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86-15-06: 86-15-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-5363. Applies to AMD Falcon 10 series airplanes, serial numbers 1 thru 196 inclusive, and 198 thru 201 inclusive, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To ensure the proper installation of the rudder servo actuator hydraulic lines, accomplish the following, unless already accomplished: A. Modify the rudder servo actuator system in accordance with AMD-BA Service Bulletin F10-27-028 (0237), dated June 24, 1983. B. 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. C. 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 bulletin from the manufacturer, may obtain copies upon request to the AMD-BA Representative, c/o F.J.C., Teterboro Airport, Teterboro, New Jersey 07608. 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, 39-5363, becomes effective August 25, 1986.
87-18-06 R1: 87-18-06 R1 BEECH: Amendment 39-5721 as amended by amendment 39-5837 applies to model and serial numbered airplanes listed below equipped with the optional hydrolock seat recline actuators on co-pilot and third and fourth seats, certificated in any category: MODEL SERIAL NUMBERS F33A CE-919, CE-923, CE-925, CE-927, CE-929, thru CE-1083 V35B D-10348, D-10353 thru D-10403 A36 E-1422, E-1551, E-1569, E-1581, E-1594 thru E-2327 A36TC and B36TC EA-21, EA-28, EA-33 thru EA-454 E55 TE-1152, TE-1181 thru TE-1201 58 and 58A TH-1027, TH-1062, TH-1067, TH-1080 thru TH-1507 58P and 58PA TJ-210, TJ-235 thru TJ-497 58TC and 58TCA TK-107, TK-108, TK-110 thru TK-151 Compliance: Required within the next 100 hours time-in-service or the next scheduled inspection, whichever occurs first after the effective date of this revised AD, unless already accomplished per the original issuance of this AD. To prevent the co-pilot and/or passenger chair armrest from coming in contact with the seat recline actuator handle and inadvertently releasing the locking feature on the seatback, accomplish the following: (a) Replace the seat recline actuator handle on the co-pilot's and the third and fourth passenger seats that are equipped with reclining backs, with a new P/N 102-530111-5 handle assembly in accordance with the instructions in Beech Service Bulletin No. 2175, revision dated June 1987. NOTE: The third and fourth passenger seats are the seats immediately behind the pilot's and co-pilot's seats. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085, or may examine these documents at the FAA, Office of the Regional Counsel, 601 East 12th Street, Room 1558, Kansas City, Missouri 64106. This amendment 39-5837 revises AD 87-18-06, Amendment 39-5721, effective October 9, 1987. This amendment 39-5837 becomes effective on February 5, 1988.
2013-21-08: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72-101, -201, - 102, -202, -211, -212, and -212A airplanes. This AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This AD requires installing a fuel quantity indicator (FQI) equipped with a locking adaptor on the electrical connector. We are issuing this AD to prevent an engine flame-out, which could result in reduced controllability of the airplane.
49-18-01: 49-18-01 CURTISS-WRIGHT Applies to all Models of C-46 Series airplanes used in passenger operation under provisions of Part 41, 42, or 61 of the Civil Air Regulations as specified in Sections 41.20 (f), 61.30 and Amendment 42-8. To be accomplished not later than the dates specified in above amendments as revised by Special Civil Air Regulation No. 329 and any subsequent regulations affecting these compliance dates. (This AD pertains only to combustion heater fire protection aspects of the above Regulation Amendments. Separate AD's will be issued covering fire protection for the powerplant installation and for the baggage and cargo compartments of the airplane). (1) Each heater exhaust pipe shall be completely enclosed with well-ventilated, fireproof shrouds. (2) Each heater combustion chamber shall be drained to the exterior of the airplane. All such drain lines shall be of fireproof construction and contain no traps in the normal flight or ground attitudes.(3) The heater fuel components presently mounted on top of each heater shall be located in fuel and fume proof enclosures, ventilated and drained to the exterior of the airplane. (4) The thermal overheat switches for each heater shall be rigged to shut off the fuel supply and ignition circuits of the heaters when overheating occurs. These switches must also be arranged so as to prevent their automatically recycling to "ON" once overheating has occurred. The present overheat switches are not intended to be used as cycling switches. In cycling to produce the required heat is necessary, it must be accomplished at a lower temperature by an additional cycling switch controlling a cycling solenoid. (5) A manual fuel shutoff valve shall be provided. (USAF Technical Order 01- 25LA-211 describes such an installation.) (6) Adequate fire extinguisher and fire detector installations shall be provided for each heater. The fire detector installation shall contain at least one detector centrally located over the heaters in the heater area and one detector in the ventilating air duct of each heater just aft of the combustion chamber. The fire extinguisher system should provide at least 1 pound of carbon dioxide for each heater directed into the inlet side of the ventilating air stream. Instructions for operating this carbon dioxide system should also require that the ventilating air duct valve be closed when carbon dioxide is injected to the heater. With the arrangement as described, no flight tests of carbon dioxide contamination of the pilots compartment or cabin area need be conducted. As outlined in the Airworthiness Directive concerning fire protection for the baggage and cargo compartments, however, flight tests to establish smoke evacuation procedures for the cargo compartments when these compartments are carrying cargo, will need to be accomplished. The results of these tests will determine the procedure to be followed to rid the airplane of noxious gases. (7) Revision pages for the Airplane Flight Manual must be prepared to cover emergency fire procedures as well as smoke and other noxious gas elimination procedures.
93-07-05: 93-07-05 AMI INDUSTRIES, INC.: Amendment 39-8537. Docket 92-NM-184-AD. Applicability: Pilot and Co-Pilot Seats, Model 1108, serial numbers 004 to 189, inclusive; as installed in, but not limited to de Havilland Model DHC-8 series airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the pilot's and co-pilot's lap belts during air turbulence, which could lead to reduced ability of the pilots to control the airplane, accomplish the following: (a) Within 60 days after the effective date of this AD, remove the lap belt attachment links and install the improved lap belt attachment link kit, P/N 1B9014-3R, in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 20, 1992. (b) 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, Seattle Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (c) 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. (d) The replacement shall be done in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 20, 1992. This incorporation by reference 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 AMI Industries, Inc., 1275 North Newport Road, Colorado Springs, Colorado 80916. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on May 10, 1993.
2022-14-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracked tailboom attachment bolts and barrel nuts. This AD requires replacing the upper left hand (LH) tailboom attachment bolt, visually inspecting the other three tailboom attachment bolts and all barrel nuts, repetitive torque checks of the tailboom attachment bolts, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
99-11-03: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA341G and SA342J helicopters. This action requires, before further flight, visually inspecting the external body of each main rotor head pitch-change rod (rod) for corrosion. If external corrosion is found, this action also requires a visual inspection of the inside of the body of that rod for corrosion. A rod with external corrosion that exceeds the repair criteria or a rod with any internal corrosion must be replaced with an airworthy rod. This amendment is prompted by the report of a deep internal corrosion fault in a rod found by a military helicopter operator performing a daily inspection. This condition, if not corrected, could result in failure of a rod and subsequent loss of control of the helicopter.
99-11-02: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney R-1340 series reciprocating engines, that requires initial and repetitive visual and fluorescent penetrant inspections of cylinders for head cracking. This amendment is prompted by reports of cylinder head cracking. The actions specified by this AD are intended to prevent cylinder head cracking, which can result in engine power loss, forced landing, and damage to the aircraft.
81-16-03: 81-16-03 DOWTY ROTOL LTD.: Amendment 39-4171. Applies to Dowty Rotol propellers Type R175/4-30-4/13E with hub and driving assembly, P/Ns 601022104 or 601022420 which do not have Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) incorporated, as installed on, but not limited to Fairchild F-27, F-27B, and Fokker F-27 Mks 100, 300 and 700 airplanes. Compliance is required as indicated, unless already accomplished To prevent propeller failure due to cracking of the propeller hub, accomplish the following repetitive actions until modified in accordance with paragraph (d) below: (a) Propeller hubs with less than 20,000 total hours time in service, inspect in accordance with paragraph (c) at next overhaul or prior to accumulating 22,000 total hours, whichever occurs first, and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on allof his propellers that exceed 20,000 total hours. (b) Propeller hubs with 20,000 or more total hours time in service, inspect as follows: (1) Hubs with more than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 600 additional operating hours after the effective date of this AD and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (2) Hubs with less than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 2000 hours since last inspection or overhaul and reinspect at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (c) Inspection Procedure: (1) During overhaul or propeller disassembly, crack test the hub front wall to snout radius in accordance with Part 2A of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found, replace the cracked hub with a hub known to be free of cracks. (2) For propellers between overhauls, remove, disassemble, inspect, reassemble and reinstall in accordance with Part 2B of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found during inspection, additional propeller disassembly is necessary to replace the cracked hub with a hub known to be free of cracks, and testing and rebalancing and resetting blade angles is necessary. (d) Terminating Action: The inspections required by this AD may be discontinued when propellers are modified by Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) dated July 1968 as revised by Revision 2 dated November 24, 1971, or FAA approved equivalent. Upon request of an operator, the Chief, Engineering and Manufacturing Branch, AGL- 210, Federal Aviation Administration, Great Lakes Region, may adjust the compliance time specified in paragraph (a) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. For purposes of this AD, an FAA approved equivalent must be approved by the Chief, Engineering and Manufacturing Branch, AGL-210, Federal Aviation Administration, Great Lakes Region. The manufacturer's specifications and procedures identified in the directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer may obtain copies upon request to Dowty Rotol, Inc., Staverton West, Sully Road, Box 5000, Sterling, VA 22170 or Dowty Rotol, Ltd., Cheltenham Road, Gloucester, England GL2 9QH. These documents may also be examined at the Great Lakes Region, FAA, 2300 East Devon Avenue Des Plaines, Illinois 60018. This amendment becomes effective July 28, 1981.
74-07-01: 74-07-01 BELL: Amendment 39-1801 as amended by Amendment 39-1864. Applies to all cyclic and collective main rotor control tube assemblies installed within a 30 degree angle of the vertical axis on Model 47 series helicopters, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this A.D., unless already accomplished, and thereafter at intervals not to exceed 1200 hours time in service from the last inspection. To detect corrosion and prevent possible failure of the control tube assemblies, accomplish the following inspection. (a) Remove the control tube assemblies from the helicopter and remove the rod end bearing and insert or clevis at each end of the tube assembly and clean the inside of the tube. (b) Inspect each control tube for internal corrosion using a light and borescope or equivalent inspection means. (c) Remove corroded control tubes from service prior to further flight, exceptas specified by paragraph (g) of this A.D. and submit a report of finding a corroded tube to Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA, P.O. Box 1689, Fort Worth, Texas, 76101. The control tube assembly part number, degree of corrosion found and total time in service should be included in the report. FAA Form 8330-2 may be used for this report. (Reporting approved by the Bureau of the Budget under BOB No. 04- R0174.) (d) Reinstall serviceable rod end bearings and inserts or clevis in the uncorroded and serviceable tubes using acceptable techniques, methods and practices as specified below. (1) Tubes with double drilled rivet holes, sharp nicks or scratches and internal corrosion are considered unserviceable. (2) Tubes must have internal corrosion protection using zinc chromate primer, hot linseed oil or other equivalent corrosion inhibitor. The tube ends must be sealed, air and water tight, as specified in Paragraphs 4 and 5, Part II, Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated December 6, 1973 or later approved revision or as specified in an equivalent FAA approved procedure when the insert, rod end bearing or clevis and rivets are installed. (e) Install control tube assemblies on the helicopter and check the controls rigging and check tracking of the main rotor blades in accordance with pertinent Model 47 maintenance and overhaul information manual. (f) The manufacturer's specifications and procedures identified and described in this directive are 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 these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated 12-11-73 pertains to this subject.) (g) Tubes with light corrosion over less than twenty-five percent of the area in any one-half inch length of the tube may be returned to service provided the tube is assembled and protected as noted in paragraph (d) of this A.D. and the tube is removed from service prior to accumulating 200 hours time in service after the initial inspection prescribed by this A.D. was conducted. NOTE: Advisory Circular No. 43-4, page 47 defines light corrosion. Amendment 39-1801 became effective April 22, 1974. This Amendment 39-1864 becomes effective May 30, 1974.