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61-16-06: 61-16-06 PIPER: Amdt. 314 Part 507 Federal Register July 29, 1961. Applies to All PA- 24 and PA-24 "250" Aircraft Modified to Incorporate Brittain Wing Tip Fuel Tanks (Supplemental Type Certificates Nos. SA4-1235 and SA4-1351). Compliance required within the next 150 hours' time in service after the effective date or at the next disassembly of fuel selector valves, whichever occurs first. The fuel selector valve handles of aircraft equipped with Brittain wing tip fuel tanks can easily be reinstalled with incorrect indexing after the valves have been disassembled for servicing and lubrication. Incorrect indexing can cause serious fuel system malfunctioning and one accident resulting from this condition has been reported. To preclude future incorrect indexing of the fuel selector valve handles, the following must be accomplished: (a) Remove any valve shafts with four flat sides at the handle end and replace with Brittain P/N 4018-15 shafts, or equivalent. The Brittain P/N 4018-15 shaft is identical to the original except that one of the four sides at the handle end has been modified to a convex shape. (b) After reassembly and reinstallation of the selector valves, determine that the valve handles are properly indexed with respect to the selector valve placard. (Brittain Aircraft Enterprises Service Letter No. 4000-1 dated April 26, 1961, covers this same subject.) This directive effective August 31, 1961.
2017-25-17: We are superseding airworthiness directive (AD) 2011-27-08 for Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters. AD 2011-27- 08 required repetitively inspecting each elevator assembly for a crack. This new AD retains the initial inspection interval and adds a repetitive borescope inspection. This AD is prompted by the discovery of another crack on an elevator assembly since AD 2011-27-08 was issued. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
2017-25-12: 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 cracking in the webs of the stub beams at certain fuselage stations. These cracks are the result of fatigue caused by cyclical loading from pressurization, wing loads, and landing loads. This AD requires repetitive inspections for cracking of the webs of the stub beams at certain fuselage stations, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-07-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747-200F and -200C series airplanes, that currently requires repetitive detailed inspections or a one-time open-hole high frequency eddy current inspection to detect cracking of certain areas of the upper deck floor beams, and corrective actions if necessary. This amendment requires new one-time inspections for cracking of the web, upper chord, and strap of the upper deck floor beams. This action also requires modifying or repairing the upper deck floor beams, as applicable, which eventually necessitates accomplishment of new repetitive inspections for cracking of the upper deck floor beams. The actions specified by this AD are intended to prevent fatigue cracks in the upper chord and web of upper deck floor beams and the resultant failure of such floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 16, 2005. \n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 16, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-53A2420, dated March 26, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 11, 1998 (63 FR 20311, April 24, 1998).
2005-08-06: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders with other than elevator or aileron part number (P/N) SY991A hinge pins installed. This AD requires you to replace any installed elevator or aileron hinge pins that are not P/N SY991A hinge pins with P/N SY991A pins. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control.
2017-25-14: We are adopting a new airworthiness directive (AD) for Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report of an engine multiple fan blade-off (MFBO) event, caused by engine fan flutter. We are issuing this AD to address the unsafe condition on these products.
61-14-06: 61-14-06 SNOW: Amdt. 306 Part 507 Federal Register July 11, 1961. Applies to All Model S2A Aircraft (Restricted Category). Initial compliance required within 25 hours' time in service after the effective date of this AD unless accomplished within 75 hours' time in service preceding such date. Subsequent compliance required at each 100 hours' time in service after the initial compliance date. Due to reports of excessive cable wear occurring at two AN 210-3B pulleys in the aileron system aft of the hopper and two AN 210-3B pulleys in the elevator system on the left and right of the pilot seat, the following must be accomplished: (a) Detach the aileron and elevator cables by disconnecting the turnbuckles to obtain slack at the two pulleys in each system. Visually inspect the cables for fraying by flexing the cable in the areas of pulley contact in accordance with Snow Service Letter No. 4. Replace all frayed cables prior to further flight. (b) Inspection of theelevator cable may be discontinued when the two AN 210-3B elevator system pulleys to the left and right of the pilot seat are replaced with AN 210-4B pulleys, in accordance with Snow Service Letter No. 6. Inspection of the aileron cable may be discontinued when the aileron cable system is replaced with a push-pull tube system in accordance with Snow Service Letter No. 7. (Snow Service Letters 4, 6, and 7 cover this subject.) This directive effective July 21, 1961.
61-14-01: 61-14-01 AERO COMMANDER: Amdt. 303 Part 507 Federal Register July 7, 1961. Applies to All Model 500 Aircraft. Compliance required within the next 100 hours' time in service after the effective date of this directive and at each 100 hours' time in service thereafter. Visually inspect the inside of angles P/N 5620023-7, -8, -9, and -10 in the area of the row of Huck bolts, nearest the radius of the angle, that attach the angles to the upper and lower mount fittings, P/N 3620025-1 and -2. If cracks are found, prior to further flight, incorporate the reinforcement as indicated in Aero Commander Service Bulletin No. 68A, dated January 20, 1961, or equivalent. Angles incorporating Federal Aviation Agency approved reinforcement need not be reinspected in accordance with the provisions of this AD. (Aero Commander Service Bulletin No. 68A dated January 20, 1961, covers this subject.) This supersedes AD 60-26-01. This directive effective August 8, 1961.
89-06-01: 89-06-01 SWITLIK PARACHUTE COMPANY, INC.: Amendment 39-6075. Applicability: Switlik TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices: all models and all part numbers manufactured from September 1, 1984, through January 30, 1985, and June 1, 1985, through October 30, 1985 (date located on identification label on front surface). Compliance: Required within one year after the effective date of this AD, unless already accomplished. To prevent the improper functioning of the carbon dioxide (CO2) inflators on TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices, accomplish the following: (a) Visually inspect the CO2 inflators for cracks and chipping and, if necessary, replace CO2 inflators with serviceable parts in accordance with Paragraph 2, Accomplishment Instructions of Switlik Parachute Company, Inc., Service Bulletin No. 25-00-19, dated September 8, 1987. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581, may adjust the compliance time specified in this AD. Switlik Service Bulletin No. 25-00-19, dated September 8, 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 Switlik Parachute Co., Inc., 1325 East State Street, P.O. Box 1328, Trenton, New Jersey 08607. This document may also be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket No. 88-ANE-05. This amendment (39-6075, AD 89-06-01) becomes effective on April 3, 1989.
88-21-06: 88-21-06 ROLLS-ROYCE plc: Amendment 39-6031. Applies to Rolls-Royce plc (R-R) (Formerly Rolls- Royce Limited) Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, and 542 series turboprop engines and all variants. Compliance is required as indicated, unless already accomplished. To prevent low cycle fatigue failure of high pressure (HP) impellers and low pressure (LP) impellers, accomplish the following: (a) Remove from service HP impellers installed in Dart Mks. 506, 510, 511, 514, and all variants, in accordance with the following schedule: (1) HP impellers to Mod 844 standard which have accumulated 8,000 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (2) HP impellers to Mod 1455 standard which have accumulated 8,600 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (3) HP impellers to Mod 844 standard which have accumulated less than 8,000 total flights since new on the effective date of this AD, at or prior to accumulating 8,400 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. (4) HP impellers to Mod 1455 standard which have accumulated less than 8,600 total flights since new on the effective date of this AD, at or prior to accumulating 9,000 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. NOTES: (1) Total flights since new is defined as the total number of flights accumulated by the part since first installation in an engine. This total includes all Mod standards the part has operated under. (2) This action establishes a new Overhaul Manual Chapter 5 life limit for HP impellers, as noted in items (a)(3) and (a)(4) above. (3) Reference R-R Service Bulletin (SB) DA72-496, dated June 1986. (b) Remove from service HP impellers installed in Dart Mks. 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Life Limit in Number of Flights Dart Mk. Pre-Mod 797 Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 Mod 1475 525 thru 529 4,500 11,000 14,000 NC NC 531 and 532 4,500 11,000 14,000 NC NC 542 NA NA 12,000 16,000 14,500 (Since incorp. of Mod 1455) NA - Model not applicable to specific impeller. NC - Life limits not covered by this AD. Information relating to these impellers is contained in the manufacturer's appropriate overhaul manual. NOTE: The above noted HP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have notchanged. This section is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (c) Remove from service LP impellers installed in Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Limit in Number of Flights Dart Mk. Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 506 10,500 11,250 11,250 510 10,500 11,250 11,250 511 10,500 11,250 11,250 514 10,500 11,250 11,250 525 thru 529 9,000 9,000 9,000 531 and 532 9,000 9,000 9,000 542 NA 9,000 9,000 NA - Model not applicable to specific impeller. NOTES: (1) LP impellers to Mod 1455 Part 1 standard (manufactured by R-R to this standard) are not affected by this AD. Life limits for this part are quoted in the overhaul manual, Chapter 5, "Time Limits". (2) The above noted LP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have not changed. This AD, with respect to LP impeller life limits, is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (3) Rolls-Royce Dart SB 72-463 also pertains to LP impeller life limits. (d) Aircraft may be ferried in accordance with provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance schedules specified in this AD. This amendment supersedes Amendment 39-1734 (38 FR 27819), AD 73-21-04. This amendment, 39-6031, becomes effective on November 6, 1988.