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66-08-01: 66-08-01 AIR and SPACE: Amdt. 39-218 Part 39 Federal Register March 23, 1966. Applies to Model 18A Gyroplanes, Serial Numbers 18-6 through 18-49. Compliance required before further flight, unless already accomplished. Modify gyroplanes in accordance with Air & Space Manufacturing Inc. Service Bulletin No. 4, dated November 16, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. This directive effective March 23, 1966.
47-06-11: 47-06-11 CESSNA: (Was Service Note 1 of AD-768-4.) Applies Only to 120 and 140 Aircraft Serial Numbers 8001 to 8799, Inclusive. Compliance required at next periodic inspection and upon each 100 hours of operation thereafter until revised door posts are installed. Inspect the forward doorposts for cracks, particularly the flange section leading from the post to the instrument panel at the base of the windshield and the post itself below the rivet cluster at the top. All inside fairing attached to the post between the top and the floor should be removed to permit a thorough inspection. Cracks in the above-mentioned flange not over 3/4 inch in length may be repaired by stop-drilling. If there are longer cracks in the flange or any cracks in the doorpost structure itself, the doorpost should be replaced with the later type post, Cessna P/N 0411867-2 and 0411867-3, in accordance with installation instructions supplied by Cessna. (Cessna Service Letter No. 20 dated October 8, 1946, covers this same subject.)
2005-20-25: The FAA adopts a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 airplanes equipped with certain avionics bus circuit breaker switches. This AD requires you to inspect the avionics bus circuit breaker switch to determine the date code and replace any without a date code. This AD also imposes a 1,000-hour safe life limit on avionics bus circuit breaker switches with a date code earlier than 0434. This AD results from reports of smoke and a burning smell in the cockpit. We are issuing this AD to prevent failure of the avionics bus circuit breaker switch, which could result in smoke and a burning smell in the cockpit. This failure could lead to reduced ability to control the airplane.
2005-20-02: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes, and all Boeing Model 720 and 720B series airplanes. This AD requires revising the Limitations section of the airplane flight manual (AFM). The AFM revisions include instructions for monitoring the low pressure lights for the center tank fuel pumps, and a statement prohibiting the resetting of a tripped circuit breaker for a fuel pump in any tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent dry operation of the fuel pumps in the center fuel tank, which could result in high temperatures or sparks inside the fuel tank, ignition of fuel vapors, and consequent fire or explosion. We are also issuing this AD to prohibit the resetting of a tripped circuit breaker for a fuel pump in any tank, which could allow an electrical fault to override the protective features of the circuit breaker, and result in sparks inside the fuel tank, ignition of fuel vapors, and consequent fire or explosion.
2018-16-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319 and A320 series airplanes; and A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of battery retaining rod failures due to quality defects of the material used during parts manufacturing. This AD requires a detailed inspection of the battery support assemblies to identify the battery retaining rod manufacturer, replacement of the battery retaining rods with serviceable battery retaining rods if necessary, and the addition of the applicable service information label on each battery retaining rod if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-16-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, -100B, -100B SUD, -200B, -200C, - 200F, -300, -400, -400D, 747SP, and 747SR, and 747-8 series airplanes. This AD was prompted by reports indicating that additional areas of Boeing Material Specification (BMS) 8-39 flexible urethane foam were found during an inspection required by a related AD. This AD requires inspecting for BMS 8-39 flexible urethane foam insulation in the floor panel assemblies and the power drive unit (PDU) cover assemblies, doing applicable on-condition actions, modifying certain dripshields, and replacing BMS 8-39 foam strips on certain dripshields with BMS 8-371 foam strips. We are issuing this AD to address the unsafe condition on these products.
87-04-17: 87-04-17 MCDONNELL DOUGLAS: Amendment 39-5545. Applies to McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10A (Military) series airplanes, certificated in any category. To prevent loss of fuel shutoff and fire extinguishing capabilities, accomplish the following within the next eighteen (18) months after the effective date of this AD, unless already accomplished: \n\n\tA.\tModify and reidentify engine No. 2 aft fuselage mounted fuel fire shutoff valve in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10/KC-10A Service Bulletin 28-168, dated April 16, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tModify, reidentify, and rotate engine No. 1 and engine No. 2 wing spar mounted fuel fire shutoff valves, and modify and reidentify engine No. 3 wing spar mounted fuel fire shutoff valves, in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 ServiceBulletin 28-55, Revision 3, dated December 19, 1980, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tAn alternate means of compliance with this AD which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base for accomplishment of the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, orthe Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis supersedes AD 86-09-10, Amendment 39-5305, and AD 86-16-08, Amendment 39-5375. \n\n\tThis Amendment, 39-5545, becomes effective March 13, 1987.
46-06-03: 46-06-03 KINNER: (Was Mandatory Note 5 of AD-707-2: 9 of AD-749-1: Special Note 12 of AM-231 and 4 of AD-336.) Applies Only to Fairchild 24J, 24JS, and 24W Series, Jobmaster DGA-18K, Meyers OTW-160, and Ryan ST-3KR Airplanes Having R-5 Series 2 (Military R-540-2) Engines, R-55 (R-540-1) Engines of the Following R-56 (R-540-3) Engines: 12005 to 12319 Inclusive; 12805 to 12846 Inclusive; 12938 to 12948 Inclusive; 12950 to 12952 Inclusive; 12954 to 12961 Inclusive; 12963 to 12973 Inclusive; 12975 to 12976 Inclusive; 13034 to 13037 Inclusive; and 13040 to 13056 Inclusive. Rework required immediately, if total engine time has already exceeded 500 hours, or if not, rework must be accomplished before exceeding 500 hours. Grind the master rod knuckle pinholes to a fit of 0.0003 to 0.0008-inch (tight) with the knuckle pins. This will necessitate reboring the connecting rod bushings, replacement of the knuckle pins and wrist pin bushings. The letter "O" preceding the engine serial number will indicate that this rework has already been accomplished. (Kinner Service Bulletins Nos. KCE-33 and KCE-4 cover this same subject.)
66-02-03: 66-02-03 de HAVILLAND: Amdt. 39-177, Part 39, Federal Register January 6, 1966. Applies to All Model 104 Dove Airplanes with Serial Numbers through 04504. Compliance required as indicated. To prevent further cracking of pistons P/N AHO.19742, installed in Dunlop pneumatic retraction jacks (cylinders) P/N AH.8463 and P/N AC.11130, fitted to the main and nose landing gear assemblies accomplish the following: (a) Unless already accomplished, replace piston P/N AHO.19742 in the pneumatic retraction jacks P/N AH.8463 and P/N AC.11130 on all airplanes that have accumulated 10,000 hours' time in service and thereafter at intervals not to exceed 10,000 hours' time in service. (b) Replacement of the pistons required in (a) may be discontinued after installation of de Havilland Modification No. 1144 which provides jacks with pistons that have an increased service life. (de Havilland Service Technical News Sheet TMS Series C.T. (104 Issue 2 dated July 11, 1960, covers this subject.) This supersedes AD 57-20-02. This directive effective February 5, 1966.
87-21-09: 87-21-09 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 5747. Applies to all Model AS 332C and L helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loss of the AC electrical generation system, accomplish the following: (a) Within the next 50 hours' time in service or the next 30 days after the effective date of this AD, inspect the electrical cable bundles connecting each AC generator to its regulating card in accordance with the instructions given in paragraph BBA of Aerospatiale Telex Service No. 05.12, transmitted by Aerospatiale Telex No. 10084, dated January 16, 1987. (b) The aircraft can be returned to operational service if the insulation values measured are greater than 2 megohms. (c) If the insulation values measured are less than 2 megohms, the installation is to be modified in accordance with the instructions given in Aerospatiale AS 332 Service Bulletin No. 24.10,paragraph 2, "Accomplishment Instructions." (d) Within 400 hours' time in service following the inspection or before December 31, 1987, whichever occurs first, modify the aircraft in accordance with the instructions given in AS 332 Service Bulletin No. 24.10, paragraph 2, "Accomplishment Instructions." (e) An alternate means of compliance which provides an equivalent level of safety may be used if approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, Fort Worth, Texas 76193-0100. This amendment becomes effective November 12, 1987.