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90-21-22: 90-21-22 BRITISH AEROSPACE: Amendment 39-6772. Docket No. 90-NM-136-AD. Applicability: All Model BAe 125-800A series airplanes, on which British Aerospace Modification 253244A has not been incorporated, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of a link pin and subsequent reduced structural integrity of the main landing gear (MLG), accomplish the following: A. Within 30 days after the effective date of this AD, with the airplane on wheels, lubricate the right and left MLG upper and lower torque link pivots (three per landing gear), in accordance with British Aerospace Service Bulletin 32-222, dated November 10, 1989. 1. If grease does appear in all places indicated in the service bulletin, no further action in accordance with this AD is required and the airplane may be returned to service. 2. If grease does not appear in all places indicated in the service bulletin, prior to further flight, disassemble that MLG, perform visual and dye penetrant inspections to detect defects (scoring, wear, necking, ovality, and/or blocked grease holes) and cracks in the pivot pins and bolts, and hand lubricate the torque link pivots, in accordance with the service bulletin. a. If the condition of the torque link pin or bolt reveals defects or cracks, prior to further flight, replace it with a serviceable part in accordance with the service bulletin. b. If the clearance between any torque link and the MLG is less than 0.002 inch, carefully abrade the surfaces of the bushes in the torque link to achieve the required .002 inch minimum/.0l0 inch maximum condition, in accordance with the service bulletin. c. At intervals not to exceed 50 landings, disassemble and repeat the special hand lubrication of the MLG upper and lower torque links, in accordance with the service bulletin. B. Incorporation of Modification 253244A, in accordance with British Aerospace Service Bulletin 32-222-3244A, Revision 1, dated March 5, 1990, constitutes terminating action for the repetitive lubrication procedures required by paragraph A.2.c. of this AD. C. 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Standardization Branch, ANM-113. D. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6772, AD 90-21-22) becomes effective on November 19, 1990.
2020-12-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report that a changed manufacturing process for the tail rotor blades (TRB) was implemented, affecting the structural characteristics of the blades and generating a new part number for these blades. This AD requires re-identifying each affected TRB having a certain part number and serial number and establishing a life limit for the new part numbers. This AD also prohibits installation of any affected TRB identified with the old part number on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2020-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent XWB-75, XWB- 79, XWB-79B, and XWB-84 model turbofan engines. This AD was prompted by analysis by the manufacturer of the low-pressure compressor (LPC) outlet guide vane (OGV) assembly and LPC OGV outer mount ring assembly. The analysis predicted that when the front engine mount is in the fail- safe condition, the most highly stressed LPC OGV outer mount ring assembly has a life that could be substantially less than one shop visit interval. This AD requires initial and repetitive inspections of the LPC OGV outer mount ring assembly and, depending on the results of the inspections, possible replacement of the LPC OGV outer mount ring assembly. The FAA is issuing this AD to address the unsafe condition on these products.
94-01-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Canadair Model CL-600-2B19 "Regional Jet" Series 100 airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to limit altitude and airspeed operations of the airplane under certain conditions of hydraulic system failure. This amendment is prompted by a report of sheared- off shear pins found on one airplane's elevator dampers. The actions specified in this AD are intended to prevent undampened vibration of the elevators in normal cruise conditions when combined with hydraulic system failures, a condition which could result in reduced controllability of the airplane.
95-21-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0100 and Model F28 Mark 0070 series airplanes. This action requires revising the Limitations Section of the Airplane Flight Manual to include information that will enable the flightcrew to identify failures of the emergency direct current (DC)/alternating current (AC) bus power supply and to take appropriate corrective actions. This amendment is prompted by one report indicating that a diode failed, which resulted in battery drain and loss of the emergency DC bus power supply; and another report indicating that the circuit breaker of the transformer rectifier unit No. 3 tripped, which resulted in the loss of the emergency DC/AC bus power supply. The actions specified in this AD are intended to ensure that the flightcrew is advised of the potential hazard related to failures of the emergency bus power supply, and the procedures necessary to address it.
78-22-08: 78-22-08 HILLER AVIATION: Amendment 39-3327. Applies to Model UH-12D and UH-12E helicopters, including the UH-12E 4-place configurations, which have been converted to turbine power in accordance with Soloy Conversions, Ltd., STC Nos. SH177WE and SH178WE respectively, certificated in all categories. Compliance required on or before January 1, 1979. To prevent loss of flight control or engine control, accomplish the following: (a) Modify the integrated collective and N2 engine control system in accordance with Soloy Conversions, Ltd., Service Bulletin 06-560 dated October 6, 1978, or later FAA approved revision. (b) Unless already accomplished, remove from service certain N1 and N2 engine control cables as identified in Soloy Conversions, Ltd., Service Bulletin 06-560 dated October 6, 1978, or later FAA approved revisions. Install replacement cables in accordance with the same bulletin. (c) An equivalent modification may be approved by the Chief, Engineering andManufacturing Branch, FAA, Northwest Region. 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 this document from the manufacturer, may obtain copies upon request to Soloy Conversions, Ltd., P.O. Box 60, Chehalis, Washington 98532. This document may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective November 30, 1978.
2020-11-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD requires a repetitive check of the fuel quantity indicating system (FQIS) fuel quantity calculation for the center wing tank (CWT) fuel quantity, developing a process to provide documentation to the flight crew that this check was done, and revising the existing airplane flight manual (AFM) to incorporate verification procedures and flight crew awareness. This AD was prompted by reports of discrepancies between the FQIS fuel quantity and the refueling truck uploaded fuel amount, followed by certain engine-indicating and crew-alerting system (EICAS) messages. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-19: 91-06-19 AEROSPATIALE (FORMERLY SUD-SERVICE/SUD AVIATION): Amendment 39-6939. Docket No. 91-NM-40-AD. Applicability: Caravelle SE 210 Model I, III, and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent collapse of the main landing gear (MLG) and consequent structural damage to the airplane, accomplish the following: A. Prior to the accumulation of 50 landings after the effective date of this AD, or within 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 2,500 landings, perform an ultrasonic inspection of the front hinge beam upper bearings on each MLG, in accordance with Figure 2 on page 18 of Messier-Hispano-Bugatti Service Bulletin 32-083, Revision 4, dated November 28, 1990. B. If defects are found as a result of the inspections required by paragraph A. of this AD, which are outside the limits specified in Messier-Hispano-Bugatti Service Bulletin 32-083, Revision 4, dated November 28, 1990, prior to further flight, remove the damaged MLG and perform an ultrasonic inspection of the hinge beam, an eddy current inspection following removal of the bushings, and a complete geometric check of the MLG, in accordance with the service bulletin. 1. MLG's which have been reconditioned in accordance with these procedures may only be returned to service provided that no defects are found. 2. If defects are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or replace affected part with a serviceable part of same part number. C. If no defects are found as a result of the inspections required by paragraph A. of this AD, and the MLG components have been overhauled, prior to further flight, accomplish the following. 1. Assemble in accordance with Overhaul Manual 32-1-61. 2. Accomplish geometric adjustment in accordance with Repair Document HS RA20017. 3. Accomplish eccentric adjustment in accordance with Repair Document HS RA20017 or Aeroservice Section 1, No. 82. 4. Repeat the inspection required by paragraph A. of this AD prior to the accumulation of 2,500 landings and thereafter at intervals not to exceed 2,500 landings. D. If no defects are found as a result of the inspections required by paragraph A. of this AD, and the MLG components have not been subjected to the procedures identified in paragraphs C.1., C.2., and C.3. of this AD during the last overhaul, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 50 landings until next overhaul, including a complete ultrasonic inspection of the hinge beam, an eddy current inspection following removal of bushings, and a complete geometric check of the MLG. 1. MLG's which have been inspected in accordance with this procedure may only be returned to serviceprovided that no defects are found. 2. If defects are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or replace affected part with serviceable part of same part number. 3. Following overhaul of the MLG components, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 2,500 landings. E. An 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. 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 information from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6939, AD 91-06-19) becomes effective on April 1, 1991.
93-24-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T93-24-51 that was sent previously to all known U.S. owners and operators of all Airbus Model A310 and A300-600 series airplanes by individual telegrams. This AD requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2. This amendment is prompted by a report that the pitch control on a Model A300-600 series airplane operated with stiffness. The actions specified by this AD are intended to prevent stiff operation of the pitch control and undetected loss of rudder travel limitation function.
2008-07-01: The FAA is superseding an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD currently requires initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently requires initial and repetitive replacements of 2nd stage turbines on 1B, 1D, and 1D1 engines only. This AD requires adding a 3,000 hour life limit to Arriel 1B 2nd stage turbine blades. This AD results from reports of failures of second stage turbine blades. We are issuing this AD to prevent failures of the 2nd stage turbine blades, which could result in uncommanded in-flight engine shutdown, and subsequent forced autorotation landing or accident. DATES: This AD becomes effective April 30, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 30, 2008.The Director of the Federal Register previously approved the incorporation by reference of Turbomeca Mandatory Alert Service Bulletins A292 72 0809, Update 1, dated October 4, 2005; and A292 72 0810, dated March 24, 2004; as of February 28, 2006 (71 FR 3754, January 24, 2006).