Results
62-26-06: 62-26-06 PIPER: Amdt. 516 Part 507 Federal Register December 8, 1962. Applies to All Models PA-28-150 and PA-28-160 Airplanes With Serial Numbers 28-03, 28-1 through 28-671, 28-678, 28-679, 28-681, 28-685, 28-690, 28-691, 28-693, 28-697, 28-706, and 28-707, Except Those With Exhaust Assembly P/N 63726 Installed. Compliance required within the next 10 hours' time in service after the effective date of this AD, and each 50 hours' time in service thereafter. There have been cracks found in the exhaust system on Piper PA-28-150 and PA-28-160 airplanes. As this condition is likely to occur in other airplanes of the same type design, accomplish the following: (a) Remove carburetor heat muff shroud and conduct a close visual inspection of the complete exhaust system piping for cracks in all welded joints and tubing bends. Pay particular attention to the area near the junction of the cylinder stacks and main exhaust manifold. (b) If cracks are found, repair by gaswelding. (The exhaust pipe is AISI 321 or 347 corrosion resistant steel.) (Piper Service Letter 389 covers this same subject.) This directive effective December 14, 1962.
62-23-03: 62-23-03 DOUGLAS: Amdt. 500 Part 507 Federal Register October 30, 1962. Applies to DC-8 Aircraft Serial Numbers 45252 to 45289 Inclusive, 45291 to 45306 Inclusive, 45376 to 45393 Inclusive, 45408 to 45413 Inclusive, 45416 to 45431 Inclusive, 45433 to 45437 Inclusive, 45442 to 45445 Inclusive, 45526, 45565 to 45570 Inclusive, 45588 to 45606 Inclusive, 45609 to 45614 Inclusive, 45616 to 45629 Inclusive, 45636, and 45638. \n\n\tCompliance required as indicated. \n\n\tTo prevent failure of the main landing gear actuating cylinder upper attach bracket accomplish the following: \n\n\t(a)\tWithin 440 hours' time in service after the effective date of this AD, unless already accomplished, on attach brackets, P/N's 5641950-1, -2, -501 or -502 having 4,000 or more hours' time in service and, prior to the accumulation of 4,440 hours' time in service on brackets having less than 4,000 hours' time in service, conduct a hardness check on the attach bracket following the procedures described in theaccomplishment instructions, paragraphs B (4), B(5) and C of Douglas Alert Bulletin No. A32-76, Reissue No. 1, Revision No. 1, dated April 5, 1962, or later, or an FAA approved equivalent. \n\n\tNOTE: To gain access to the bracket it is necessary to remove the hydraulic lines from the rework area, remove swivel glands as applicable, remove the retract cylinder upper bolt and swing the cylinder down out of the way. \n\n\t(b)\tBrackets testing within Rockwell C39.0 (175,000 p.s.i.) and C43.0 (200,000 p.s.i.) range are acceptable for further use and may be continued in service provided they are not otherwise defective. These brackets shall be identified by applying a 1/4 to 1/2-inch stripe of Cat-A-Lac, yellow No. 443-3-129 enamel or equivalent on the bracket. The identification stripe should be located in a place on the bracket so that it is clearly visible without having to remove the retract cylinder to observe the stripe. \n\n\t(c)\tBrackets testing outside the C39.0 to C43.0 heat-treatrange shall be inspected for cracks in the area of the junction of the grease fitting hole and the actuating cylinder attach hole using a dye penetrant or equivalent inspection method. The bushing, Douglas P/N 2641952 must be removed to conduct this inspection. \n\n\t\t(1)\tAny of these brackets found to be free of cracks during inspection, and not otherwise defective, may be continued in service provided the inspection is repeated at intervals not exceeding 350 hours' time in service thereafter. \n\n\t\t(2)\tReplace cracked parts prior to further flight with an appropriate part (Douglas P/N 5641950-1 or -2, 5641950-501 or -502) falling within the C39.0 to C43.0 heat-treat limits and marked with the yellow stripe for identification, with new P/N's 5774066-501 or -502, or with an FAA approved equivalent. \n\n\t(d)\tUpon request of the operator, an FAA maintenance inspector, subject to prior 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(Douglas Alert Service Bulletin No. A32-76, Reissue No. 1, Revision No. 1, dated April 5, 1962.) \n\n\tThis directive effective November 29, 1962.
74-11-05: 74-11-05 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 1849. Applies to Grumman G-1159, Serial Number 1 through 110 and 775 except 91 and 95, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To provide dual electrical fire extinguisher squib circuits, accomplish the following or an equivalent rework approved by the Chief, Engineering and Manufacturing Branch, Southern Region. Remove the left and right fire extinguisher switches MS24523-21 and install MS24524- 21 switches in their place. Wire switches in accordance with Grumman Gulfstream II Aircraft Service Change 121. Replace pilot's circuit breaker panel nameplate 1159AV2042 with nameplate 1159SB20082-11. This rework is outlined in detail in the Grumman Gulfstream II Aircraft Service Change 121. This amendment is effective May 24, 1974.
62-12-04: 62-12-04 DOUGLAS: Amdt. 439 Part 507 Federal Register May 17, 1962. Applies to All DC-8 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tA number of wing flap actuating cylinder rod-end bearings have cracked and in one case there was complete failure. To preclude failure of the rod-end bearings in cylinders located at wing Stations 98 and 219, accomplish the following: \n\n\t(a) Assemblies having 4,650 hours' or more time in service as of the effective date of this AD shall be inspected in accordance with (b) within the next 350 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 350 hours' time in service. Assemblies having less than 4,650 hours' time in service as of the effective date of this AD shall be inspected in accordance with (b) prior to the accumulation of 5,000 hours' time in service and thereafter at intervals not exceeding 350 hours' time in service. \n\n\t(b) Visually inspect rod-end bearings P/N 4648686 in the area of the bearing case adjacent to the bearing dust shield using at least a 10-power glass, for evidence of cracks. Caution: Do not remove rod-end bearing dust shield or magnetically inspect the rod-ends. \n\n\t(c) If cracks are found, replace the defective part. If no cracks are found, the 350 hour periodic inspection, specified in (b), shall be continued. \n\n\t(d) When replacement assemblies P/N 4648686 are used, the inspection prescribed in (b) shall be accomplished prior to the accumulation of 5,000 hours' time in service and thereafter at intervals not exceeding 350 hours' time in service. \n\n\t(e) When assembly P/N 4648686 is replaced by Douglas P/N 4648686-501 (Shafter P/N YD-200A) or -503 (Shafter P/N YD-200B), or FAA approved equivalent, the inspections called for in this AD may be discontinued. \n\n\t(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering & 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(Douglas Service Bulletin No. 27-127 reissue No. 2 dated January 28, 1964, covers this same subject.) \n\n\tThis directive effective May 17, 1962. \n\n\tRevised August 12, 1964.
2005-03-14: This amendment supersedes an existing airworthiness directive (AD) that applies to all Airbus Model A300 B2 and B4 series airplanes. The existing AD currently requires determining the part and amendment number of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions if necessary. For certain VLAs, this new AD requires repetitive inspections of the VLA and corrective action if necessary. This new AD also provides a terminating action for the repetitive inspections. Furthermore, this new AD reduces the applicability of affected airplanes. The actions specified by this AD are intended to prevent failure of both spring boxes of certain VLAs due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
72-12-05: 72-12-05 HAWKER SIDDELEY AVIATION LTD.: Amdt. 39-1458. Applies to Hawker Siddeley deHavilland Model DH-114 "Heron" airplanes which do not have Modification 1161 incorporated on all of the main landing gear and nose landing gear operating jacks. Compliance required as indicated. To prevent the possible failure of the main or nose landing gear operating jacks accomplish the following: (a) Within the next 50 landings after the effective date of this AD, or before accumulating a total of 5,000 landings on a piston, P/N AHO 19742, in an operating jack assembly, whichever occurs later (1) Replace the affected operating jack assembly with a serviceable jack assembly which has been modified to incorporate piston, P/N ACO 23389, (Modification 1161) in accordance with de Havilland Aircraft Service, Modification News Sheet No. Heron 1161, dated March 17, 1958, or an FAA-approved equivalent, or (2) Replace the piston in each affected operating jack assembly with a newpiston of the same part number and thereafter continue to replace P/N AHO 19742 pistons at intervals not to exceed 5,000 landings. (b) Operators who have not kept records of the number of landings on individual pistons, P/N AHO 19742, shall substitute the total number of airplane landings accumulated in lieu thereof. (de Havilland Aircraft Service, Technical News Sheet, Series: Heron (114) No. S.2 dated March 1, 1959, covers this same subject.) This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective upon receipt of the airmail letter dated April 20, 1972, which contained this amendment.
2005-11-01: The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 1A turboshaft engines. This AD requires initial and repetitive testing of the Free Turbine Overspeed Protection System. This AD results from an investigation into the Digital Electronic Control Unit (DECU) that revealed a malfunction of the Free Turbine Overspeed Protection System. This malfunction can exist despite the DECU passing all functional tests specified in the Engine Maintenance Manual. We are issuing this AD to prevent uncontained engine failure if a free turbine overspeed occurs.
75-09-08: 75-09-08 MOONEY: Amendment 39-2181. Applies to Mooney Models M20C, M20D, M20E, M20F, and M20G airplanes with the following serial numbers having accumulated 400 or more hours' time in service: M20C - 1852, 1940 thru 3466, 670001 thru 700091, 20-0001 thru 20-1156. M20D - 101 thru 260. M20E - 101 thru 1308, 670001 thru 700061, 21-0001 thru 21-1165. M20F - 660003 thru 700072, 22-0001 thru 22-1207. M20G - 680001 thru 700006. Compliance required within the next 50-hours' time in service after the effective date of this AD or before the accumulation of 450-hours' time in service, whichever occurs later, unless already accomplished within the last 50-hours' time in service, and thereafter at intervals not to exceed 100-hours' time in service from the last inspection. a. To detect cracked engine mount members, inspect the mount in accordance with instructions in Mooney Service Bulletin No. M20-192 dated April 7, 1975, or later FAA approved revision, or an FAA approved equivalent method. b. If cracks are detected, repair or replace in accordance with instructions in Mooney Service Bulletin No. M20-192 dated April 7, 1975, or later FAA approved revision or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, Fort Worth, Texas. c. The 100-hour repetitive inspection may be discontinued upon repair of a cracked or uncracked mount, or upon installation of a new mount in accordance with Mooney Service Bulletin No. M20-192 dated April 7, 1975, or later FAA approved revision or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective April 30, 1975.
2000-06-13 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200, -200C, -300, and -400 series airplanes, that currently requires repetitive visual and high frequency eddy current (HFEC) inspections to detect cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions, if necessary. That amendment also mandates accomplishment of a modification to the aft cargo door, which would terminate the repetitive inspection requirements. This amendment revises the compliance time for the terminating modification. The actions specified by this AD are intended to prevent fatigue cracking of the corners of the doorframe and the crossbeams of the aft cargo door, which could result in rapid depressurization of the airplane. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 9, 2000 (65 FR 17583, April 4, 2000).\n\n\n\tThe incorporation by reference of Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996, as listed in the regulations, was approved previously by the Director of the Federal Register as of December 24, 1998 (63 FR 67769, December 9, 1998).
73-26-05: 73-26-05 SCOTT AVIATION DIVISION of ATO INC: Amdt. 39-1756. Applies to chemical oxygen generators, Scott Part Numbers 801386-01, -02, and -03, and 801462-01, -02, and -03. Compliance required within the next six months after the effective date of this AD, unless already accomplished. To detect generators showing evidence of corrosion, and to replace corroded units, accomplish Scott Aviation Service Bulletin 35-38, dated February 1, 1973, and Revision Number 1, dated May 11, 1973, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 20, 1973.