Results
2004-05-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes, and Model MD-90-30 airplanes. This action requires repetitive inspections to detect cracking of the shock strut cylinders of the left and right main landing gears (MLG), and replacement of any cracked shock strut cylinder. This action is necessary to prevent failure of the shock strut cylinders of the MLGs due to cracking, which could result in collapse of the MLGs and consequent reduced controllability during landing. This action is intended to address the identified unsafe condition.
2010-26-11: We are adopting a new airworthiness directive (AD) for the Kaman Model K-1200 helicopters. This AD requires revising the Limitations section of the Instructions for Continued Airworthiness (ICA) by establishing a life limit of 8,000 hours time-in-service (TIS) for each main rotor blade (blade) set. Also, this AD requires removing each blade set from service if it has accumulated 8,000 or more hours time-in-service (TIS). This AD also requires replacing certain blade sets with airworthy blade sets at specified intervals based on the blade set serial number (S/N). This AD was prompted by an accident and the subsequent discovery of cracks in multiple blade spars. We are issuing this AD to prevent blade failure and subsequent loss of control of the helicopter.
2021-10-20: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport Regional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by reports of temporary loss of all display units and the integrated electronic standby instrument (IESI). This AD requires revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to update a systems limitation, limiting dispatch with certain equipment inoperative, performing an operational test of a certain contactor and an electrical test of a certain battery toggle switch, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
67-06-04: 67-06-04 HARTZELL: Amendment 39-725. Applies to Models HC-93Z30/19152-5 1/2, HC-B3Z30/10152-5 1/2, HC-B3W30/10152-5 1/2, HC-B3Z30/10160-6 and HC-B3W30/10160-6 Propellers. Installed on Pratt and Whitney Model R985 Series Engines. Compliance required as indicated. To prevent propeller blade shank failures accomplish the following: (a) For blades previously inspected by a procedure described in (c), reinspect in accordance with (c) every 600 hours' time in service from last inspection (b) For all other blades: (1) Blades with 300 hours' time in service, inspect in accordance with (c) within the next 25 hours' time in service after the effective date of this AD and reinspect every 600 hours' time in service from the last inspection. (2) Blades with less than 300 hours' time in service, inspect in accordance with (c) prior to the accumulation of 325 hours and reinspect every 600 hours' time in service from the last inspection (c) Remove blades from propeller and inspect each blade in the shank retention area for cracks using penetrant inspection method or equivalent approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. Replace before further flight any cracked blade with a new blade or a blade that has been inspected according to this AD. Effective February 21, 1967. Revised March 4, 1969.
2004-04-07: The FAA is superseding two existing airworthiness directives (ADs) for GE CF6-80 series turbofan engines with certain stage 1 high- pressure turbine (HPT) rotor disks. Those ADs currently require initial and repetitive inspections of certain stage 1 HPT rotor disks for cracks in the bottom of the dovetail slot. This action retains the initial inspection requirement, as a qualification for the mandatory rework procedures for certain disks, and continues repetitive inspections only for the disks for which the rework procedures are not yet defined. This action requires reworking certain disks before further flight. In addition, this AD expands the population of affected engines and removes certain CF6-80E1 series disks from service. This AD results from the manufacturer's investigation and development of a rework procedure that chamfers the aft breakedge of the dovetail slot bottom. We are issuing this AD to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.
71-17-04 R1: 71-17-04 R1 SIAI-MARCHETTI: Amendment 39-1266 as amended by Amendment 39-4516. Applies to Models S.205-18/F, S.205-18/R, S.205-20/F, S.205-20/R, S.205-22/R, S.208, and S.208A airplanes (all serial numbers) certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To prevent failure of the main landing gear, accomplish the following: (a) Before further flight, unless already accomplished within the last 50 hours time- in-service, and thereafter at intervals not to exceed 100 hours time-in-service from the last check, visually check, using a magnifying glass of at least 5 power, the main landing gear wheel axle-to- strut-tube fittings for cracks in accordance with "INSTRUCTIONS" paragraph (a), SIAI- Marchetti Service Bulletin No. 205B27A, dated October 7, 1977. If cracks are found, comply with paragraph (c) or (d) as appropriate. The checks required by this paragraph may be performed by the pilot, who must make the prescribed maintenance record entry indicating compliance with paragraph (a) of this AD. (b) Within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished within the last 450 hours time-in-service and thereafter at intervals not to exceed 500 hours time-in-service from last inspection, inspect the main gear wheel axle-to- strut-tube fittings for cracks, using a dye penetrant method, in accordance with "INSTRUCTIONS" paragraph (b), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977. If cracks are found, comply with paragraph (c) or (d) as appropriate. (c) If cracks which do not extend to the lateral external surface of a fitting are found during a check required by paragraph (a) or during an inspection required by paragraph (b), within the next 50 hours time-in-service, and thereafter at intervals not to exceed 50 hours time- in-service from the last inspection, inspect the main landing gear wheel axle-to-strut tube fittings for cracks, using a dye penetrant method in accordance with "INSTRUCTIONS" paragraph (b), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977. (d) If cracks are found on the lateral external area of a fitting during a check required by paragraph (a), or during an inspection required by paragraph (b) or (c), before further flight replace the cracked part with a new part of the same part number, in accordance with "INSTRUCTIONS" paragraph (d.1), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977, or FAA approved equivalent, and continue to check in accordance with paragraph (a) and continue to inspect in accordance with paragraph (b). (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. Amendment 39-1266 became effective upon publication in the Federal Register to all persons except those persons to whom it was made immediately effective upon receipt of the airmail letter dated July 16, 1971, which contained this amendment. This Amendment 39-4516 becomes effective December 27, 1982.
2010-26-03: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires fabricating and installing a placard incorporating information that limits operation when there is known or forecast icing and requires replacing a section of the pneumatic supply tube for the tail deice system with a new tube of a different material. This AD requires fabricating and installing a placard incorporating information that limits operation when there is known or forecast icing and requires replacing the entire length of the pneumatic supply tube for the tail deice system with a new tube of a different material. This AD was prompted by reports of two failures of the pneumatic supply tube for the tail deice system outside the area covered by AD 2008-07-10. We are issuing this AD to prevent collapsed pneumatic supply tubes, which could result in failure of the tail deice boots to operate. This failure could lead to loss of control in icing conditions.
2021-10-24: The FAA is superseding Airworthiness Directive (AD) 2015-25-04 for Agusta S.p.A (now Leonardo S.p.a.) Model A109A and A109A II helicopters. AD 2015-25-04 required inspecting the slider assembly pitch control (slider) for play and replacing the slider if the play exceeds certain limits. This AD was prompted by further investigation that led to the determination that the play was caused by a manufacturing issue. This AD retains certain requirements of AD 2015- 25-04, requires replacing certain part-numbered sliders as a terminating action for the inspections, and prohibits installing the affected part on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
66-19-02: 66-19-02 CESSNA: Amdt. 39-270 Part 39 Federal Register August 4, 1966. Applies to Models 210 and 210A Airplanes, Serial Numbers 616, 618, 57001 through 57575, and 21057576 through 21057840. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent engine power failures caused by the loss of fuel flow resulting from the uncovering of the fuel tank outlet during landing approaches and prolonged slips, install an operating limitation placard, reading as follows, adjacent to the fuel gauges: "Avoid landing approach in red arc and over 30 seconds slips under 1/2 tank (Reference Owner's Manual)". (Cessna Service Letter 65-39 pertains to this subject.) This directive effective August 14, 1966.
91-09-02: 91-09-02 BOEING: Amendment 39-6983. Docket No. 90-NM-269-AD. \n\n\tApplicability: Model 757 series airplanes, equipped with Rolls Royce RB211-535 engines; as listed in Boeing Service Bulletin 757-76-0008, dated March 22, 1990; certificated in any category. \n\n\tCompliance: Required within the next 3,000 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent chafing of the thrust control cable assemblies, wire bundle clamps, and wire bundles, accomplish the following: \n\n\tA.\tAccomplish the following in accordance with Boeing Service Bulletin 757-76- 0008, dated March 22, 1990: \n\n\t\t1.\tInspect thrust control cable assemblies for damage, and replace any damaged thrust control cable assemblies prior to further flight; \n\n\t\t2.\tInspect the wire bundles for evidence of chafing, and repair any chafed wire bundles prior to further flight; and \n\n\t\t3.\tModify the wire bundles. \n\n\tB.\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6983, AD 91-09-02) becomes effective on May 28, 1991.