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61-19-01: 61-19-01\tBOEING: Amdt. 332 Part 507 Federal Register September 14, 1961. Applies to All Model 720 Series Aircraft Which Have Not Previously Been Modified By Installation of Micro P/N 5EN11-6B. \n\n\tCompliance required as indicated. \n\n\tFaults occurring in the fuel dump chute safety switch of the retractable dump chute system have caused burning of the lead wires at the switch and, in one case, caused a fuel dump valve to cycle open and close allowing fuel to enter the fuel dump manifold and leak out through the dump chute secondary seal. To prevent this, the following inspection and modification shall be accomplished: \n\n\t(a)\tCommencing within 10 days after the effective date of this AD unless the lead wire insulation has been reinforced by wrapping with suitable electrical tape at the switch, conduct daily inspections of the fuel dump chute safety switch (Micro P/N 5EN11-6) to determine if the wires are burned or charred where they protrude. If wires are found burned or charred,prior to further flight replace safety switch with improved type Micro P/N 5EN11-6B, after which the daily inspection can be discontinued.\n \n\t(b)\tUnless already accomplished in accordance with paragraph (a), within the next 350 hours' time in service after the effective date of this AD, replace fuel dump valve safety switches Micro P/N 5EN11-6 with switch Micro P/N 5EN11-6B, using standard Boeing Maintenance Manual procedures. Upon installation of switch Micro P/N 5EN11-6B the daily inspection required by (a) can be discontinued. \n\n\t(c)\tUpon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. \n\n\t(Boeing Service Bulletin No. 1305, dated May 22, 1961, covers thismodification.) \n\n\tThis directive effective September 14, 1961.
2017-09-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD requires a detailed inspection of the circuit breakers, replacement of damaged circuit breakers, and installation of a circuit breaker bushing assembly. This AD was prompted by a report of cracks found in the plastic casing of cockpit circuit breaker panels. We are issuing this AD to address the unsafe condition on these products.
86-06-03 R1: 86-06-03 R1 SAAB-FAIRCHILD: Amendment 39-5258 as amended by amendment 39-5917. Applies to Model SF-340A series airplanes, serial numbers 003 through 048, inclusive, certificated in any category. Compliance is required as indicated below, unless previously accomplished. To prevent uncommanded pitch excursions, accomplish the following: 1. Within the next 7 days after the effective date of this AD, incorporate the following into the limitations section of the airplane flight manual: "More than 20 degrees flap is not authorized at any time." This may be accomplished by including a copy of this AD in the airplane flight manual. 2. Within the next 21 days after the effective date of this AD, install a mechanical stop on the flap handle to limit the flap extension to a maximum setting of 20 degrees, in accordance with SAAB-Fairchild Service Bulletin SF340- 27-036, dated February 13, 1986. 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 the inspections and/or modifications required by this AD. 4. Alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. 5. Installation of Modification 1784 in accordance with SAAB Service Bulletin SF340-27-049, Revision 1, dated July 21, 1987, and Modification 1462 in accordance with SAAB Service Bulletin SF340-55-008, Revision 2, dated March 31, 1988, constitutes terminating action for the requirements of paragraphs 1. and 2., above. 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-Scania, 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 39-5917 amends AD 86-06-03, Amendment 39-5258. This amendment 39-5917 becomes effective June 17, 1988.
2017-08-05: We are superseding Airworthiness Directive (AD) 2016-13-05 for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90- 90B, and GE90-94B turbofan engines. AD 2016-13-05 required eddy current inspection (ECI) of the high-pressure compressor (HPC) stage 8-10 spool at each shop visit for all affected engines and ECI or ultrasonic inspection (USI) for certain affected engines. This new AD requires initial and repetitive on-wing USIs of the HPC stage 8-10 spool for certain engines prior to shop visit and ECI of all affected engines at each shop visit. This AD was prompted by analysis that the risk of the failure of an HPC stage 8-10 spool was excessive without repetitive USI prior to shop visit. We are issuing this AD to correct the unsafe condition on these products.
84-26-02: 84-26-02 INDUCTION AIR FILTERS: Amendment 39-4966. Applies to all paper induction air filters used in small airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible engine power loss or stoppage caused by engine ingestion of fragments of a deteriorated induction air filter, accomplish the following: Within the next one hundred hours time-in-service after the effective date of this AD or prior to the accumulation of 500 hours time-in-service on the filter, whichever occurs later, and thereafter at intervals not exceeding 500 hours time-in-service on the filter: (a) Replace the air filter with a new filter that is FAA approved for the airplane installation. (b) Within 100 hours time-in-service replace any filter on which the time-in-service cannot be determined utilizing the airplane maintenance records for this determination. NOTE: This AD does not alter current maintenance procedures which require inspection of paper induction air filters at 100 hours time-in-service and annual inspections and replacement as necessary based on filter condition. This amendment becomes effective January 29, 1985.
64-04-06: 64-04-06 PRATT READ: Amdt. 685 Part 507 Federal Register February 12, 1964. Applies to All Model PR-G1 Gliders. Compliance required as indicated. Due to a deteriorating condition of the wood structure supporting the aft elevator bellcrank, resulting in loss of elevator control, accomplish the following within 25 hours' time in service after the effective date of this AD unless already accomplished within the last 75 hours' time in service, and at intervals thereafter not to exceed 100 hours' time in service from the last inspection, or one year, whichever occurs first. (a) Remove the stabilizer and elevators and any other obstructing structure necessary to gain access to the aft internal fuselage area (tail cone section). (b) With the use of a light and mirror, visually inspect for deterioration both the front and rear side of the wood bulkhead in the vicinity of its support of the aft elevator bellcrank. (c) If indications of deterioration of the wood structureare found, repair that bulkhead in accordance with an FAA approved repair before further flight, or replace with a part having the same part number, or an FAA approved equivalent before further flight. NOTE: After installation of a new or repaired bulkhead, it should be ascertained that the elevator is functioning properly throughout the entire range. This directive effective March 13, 1964.
2017-07-01: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LLC Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227- AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by detachment of the power lever linkage to the TPE331 engine propeller pitch control. This AD requires repetitively inspecting the propeller pitch control for proper torque, with corrections as necessary until required replacement or rework of the PPC assembly to have a threaded hole in the splined end of the shouldered shaft and installation of a secondary retention device is done. We are issuing this AD to correct the unsafe condition on these products.
61-18-02: 61-18-02 BRANTLY: Amdt. 327 Part 507 Federal Register August 24, 1961. Applies to All Model B-2 Helicopters prior to Serial No. 112. Compliance required within the next 25 hours' time in service after effective date of this directive unless already accomplished. Investigation of a recent Model B-2 helicopter accident indicated evidence of limited tail rotor control. Accordingly, in order to provide directional control over a wider main rotor r.p.m. range, the following modification and rerigging of the tail rotor is required: (a) Modify the rudder control arm P/N B2-284-1 as follows. (1) Disconnect the vertical rudder rod P/N B2-251-5 at its top end by removing the AN 3-10A bolt. (2) Drill a 1/16-inch diameter hole and then enlarge to 0.187-inch diameter 1/2 inch inboard (center to center) from the existing hole in the rudder control arm P/N B2-284-1. Deburr edges. (3) Cut off the end of the rudder control arm P/N B2-284-1 with the old 0.187-inch hole 0.344-inch outboard from the centerline of the new 0.187-inch hole (0.250-inch edge distance from new hole) and perpendicular to the longitudinal axes of the rudder control arm. Break all sharp edges. (4) Rerig the tail rotor in accordance with the manufacturer's instructions, Service Bulletin No. 15. (Brantly Service Bulletin No. 15 dated June 23, 1961, covers this subject.) This directive effective August 29, 1961.
83-25-01: 83-25-01 SHORT BROTHERS LIMITED: Amendment 39-4783. Applies to all Models of the SD3-30 airplane, certificated in all categories, with the serial numbers specified below. To prevent a potential fuel fire hazard, accomplish the following within the next 60 days after the effective date of this AD, unless already accomplished. A. For aircraft serial numbers SH3002 to SH3091 inclusive, modify the fuel vapor exhaust ducting in accordance with paragraph 2, Accomplishment Instructions, of Shorts Service Bulletin No. SD3-53-47, Revision 3, dated June 23, 1983. B. For aircraft serial numbers SH3002 to SH3089 inclusive, replace the existing flexible vapor proof shrouds covering fuel lines in the passenger compartment in accordance with paragraph 2, Accomplishment Instructions of Shorts Service Bulletin No. SD3-28-17, Revision 2, dated June 23, 1983. NOTE: The actions of paragraph A., above, must be accomplished before performing the requirements of paragraph B. C. For aircraft with serial numbers specified in paragraph 1, Planning Information, of Shorts Service Bulletin No. SD3-28-16, Revision 3, dated June 23, 1983, inspect, replace components if necessary, and pressure check the fuel lines as required in accordance with paragraph 2, Accomplishment Instructions, of the service bulletin. NOTE: The actions of paragraphs A. and B., above, must be accomplished before performing the requirements of paragraph C. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle 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 airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. F. This AD supersedes Amendment 39-4677 (48 FR 31631, July 11, 1983), AD 83- 13-07. This amendment becomes effective January 8, 1984.
2017-05-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.