Results
2005-13-28: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes. This AD requires a one-time inspection of the clevis end of the vertical tie rods that support the center stowage bins to measure the exposed thread, installation of placards that advise of weight limits for certain electrical racks, a one-time inspection and records check to determine the amount of weight currently installed in those electrical racks, corrective actions, and replacement of the vertical tie rods for the center stowage bins or electrical racks with new improved tie rods, as applicable. The actions specified by this AD are intended to prevent failure of the vertical tie rods supporting certain electrical racks and the center stowage bins, which could cause the center stowage bins or electrical racks to fall onto passenger seats below during an emergency landing, impeding an emergency evacuation or injuring passengers. This action is intended to address the identified unsafe condition.
2018-10-04: We are superseding Airworthiness Directive (AD) 2018-03-15 for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as reports of finding abrasion damage behind the instrument panel caused by ventilation hose chafing. We are issuing this AD to require actions to address the unsafe condition on these products.
85-05-51 R2: 85-05-51 R2 BRITISH AEROSPACE: Amendment 39-5077. Applies to Model BAe 146 airplanes certificated in all categories on which Modification HCM00650A has not been accomplished. Compliance is required before further flight after the effective date of this airworthiness directive (AD). To prevent fuel leaks into the passenger cabin and prevent potential fire, accomplish the following unless previously accomplished: A. Before further flight: 1. Drain center fuel tank, and 2. Incorporate the following information into the airplane flight manual and provide to flight crews: DO NOT DISPATCH WITH FUEL IN THE CENTER TANK. B. Within 48 hours after the effective date of this AD, modify the airplane in accordance with BAe 146 Alert Service Bulletin 28-A3 Revision 2, dated March 25, 1985, paragraph 2A. C. Incorporation of British Aerospace Modification HCM00650A terminates the requirement to comply with paragraphs A. and B., above, of this directive. D. Alternate 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. NOTE: Compliance with paragraph A.2. of this directive may be effected by including a copy of the AD in the airplane flight manual and operating manual. All persons affected by this proposal who have not already received these documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or 9010 East Marginal Way South, Seattle, Washington. This Amendment 39-5077 becomes effective June 24, 1985. It was effective earlier to all recipients of telegraphic AD T85-05-51 issued March 15, 1985, and T85-05-51 R1, issued March 22, 1985, which containedthis amendment.
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.)
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.
2018-09-16: We are superseding Airworthiness Directive (AD) 2015-15-13, which applied to certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015- 15-13 required a modification of the potable water service panel and waste water service panel, including doing applicable related investigative and corrective actions. This AD requires a modification of the waste water and potable water service panels with new compliance times. This AD also removes certain airplanes from the applicability and adds Model A320-216 airplanes to the applicability. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the potable water and waste water service panel areas are subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
52-04-07: 52-04-07 MARTIN: Applies to All Models 202 and 202A Aircraft Except as Noted. Compliance required not later than July 1, 1952. The following controls and their wiring are common to two wing anti-icing heaters. The controls listed are identical in each nacelle. Modify the system so each of the controls serves only one heater: 1. Emergency high heat 400 degrees cutout switch. 2. Firewall shutoff switch. 3. Fuel pump circuit breaker (supplies power to ignition controls and master fuel controls). 4. Fuel shutoff relay. 5. Wiring to the master and auxiliary solenoid valves. 6. Fuel booster pump relay (has dual power input but single ground on the control circuit). 7. Ignition relay (202 only). 8. Ignition transformer (202 only). 9. Ignition circuit breaker (202 only). 10. AC safety relay (202 only). (Trans World Airlines Engineering Order 5838 covers this same subject for the 202A).
63-19-01: 63-19-01 de HAVILLAND: Amdt. 611, Part 507, Federal Register September 7, 1963. Applies to All Model DH 104 Dove Aircraft. Compliance required as indicated. As a result of cracks in the aileron, rudder, elevator and flap hinge links and hinge brackets, accomplish the following: (a) Hinge links and brackets not incorporating Modifications 841, 842 or 843 shall be inspected for cracks at intervals not exceeding 600 hours' time in service, or each 12 months, whichever occurs first. Remove the point from the components before inspection, and reapply protective coating after inspection. (b) Hinge links and brackets incorporating Modifications 841, 842 or 843 shall be inspected for cracks at intervals not exceeding 1,800 hours' time in service. (c) Replace cracked parts before further flight. (de Havilland Service Technical News Sheet CT (104) No. 123, Issue 5 dated March 19, 1962, covers this subject.) This supersedes AD 56-15-05. This directiveeffective September 7, 1963.
53-10-01: 53-10-01 CURTISS-WRIGHT: Applies to all C-46 Series aircraft. To be accomplished not later than November 1, 1953. To guard against the possibility of excessive air temperatures and associated fire hazards in the vacuum system discharge line, one of the following modifications must be accomplished: 1. Install a fusible plug in the side of the vacuum pump discharge port at right angles to the axis of the discharge port boss. Some pumps incorporate a plugged hole in the discharge port which may be enlarged to a 3/8-inch pipe tapped hole to accommodate the fusible plug. This plug should employ an AN 840-8D fitting with a binary eutectic mixture of 67.8 percent tin and 32.2 percent cadmium, which has a melting point of 351 degrees F. A drawing describing the design of such a plug is shown in Figure Douglas 2. The 3/8-inch fusible plug fitting is intended for pumps such as the Model 3P-211. Brass fittings of the same design as the above dural fittings are also acceptable. Incorporation of an overboard drain line clamped to the fusible plug is recommended, but is not mandatory. On installations which do not use an overboard discharge line the possibility exists that the plug may damage other nacelle components if it can hit them upon being blown out of the adapter at high velocity. Therefore, if no overboard discharge line is provided, the installation must be made in such a manner that the plug will not be directed toward any vulnerable components when it is blown from the adapter. Also, incorporation of steel lines with fire resistant hoses and utilizing hose liners and clamps in the vacuum discharge line is recommended if cracking and drying out of the flexible hose assemblies is experienced. In lieu of this fusible plug installation: 2. An oil separator equivalent in principle to the Genisco No. 40081 incorporating a pressure relief valve which can be disassembled for cleaning must be provided. (Genisco Co. is located at 2233 Federal Ave., Los Angeles 64, Calif.)
2018-10-02: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 airplanes. This AD requires inspecting the part number of the occupant restraint system on the standard attendant seats, and doing additional inspections and corrective actions if necessary. This AD was prompted by a report of loose attachment bolts on the occupant restraint system on a standard attendant seat due to the bolts being over-torqued during production. We are issuing this AD to address the unsafe condition on these products.
85-20-02: 85-20-02 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5144. Applies to Lockheed Model L-1011 series airplanes, certificated in any category, incorporating Kevlar/Nomex honeycomb elevator trailing edge panels. Compliance required as indicated, unless previously accomplished. To prevent the potential of major structural damage to the airplane due to flutter divergence as a result of water retention in the elevator trailing edge panels, accomplish the following: a. Within 300 hours time-in-service after the effective date of this AD, inspect by X- ray, moisture meter, or in-situ balance check, the elevator trailing edges for water entrapment in accordance with Lockheed Service Bulletin 093-55-026 dated November 20, 1984, or later FAA approved revision: 1. If no water is detected and the trailing edge has less than 20,000 hours time-in-service, reinspect in accordance with paragraph (a) at intervals not to exceed 3,500 hours time-in-service. 2. If no water is detected and the trailing edge has 20,000 or more hours time-in-service, reinspect in accordance with paragraph (a) at intervals not to exceed 7,000 hours time-in-service. 3. If water is present and the calculated or measured unbalance is within allowable limits, reinspect in accordance with paragraph (a) at intervals not to exceed 1,100 hours time-in-service. 4. If water is present and the total elevator unbalance cannot be brought within allowable limits, replace the trailing edge panel or panels before further flight. b. If the trailing edge is replaced by a trailing edge part number 1580585-103 or - 105, within 3,500 hours time-in-service after the replacement inspect in accordance with paragraph (a) and reinspect in accordance with paragraphs (a)(1), (a)(2), or (a)(3). c. The repetitive inspections required by paragraphs (a)(1), (a)(2), and (a)(3) may be discontinued after the trailing edge is modified in accordance with Lockheed Service Bulletin 093- 55-027, dated November 20, 1984, or later FAA-approved revision. d. Alternate means of compliance with this AD which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. e. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base for accomplishment of inspections or modifications required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective November 12, 1985.
2018-09-07: We are adopting a new airworthiness directive (AD) for Rolls- Royce plc (RR) Viper Mk. 601-22 turbojet engines. This AD requires removing the oil pump assembly, part number (P/N) V112027, and oil pressure filter, P/N V21264, from service and replacing them with parts eligible for installation. This AD was prompted by a report of an engine failure caused by installation of an incorrect oil filter. We are issuing this AD to correct the unsafe condition on these products.
87-06-07: 87-06-07 WEBER AIRCRAFT: Amendment 39-5574. Applies to Ancra part number 45238-10 (Weber SCD 833437-401) and Ancra part numbers 45232-10, -11, -12 (Weber SCD 833509-401, 403, 405) aft seat track fittings used on Weber Aircraft TSO C39a passenger and flight attendant seats. NOTE: Part numbers are not marked on the individual seat track fittings. Weber Service Bulletins Nos. 833437-25-505, dated March 14, 1986, and 833509-25-508, dated June 15, 1986, describe how these fittings can be identified and list the seat assembly part numbers, seat assembly serial numbers, aircraft, and aircraft customer on which these seat track fittings were installed by Weber. Compliance required within 90 days after the effective date of this AD, unless previously accomplished. To eliminate aft seat track fittings from service which do not meet minimum airworthiness requirements and would not provide required seat restraint in the event of an emergency landing, accomplish the following:A. Replace the seat track fittings in accordance with Weber Aircraft Service Bulletins Nos. 833437-25-505, dated March 14, 1986, and 833509-25-508, dated June 15, 1986, or later FAA-approved revisions. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Weber Aircraft, 2820 Ontario Street, Burbank, California 91504. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Western Aircraft Certification Office at 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective April 6, 1987.
63-17-05: 63-17-05 PIPER: Amdt. 607 Part 507 Federal Register August 22, 1963. Applies to Model PA-25-235 Aircraft Serial Numbers 25-2000 through 25-2519 (Restricted and Normal Category). Compliance required as indicated. To preclude weld separations on the end of the landing gear shock strut assembly, Piper P/N 486604, which attaches to the landing gear vee assembly, accomplish the following: (a) Perform a daily inspection of the specified weld joints for cracks using dye penetrant or FAA approved equivalent methods until (b) is accomplished. Replace cracked landing gear shock struts before further flight. (b) Within 25 hours' time in service after the effective date of this AD, unless already accomplished, replace each landing gear shock strut assembly, Piper P/N 486604, with a new shock strut assembly having the same part number but identifiable by the coating of red oxide primer paint. (Piper Service Bulletin No. 217, dated July 11, 1963, covers this same subject.) This directive effective September 3, 1963.