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90-17-16: 90-17-16 AIRBUS INDUSTRIE: Amendment 39-6703. Docket No. 90-NM-52-AD. Applicability: Model A300, A310, and A300-600 series airplanes, on which Modification 6240 has not been incorporated, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect corrosion in the passenger/crew door emergency operation cylinders, accomplish the following: A. Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed 18 months, inspect the dampers and emergency operation cylinder strikers, in accordance with Airbus Industrie Service Bulletins A300-52-130, or A310-52-2018, or A300-52-6008, all dated December 12, 1985, as applicable. NOTE: The above-referenced service bulletins reference Ratier-Figeac Service Bulletin No. 701-2650-52-3 for additional instructions. B. If corrosion is found, repair, prior to further flight, in accordance with Ratier- Figeac Service Bulletin No. 701-2650-52-3. C. Incorporation of Modification 6240, in accordance with Airbus Industrie Service Bulletins A300-52-132, Revision 2, dated October 9, 1987; or A300-52-6010, Revision 3, dated July 15, 1989; or A310-52-2020, Revision 4, dated July 15, 1989; as applicable, constitutes terminating action for the repetitive inspection required by paragraph A., of this AD. NOTE: The above referenced service bulletins reference Ratier-Figeac Service Bulletin No. 701-5000-52-5 and 701-5000-52-7 for additional modification instructions. 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, 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 Manager, Standardization Branch, ANM-113. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6703, AD 90-17-16) becomes effective on September 21, 1990.
83-08-05: 83-08-05 BEECH: Amendment 39-4637. Applies to Models 60, A60, and B60 (S/Ns P-4 through P-577, P-579 through P-587, P-589, and P-592) airplanes, having optional air conditioning systems installed, certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD unless already accomplished. To prevent loss of power or inflight fires caused by a loose air conditioner compressor clutch pulley contacting an adjacent fuel line, accomplish the following: a) Modify the air conditioner compressor installation by incorporating the appropriate Beech Kit No. 60-5026-1S or No. 60-5026-3S as identified by criteria in Beechcraft Class I Service Instructions No. 1236 or; b) Deactivate the air conditioner system in accordance with the following: (1) Remove the air conditioner compressor belt. (2) Pull and block the air conditioning circuit breaker so that it cannot be inadvertently reset. (3) Install a permanent placard in full view of the pilot near the cabin comfort control which reads as follows: "AIR CONDITIONER DEACTIVATED." c) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. d) An equivalent means of compliance with this AD may be used, if approved, by the Manager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. This amendment becomes effective on May 3, 1983.
2000-20-05: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM), and either installing hydraulic tube assemblies incorporating a check valve, or visually inspecting the check valve if already installed and corrective action, if necessary. 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 the landing gear doors from becoming blocked from opening during application of emergency procedures in the event of a loss of hydraulics.
86-20-02: 86-20-02 AEROSPATIALE: Amendment 39-5429. Applies to Model ATR-42 airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent uncommanded pitch excursions from occurring during flight in icing conditions at a flap setting of 45 degrees, accomplish the following: A. Within seven days after effective date of this AD, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Flap extension in excess of 30 degrees is not authorized during any normal or abnormal flight conditions. During an emergency landing or ditching, as required by the flight crew, flap 45 degrees may be used." B. Within 21 days after effective date of AD, apply temporary Scotchcal adhesive labels to the speed limits placard and to the flaps control sector markings, to provide VFE and approach/landing settings consistent with the limitations required in paragraph A., above, in accordance with Aerospatiale (ATR) Service Bulletin ATR42-27-0004, dated September 3, 1986. C. No later than December 1, 1986, replace previously installed temporary adhesive labels with permanent engraved labels with the same markings, and install a stop on the flaps control in accordance with Aerospatiale (ATR) Service Bulletin ATR42-27-0004, dated September 3, 1986. NOTE: The mechanical stop which precludes the normal use of flaps 45 degree operations may be removed in case of emergency ditching or emergency landing, when, at the discretion of the flight crew, additional safety would be provided by using flaps 45 degrees. 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 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, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective October 15, 1986.
93-14-18: 93-14-18 GENERAL ELECTRIC COMPANY: Amendment 39-8643. Docket 92-ANE-10. Applicability: General Electric Company (GE) CF6-6/-45/-50/-80A/-80C2 series turbofan engines that contain high pressure turbine (HPT) thermal shields as listed in the applicable service bulletins that are referenced in this AD, installed on but not limited to Airbus A300 and A310 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained engine failure, accomplish the following: (a) Perform either an impression and optical comparitor inspection or an ultrasonic inspection of the HPT thermal shield at the next HPT shop visit, or by December 12, 1995, whichever occurs first, as follows: (1) For GE CF6-6 engines, in accordance with GE CF6-6 Service Bulletin (SB) No. 72-983, Revision 1, dated October 10, 1991. (2) For CF6-45/-50 engines, in accordance with GECF6-50 SB No. 72-1021, Revision 1, dated October 10, 1991. (3) For CF6-80A engines, in accordance with GE CF6-80A SB No. 72-596, Revision 1, dated October 10, 1991. (4) For CF6-80C2 engines, in accordance with GE CF6-80C2 SB No. 72-565, Revision 1, dated October 10, 1991. (b) Remove from service prior to further flight, and replace with a serviceable part, HPT thermal shields that do not meet the service criteria contained in the applicable service bulletins as specified in paragraph (a) of this AD. (c) For the purpose of this AD, a shop visit is defined as the removal of the HPT module from the engine for any reason. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) 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. (f) The inspections shall be done in accordance with the following service bulletins: Document No. Pages Revision Date GE CF6-6 SB 1-3 1 October 10, 1991 No. 72-983 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-50 SB 1-3 1 October 10, 1991 No. 72-1021 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-80A SB 1-3 1 October 10, 1991 No. 72-596 4-31 Original September 19, 1991 Total Pages: 31 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFRpart 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2000-20-04: This document supersedes an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-90-30 series airplanes. That AD currently requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. The actions specified in that AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight. This amendment is prompted by the Federal Aviation Administration's determination that the existing AD must be revised to ensure that the requirements apply to the appropriate airplane groups. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin MD90-24-062, dated February 3, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of November 13, 2000.The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD90-24A060, Revision 01, dated September 2, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 19, 2000 (65 FR 49728, August 15, 2000).
2015-26-04: We are superseding airworthiness directive (AD) 2002-13-11 for Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2002-13-11 required installing front and side covers on the cabin floor to protect the yaw control at both the pilot and co-pilot stations. Since we issued AD 2002-13-11, we have determined that the required actions should apply only to the cabin's right-hand pilot station. This AD retains the requirements of AD 2002-13-11 but for only the pilot station. These actions are intended to prevent an object from sliding between the canopy and the cabin floor, loss of yaw control, and subsequent loss of helicopter control.
2000-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, for certain airplanes, inspection(s) to detect cracks of the doorjamb corners and follow-on actions. For certain other airplanes, this AD requires installation of a preventative modification; an inspection to detect cracks at the corners of the doorjambs of the passenger and service doors; and follow-on actions. This amendment is prompted by reports indicating that fatigue cracks were found in the fuselage skin and doublers at the corners of the doorjambs of the passenger and service doors. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
2000-20-02: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This action requires inspection of the low pressure turbine nozzle lock assemblies, and replacement of the borescope plug with a new design plug. This amendment is prompted by three uncontained engine failures. The actions specified in this AD are intended to detect loose or missing LPT nozzle lock assembly studs that could lead to failure of the locks and subsequent uncontained failure of the engine.
81-09-08: 81-09-08 HILLER AVIATION: Amendment 39-4137. Applies to Models UH-12D, UH-12E, UH-12E4 Series Helicopters, including military Models H-23F, OH-23G, and all models converted by STC SH178WE and STC SH177WE, equipped with main rotor blades Part No. 53200-03, certified in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible main rotor blade failure due to the delamination of the skin at the blade tip, accomplish the following: (a) Prior to further flight, after the effective date of this AD or receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first: (1) Remove blade tip cap and visually inspect for skin bond separation in the tip cap area, in accordance with Para. II.D of Hiller Aviation Service Bulletin No. 51-8 dated March 25, 1981. (2) If the skin bond separation is detected, replace blade with like serviceable item or repair in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. Submit data defining exact areas of delamination when requesting repair approval. (3) If no skin bond separation is detected, replace the tip cap and seal, in accordance with Para. II.F of Hiller Aviation Service Bulletin No. 51-8, dated March 25, 1981. (b) Upon the effective date or upon receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first, whenever the rotor blade tip cap is removed for whatever reason, comply with the inspection requirements and tip cap reinstallation requirements of Para. (a) of this AD prior to return to service. Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections or modifications required by this AD. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and ManufacturingBranch, FAA Western 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 West Scranton Avenue, Porterville, California 93275. These documents may also be examined at FAA Western Region Office, Rules Docket, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, Rules Docket, Room 916, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA Headquarters in Washington, D.C. and the FAA Western Region Office. This amendment becomes effective June 25, 1981 to all persons, except those to whom it was made immediately effective by priority mail AD 81-09-08, issued April 27, 1981.