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53-24-01: 53-24-01 GRUMMAN AIRCRAFT: Amendment 39-1264. Applies to all G-21A (Converted OA-9, JRF-1 through JRF-5 Under TC 654) Aircraft. Compliance required as indicated. 1. Within the next 50 hours in service after the effective date of the revision to this airworthiness directive, unless already accomplished within the last 50 hours' in service and at intervals thereafter not to exceed 50 hours' in service, accomplish Paragraph (3) for the stabilizer forward attachment fittings (P/N 12548 and P/N 12093). 2. Within the next 100 hours' in service after the effective date of this airworthiness directive, unless already accomplished within the last 100 hours in service and at intervals thereafter not to exceed 100 hours in service, accomplish paragraph (3) for the upper terminal (P/N 12561-1) of stabilizer strut (P/N 12560). 3. Inspect for cracks extending radially from the outside edge of the ears to the inside of the hole into which the shoulder bushings are pressed.Cracked parts must be replaced before further flight with parts inspected in accordance with this Directive or with equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 4. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this airworthiness directive may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. (Grumman Aircraft Engineering Corporation Service Bulletin No. 21 dated March 17, 1948, and Customer Bulletin No. 5 dated October 30, 1953 cover this same subject). AD 53-24-01 which was to have been accomplished by January 15, 1954 supersedes AD 48-18-01. This amendment 39-1264 is effective August 17, 1971.
98-06-01: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 50 series airplanes, that requires a one-time inspection of the clearances around the wiring harnesses of the right-hand electrical cabinet, and readjustment of the clearances, if necessary. This amendment will also require installation of protective strips on the wiring harnesses and equipment supports. This amendment is prompted by issuance of mandatory continued airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent interference between the wiring harnesses and adjacent equipment, support brackets, and structural elements, which could cause an electrical short circuit resulting in fire, and consequent loss of electrical power to essential flight systems.
2006-12-09: The FAA is superseding an existing airworthiness directive (AD), which applies to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. That AD currently requires one-time inspections of the inner webs and flanges at frames 15, 18, 41, and 43 for evidence of corrosion or cracking; and corrective actions if necessary. This new AD instead requires new repetitive inspections and expands the area to be inspected. This new AD also expands the applicability and provides an optional action that would extend the repetitive inspection interval. This AD results from a report indicating that in some cases the inspections required by the existing AD revealed no damage, yet frame corrosion and cracking were later found during scheduled maintenance in the two forward fuselage frames 15 and 18. We are issuing this AD to prevent reduced structural integrity of the airplane.
73-16-01: 73-16-01 SIKORSKY: Amendment 39-1694. Pursuant to the authority of the Federal Aviation Act of 1958, as amended, delegated to me by the Administrator, the following airworthiness directive applicable to operators of Sikorsky S-55 series helicopters modified to incorporate AiResearch TSE331-3U-303N engines installed in accordance with Supplemental Type Certificate No. SH125-WE or SH127WE was effective immediately upon receipt of the telegram dated July 17, 1973. This directive is necessary because of the possibility of engine overspeed and resultant third stage turbine failure. Except as provided by FAR 21.197, the following is required prior to further flight: (a) Install a fuel bypass system in accordance with AiResearch Service Bulletin No. TSE331-73-5004 and Aviation Specialties Service Bulletin No. AS55-01-1, both dated July 16, 1973, or later FAA-Approved revisions thereto. (b) Incorporate the FAA-Approved Aviation Specialties Rotorcraft Flight Manual Revision3 dated July 17, 1973. (c) Equivalent modifications and rotorcraft flight manual revisions may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment is effective July 31, 1973, for all persons except those to whom it was made effective immediately by telegram dated July 17, 1973.
2006-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited Model DHC-7 airplanes. This AD requires revising the FAA-approved Airworthiness Limitations section of the airplane maintenance manual to prohibit operation of the airplane past its designed life limit for the primary structure, which is 80,000 total flight cycles. This AD also requires contacting the FAA for approval of analysis that substantiates that the airplane is safe to continue operation beyond the designed life limit. This AD results from a report that the designed life limit for the primary structure for the affected airplanes is 80,000 total flight cycles. We are issuing this AD to prevent continued operation of an airplane beyond its designed life limit for the primary structure, which could result in reduced structural integrity of the airplane.
71-02-03: 71-02-03 GENERAL DYNAMICS: Amdt. 39-1145 as amended by Amendment 39- 1165. Applies to Model 340, 440 and C-131E Airplanes including those airplanes converted to turbopropeller power, certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD unless already accomplished within the last 200 hours time in service. To prevent failures of the left and right main landing gears, accomplish the following: (a) Inspect the entire outer surface of the main landing gear cylinders (P/N 528002 or P/N 528402), including the fulcrum arms, for cracks using magnetic particle or dye penetrant methods, or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) If cracks are found, before further flight either rework the cylinder in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region or replace the cylinder with a cylinder which has been inspected per (a) above and found free of cracks. (c) If cylinders are reworked in accordance with (b) above, accomplish the following before further flight: 1. Identify and record the cylinders and areas reworked. 2. Limit the use of reworked cylinders to those aircraft operating below or at a maximum of 55,000 lbs. take-off gross weight. If any cylinder reworked per (b) above is installed in any aircraft converted to turbopropeller power in accordance with STC SA4-1100 (known as Model 580), install a placard in only those aircraft previously approved for operating weights above 55,000 pounds, and in full view of the pilot, which reads as follows: "Maximum take-off gross weight 55,000 lbs." 3. Repeat (a) above at intervals of 1,000 hours' time in service from the last inspection. (d) If no cracks are found as a result of the inspection required by (a) above and it is definitely determined that a cylinder has less than 14,000 hours' time in service, repeat (a) above, before 15,000 hours' time in service have been accumulated. (e) If no cracks are found as a result of the inspection required by (a) or (d) above, and a cylinder is considered to have more than 14,000 hours' time in service, repeat (a) above at intervals of 1,000 hours time in service from the last inspection. Amendment 39-1145 effective January 21, 1971. This amendment 39-1165 becomes effective March 9, 1971.
58-08-06: 58-08-06 VICKERS: Applies to all Viscount 700 Series Aircraft. Compliance required as indicated. As a result of further cracks found in main chassis ram foot fittings, Vickers-Armstrong (Aircraft) Limited has recommended revised inspections which the British Air Registration Board considers mandatory. When each main chassis ram foot fitting has completed 1,500 landings, it should be inspected as follows: 1. A visual inspection is to be made within every 135 flying hours for the possible presence of cracks in the external surface of each ram foot fitting, particularly in the area of the base and sides of the ram socket for a distance of approximately 2 inches vertically from the base; 2. Inspect within the next 600 flying hours and thereafter within each subsequent 3,000 flying hours as follows: Remove the ram foot from each main undercarriage assembly and inspect for the possible presence of cracks, both inside and outside of the ram socket bore. The examination should be carried out using an approved method of crack detection and particular attention should be given to the radius at the bottom of the ram socket bore joining the bottom flange and the wall of the bore; 3. Any fittings found cracked should be replaced by new parts; 4. After compliance with Vickers-Armstrongs Modification D. 2695, the inspection outlined above may be discontinued. After January 31, 1959, all ram foot fittings exceeding 1,500 landings must incorporate Modification D.2695 or be replaced. The FAA concurs with this action and considers compliance therewith mandatory. (Vickers-Armstrongs PTL No. 175, Issue 2, and Modification D.2695, covers this subject.) This supersedes AD 57-26-01.
68-07-01: 68-07-01 GENERAL DYNAMICS: Amendment 39-568. Applies to Models 340, 440 and C-131E airplanes including those using turbo propeller power. Compliance required as indicated. Due to numerous reports of cracks developing in the Pilot and Copilot Direct Vision Window Frame Casting, PNs 340-3110314-9, -10, -13 and -14 (hereinafter referred to as the Casting) which affects the structural integrity of the Casting and which, in some cases, has caused loss of cabin pressurization, accomplish the following: (a) Inspect each Casting with 4500 or more hours' time in service on the effective date of this AD for cracks in accordance with Paragraph (c) within the next 250 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (b) Inspect each Casting with less than 4500 hours' time in service on the effective date of this AD for cracks in accordance with Paragraph (c) prior to the accumulation of 4750 hours' time in service and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (c) Inspect all visible areas of the main body of each Casting for cracks by means of either a visual inspection with the aid of an eight power glass, a dye penetrant inspection method, an eddy current inspection method, or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: In performing the inspection specified in Paragraph (c), special attention should be given to the lower left and right hand corner of the Casting. NOTE: For purposes of complying with this AD, the main body of the Casting includes only that part of the Casting which outlines the Direct View Window and does not include the attach flanges. (d) If a crack or cracks are found in a Casting comply with subparagraphs (1) and (2) of this Paragraph as appropriate: (1) If the cracked Casting is completely severed at any point, replace the affected Casting with a new part, P/N 340-3110314-9 or -13 (left hand side) or P/N 340- 3110314-10 or -14 (right hand side), prior to further flight after discovery of the crack (except that the airplane may be flown at a cabin pressure differential of zero p.s.i. in accordance with FAR 21.197 to a base where the replacement can be accomplished); and (2) If the cracked Casting is not completely severed at any point replace the affected Casting with a new part, P/N 340-3110314-9 or -13 (left hand side) or P/N 340- 3110314-10 or -14 (right hand side) within 250 hours' time in service after discovery of the initial crack except that until such time as the affected Casting is replaced in accordance with this Subparagraph: (i) The affected airplane must be operated at a cabin pressure differential of zero p.s.i.; and (ii) Prior to the initial takeoff after discovery of the initial crack, an operating limitation in the form of a placard must be installed inthe affected airplane in clear view of the pilot stating: "Operation Limitation. Pressurized Flight Prohibited." (e) Operators who have not kept records of hours' time in service of individual Castings shall substitute hours' time in service of the airplane in lieu thereof. (f) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the compliance times herein if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective on April 29, 1968.
67-27-02: 67-27-02 AVIONS MARCEL DASSAULT: Amdt. 39-478, Part 39, Federal Register September 9, 1967. Applies to Fan Jet Falcon Airplanes Serial Numbers 1 thru 89, except Serial Numbers 73, 78, 82, 85 and 87. Compliance required as indicated. To detect and prevent corrosion of the wing to fuselage recess and the wing to fuselage attachment bolts accomplish the following, unless already accomplished: (a) For all airplanes, within the next 200 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, visually inspect the recesses of the wing fuselage junction for signs of corrosion, in accordance with Dassault Service Bulletin No. 282 (57-14), dated April 12, 1967, or later SGAC- approved or FAA-approved revision, or in accordance with an FAA-approved equivalent. (b) For airplanes without Dassault Modifications M1014A and M1014C and with more than 400 hours' time in service on the effective date of this AD, within the next 200 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, inspect the wing to fuselage attachment bolts for signs of corrosion, in accordance with Dassault Service Bulletin No. 282 (57-14), dated April 12, 1967, or later SGAC-approved or FAA-approved revision, or in accordance with an FAA- approved equivalent. (c) For airplanes without Dassault Modifications, M1014A and M1014C and with less than 400 hours' time in service on the effective date of this AD, prior to the accumulation of 600 hours' time in service, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, inspect the wing to fuselage attachment bolts for signs of corrosion, in accordance with Dassault Service Bulletin No. 282 (57-14), dated April 12, 1967, or later SGAC- approved or FAA-approved revision, or in accordance with an FAA-approved equivalent. (d) If corrosion is found when conducting the inspections required by paragraphs (a), (b), or (c), within the next 200 hours' time in service, comply with paragraph (f). (e) If no corrosion is found during the inspections required by paragraphs (a), (b), or (c), incorporate the modifications specified in paragraph (f) prior to the accumulation of 1200 hours' time in service from the effective date of this AD, but in any event not later than December 31, 1968. (f) Incorporate Dassault Modifications M1014C and M1057, in accordance with Dassault Service Bulletins No. 234, revision 1, dated April 12, 1967, and No. 259, dated April 12, 1967, or later SGAC-approved or FAA-approved revisions, or an FAA-approved equivalent. (g) The repetitive inspections, required by paragraphs (a), (b), and (c), may be discontinued after the incorporation of Dassault Modifications M1014A, M1014C and M1057. This amendment effective October 9, 1967.
70-03-05: 70-03-05 BEECH: Amdt. 39-935 as amended by Amendment 39-1030 is further amended by Amendment 39-1472. Applies to Models H35, equipped with Continental O-470-G- CI engines, J35, K35, M35, N35, P35, S35, S35TC, V35, V35-TC, V35A, and V35A-TC, Serial Numbers D5062, D5331 through D9068; Models 35-33, 35-A33, 35-B33, 35-C33 and E33, Serial Numbers CD-1 through CD-1234; Models 35-C33A and E33A, Serial Numbers CE-1 through CE-289; Model F33C, Serial Numbers CJ-26 and up; Model E33C, Serial Numbers CJ-1 and up; Model 36, Serial Numbers E-1 through E-184 airplanes. Compliance: Required as indicated, unless already accomplished. A) Effective immediately, turning type takeoffs and a takeoff immediately following a fast taxi turn are prohibited. Avoid prolonged slips (20 seconds or more) with fuel tanks less than half full. B) Within 20 hours' time in service after the effective date of this AD, install a permanent type placard on the instrument panel in clear view of the pilot utilizing a minimum of 1/8 inch high letters, or at any equivalent location approved by an FAA Flight Standards Inspector, with the following wording: "TURNING TYPE TAKEOFFS, AND TAKEOFF IMMEDIATELY FOLLOWING FAST TAXI TURN PROHIBITED. AVOID PROLONGED SLIPS (20 SECONDS OR MORE) WITH FUEL TANKS LESS THAN HALF FULL." NOTE: The operator/owner may make and install the placard. C) Within 20 hours' time in service after the effective date of this AD, on Beech Models V35A (Serial Numbers D-8828 through D-9068), E33 (Serial Numbers CD-1181 through CD-1234), E33A (Serial Numbers CE-227 through CE-289) and 36 (Serial Numbers E-1 through E-184) airplanes and those Beech Model airplanes previously modified in accordance with Beech Service Instruction 0133-286 obliterate or remove Beech placard, P/N 33-924017, located either on the Fuel Selector Valve Cover Plate or on the Top Center of the floating instrument panel, which reads: "CAUTION - TO PREVENT FUEL FLOW INTERRUPTIONS DUE TO GRAVITY OR CENTRIFUGAL FORCE, SELECT THE HIGH-WING TANK IN SLIPS AND INSIDE TANK DURING TURNING TAKEOFFS." Naphtha will remove the instrument panel placard. (Beech Service Instruction 0133-286 has been cancelled.) D) Within 20 hours' time in service after the effective date of this AD, revise the Airplane Flight Manual, P/N 33-590004-1, dated September 28, 1968, on the Beech Model E33 airplanes and the Airplane Flight Manual, P/N 35-590116-3, dated September 20, 1968, on the Beech Model V35A airplanes as follows: In Section I, Limitations, under Item I obliterate the "required placard" paragraph which states, "CAUTION - TO PREVENT FUEL FLOW INTERRUPTIONS DUE TO GRAVITY OR CENTRIFUGAL FORCE, SELECT THE HIGH- WING TANK IN SLIPS AND INSIDE TANK DURING TURNING TAKEOFFS", and in its place insert a new paragraph with the words specified on the placard required by Paragraph B of the AD. Accomplish this insertion by affixing a typewritten or printed insert over the existingparagraph. Note: This insert may be made and installed by the operator/owner. E) (1) Beech Models K35, M35, N35, P35, S35, S35-TC, V35, V35-TC, V35A, V35A-TC, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33C and 36 airplanes with fuel cell baffles installed in both wings in accordance with Beech Service Instructions 0459- 281 (Beech Kit Nos. 35-9009-1S, 35-9009-2S, 35-9009-3S or 35-9009-4S) or 365-281, Rev. 1, (Beech Kit Nos. 35-9009S or 35-9009-5S) or later revisions, or fuel reservoirs installed in both wings per Beech Kit 35-9012 or a fuel reservoir in one wing and a baffled cell in the other are exempt from compliance with the turning takeoff and 20 second side slip limitations of this AD. (2) On Models 35-C33A, E33A, E33C, F33C and 36 airplanes which have complied with Paragraph E(1) install a placard on the instrument panel in full view of the pilot with the wording, "MAXIMUM SIDESLIP DURATION 30 SECONDS", and operate the airplane accordingly.(3) On all other model airplanes listed in Paragraph E(1) (except those listed in Paragraph E(2), which have complied with Paragraph E(1), operate the airplane in accordance with the limitations set forth in Airplane Flight Manual Supplement P/N 35-590118-15 dated February 11, 1972, or later revision. F) Beech Models H35 (equipped with Continental O-470-G-CI engines) and J35 airplanes which have complied with Beech Service Instruction No. 0459-281 are exempt from compliance with this AD. Amendment 39-935 became effective February 5, 1970. Amendment 39-1030 became effective July 18, 1970. This Amendment 39-1472 becomes effective June 30, 1972.