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89-05-01: 89-05-01 CASA: Amendment 39-6147. Applicability: All CASA Model C-212 series airplanes, certificated in any category. Compliance: Required as indicated below, unless previously accomplished. To prevent failure of the wing flap control system, accomplish the following: A. Within 180 days after the effective date of this AD, modify the bellcrank-to- control rod joints in the wing flap control system in accordance with CASA Service Bulletin 212- 27-22, Revision 3, dated May 20, 1988. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6147, AD 89-05-01) becomes effective April 3, 1989.
54-24-01: 54-24-01 BELL: Applies to All Models 47B, 47B3, 47D, 47D1, 47E, 47G Except 47G Serial Numbers 1286, 1287, 1294, 1295, and 1299 and Subsequent. Compliance required no later than next 25-hour inspection. In order to preclude improper installation of antitorque pedal assembly for dual controls, install two stop assemblies, P/N 47-722-165-1. (Bell Mandatory Service Bulletin No. 98 dated October 29, 1954, covers this same subject and outlines the details for the installation.)
85-03-51: 85-03-51 CESSNA: Amendment 39-5022. Applies to Cessna Model 552 series airplanes, serial numbers 552-0001, 552-0003 through 552-0006 and 552-0008; and Model 650 series airplanes, serial numbers 650-0001 through 650-0072; certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent short-to-ground of the nickel cadmium battery which could result in an electrical fire, accomplish the following: A. Prior to further flight, inspect the aircraft battery to determine if a SAFT type 40976, P/N 18585, is installed: 1. If SAFT type 40976 battery, P/N 18585, is not installed, no other action is necessary. 2. If SAFT type 40976 battery, P/N 18585, is installed: for Model 650 airplanes, modify the battery in accordance with Cessna Service Letter SL650-24-03, dated January 21, 1985, and SAFT Service Bulletin 0005, dated January 17, 1985, referenced therein; for Model 552 airplanes, modify in accordance with SAFT Service Bulletin 0005, dated January 17, 1985. a. Thereafter, reinspect the insulators installed on the SAFT type 40976 batteries every 100 flight hours. b. These inspections may be terminated upon installation of an approved Marathon battery, Cessna P/N 9914058-2, or SAFT battery, Cessna P/N 9914058-5, on the Model 650 airplanes; or SAFT battery, Cessna P/N 9914058-5, on the Model 552 airplanes. B. Alternate means of compliance with this AD which provide an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Cessna Marketing Division, Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277, or may be examined either at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas, or at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. This Amendment becomes effective April 11, 1985. It was effective earlier to all recipients of Telegraphic AD T85-03-51, dated February 6, 1985.
2018-03-03 R1: We are revising Airworthiness Directive (AD) 2018-03-03 for certain Textron Aviation Inc. Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, and 425 airplanes. AD 2018-03-03 required repetitively inspecting the left and the right forward lower carry through spar cap for cracks and replacing the carry through spar cap if cracks were found. This AD addresses the same unsafe condition and requires the same actions as AD 2018-03-03, but clarifies the compliance times for the initial inspection of the carry through spar cap. This AD was prompted by several reports of confusion in interpreting the compliance times for the initial inspection of the carry through spar cap. We are issuing this AD to eliminate confusion in interpreting the compliance times for this inspection.
63-13-02: 63-13-02 DOUGLAS: Amdt. 576 Part 507 Federal Register June 13, 1963. Applies to Model DC-8 Aircraft, Serial Numbers 45253-45289, 45291-45306, 45376, 45382, 45384-45393, 45408-45413, 45416-45419, 45421-45431, 45433, 45442-45445, 45526, 45565-45570, 45588-45606, 45609-45614, 45617, 45618, 45620-45622, and 45624-45627. \n\n\tCompliance required within 420 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tIn order to eliminate interference with the exit door caused by the lower door jamb on aircraft modified in accordance with AD 62-17-03, accomplish the following: \n\n\tRework the exit door lower jamb in accordance with the rework procedures outlined in step (13) of paragraph 2, Accomplishment Instruction of DC-8 Service Bulletin No. 52-21 Revision No. 2 dated October 30, 1962, or FAA approved equivalent. \n\n\t(Douglas DC-8 Service Bulletin No. 52-21 Revision No. 2 dated October 30, 1962, pertains to this same subject.) \n\n\tThis directive effective July 15, 1963.
63-12-02: 63-12-02 PIPER: Amdt. 572 Part 507 Federal Register June 7, 1963. Applies to Model PA-23 Aircraft Serial Numbers 23-1 Through 23-1284, and 23-1286. Compliance required as indicated. Due to cracks being found in the P/N 17058-3 elevator butt rib and the P/N 17058-20 elevator butt rib doubler plate, which parts are incorporated in the P/N 17058-00 elevator assembly originally installed on the above serial numbered aircraft, the following shall be accomplished: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and within every 100 hours' time in service thereafter visually inspect for cracks, elevator butt rib, P/N 17058-3 and elevator butt rib plate, P/N 17058-20 on the P/N 17058-00 elevator assembly. Replace cracked parts before further flight. (b) After P/N 19446 elevator assembly is installed, the inspection specified in (a) is no longer required. (c) Parts shall be assembled and installed to obtain proper alinement and to prevent distortion and over-torquing of the attachment bolts. (Piper Service Bulletin No. 146B, dated October 25, 1962, pertains to this same subject.) This directive effective June 7, 1963.
60-01-07: 60-01-07 PIPER: Amdt. 77 Part 507 Federal Register January 15, 1960. Applies to All Models PA-12, PA-14, PA-20, PA-22, PA-22 "135", PA-22 "150" and PA-22 "160" Series Aircraft. Compliance required not later than January 30, 1960, and at each 100 hours' time in service thereafter, except Model PA-22 compliance required within the next 100 hours' time in service after the effective date of this amendment, and at each 100 hours' time in service thereafter. A number of failures of a tail brace wire, P/N 10074-2 or P/N 10074-3 have occurred. In order to prevent the possibility of a catastrophic accident in the event one of these wires should fail, the following inspection shall be accomplished: (a) Clean the tail brace wires and inspect for cracks, nicks, manufacturing flaws, and tool marks with a 10-power magnifying glass, paying particular attention to the leading and trailing edges. The wires may remain on the airplane for this inspection. (b) Should cracks or nicks be found, it shall be acceptable to sand the affected area with No. 500 sandpaper or equivalent, to remove the cracks or nicks. Sanding shall not reduce the width of the wire by more than the 0.015 inch (1/64th). After the sanding operation the wires shall be painted to preclude corrosion of the sanded area. Any wire containing a crack or nick which cannot be removed by sanding within the specified limits shall be replaced. (The defective wires should be destroyed or permanently marked to prevent inadvertent reuse.) (c) If the streamline tail brace wires, P/N 10074-2 and P/N 10074-3 are replaced by round tail brace wires, P/N 10555-2 and P/N 10556-2, respectively, the 100 hours' time in service repetitive inspections specified herein are no longer required. Attach the round tail brace wires using the following parts: (1) Fuselage tie rod attachment: AN 3-5A bolt, MS 20365-1032C nut. (2) Stabilizer toe rod attachment: AN 3-15A bolt, Piper P/N 82732-72bushings, AN 960-10 washer, MS 20363-1032C nut. (3) Fin tie rod attachments: AN 4-15A bolt, Piper P/N 40131 radius washers, MS 20365-428C nut. (Piper Service Bulletin No. 183 dated November 9, 1959 and Piper Service Letter No. 400 dated March 20, 1963, covers this subject.) Revised September 30, 1960. Revised May 29, 1963.
2018-09-01: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the main landing gear (MLG) beam forward support fitting. This AD requires repetitive inspections for cracking of the MLG beam forward support fitting, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
63-07-02: 63-07-02 MACCHI: Amdt. 548 Part 507 Federal Register April 2, 1963. Applies to All Models AL-60 (formerly LASA 60) and AL-60B Aircraft. Compliance required as indicated. As a result of several cases of engine exhaust manifold failures, accomplish the following within the next 25 hours' time in service after the effective date of this AD, and thereafter within every 25 hours time in service from the last inspection. (a) Inspect the turbo inlet assembly manifold P/N 629-250 for cracks in the weld area between the two exhaust pipes. (b) If cracks are found, replace or repair the part before further flight. Repair by arc welding a stainless steel plate reinforcement over the area in accordance with Aeronautical Macchi Service Bulletin No. 1, or FAA approved equivalent repair. This directive effective May 2, 1963.
63-06-02: 63-06-02 BELLANCA: Amdt. 543 Part 507 Federal Register March 19, 1963. Applies to Bellanca 14-13 Series and Downer 14-19 and 14-19-2 Aircraft. Compliance required as indicated. As a result of instances of elongation of the control cable attachment bolt hole in the rudder bellcrank, P/N 9817, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, unless accomplished within the last 75 hours' time in service, and thereafter within 100 hours' time in service from the last inspection, remove the left and right rudder bellcranks, P/N 9817, located at the left and right ends of the rudder torque tube. (This may be accomplished by working from inside the cabin and through the inspection hole in the bottom cabin cowl.) Inspect the control cable attachment bolt hole in the rudder bellcrank. (b) If the bolt hole is elongated beyond maximum diameter of 0.210 inch, replace the rudder bellcrank with a new rudder bellcrank of the same part number (P/N 9817), or P/N 9817 modified in accordance with Downer EAI No. 93021, or FAA approved equivalent prior to further flight. NOTE: Modified replacement parts for the Models 14-13, 14-19 and 14-19-2, Serial Numbers 4001 through 4088, are stamped "9817-DEAI-93021". Modified replacement parts for the Model 14-19-2, Serial Numbers 4089 through 4105, are stamped "9817-E EAI 93021". Parts numbered 9817-E are made of steel and may be modified in accordance with Downer EAI-93021 or an FAA approved equivalent. (c) The 100 hour repetitive inspections of the bellcrank hole which are required by (a) may be discontinued when rudder bellcrank P/N 9817 modified in accordance with Downer EAI No. 93021 or FAA approved equivalent is installed. This supersedes AD 62-19-01. This directive effective March 19, 1963.