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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).
78-12-08: 78-12-08 AVCO LYCOMING: Amendment 39-3239. Applies to O-320-H series engines Serial Numbers L-101-76 through L-3829-76, L-3831-76, L-3843-76 through L-3859-76, L-3864-76, L-3866-76, L-3871-76, L-3902-76 through L-3907-76 and all O-320-H series engines overhauled (Remanufactured by Lycoming) before March 24, 1978. Compliance required within the next 10 hours in service, unless already accomplished. a. To prevent oil pump failures, remove, inspect and alter the oil pump body and replace the oil pump driving impeller with driving impeller P/N LW-15998 and the oil pump driven impeller with driven impeller P/N LW-15999 in accordance with AVCO Lycoming Service Bulletin No. 423 dated March 24, 1978, or FAA approved equivalent. b. Equivalent method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective June 20, 1978.
2020-11-06: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/ B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as flap actuator taper pins that were not swaged during the manufacturing process. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
92-27-05: 92-27-05 PIPER AIRCRAFT CORPORATION: Amendment 39-8438. Docket No. 91- CE-14-AD. \n\n\tApplicability: PA-31 Series airplanes (all models and serial numbers), certificated in any category. \n\n\tCompliance: Required the next time the aileron cables are disconnected for any reason, but no later than 12 calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent improper connection of the aileron control systems, which could result in loss of lateral control of the airplane, accomplish the following: \n\n\t(a)\tUsing red enamel paint, color code the aileron balance cable and the bellcrank lug of both aileron control systems in accordance with Figure 1 of this AD. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. \n\n\t(d)\tAll persons affected by this directive may examine any information that is applicable to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\t(e)\tThis amendment becomes effective on January 29, 1993. \n\n\n\t\t\t\tFIGURE 1 AD 92-27-05\n\t\tVIEW LOOKING THRU TOP WING SKIN (LEFT WING)\n\t\t\t\t RIGHT WING OPPOSITE
76-24-05: 76-24-05 ROLLS-ROYCE (1971) LIMITED: Amendment 39-2781. Applies to Rolls-Royce Bristol Viper Mk 601-22 engines installed, or being held for installation on Hawker Siddeley/Beechcraft Hawker Model DH/BH-125 series airplanes, certificated in all categories. Compliance is required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible turbine disc damage, replace the inner exhaust turbine cone assembly in accordance with the "Accomplishment Instructions" of Rolls-Royce Alert Service Bulletin No. 72-A69, dated May 1976, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, APO New York, N.Y. 09667. This amendment becomes effective December 14, 1976.
92-02-14: 92-02-14 AIRBUS INDUSTRIE: Amendment 39-8150. Docket 91-NM-255-AD. Applicability: Model A320 series airplanes through manufacturer's serial number 175, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the overwing emergency escape slides to deploy, accomplish the following: (a) Within 50 hours time-in-service after the effective date of this AD, perform an inspection of the flexible control cables on the right-hand and left-hand overwing emergency escape slides to ensure that the flexible control assembly on each overwing escape slide is correctly installed, in accordance with Airbus Industrie All Operator Telex (AOT) 25-02, dated May 16, 1991. (1) If each flexible control assembly is correctly installed, no further action is required. (2) If a flexible control assembly is incorrectly installed, prior to further flight, reconnect the assembly, in accordance with the AOT.(b) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and reconnections of the flexible control assemblies and release cable assemblies required by this AD shall be done in accordance with Airbus Industrie All Operator Telex 25-02, dated May 16, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Standardization Branch, ANM-113, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (e) This amendment (39-8150, AD 92-02-14) becomes effective on March 2, 1992.
77-07-09: 77-07-09 AVIONS MARCEL DASSAULT/BREGUET AVIATION (AMD/BA): Amendment 39-2867. Applies to Falcon 10 airplanes, certificated in all categories, equipped with Grumman tailpipe, P/N F10A5B10003-7, installed without back-up ring, P/N F10A5B10606-11. Compliance is required as indicated, unless already accomplished. To prevent the possible loss of the tailpipe, accomplish the following: (a) For tailpipes having more than 750 hours time in service on the effective date of this AD, comply with paragraph (c) of this AD within 90 days or 150 hours time in service after the effective date of this AD, whichever occurs first. (b) For tailpipes having 750 hours or less time in service on the effective date of this AD, comply with paragraph (c) of this AD prior to the accumulation of 900 hours total time in service. (c) Replace tailpipe, P/N F10A5B10003-7, with a new part of the same part number, or with a serviceable part of improved design, P/N F10A5RDB20217-3, and in either case install with back-up ring P/N F10A5B10606-11. (Falcon 10 Service Bulletin No. 0129, dated December 21, 1976, covers this subject.) This amendment becomes effective April 18, 1977.