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91-03-05: 91-03-05 AIRSHIP INDUSTRIES: Amendment No. 39-6871; Docket No. 90-CE-50-AD. Applicability: Skyship Model 600 airships (all serial numbers), certificated in any category. Compliance: Required within the next 250 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent ignition control unit failure and subsequent total loss of engine power, accomplish the following: (a) Remove all ignition control units, Part Number (P/N) ASI/L/80 Issue D, MOD 1 or 2, and replace with P/N ASI/L/80 Issue E, MOD 3 ignition control units, as described in Airship Industries Service Bulletin (SB) REF 600-74-314, Revision 1, dated June 5, 1990. (b) 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. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Airship Industries Limited, Manager, Technical Publications, Shortstown, Bedford, MK42 OTF, England; or Airship Industries USA, Inc., Engineering Manager, Route 4, Box 109, Elizabeth City, North Carolina 27909; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6871, AD 91-03-05) becomes effective on February 28, 1991.
93-25-13: 93-25-13 AIRBUS INDUSTRIE: Amendment 39-8777. Docket 93-NM-130-AD. Applicability: Model A320 series airplanes, manufacturer's serial numbers (MSN) 002 through 051 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could lead to reduced structural integrity of the wing, accomplish the following: (a) Prior to the accumulation of 12,000 total landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD in accordance with Airbus Industrie Service Bulletin A320-57-1060, dated December 8, 1992. (1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the MLG, except for the holes that are for taper-lok bolts. (2) Perform a cold expansion of the holes at the actuating cylinder anchorage of the MLG. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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 cold expansion shall be done in accordance with Airbus Industrie Service Bulletin A320-57-1060, dated December 8, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac, Cedex France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 14, 1994.
2022-25-16: The FAA is superseding Airworthiness Directive (AD) 2018-18- 05, which applied to certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes; and AD 2020- 09-16, which applied to all ATR-GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2018-18-05 and AD 2020- 09-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD is prompted by a determination that additional new or more restrictive airworthiness limitations are necessary. This AD retains the requirements of AD 2020-09-16. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive maintenance requirements and airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
98-25-08: 98-25-08 British Aerospace Regional Aircraft [Formerly Jetstream Aircraft Limited; British Aerospace (Commercial Aircraft) Limited]: Amendment 39-10934. Docket 98-NM-216-AD. Applicability: Model ATP airplanes, constructor s numbers 2002 through 2063 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the nosewheel steering control cables, which could result in loss of the nosewheel steering or collapse of the nose landing gear (NLG), and possible injury to the flightcrew and passengers, accomplish the following: (a) Perform a visual and tactile inspection of the nosewheel steering control cables located in the nosewheel bay of the NLG to detect excessive wear, and test the cable pulleys for seizing, in accordance with British Aerospace Service Bulletin ATP-32-91, dated May 19, 1998; at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. Thereafter, repeat the inspection and test at intervals not to exceed 1,800 flight hours, or 2,400 landings, whichever occurs first. (1) For airplanes on which the nosewheel steering control cables have accumulated 6,000 or more total flight hours, or 8,000 or more total landings as of the effective date of this AD, and for airplanes on which the time-in-service of the nosewheel steering control cables is unknown: Inspect and test within 600 flight hours or 800 landings after the effective date of this AD, whichever occurs first. (2) For airplanes on which the nosewheel steering control cables have accumulated less than 6,000 total flight hours or 8,000 total landings as of the effective date of this AD: Inspect and test within 900 flight hours or 1,200 landings after the effective date of this AD, whichever occurs first. (b) If any cable wear is outside the limits specified in British Aerospace Service Bulletin ATP-32-91, dated May 19, 1998, or if any discrepant pulley is detected during any inspection or test required by paragraph (a) of this AD, prior to further flight, replace the discrepant cable or pulley with a new component in accordance with the service bulletin. Thereafter, continue accomplishment of the actions required by paragraphs (a) and (c)of this AD at the intervals specified in those paragraphs. (c) Replace the nosewheel steering control cables with new cables at the later of the times specified in paragraphs (c)(1) and (c)(2) of this AD in accordance with British Aerospace Service Bulletin ATP-32-91, dated May 19, 1998. Thereafter, repeat the replacement at intervals not to exceed 6,000 total flight hours or 8,000 total landings on the nosewheel steering cables, whichever occurs first. (1) Within 900 flight hours or 1,200 landings after the effective date of this AD, whichever occurs first. (2) Prior to the accumulation of 6,000 total flight hours or 8,000 total landings on the nosewheel steering cables, whichever occurs first. NOTE 2: Accomplishment of the initial inspection or initial replacement of the nosewheel steering control cables prior to the effective date of this AD in accordance with British Aerospace Alert Service Bulletin ATP-A32-90, dated March 21, 1998, is considered acceptable forcompliance with the initial inspection or initial replacement required by this AD. (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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The actions shall be done in accordance with British Aerospace Service Bulletin ATP-32-91, dated May 19, 1998. 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 AI(R) American Support, Inc., 13850 Mclearen Road, Herndon, Virginia 20171. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in British airworthiness directive 004-05-98. (g) This amendment becomes effective on January 14, 1999.
82-12-03: 82-12-03 BRITISH AEROSPACE (Hawker Siddeley): Amendment 39-4393. Applies to all Model HS/BH/DH 125 aircraft up to and including Series 600A aircraft, certificated in all categories, S/Ns as listed in British Aerospace, Aircraft Group, 125 Series Aircraft Service Bulletin 49-23-(6525), Revision 5, dated August 18, 1981. Compliance is required as indicated unless already accomplished. To protect the PE busbar and ensure APU start circuit operation, accomplish the following: 1. Within the next 100 hours time in service after the effective date of this AD, install a 275 ampere airfuse in accordance with the applicable instructions in paragraph 2, "Accomplishment Instructions," of British Aerospace, Aircraft Group, 125 Series Aircraft Service Bulletin (SB) No. 49-23-(6525), Revision 5, dated August 18, 1981. 2. 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 inspections and/or modificationsrequired by this AD. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain 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). This amendment becomes effective June 8, 1982.
2021-16-09: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by corrosion on the inlet check valve banjo fitting of emergency flotation system (EFS) float assemblies. This AD requires visually inspecting each banjo fitting installed on an affected EFS float assembly, and depending on the results, removing the banjo fitting from service. This AD also requires applying corrosion inhibiting compound and prohibits installing an affected EFS float assembly unless certain requirements have been accomplished as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-11-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330 and A340 series airplanes. This action requires repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA); and corrective action, if necessary. This action is necessary to prevent degraded operation of the THSA due to the entrance of water into the ball nut. Degraded operation could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
90-21-01:
2022-25-03: The FAA is superseding Airworthiness Directive (AD) 2016-16- 06, which applied to certain Airbus SAS Model A300 B4-603, B4-605R, and B4-622R airplanes; and Model A310-304, -324, and -325 airplanes. AD 2016-16-06 required inspections around the rivet heads of the seal retainer run-out holes at certain frames and corrective actions if necessary. This AD was prompted by a report of a crack found on a certain door frame, and a determination that other frames may also be susceptible to cracking, and that additional airplanes may be affected by the unsafe condition. This AD continues to require the actions in AD 2016-16-06 and adds airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-17-04 R1: We are revising Airworthiness Directive (AD) 2016-17-04, which applies to all hot air balloons equipped with BAL[Oacute]NY KUB[Iacute][Ccaron]EK spol. s r.o. Model Kub[iacute][ccaron]ek burners. Both the original and revised AD result from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. This AD action revises AD 2016-17-04 to eliminate certain unnecessary documentation requirements.