Results
98-22-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model SN 601 (Corvette) series airplanes, that requires repetitive inspections to detect discrepancies of the upper and lower reinforcement panels and panel fasteners of the wing roots; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent debonding of the upper and lower reinforcement panels of the wing roots, which could result in reduced structural integrity of the wing.
67-14-01: 67-14-01 AIR and SPACE: Amdt. 39-405 Part 39 Federal Register April 29, 1967. Applies to Model 18A Gyroplanes Equipped with Air and Space Rotor Blades. Before further flight of any Air and Space Model 18A gyroplane, unless already accomplished, modify the rotor blades in accordance with Air and Space Manufacturing, Inc. Service Bulletin No. 15, dated December 27, 1966, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. Upon completion of this modification the rotor blade set need not be rebalanced, but must be tracked before return to service. NOTE: Pursuant to Air and Space Manufacturing, Inc. Maintenance and Rigging Manual, page 30, Section M, no separations are permitted in the leading edge protective strip of the rotor blade. If separation is detected, the blade should be discarded unless a repair is authorized by the Chief, Engineering and Manufacturing Branch, FAA Central Region. This directive effective April29, 1967 and supersedes the telegraphic airworthiness directive of January 17 on the subject.
67-15-04: 67-15-04 SUD AVIATION: Amdt. 39-396 Part 39 Federal Register April 14, 1967. Applies to Model SE 3130 Alouette II Helicopters. Compliance required as indicated. To detect cracks in the tail rotor gear box drive shaft, Sud Aviation P/N 3130-66-22-002, accomplish the following: (a) Within the next 80 hours' time in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and thereafter at intervals not to exceed 180 hours' time in service from the last inspection, inspect the tail rotor gear box drive shaft, Sud Aviation P/N 3130-66-22-002, for cracks using dye penetrant in accordance with Sud Service No. 65-30, or later SGAC-approved issue, or an FAA-approved equivalent. (b) If cracks are detected during the inspection required by (a) of this AD, replace tail rotor gear box drive shaft P/N 3130-66-22-002 with new tail rotor gear box drive shaft P/N 3130-66-22-007. (c) Repetitive inspections required by (a) of this AD may be discontinued after new replacement tail rotor gear box drive shaft P/N 3130-66-22-007 is installed. This directive effective May 14, 1967.
2018-19-12: We are superseding Airworthiness Directive (AD) 2015-17-04, which applied to certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2015-17-04 required replacement of left and right fixed control rods and lever assemblies of the elevator control system. This AD adds a detailed visual inspection of the key washers and self-locking nuts of the elevator control linkages and corrective actions if necessary. This AD was prompted by reports of a disconnect between the elevator lever and control rod and a report indicating that certain revisions of the service information were missing instructions for proper installation of certain key washers. We are issuing this AD to address the unsafe condition on these products.
98-11-14: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-11-14 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 205A-1 and 205B helicopters by individual letters. This AD requires inspecting the trunnion assembly or tail rotor flapping stop (flapping stop), whichever is applicable, installing a trunnion assembly or flapping stop, if necessary; and replacing the tail rotor yoke (yoke). This amendment is prompted by an accident involving a BHTI Model 205A-1 helicopter in which the yoke failed during flight. This condition, if not corrected, could lead to failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
67-07-03: 67-07-03 DOUGLAS: Amdt. 39-356 Part 39 Federal Register March 2, 1967. Applies to Model DC-9 Airplanes Equipped With the Sperry SP-50A Autopilot. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo prevent an unsafe condition which may result when the autopilot does not disengage when the control wheel disconnect button is used, accomplish the following: \n\n\t(a)\tFor airplanes having Sperry SP-50A autopilot control panels with 1,500 or more hours' time in service on the effective date of this AD, comply with (d) prior to completing the next 50 hours' time in service. \n\n\t(b)\tFor airplanes having Sperry SP-50A autopilot control panels with less than 1,500 hours' time in service on the effective date of this AD, comply with (d) prior to completing 1,550 hours' total time in service. \n\n\t(c)\tOperators who have not kept records of hours' time in service of individual Sperry SP-50A autopilot control panels shall substitute hours' time in service for the airplane or airplanes in which the individual autopilot control panel was installed. \n\n\t(d)\tInstall a placard in clear view of the pilot with the following information: \n\n\tAutopilot(s) must be turned off when operating below 3,000 feet above ground level in a terminal area. Verify by position of the control panel engage lever. \n\n\t(e)\tThe placard installed in accordance with (d) may be removed when the Sperry SP- 50A autopilot control panel switches have been reworked to Sperry Service Bulletin TA-693-37. \n\n\tThis directive effective March 2, 1967.
67-06-01: 67-06-01 BELL: Amdt. 39-348, Part 39, Federal Register February 4, 1967. Applies to Model 204-B Helicopters Equipped With Tail Rotor Hub and Blade Assembly, P/N 204-011-701- 9 or 204-011-701-15. Compliance required as indicated. To assure proper balance and track of the tail rotor blades, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 25 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the date of the last tracking, the hub and blade assembly must be tracked in accordance with the Bell Model 204B Maintenance Manual, Section VI. (b) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 200 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service from the date of the last balancing, the hub and blade assembly must be balanced in accordance with the Bell Model 204B Maintenance Manual, Section VI. (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive balancing and tracking 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 interval increase for such operator. (Bell Service Bulletin 204B-1 also pertains to this subject.) This directive effective February 9, 1967.
2000-22-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires replacement of the existing wire between certain circuit breakers with an improved wire. The actions specified by this AD are intended to prevent overheating of the wire between certain circuit breakers, which could result in smoke emissions in the cockpit. This action is intended to address the identified unsafe condition.
2018-19-17: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a revision of a certain airworthiness limitations item (ALI) document, which specifies new or more restrictive instructions and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. We are issuing this AD to address the unsafe condition on these products.
52-20-02: 52-20-02 WRIGHT: Applies to All Models C18BA and C18BD Engines. Compliance required as soon as possible but not later than October 31, 1952. To prevent crankpin sludge from washing into the master rod bearing oil supply passages causing failure of the bearing, the use of oil dilution must be discontinued and the dilution lines disconnected or removed. This restriction on oil dilution is to continue until an adequate sludge controlling device is developed and incorporated in these engines.