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88-03-02: 88-03-02 BRITISH AEROSPACE: Amendment 39-5835. Applies to all Model H.S. 748 series airplanes, which have been modified in accordance with British Aerospace (BAe) Service Bulletins 57/31, 57/32, or 57/33, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent further cracking which could lead to reduced structural capability of the wing, accomplish the following: A. On airplanes previously modified in accordance with BAe Service Bulletin 57/31 or 57/33, inspect and modify the lower wing skins in accordance with BAe Service Bulletin 57/81, Revision 1, dated October 1985, prior to 7,500 hours since modification in accordance with BAe Service Bulletins 57/31 or 57/33, or within the next 750 hours time in service after the effective date of this AD, whichever occurs later. B. On airplanes previously modified in accordance with BAe Service Bulletin 57/32, inspect and modify the lower wing skins in accordance with BAe Service Bulletin 57/82, Revision 1, dated November 1985, prior to 10,000 hours since modification in accordance with BAe Service Bulletin 57/32, or within the next 750 hours time in service after the effective date of this AD, whichever occurs later. C. Any cracks found during the inspections required by paragraphs A. or B., above, must be repaired, prior to further flight, in accordance with BAe Service Bulletin 57/81, Revision 1, dated October 1985, or BAe Service Bulletin 57/82, Revision 1, dated November 1985, as applicable. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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 British Aerospace, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 1, 1988.
2005-05-20: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2005-05-20 that was sent previously to all known affected U.S. operators of certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-300, 747-400, 747-400D, 747SP, 747SR, 767-200, 767-300, 777- 200, 777-300, and 777-300ER series airplanes by individual notices. This AD requires modification of certain flight deck door electronic equipment. This AD results from a report indicating that this equipment is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.
99-21-01: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA- 360C, SA-365C, C1, and C2 helicopters. This action requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. This condition if not corrected could result in loss of electrical continuity, which could cause loss of critical rotorcraft electrical systems and subsequent loss of control of the helicopter.
99-20-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires modification of the pressure web of the nose landing gear wheel well. This amendment is prompted by reports of fatigue cracks in the pressure web of the nose landing gear wheel well. The actions specified by this AD are intended to prevent cracking of the pressure web of the nose landing gear wheel well, which could result in loss of airplane pressurization.
89-13-03: 89-13-03 GQ PARACHUTES LTD: Amendment 39-6221. Applicability: Type 350 Parachute Assemblies (P/N's MRI GQ 1277, MRI GQ 1304 and MRI GQ 1325), 850 Parachute Assemblies (P/N's MRI GQ 1284, MRI GQ 1315 and MRI GQ 1330), and 4.8m SAC Parachutes (P/N's MRI GQ 1308 and MRI GQ D 22918/2). Compliance: Required as indicated, unless already accomplished. To prevent the use of FAA approved canopies which may contain understrength material, accomplish the following prior to next use after the effective date of this AD: (a) Perform an acid test on each mesh panel, in accordance with page 11 of GQ Parachutes Ltd. Service Bulletin (SB) No. 25-01, dated January 18, 1989. Those canopies found to be free of acid contamination may be approved for return to service. (b) For those canopies found to have acid contamination, perform the acid neutralization, pH test, and tensile test, in accordance with pages 5 and 6 of GQ Parachutes Ltd., (SB) No. 25-01, dated January 18, 1989. Those canopies having a pH value greater than 5.5 and a minimum tensile strength of 180 N/25mm (405.5 lbs./in.) may be approved for return to service. For those canopies found to have a pH value of 5.5 or less and/or a tensile strength less than 180 N/25mm (40.5 lbs./in.), remove or obliterate the TSO-C23c marking. (c) In lieu of compliance with paragraphs (a) and (b) above, the TSO-C23c markings must be removed or obliterated and the parachute must not be used as an approved parachute. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance times specified in this AD or approve an equivalent means of compliance with this AD. The repair and inspection procedures shall be done in accordance with GQ Parachutes Ltd. Service Bulletin No. 25-01, dated January 18, 1989. 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 GQ Parachutes Ltd., Portugal Road, Woking, Surrey, GU21 5JE England. Copies may be inspected at the Federal Aviation Administration, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, DC 20591. This amendment (39-6221, AD 89-13-03) becomes effective on July 31, 1989.
2006-07-18: The FAA is adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD requires a one- time inspection of the interior of the internal elevator torque tube of each elevator control surface for oxidation and corrosion, and corrective actions. This AD results from corrosion in torque tubes of the elevators found during scheduled maintenance. We are issuing this AD to detect and correct corrosion in the torque tubes of the elevators, which could lead to an unbalanced elevator and result in reduced controllability of the airplane.
87-20-06: 87-20-06 AIRBUS INDUSTRIE: Amendment 39-5734. Applies to Model A310 series airplanes with serial numbers listed in Airbus Service Bulletin A310-29-2010, Revision 3, dated August 21, 1985, certificated in any category. Compliance is required within 700 hours time in service after the effective date of this AD, unless previously accomplished. To prevent failure of the ram air turbine (RAT) extension system and ensure deployment of the RAT when required, accomplish the following: A. Test, inspect, and rework, if necessary, the RAT uplock hook and roller in accordance with Airbus Industrie Service Bulletin A310-29-2010, Revision 3, dated August 21, 1985. B. Repeat the tests, inspections, and necessary rework required by paragraph A., above, at intervals not to exceed 1,400 hours time in service. C. Incorporation of both Modification AI-5876 described in Airbus Industrie Service Bulletin A310-29-2011, Revision 1, dated September 2, 1986, and Modification AI 5958 described in Airbus Industrie Service Bulletin A310-29-2012, Revision 1, dated September 2, 1986, constitutes terminating action for the repetitive inspection requirements of paragraph B. of this AD. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective October 30, 1987.
99-21-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires revising the Airplane Flight Manual (AFM) for operation in the rain, and modifying the anemometric static ports. This action also provides for optional terminating action for the requirements of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to limit or prohibit the use of the autopilot and flight director during the descent and approach to land in the rain, and to prevent fluctuations and erratic indications in the vertical speed, airspeed, and altitude readings in the cockpit during the descent and approach to land in the rain; such conditions could result in reduced controllability of the airplane during the descent and approach to land in the rain.
85-14-09: 85-14-09 McDONNELL DOUGLAS: Amendment 39-5096. Applies to McDonnell Douglas Model DC-10 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo assure the fire containment capability of the lavatory waste containers, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this airworthiness directive (AD), modify the H/J type lavatory waste containers in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 25-330, January 25, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to abase in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective August 16, 1985.
99-20-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modification of the 90VU electronics rack umbrellas, the 91VU upper shelf assembly, the cockpit drain circuit, and the electrical wire routing above the 90VU electronics rack. 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 damage to computer electrical connectors due to ingress of water into the avionics bay, which could result in malfunctioning of the avionics computers.