in service after the effective date of this AD, unless already accomplished, install protective surfaces on the lower surface of floor panels in accordance with paragraph (g). (c) For Models 744, 745D and 810 airplanes with lead acid batteries in the primary electrical system within the next 1500 hours' time in service after the effective date of this AD, unless already accomplished, replace the control rods in accordance with paragraph (e) and replace the electrical panel guard covers in accordance with paragraph (f). (d) For Models 744 and 745D airplanes with lead acid batteries in the primary electrical system, within the next 1500 hours' time in service after the effective date of this AD, unless already accomplished, install protective panels on the lower surface of floor panels in accordance with paragraph (g). (e) Replace applicable control rods listed in Column A with the control rods listed in Column B: (1) For Models 744 and 745D airplanes : COLUMN A Remove Part Numbers COLUMN B Install Part Numbers 70133 Sht. 97 70133 Sht. 231 Aileron 70133 Sht. 185 70133 Sht. 235 70133 Sht.93 70133 Sht. 227 Elevator 70133 Sht. 95 70133 Sht. 229 70133 Sht. 93 70133 Sht. 227 Rudder 70133 Sht. 95 70133 Sht. 229 (2) For Model 810 airplanes: COLUMN A Remove Part Numbers COLUMN B Install Part Numbers 70133 Sht. 97 70133 Sht. 231 Aileron 80233 Sht. 31 80233 Sht. 391 70133 Sht. 93 70133 Sht. 227 Elevator 70133 Sht. 153 70133 Sht. 233 70133 Sht. 93 70133 Sht. 227 Rudder 70133 Sht. 153 70133 Sht. 233 (f) Replace Perspex electrical panel covers listed in Column A with glasscloth resin laminate covers listed in Column C, or FAA-approved equivalent covers. (1) For Models 744 and 745D airplanes: COLUMN A COLUMN B COLUMN C Remove Part Numbers Location Install Part Numbers 72436-1903 74536-315 Over fuses at top of power panel "K" At cut-out for control rods at top of power panel "J" 72436 Sht. 735 74536-1481 72436-663 Over wing root panel "H" 72436 Sht. 737 72436-665 Over wing rootpanel "G" 72436 Sht. 739 (2) For Model 810 airplanes: COLUMN A COLUMN B COLUMN C Remove Part Numbers Location Install Part Numbers 81236-2713 Over wing root panel "H" 81236 Sht. 147 81236-2715 Over wing root panel "G" 81236 Sht. 149 (g) Install 2024 aluminum alloy sheeting with a minimum thickness of .028 inches, or an FAA-approved equivalent fire resistant material, on the lower surface of all floor panels made of plywood or material with similar fire resistant characteristics, between fuselage stations 357.85 and 414.00. (British Aircraft Corporation Bulletins for Modification D.3249 (700 Series) and FG.2127 (800/810 Series) cover this same subject). This amendment becomes effective 6 September 1972.
63-19-05: 63-19-05 SUD AVIATION: Amdt. 614 Part 507 Federal Register September 10, 1963. Applies to All SE 3130 Alouette II Aircraft. Compliance required as indicated. To prevent fatigue failure of the main rotor hub P/N 3130.12.20.001 the following must be accomplished: (a) The main rotor hub must be replaced with a new hub prior to accumulating a total of more than 600 hours' time in service, except as provided for in (b). (b) The service life of the main rotor hub may be extended to a maximum of 1,200 hours' time in service if the hubs are inspected by means of the ultrasonic method specified in Sud Service Bulletin No. AL.II 12.11.204/A, or an FAA approved equivalent method, as follows: (1) Hubs which have accumulated less than 600 hours' time in service on the effective date of this AD shall be inspected prior to 600 hours' time in service and thereafter at intervals not exceeding 50 hours' time in service. (2) Hubs which have accumulated more than 600 hours' time in service on the effective date of this AD shall be inspected within 10 hours' time in service after the effective date, and thereafter at intervals not exceeding 50 hours' time in service. (3) Replace cracked hubs before further flight. (Sud Service Bulletin No. AL.II 12.11.204/A dated April 18, 1962, covers the same subject.) This directive effective September 16, 1963.
85-24-02: 85-24-02 BOEING: Amendment 39-5170. Applies to all Model 727-200 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. \n\n\tTo detect corrosion of the wing lower skin that could result in fuel entering the ram air plenum chamber accomplish the following: \n\n\tA.\tOn airplanes with more than 10,000 hours time-in-service or 4 years since date of manufacture, accomplish the following within the next 3,000 hours time-in-service or 1 year, whichever occurs first after the effective date of this AD: \n\n\t\t1.\tVisually inspect the upper wall of the air conditioning ram air plenum chamber for corrosion in accordance with Part II of Boeing Service Bulletin 727-51-17, dated April 26, 1974, or later FAA approved revision. \n\n\t\t2.\tIf corrosion is detected, repair and refinish in accordance with Figure 3 of the Boeing Service Bulletin 727-51-17 dated April 26, 1974, or later FAA-approved revision, or in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tRepeat the procedures required in paragraph A., above, at intervals not to exceed either 8,000 hours time-in-service or 4 years, whichever occurs first. \n\n\tC.\tInspections accomplished in accordance with Part II of Boeing Service Bulletin 727-51-17 prior to the effective date of this AD satisfy the initial inspection requirements of this AD. \n\n\tD.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\tSpecial 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. \n\n\tAll persons affected by this proposal who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents 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. \n\n\tThis amendment becomes effective December 23, 1985.