Results
54-19-02: 54-19-02 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required before October 1, 1954. To insure against the loosening of the servo pilot valve locknut and subsequent improper servo operation, safety clips, Sikorsky P/N S-14-40-5194, should be installed and safetied to P/N S14-40-3227-24 lockwasher. (Sikorsky Service Information Circular 1440-458 covers this same subject.)
69-05-02: 69-05-02 FAIRCHILD: Amendment 39-729 as amended by Amendment 39-1588 is further amended by Amendment 39-2641. Applies to FH-227 Type Airplanes Certificated in all categories. Compliance required as indicated. To detect the development of cracks in the wing area, accomplish the following: (a) Within 25 hours time in service after the accumulation of the specified hours in service, unless already accomplished, inspect or continue to inspect in accordance with Fairchild Service Bulletin 51-1, as amended by Revision 6, of December 12, 1975 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or with an approved equivalent inspection. (b) Where a visual inspection may be accomplished in lieu of x-ray, at least a 10-power glass must be used. (c) For those aircraft incorporating Fairchild Service Bulletin 51-1, Appendix No. 1, dated January 5, 1973, or an approved equivalent special structural inspection and alteration, the inspection interval for the outer wing panel without cracks remains at 1200 hours. If any cracks were discovered prior to the alteration the inspection interval will be that specified in paragraph 1.D(1) of the Appendix. (d) If new cracks are found or if repaired cracks are found to be propagating, replace the cracked part with a part of the same part number or with an approved equivalent part, or incorporate an approved repair before further flight. However, upon request, with descriptive information of the crack and proposed operating limitations submitted through an FAA maintenance inspector, the flight of the airplane in accordance with FAR 21.197 to a base where the repair can be made, may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Equivalent inspection, repairs or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (f) Upon request, with substantiating data submittedthrough an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-729 was effective March 12, 1969. Amendment 39-1588 was effective January 31, 1973. This amendment 39-2641 is effective June 18, 1976. NOTE: Amendment 39-2641 was distributed on June 7, 1976, as AD 76-12-04. The issuing office intended Amendment 39-2641 to be published as a revision to AD 69-5-2. Accordingly, the AD is being republished to reflect the correct AD number and AD 76-12-04 is cancelled.
68-05-02: 68-05-02 BRANTLY: Amdt. 39-572. Applies to Models B-2, B-2A and B-2B series helicopters with serial numbers 4 through 482 inclusive and Brantly Model 305 helicopters with serial numbers 1002 through 1045 inclusive. Compliance required as indicated. To prevent failure of the tail rotor drive shaft, accomplish the following: (a) Within 10 hours' time in service after receipt of this Airworthiness Directive, unless already accomplished, inspect the tail rotor drive shaft for corrosion using a borescope and treat it with a corrosion preventive compound in accordance with Brantly Service Bulletin, SB No. B2B-68-2, dated February 24, 1968, or FAA-approved equivalent. After treatment, and before the tail rotor drive shaft plug is installed, reinspect the tail rotor drift shaft, using a borescope, to assure that the entire internal surface of the shaft is completely covered with the corrosion preventive compound. (b) If corrosion is found as a result of the inspection required by paragraph (a) of this Airworthiness Directive which cannot be removed or leaves pits visible without magnification, disregard the treatment required by paragraph (a) of this Airworthiness Directive and prior to further flight replace the tail rotor drive shaft with a replacement part which complies with Brantly Service Bulletin, SB No. B2B-68-2, dated February 24, 1968, or FAA-approved equivalent. This amendment becomes effective March 30, 1968
57-03-03: 57-03-03 DOUGLAS AND LOCKHEED: Applies to Lockheed Constellation Series and Douglas DC-7 Series Airplanes. \n\n\tCompliance required by April 1, 1957, for Constellation aircraft and by May 1, 1957, for DC-7 aircraft. \n\n\tUnder certain cold weather operating conditions the perforated paper covering around the Purolator micronic filter elements are subject to accumulation of ice as a result of entrained water crystals in the fuel freezing on this covering. This interferes with proper fuel filtering by causing the fuel to pass through the bypass valve in the filter unit. To make the micronic filter less susceptible to clogging by ice, the perforated paper covering around the filter element is to be removed. Removal of the perforated cover does not affect the filtering characteristics of the filter element. Filter elements without the paper covering are identified as Purolator P/N 30868-3.
67-23-04: 67-23-04 FAIRCHILD-HILLER: Amdt. 39-458, Part 39, Federal Register August 5, 1967. Applies to Model F-27J Airplanes, Serial Numbers 111, and 113 through 121, inclusive and FH-227 Series Airplanes, Serial Numbers 501 through 520, inclusive. Incorporating Solar Auxiliary Power Unit, Model T62T25. Compliance required within the next 400 hours' time in service after the effective date of this AD, unless already accomplished. To prevent electrical damage to the A.C. engine-driven generator resulting from an unregulated and unloaded condition when the APU-driven generator (A.C.) is switched on the line, accomplish the following: (a) Rewire the engine-driven A.C. generator control sensing circuit in accordance with Fairchild-Hiller F-27 Service Bulletin 30-12, Revision No. 1, dated September 15, 1966, for F-27J aircraft and Fairchild-Hiller FH-227 Service Bulletin 30-1 dated August 23, 1966, for FH-227 aircraft, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or perform an equivalent rewiring modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA maintenance inspector, an increase in the compliance time may be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective August 31, 1967.
55-15-04: 55-15-04 DOUGLAS: Applies to all DC-6 Series Airplanes Below fuselage No. 487 Equipped With Hamilton Standard Propellers. \n\n\tCompliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. \n\n\tTo increase the integrity of the propeller feathering system in the event of a powerplant fire, all existing propeller feathering lines located forward of the firewall must be replaced with lines and flexible hose assemblies which will meet current fireproof and fire resistant requirements. \n\n\t(a)\tReplace the existing flexible hose portion of the feathering line between the union on the forward pipe assembly and the elbow on the inner ring with a new hose assembly Aeroquip P/N 304004-10-17 1/2. Douglas General Service Letter DC-6 No. 206 dated August 26, 1954, covers this subject. Resistoflex SSFR-3800-10 hose assembly and Aeroquip 309009-10S hose assembly are also considered acceptable for this application. \n\n\t(b)\tThe existing flexible hose assembly connecting to the governor is not affected by this directive. \n\n\t(c)\tRemove the existing short 304 sleeves or flexible metal sleeve from the feathering pump supply line, Aeroquip P/N 304002-16D-12 3/8, and install a fireproof cover, Douglas P/N 3500614-1. Douglas General Service Letter DC-6 No. 206 dated August 26, 1954, covers this subject. Aeroquip 601000 hose assembly equipped with Aeroquip 304 full length protective sleeve or Aeroquip 680-16S hose assembly equipped with Aeroquip 304 short sleeves covering the end fittings are also considered acceptable for this application.
55-23-03: 55-23-03 LOCKHEED: Applies to Models 49, 149, 649, 749 and 1049 Aircraft, Serial Numbers 1963 Through 1980, 2021 Through 2088, 2503 Through 2590, 2610, 2611, and 2614 Through 2677, 4001 Through 4024, 4163 Through 4166, 4501 Through 4581, 4583 Through 4594, 4602 Through 4604, and 4613 Through 4615. Compliance required as indicated. 1. As soon as possible, but not later than next 250 hours conduct magnetic particle or magnaglow inspections on main landing gear downlock spring cylinder assembly rod end P/N 295168 for cracks in the threaded portion. If cracks are found replace the part immediately. Repeat inspection, magnetic particle or 20-power magnifying glass at 300-hour intervals until replacement in accordance with paragraph 2 is accomplished. 2. Replace downlock spring cylinder assembly P/N 270104 with new assembly P/N 475211 as soon as practical but not later than the next progressive or base overhaul period approximately 2,500 hours. Concurrently with this replacement, line ream the lugs on the downlock strut assembly to (0.3770 inch-0.3780 inch) diameter and replace the spacer P/N 268225-2 with bushing P/N LS3859-4-1094 and replace bolt AN 23-21 with AN 23-22 attaching the lower end of the spring cylinder assembly to the downlock strut. (Lockheed Service Bulletins 49/860 and 1049/2709 also cover this subject.)
71-05-03: 71-05-03 BEECH: Amendment 39-1159 as amended by Amendment 39-1222 is further amended by Amendment 39-1244. Applies to Models A60 (Serial Numbers P123, P127 through P167), and all 99 series airplanes (Serial Numbers U-1 through U-136) approved for flight into known icing conditions. Compliance: Required as indicated, unless already accomplished. To prevent operation under unsafe environmental conditions, accomplish the following: A) Effective immediately, operation of the airplane in known icing conditions is prohibited. B) Prior to further flight, modify the existing operating limitations placard located on the righthand side wall adjacent to the copilot oxygen outlet on Beech Model A60 airplanes and located on the overhead panel on all Beech 99 series airplanes to read as follows: THIS AIRPLANE IS NOT APPROVED FOR FLIGHT IN KNOWN ICING CONDITIONS. C) On Beech Models A60 airplanes, install either transducer unit, P/N 3E1793, P/N 190-1, or P/N 190-2 in accordance with Beech Service Instruction 0430-355, Rev. 1, or by the accomplishment of any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) On all Beech 99 series airplanes, install transducer unit P/N 795-1 in accordance with Beechcraft Service Instructions No. 0378-355, or by the accomplishment of any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. E) Upon accomplishment of the modifications provided in Paragraphs C or D, compliance with the provisions of Paragraphs A and B is no longer required. NOTE: The Airplane Flight Manuals and Type Certificate Data Sheets for these model airplanes will be amended to reflect these changes. Amendment 39-1159 became effective March 2, 1971. Amendment 39-1222 became effective June 3, 1971. This Amendment 39-1244 becomes effective July 16, 1971.
93-16-13: 93-16-13 AEROSTAR INTERNATIONAL, INC.: Amendment 39-8697. Docket No. 93-CE-44-AD. Applicability: Models RX-6, RX-7, RX-8, RXS-8, S-40A, S-49A, S-50A, S-52A, S-55A, S-57A, S-57S, S-60S, S-60A, S-66A, S-71A, S-77A, 78C, 90C, QUBE-80, CTS, W100LB, 110P, and SPII balloons (all serial numbers), certificated in any category, that are equipped with hoses identified with one of the following: o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 1Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 2Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 3Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 4Q92; or o If hose identification is not legible. Compliance: Required as indicated after receipt of this AD, unless already accomplished. To prevent an uncontained fire in the balloon basket caused by a leaking fuel hose, accomplish the following: (a) Prior to further flight, remove each fuel hose fromthe leather sleeve, and, at system pressure, sniff test the entire length of the hose for signs of leakage. These signs could include frosting or chilling. (1) If any sign of fuel leakage is found, prior to further flight, replace the entire fuel hose/manifold assembly with an approved assembly that includes hoses with markings different than that specified in the Applicability section of this AD. (2) If no sign of fuel leakage is found, perform this fuel leakage test prior to each flight thereafter until the replacement required by paragraph (b) of this AD is accomplished. (b) Within the next 10 hours time-in-service after the effective date of this AD, unless already accomplished in accordance with paragraph (a)(1) of this AD, replace the entire fuel hose/manifold assembly with an approved assembly that includes hoses with markings different than that specified in the Applicability section of this AD. (c) Replacing the entire fuel hose/manifold assembly as required by either paragraph (a)(1) or (b) of this AD eliminates the repetitive test requirement of this AD. NOTE 1: Aerostar Service Bulletin No. 132, dated August 12, 1993, references the actions required by this AD. For the sake of inclusiveness, the procedures presented in this service bulletin have been incorporated into this AD. (d) The test and fuel hose/manifold assembly replacement required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by Federal Aviation Regulations (FAR) 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may concur or comment and then send it to the Manager, Chicago Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago Aircraft Certification Office. (f) Replacement fuel hose/manifold assemblies and copies of the service bulletin referenced in NOTE 1 of this AD may be obtained from Aerostar International, Inc., 1812 E. Avenue, P.O. Box 5057, Sioux Falls, South Dakota 57117-5057. The service information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (g) This amendment becomes effective on October 15, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-16-13, issued August 18, 1993, which contained the requirements of this amendment.
95-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, -2A12, -2B16, and -2B19 series airplanes, that requires an inspection to verify the proper operation of the uplock latch of the air driven generator (ADG), and replacement of the uplock latch with a serviceable part, if necessary. This amendment also requires replacing the uplock assembly with a modified uplock assembly, and performing a rigging inspection. This amendment is prompted by a report indicating that, upon operation of the manual release system, the ADG did not deploy due to failure of the shaft pin. The actions specified by this AD are intended to prevent failure of the shaft pin, which could lead to the inability of the pilot to manually deploy the ADG when necessary (i.e., when an airplane's primary electrical power sources are lost and the ADG fails to deploy automatically).