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62-19-03: 62-19-03 PIPER: Amdt. 478 Part 507 Federal Register August 23, 1962. Applies to All Model PA-28 Aircraft, Serial Numbers 28-1 to 28-314 Inclusive, 28-317 to 28-326 Inclusive, 28- 328 to 28-331 Inclusive, 28-333 to 28-341 Inclusive, 28-343, 28-345 to 28-348 Inclusive, 28- 351, 28-352, 28-356, 28-359, and 28-365. Compliance required as indicated. There has been inflight failure of the propeller attach bolts due to under-torquing of the bolts. In order to preclude the loss of the propeller due to the failure of the bolts, the following is required: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, remove the propeller spinner and remove each propeller attach bolt. (b) Inspect for cracks in the bolt in the area of the threads using magnetic particle or FAA-approved equivalent inspection method in conjunction with a 5-power or higher magnifying glass. Inspect the grip shank for brinelled surfaces with a5-power or higher magnifying glass. (c) If cracks are found or if the bolt is brinelled on the grip shank, replace with new bolts, AN 76-41S. Torque to 300 inch-pounds. (d) If cracks are not found, reinstall the bolts and torque to 300 inch-pounds. (e) In lieu of the inspection requirement of (b), new bolts, AN 76-41S, may be installed and torqued to 300 inch-pounds. (Piper Service Bulletin No. 209, dated April 17, 1962, covers this same subject.) This directive effective August 28, 1962.
2018-07-07: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES D, E, F, and G airplanes; and certain Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by reports of the collapse of the main landing gear (MLG) on touchdown. This AD requires an electrical modification of the landing gear sequence logic. We are issuing this AD to address the unsafe condition on these products.
86-07-11: 86-07-11 BOEING: Amendment 39-5285. Applies to Boeing Model 757 airplanes, line numbers 1 through 90, certificated in any category. Compliance is required within 30 days after the effective date of this amendment. To ensure proper door opening, accomplish the following, unless already accomplished: \n\n\tA.\tInspect the left and right side Number 1, 2, and 4 passenger doors to verify proper engagement of the upper pinch bolt, and reinstall, if necessary, in accordance with Boeing Service Bulletin 757-52A0019, dated February 27, 1986, or later FAA-approved revisions. \n\n\tB.\tAlternate means of compliance or adjustment of compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not already received copies of the service bulletin cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 28, 1986.
62-17-04: 62-17-04 EDO: Amendment 473 Part 507 Federal Register August 4, 1962. Applies to Model 249A2870 (A Model Only) Float Installations, Float Serial Numbers 1 to 280, Installed on Cessna Model 180 Series Per STC SA1-622 and Cessna Model 185 Seaplanes. Compliance required within the next 5 hours' time in service after the effective date of this AD, unless already accomplished. Longitudinal cracks have been found on Edo streamlined struts P/N 6061T6, in the area near the 30 and 60 percent chord sections. To preclude operations with defective struts accomplish the following: Visually inspect each side of the full length of the attachment strut, P/N 6061T6, for longitudinal cracks. Replace cracked struts prior to further flight. NOTE: Report the details on any defective struts found to the FAA Engineering and Manufacturing Branch, ATTN: EA-212, Hangar 18, Room 210, New York International Airport, Jamaica 30, New York. (Edo telegram of July 7, and Edo letter ofJuly 9, 1962, cover the same subject.) This directive effective August 14, 1962.
84-23-05: 84-23-05 BOEING: Amendment 39-4949. Applies to Boeing Model 737 series airplanes, certificated in all categories, listed in Boeing Service Bulletin 737-55A1029, Revision 3. To ensure continued structural integrity of the horizontal stabilizer, accomplish the following, unless previously accomplished: \n\n\tA.\tInspect the rear spar horizontal stabilizer attach lugs for cracks in accordance with instructions in Boeing Service Bulletin 737-55A1029, Revision 3, or later FAA approved revision, upon the accumulation of the threshold number of landings specified in Table I of the service bulletin or within 200 landings after the effective date of this AD, whichever occurs later. Repeat these inspections at intervals not exceeding those specified in Table I of the service bulletin. \n\n\tB.\tCracked parts must be replaced or repaired in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region before further flight. \n\n\tC.\tAirplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and 21.199 with prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tFor purposes of complying with the AD, subject to the acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tE.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tUpon request by the operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection interval in this AD, if the request contains substantiating data to justify the increase for the operator. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis supersedes Amendment 39-4122 (46 FR 28147; May 26, 1981), AD 81-11-07. \n\tThis Amendment 39-4949 becomes effective December 15, 1984.
62-13-01: 62-13-01 ANDREA RADIO CORPORATION: Amdt. 447. Part 507 Federal Register June 1, 1962. Applies to All Aircraft Equipped With Intercommunication Sets Models AN/AIC-10A and AN/AIC-18(A-81), Except Those With Control Panel Serial Number 332 and Subsequent. Compliance required as indicated. Within the next 200 hours' time in service after the effective date of this airworthiness directive unless already accomplished, modify Model AN/AIC-18(A-81) in accordance with Andrea Radio Corporation Field Modification C41-5115 and Model AN/AIC-10A in accordance with Andrea Radio Corporation Field Modification C41-5116, so that the adjustable attenuation range does not exceed 10 decibels. When the modification has been completed add marking "MOD" adjacent to the TSO-C50 label. Within the next 10 hours' time in service after the effective date of this airworthiness directive unless already accomplished, as an interim procedure pending modification, install a placard requiring that the master level control on the isolation amplifier be full "ON" at any time range problems are being worked. (Andrea Radio Corporation Field Modification C41-5115 for AN/AIC-18(A-81) and C41-5116 for the AN/AIC-10A, both dated April 5, 1962, cover this same subject.) This directive effective June 1, 1962.
62-10-03: 62-10-03 PIPER: Amdt. 431 Part 507 Federal Register April 26, 1962. Applies to Models PA-24 and PA-24 "250" Aircraft, Serial Numbers 24-1 through 24-2264. Compliance required within the next 50 hours' time in service after the effective date of this AD. Inspect the aileron counterweight bays on both wings for the presence of Rubatex blocks. If any of these blocks, whether loose or attached, are found they must be removed from the aircraft in order to prevent possible restriction of aileron travel. (Piper Service Letter No. 364A, dated March 14, 1962, pertains to this subject.) This directive effective April 26, 1962.
2005-13-04: The FAA is adopting a new airworthiness directive (AD) for certain Avcraft Dornier Model 328-100 and -300 airplanes. This AD requires a pressure test and detailed inspection of each fuselage drain line to determine if there is a blockage, and related investigative/ corrective actions if necessary. This AD is prompted by a report of leakage at one of the drain lines in the fuselage. We are issuing this AD to prevent blockage within the drain lines, causing fluids to collect. These fluids may freeze and expand, damaging the drain lines, and allowing fuel to leak into the cabin and fuel vapors to come into contact with ignition sources, which could result in consequent fire in the cabin.
88-14-05: 88-14-05 HOFFMANN AIRCRAFT GES.M.B.H.: Amendment 39-5930. Applies to model H36 Dimona motor gliders certificated in any category. Compliance is required as indicated unless already accomplished. To prevent failure of the rod end bearing on the front horizontal tail surface mount, accomplish the following: (a) Within the next ten hours time in service after the effective date of this AD, visually inspect the rod end bearing on the front horizontal tail surface mount using a 5 power or greater magnifying glass for cracks in the area of the threaded shank, in accordance with inspection requirements of paragraph 1 of the Actions section of Hoffmann Aircraft Ges.m.b.h. Service Bulletin (SB) No. 15/2, dated January 20, 1987. (b) Before further flight, replace cracked rod end bearings (SMXCP 10 M) with a modified rod end bearing, Hirschmann "SMXC 10 special design", in accordance with Work Instruction No. 7, contained in Hoffmann Aircraft Ges.m.b.h. SB No. 15/2, datedJanuary 20, 1987. (c) Within 50 flight hours after accomplishment of inspection per paragraph (a) of this AD, or prior to August 1, 1988, whichever comes first, replace any rod end bearing (SMXCP 10 M) not replaced in accordance with paragraph (b), in accordance with Work Instruction No. 7, contained in Hoffmann Aircraft Ges.m.b.H. SB No. 15/2, dated January 20, 1987. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 rue de la Loi B-1040 Brussels, Belgium; telephone No. 513.38.30, Ext. 2710; or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791- 6680. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Hoffmann Aircraft SB No. 15/2, dated January 20, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Hoffmann Aircraft, Ges.m.b.H., Richard Neutra Gasse 5, A-1214, Vienna, Austria. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 88-ANE-20, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5930, becomes effective July 13, 1988.
62-08-02: 62-08-02 AERO COMMANDER: Amdt. 418 Part 507 Federal Register April 11, 1962. Applies to Models 520 and 560 Aircraft With Serial Numbers 1 Through 230. Compliance required within the next 25 hours' time in service after the effective date of this directive. As a result of reported cases of fluid line chafing in the wing trailing edge area and fuel leakage in the aft fuselage and electronic equipment area, the following corrective action is required: (a) Replace the fuel system aluminum drain tubing with flexible hose assemblies in accordance with Aero Commander Service Bulletin No. 77 dated March 16, 1962, or FAA approved equivalent. (b) Modify the wing trailing edge between wing Stations 24.00 and 59.00 in accordance with Aero Commander Service Bulletin No. 79 dated March 16, 1962, or FAA approved equivalent. This directive effective April 11, 1962.