Results
98-24-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France (ECF) Model AS 332C, AS 332L, AS 332L1, and AS 332L2 helicopters. This action requires inserting instructions into the Model AS 332C, AS 332L, AS 332L1, and AS 332L2 Rotorcraft Flight Manuals (RFMs) regarding actions to take if either the "OVSP 1" or "OVSP 2" amber warning light illuminates. This action also requires, for the Model AS 332C, AS 332L, and AS 332L1 helicopters, measuring the vibration levels of the engine-to-main gearbox (MGB) shaft, inspecting the torque on the MGB coupling bolts, and conducting an engine-to-MGB coupling 23,000 revolutions per minute (RPM) input check. This amendment is prompted by an accident involving a Model AS 332L1 helicopter in which the helicopter experienced an engine overspeed resulting in failure of both engines. The actions specified in this AD are intended to prevent failure of the rotor drive engine-to-MGB coupling, which, if undetected, could result in an engine overspeed leading to an uncontained engine turbine wheel burst and subsequent loss of control of the helicopter.
76-24-03: 76-24-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-2776. Applies to all Pratt & Whitney Aircraft JT9D turbofan engines containing fan blades, part numbers 658931, 718431, 726221, 734721, 735831, 735841, 740421, 740431, 740441, 740521, 741131, 741141, 748231, 748321, 748931, 750621, 750631, 758031, 758181, 758191, 758221, 760631, 760641, 760721, 760731, 760831, 760841, 760941, 761041, 761121, 761131, and 761141. Compliance required as follows unless already accomplished. To preclude failure of fan blades due to fatigue originating from undetected foreign object damage, inspect the critical areas of the blades in accordance with the procedures given in PWA ASB 4573, dated March 26, 1976, or later FAA approved revision, as follows: 1. Visually inspect all fan blades within the next 600 hours time in service after the effective date of this AD, and every 600 hours time in service thereafter. 2. Eddy current inspect all fan blades that have been previously damaged and blend repaired within the next 600 hours time in service after the effective date of this AD. 3. Eddy current inspect fan blades reworked per PWA Service Bulletins 4124 or 4262, without prior or subsequent damage or blend repairs, within the next 3500 hours time in service after the effective date of this AD. If foreign object damage with a depth of .005 inch or more is found in the critical area, blend and inspect in accordance with Option 1 or Option 2 procedures given in PWA ASB No. 4573, dated March 26, 1976, or later FAA approved revision. (NOTE: The AD does not change the present fan blade blend limits given in the JT9D engine manual.) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA New England Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data tojustify the increase for that operator. The manufacturer's specifications and procedures identified and described in this directive are 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 these documents from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the New England Region. This amendment becomes effective December 30, 1976.
98-21-09: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-21-09, which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires installing fuel tank vent tube(s), with modified attachment to the mast tube, if not previously accomplished; installing a spring into the flexible tube leading to the main fuel tank; and installing a spring into the flexible tube leading to the auxiliary fuel tank, if an auxiliary fuel tank is installed. This amendment is prompted by an incident in which the flexible vent connecting the rigid vent tube to the main fuel tank kinked, resulting in fuel starvation and a hard landing after uncommanded engine shutdown. The actions specified by this AD are intended to prevent fuel starvation, loss of engine power, and a subsequent forced landing.
2022-11-04: The FAA is superseding Airworthiness Directive (AD) 2020-26- 13, which applied to certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. AD 2020-26-13 required establishing the life limit for certain part-numbered horizontal stabilizer root fittings FWD (forward root fittings) and certain part-numbered stabilizer strut fittings. AD 2020-26-13 also required repetitively inspecting certain parts, and depending on the inspection results, removing parts from service. Finally AD 2020-26-13 prohibited installing certain stabilizer assemblies on any helicopter. Since the FAA issued AD 2020-26-13, the manufacturer notified the FAA that due to an error in the service information, certain part numbers in AD 2020-26-13 are incorrect. Also, the FAA determined that additional inspections are required to address the unsafe condition. This AD retains certain requirements and the prohibition for installing certain stabilizer assemblies on any helicopter from AD 2020-26-13, corrects certain part numbers, and requires additional repetitive inspections. The actions of this AD are intended to address an unsafe condition on these products.
98-24-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10 sailplanes. This AD requires replacing the flap drive rocker, part number (P/N) 10SW-RMW, with a modified flap drive rocker. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the flap drive rocker caused by the design of the original part, which could result in loss of lateral control and wing flap control with consequent reduced and/or loss of sailplane control.
2013-11-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of hydraulic fluid contamination (including contamination caused by hydraulic fluid in its liquid, vapor, and/or solid (coked) form) found in the strut forward dry bay. This AD requires repetitive general visual inspections of the strut forward dry bay for the presence of hydraulic fluid, and related investigative and corrective actions (including checking drain lines for blockage due to hydraulic fluid coking, and cleaning or replacing drain lines to allow drainage) if necessary. We are issuing this AD to detect and correct hydraulic fluid contamination of the strut forward dry bay, which could result in hydrogen embrittlement of the titanium forward engine mount bulkhead fittings, and consequent inability of the fittings to carry engine loads, resulting in engine separation. Hydraulic embrittlement also could cause a through-crack formation across the fittings through which an engine fire could breach into the strut, resulting in an uncontained strut fire.
98-24-12: This amendment adopts a new airworthiness directive (AD) that applies to all Ursula Hanle (Hanle) Model H101 "Salto" sailplanes. This AD requires replacing the airbrake lever with one of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the airbrake from deploying during high g maneuvers, which could result in an overstressing effect on the airframe with consequent reduced sailplane control.
98-24-07: This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300, EA-300S, and EA-300L airplanes. This AD requires repetitively inspecting the rudder pedal for proper alignment, the safety control stop for wear and proper clearance, the rudder cables for elongation, and the rudder pedal footrest for cracks. This AD also requires correcting or replacing any discrepant part, as applicable. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the rudder pedal footrest caused by overloading the rudder pedal safety control stop, which could result in loss of directional control of the airplane.
90-02-05: 90-02-05 GULFSTREAM: Amendment 39-6472. Docket No. 89-NM-177-AD. Applicability: All Model G-II (G-1159), G-III (G-1159A), G-IIB (G-1159B) and certain G-IV, Serial Numbers 1000 through 1092, series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent an airplane taking off in an unsafe takeoff configuration, accomplish the following: A. For all Model G-II (G-1159) and G-IIB (G-1159B) series airplanes: Within 25 hours time- in-service after the effective date of this AD, and thereafter at intervals not to exceed 150 hours time-in- service, perform an operational check of the takeoff warning system, and repair, if necessary, in accordance with Gulfstream Aerospace Customer Bulletin Number 388, Amendment 1, dated August 15, 1989. If the system does not function properly, it must be repaired prior to further flight, in accordance with the Customer Bulletin. B. For all Model G-III (G-1159A) series airplanes: Within 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 150 hours time-in-service, perform an operational check of the takeoff warning system, in accordance with Gulfstream Customer Bulletin Number 106, dated May 1, 1989. If the system does not function properly, it must be repaired prior to further flight, in accordance with the Customer Bulletin. C. For Model G-IV series airplanes, Serial Numbers 1000 through 1092: Within 25 hours time-in-service after the effective date of this AD, perform an operational check and modification of the takeoff range warning indication switches, in accordance with Gulfstream Aircraft Service Change Number 122, dated May 31, 1989. A functional check must be repeated at intervals not to exceed 150 hours time- in-service. If the system does not function properly, it must be repaired prior to further flight, in accordance with the Service Change. D. 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, Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI) or Principal Avionics Inspector (PAI), who will either concur or comment, and then send it to the Manager, Atlanta Aircraft Certification Office. E. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Gulfstream Aerospace Corporation, P.O. Box 2206, M/S D-10, Savannah, Georgia 31402-9980. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6472, AD 90-02-05) becomes effective on February 13, 1990.
2013-12-03: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-725A1-12 turbofan engines with fuel pump tube part number FW64852 installed. This AD requires removal of the affected fuel pump tube and its replacement with a part eligible for installation. This AD was prompted by the discovery that cracks have occurred in the affected fuel pump tube between the fuel metering unit and the main fuel pump. We are issuing this AD to prevent loss of fuel supply to the engine, which could result in in-flight engine shutdown of one or more engines, loss of thrust control and damage to the airplane.