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58-18-01: 58-18-01 HAMILTON STANDARD: Applies to All Hamilton Standard Propellers Controlled by 5U18 Governors and Installed on TC18DA and TC18EA Series Engines. Compliance required at first governor overhaul after December 1, 1958, but not later than June 1, 1959. Adverse environmental conditions in the propeller governor resulting from certain types of engine failure have caused improper operation of the governor in such a manner as to result in propeller overspeeding, failure to feather and reversing when feathering was initiated. In order to minimize the possibility of such occurrences, provide a means for feathering that will be independent of the low pressure relief and pilot valves incorporated in the 5U18 governors. Installation of the Deterjet Model DJ-1025 governor bypass valve or replacement of the 5U18 governor by the Hamilton Standard 5AA22 governor are considered acceptable means to accomplish the desired objective. (installation of Deterjet Model DJ-1025 on Douglas DC-7C approved under Supplemental Type Certificate SA4-507.) (Deterjet Service Bulletin No.1 and Hamilton Standard Bulletin No. 561 cover this same subject.)
73-26-10: 73-26-10 GENERAL DYNAMICS: Amdt. 39-1765. Applies to all Models 22, 22M, and 30A airplanes certificated in all categories incorporating Hamilton Standard Electric Freon Packs Part Numbers 574056 or 573970 (Model 22), P/N 573971 (Model 22M), P/N 574057 (Model 30A). Compliance required as indicated. To prevent partial or total loss of generator power due to electric freon pack compressor motor failure, accomplish the following: (a) Model 22 airplanes. Within 50 hours' time in service after the effective date of this AD, unless already accomplished, replace the freon pack fuses with LPN 110 fuses, per paragraph 2B., Accomplishment Instructions, General Dynamics Service Bulletin 880 S.B. No. 24-56, dated November 21, 1973, or later FAA-approved revisions. Airplanes with existing fuses rated at 110 amperes or less need not accomplish the foregoing installation. (b) Models 22, 22M and 30A airplanes. Within 300 hours' time in service after the effective dateof this AD, unless already accomplished, modify the freon pack compressor motor protectors, P/N 573667, per paragraph 2A., Accomplishment Instructions General Dynamics Service Bulletins 880 S.B. No. 24-56, dated November 21, 1973 (for Model 22), 880M S.B. No. 24-15, dated November 21, 1973 (for Model 22M), and 990 S.B. No. 24-16, dated November 21, 1973, (for Model 30A), or later FAA- approved revisions to the bulletins. (c) Equivalent installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. (d) Airplanes may be operated to a maintenance base under special flight permits per Sections 21.197 and 21.199 of the Federal Aviation Regulations for the purpose of accomplishing this AD. This amendment becomes effective February 1, 1974.
75-13-02: 75-13-02 BEECH: Amendment 39-2239. Applies to Models 95, B95, B95A, D95A, E95 (Serial Numbers TD-2 through TD-721) airplanes. Compliance: Required as indicated, unless already accomplished. To reduce the possibility of operations that may impose excessive propeller blade vibration stresses, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A) Install a Beech P/N 95-324079-1 operational limitation placard adjacent to the manifold pressure indicator which reads: "DO NOT EXCEED 23" HG M.P. BELOW 2300 RPM" and install a corresponding Beech P/N 95-590014-69 flight manual supplement in the airplane flight manual and operate the aircraft in accordance with this limitation. B) Remove, functionally test, and calibrate the tachometer(s) to obtain an accuracy of + or - 25 rpm at 2300 rpm and 2700 rpm. C) Remove, functionally test, and calibrate the manifold pressure indicator(s) to obtain an accuracyof + or - .4 inch Hg at 2300 inches Hg manifold pressure. D) Replace any instruments not meeting the tolerances specified in Paragraphs B and C above with instruments that meet those tolerances. E) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. NOTE: The FAA asks that an M or D Report be filed stating the amount and direction of any error on any tachometer or manifold pressure indicator not meeting the specified tolerances at the initial check. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174.) Beechcraft Service Instruction No. 0723-241 and Hartzell Propeller Service Bulletin No. 107A dated January 27, 1975, refer to this subject. This amendment becomes effective June 23, 1975.
75-04-03: 75-04-03 MCDONNELL DOUGLAS: Amendment 39-2085. Applies to Douglas Model DC-10-10, -30, and -40 Series airplanes, certificated in all categories. \n\n\tCompliance required as follows unless already accomplished. \n\n\tTo improve cabin oxygen mask deployment reliability, accomplish the following: \n\n\tA.\tWithin the next 300 hours' additional time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service: \n\n\t\t1.\tConduct an oxygen mask functional (drop) test, by cabin or by each section, in accordance with Paragraph IX of Douglas All Operators Letter No. 10-742, dated December 13, 1974, or 10-742A, dated January 24, 1975, or later FAA-approved revisions. \n\n\t\t2.\tOxygen compartments that fail to open must be inspected and modified in accordance with all of the applicable provisions of Douglas All Operators Letter No. 10-742, dated December 13, 1974, or 10-742A, dated January 24, 1975, or later FAA-approved revisions. \n\n\t\t3.Repeat the oxygen mask functional test until 100% mask drops are achieved by cabin or by each section. \n\n\tB.\tWithin the next 1500 hours' additional time in service after the effective date of this AD: \n\n\t\t1.\tModify partition oxygen compartment doors to insure 180 degrees opening in accordance with Douglas Service Bulletin No. 25-163, dated June 11, 1974, or later FAA-approved revisions. \n\n\t\t2.\tInstall pictorial warning placards on oxygen generator heat shields in accordance with Douglas Service Bulletin No. 35-12, dated April 26, 1974, or later FAA-approved revisions. \n\n\t\t3.\tModify oxygen compartments in passenger seat backs and partitions in accordance with Douglas Service Bulletin No. 35-16, dated August 19, 1974, or later FAA-approved revisions. \n\n\t\t4.\t(a)\tInspect and modify the cabin oxygen system, as applicable, in accordance with Douglas All Operators Letter No. 10-742, dated December 13, 1974, or 10-742A, dated January 24, 1975, or later FAA-approved revisions.(b)\tRepeat the oxygen mask functional test until 100% mask drops are achieved by cabin or by each section. \n\n\tC.\tResults of the functional tests required in paragraphs A. and B. must be forwarded within 30 days in a written report to the Chief, Aircraft Engineering Division, FAA Western Region. Recording approved by the Bureau of the Budget under Order BOB No. 04-R0174. \n\n\tD.\tThe Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspections and modifications upon submittal of substantiating data. \n\n\tE.\tAircraft may be flown to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199. \n\n\tThis amendment becomes effective February 14, 1975.
74-13-09: 74-13-09 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-1882 is further amended by Amendment 39-1903. Applies to Model TFE731-2-1C, and -2-2B engines installed in, but not limited to AMD Falcon 10 aircraft, certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished, and prior to installing replacement fuel pump assemblies. To detect the improper configuration of the fuel pump, accomplish the following: (a) Inspect the fuel pump assembly in accordance with the instructions contained in AiResearch Service Bulletin TFE731-73-3004, dated June 14, 1974, or later FAA-approved revisions. (b) The inspection prescribed in paragraph (a), above, need not be accomplished prior to the installation of replacement fuel pumps identified as P/N 3070851-7 and -8, or later dash number designations. (c) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (d) Aircraft may be flown to a base for performance of maintenance required by this AD per FAR's 21.197 and 21.199. Amendment 39-1882 became effective June 28, 1974. This Amendment, 39-1903 becomes effective July 31, 1974.
75-09-16: 75-09-16 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2192. Applies to Lockheed-California Company Model L-1011-385-1 series airplanes certificated in all categories with hydraulic dampers identified by Part Number 672470-101, -103, -105. To prevent occurrence of dangerous flutter which could result in damage or loss of elevators, outboard ailerons and rudder control surfaces, and/or the associated lifting surface accomplish the following: (a) Within 300 flight hours of the effective date of this AD unless previously accomplished within 200 hours flight time prior to the effective date of this AD, and at intervals not to exceed 500 flight hours thereafter, accomplish the inspections, servicing and replacement of dampers if required, on the elevators of aircraft with Serial Number 193X-1102 and subsequent, per Lockheed Alert Service Bulletin 093-27-A126, dated March 28, 1975 or later FAA-approved revisions. (b) Within 500 flight hours of the effective date of this AD, and at intervals not to exceed 500 flight hours thereafter, accomplish the inspections, servicing and replacement of dampers as required on the outboard ailerons per Lockheed Alert Service Bulletin 093-27-A126, dated March 28, 1975, or later FAA-approved revisions. (c) Within 1500 flight hours after the effective date of this AD, and at intervals not to exceed 1500 flight hours thereafter, accomplish the inspections, servicing and replacement of dampers as required on the rudder per Lockheed Alert Service Bulletin 093-27-A126, dated March 28, 1975, or later FAA-approved revisions. (d) If damper replacement is required per instructions of above Lockheed Alert Service Bulletin 093-27-A126, dated March 28, 1975, or later FAA-approved revisions, replace the damper with (-105) damper configuration only, as defined in the Lockheed Service Bulletin 093-27-088, Revision No. 1 dated February 28, 1974, or later FAA-approved revisions. (e) Equivalent inspections and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Airplanes may be flown to a base for the accomplishment of the inspections required by the AD, per FAR's 21.197 and 21.199. This amendment becomes effective May 2, 1975.
71-23-02: 71-23-02 GRUMMAN: Amdt. 39-1328. Applies to all Model G-159 airplanes. Compliance required as indicated. To detect cracking in the wing to fuselage attachment fittings at butt line 9 of Grumman Model G-159 airplanes, accomplish the following: a. Within six months time in service after the effective date of this AD, unless already accomplished, inspect the wing to fuselage attachment fittings, P/Ns 159WM10064 and 159WM10065 (P/N 159WM10223 assembly), and P/N 159WM10045 at butt line 9 left and right, wing front beam for cracks, deformation, gaps or improper shimming in accordance with Grumman Gulfstream I Aircraft Service Change No. 190, dated June 28, 1971, or later FAA approved revision or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. b. If cracks, deformation, gaps or improper shimming are found when conducting the inspection required by paragraph a., within 100 hours time in service after detection correct in accordance with Aircraft Service Change 190 or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. c. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the inspection time to coincide with inspections for wing corrosion required by AD 67-04- 01. This amendment becomes effective November 26, 1971.
70-17-06: 70-17-06 MORANE SAULNIER: Amdt. 39-1068. Applies to Models MS. 880B, MS. 885, and MS. 894A airplanes. To prevent the possibility of flames or harmful gases passing into the cabin from the engine compartment, within the next 100 hours' time in service after the effective date of this AD, unless already accomplished, replace the existing firewall sealant with "STABOND HT-4", Specification LAC-40-475 fire-resistant sealant manufactured by American Latex Product Corporation, or other FAA-approved fire-resistant sealant. This amendment becomes effective September 12, 1970.
75-03-07: 75-03-07 LOCKHEED: Amendment 39-2081. Applies to Model L-1011-385-1 airplanes certificated in all categories. Compliance required as indicated. To prevent possible malfunctions resulting in unuseable passenger evacuation slides and slide/rafts and improve the overall reliability of the passenger evacuation system, accomplish the following: (a) Within the next 30 days' calendar time after the effective date of this AD, unless already accomplished, rework the escape slides and slide/raft primary valise release cables and inspect slide/raft packs for steel reenforcing plate delamination in accordance with Lockheed Service Bulletin 093-25-206, dated January 10, 1975, or later FAA-approved revisions, or equivalent inspections and/or modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Within the next 180 days' calendar time after the effective date of this AD, unless already accomplished, replace escape slide release pin assemblies in accordance with Air Cruisers Service Bulletin 25-16, dated March 22, 1974, or later FAA-approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Within the next 180 days' calendar time after the effective date of this AD, unless already accomplished, inspect for proper escape slide girt extension and pack height in accordance with Lockheed Service Bulletin 093-25-205, dated January 10, 1975, or later FAA-approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Within the next 180 days' calendar time after the effective date of this AD, unless already accomplished, install heat shrinkable tubing on escape slide and slide/raft release pin assemblies in accordance with Lockheed Service Bulletin 093-25-212, dated January 10, 1975, or later FAA-approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division,FAA Western Region. (e) This paragraph is superseded by AD 76-01-07, paragraph (d). (f) Aircraft may be flown to a base for performance of the maintenance required per this AD in accordance with FAR's 21.197 and 21.199. This amendment becomes effective March 5, 1975.
76-05-04: 76-05-04 BEECH: Amendment 39-2536 as amended by Amendment 39-2662. Applies to Models 35, 35R, A35 and B35 (Serial Numbers D-1 thru D-2680) and Pine Air Model Super-V (Serial Numbers SV-XXX-D-1 thru SV-XXX-D-2680) airplanes, having 1,000 or more hours' time in service. Compliance required as indicated, unless already accomplished per AD 75-20-04. To prevent possible stabilizer loss or failure, on those airplanes having the P/N 35- 405130 stabilizer attach fitting, within 50 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours' time in service, accomplish the following in accordance with Beechcraft Service Instructions 0729-130, Rev. I or later FAA-approved revisions: A) Remove stabilizer attach bolts, plates and other components necessary to provide access to the stabilizer attach fitting and then remove said fitting. B) Inspect the stabilizer attach fitting by visual and dye penetrant methods in accordance with the procedures specified in FAA Advisory Circular (AC) 43.13-1A. C) If as a result of any inspection required herein, a stabilizer attach fitting is found cracked, prior to further flight, replace it with a new or airworthy P/N 35-405130, P/N 35- 650044-1 or P/N 35-405130-3 stabilizer attach fitting. D) When P/N 35-650044-1 or P/N 35-405130-3 stabilizer attach fitting has been installed the requirements of this AD no longer apply. E) If a crack is found as a result of any inspection required herein, provide the FAA with written notification thereof utilizing Malfunction and Defect Report (FAA Form 8330-2) stating the location and length of any crack discovered and the total operating time of the airplane or part of the time of discovery. (Reporting approved by the Office of Management and Budget under ONB No. 04-R0174.) F) Aircraft may be flown in accordance with FAR 21.197 to a base where the repair can be performed. G) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-2536 supersedes AD 75-20-4, Amendment 39-2370. Amendment 39-2536 became effective March 12, 1976. While the effective date of this amendment 39-2662 is July 12, 1976, the effective date for determining compliance with AD76-05-04 remains March 12, 1976.