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92-15-12: 92-15-12 AEROSPATIALE: Amendment 39-8306. Docket No. 92-NM-31-AD. Applicability: Model ATR42-300 and -320 series airplanes on which Modification 1694 (Aerospatiale Service Bulletin ATR42-32-0021) has been accomplished and on which Modification 2063 (Aerospatiale Service Bulletin ATR42-32-0028) has not been accomplished, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a gear-up landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the nose landing gear (NLG) retraction control logic, and perform a functional test of the landing gear retraction manual override control, in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991. (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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 modification and functional test shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 11, 13-21 3 February 12, 1991 3-10, 12 1 February 23, 1990 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on September 8, 1992.
2022-21-15: The FAA is adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a loose rudder T-yoke axle nut. This AD requires replacing the rudder T-yoke axle with an improved rudder T-yoke axle. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-02: The FAA is superseding Airworthiness Directive (AD) 2000-20- 15, which applied to certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000-20-15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000-20-15, but at reduced compliance times, 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.
2004-22-01: This amendment adopts a new airworthiness directive (AD), applicable to various transport category airplanes on which cargo restraint strap assemblies have been installed per STC ST01004NY. This amendment requires revising the airplane flight manual to include a procedure for discontinuing the use of certain cargo restraint strap assemblies installed per STC ST01004NY, if used as the only cargo restraint. This amendment also requires revising the airplane weight and balance manual to include the same procedure described previously. The actions specified by this AD are intended to prevent shifting or unrestrained cargo in the cargo compartment, which could cause an unexpected change in the airplane's center of gravity, damage to the airplane structure and/or flight control system, a hazard to the flightcrew, and/or possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
99-26-13: This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires inspecting each tail rotor blade (blade) for a crack and replacing any cracked blade. This amendment requires, before further flight, inspecting any blade with 400 or more hours time-in-service (TIS) for a crack and replacing any cracked blade. This amendment is prompted by another report of a cracked blade since the issuance of the existing AD. Two of the three occurrences of cracked blades involved the loss of the tail rotor and 90-degree gearbox. The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
2022-20-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by a determination that in the event of rapid decompression at a specific location of the airplane, possible deflections of the passenger floor cross beams may result in wiring damages, leading to potential system losses. This AD requires amending the operator's existing airplane flight manual (AFM) to update the landing performance database, 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.
91-06-14: 91-06-14 BRITISH AEROSPACE: Amendment 39-6936. Docket No. 90-NM-254-AD. Applicability: All Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect disbonding of the nickel sheath from the propeller blades, accomplish the following: A. Within 125 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 125 hours time-in-service, perform a visual inspection of the propeller blades for disbonding of the leading edge nickel sheath, in accordance with British Aerospace Alert Service Bulletin A-ATP-61-5, dated April 4, 1990. B. If disbonding is found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate. 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 Manager, 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 (39-6936, AD 91-06-14) becomes effective on April 18, 1991.
99-26-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that requires installation of a drain at each of the number 2 window frame assemblies in the airplane. This amendment is prompted by reports that flight deck emergency exits (number 2 windows) were found frozen shut after landing. The actions specified by this AD are intended to prevent water accumulation in the lower corners of the flight deck emergency exits (number 2 windows), which can freeze and prevent the exits from being used during an emergency evacuation.
2004-19-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires repetitive inspections for corrosion and cracking of the pivot hinge pins of the horizontal stabilizer, certain follow-on inspections, and replacement of the hinge pins with new or serviceable pins if necessary. This action is necessary to prevent failure of the outer and inner hinge pins due to corrosion or cracking, which could allow the pins to migrate out of the joint and result in intermittent movement of the horizontal stabilizer structure and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2022-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc., Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters; certain Erickson 214 Holdings, LLC, Model 214B and 214B-1 helicopters; certain Leonardo S.p.a. Model AB412 and AB412 EP helicopters; and certain various restricted category helicopters. This AD was prompted by reports of two in-service failures of forward crosstubes due to fatigue damage and the issuance of newly established life limits. This AD requires determining the total number of landings on certain part-numbered forward crosstubes and incorporating requirements (airworthiness limitations) into existing maintenance records. The FAA is issuing this AD to address the unsafe condition on these products.
77-09-04: 77-09-04 CANADAIR: Amendment 39-2885. Applies to Canadair CL-215-1A10 airplanes, Serial Nos. 1001 to 1040 inclusive, not altered with Canadair Reinforcement Kit K215- 30043 or an FAA approved equivalent. Compliance is required as indicated. To assure the structural integrity of the main landing gear wheel well angles, P/N 215- 32200-58, -59, -60, -61, accomplish the following: (a) On aircraft with 1000 or more hours in service, compliance with paragraph (c) is required before the next flight. The inspection of paragraph (c) must be repeated at intervals not to exceed 150 hours in service. (b) On aircraft with less than 1000 hours in service, compliance with paragraph (c) is required at or before 1000 hours in service. The inspections of paragraph (c) must be repeated at intervlas not to exceed 150 hours in service. (c) Inspect for cracks and modify in accordance with Canadair Service Information Circular No. 104-CL-215 dated September 5, 1975, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time in this AD. This amendment becomes effective May 9, 1977.
2022-20-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by a report of cracks found in the fastener holes at a certain location in the center wing box rear spar, lower skin. This AD requires repetitive inspections for cracking of certain areas of the center wing box rear spar, lower skin and lower chord; and repair. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a report that a spoiler sensor failure may go undetected by the autothrottle (A/T) computer. This AD requires repetitive built-in test equipment (BITE) tests of the A/T computer to detect a spoiler sensor failure, and corrective action if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-21-01: The FAA is superseding an existing AD for certain Hartzell Propeller Inc. (formerly Hartzell Propeller Products Division) Model HC-B5MP-3( )/M10282A( )+6 five bladed propellers. That AD currently requires initial and repetitive torque check inspections on the attach bolts on certain model Hartzell HC-B5MP-3 five bladed propellers, and replacement of attach bolts if necessary. This AD requires the same inspections, but reduces compliance time for the initial inspection on certain Short Brothers Ltd. Model SD3-30 airplanes to before further flight and within 100 hours time-in-service for propellers installed on certain Aerospatiale (Nord) Model 262A airplanes. This AD also requires repetitive torque check inspections at reduced intervals on SD3-30 airplanes, and requires additional visual inspections of mounting flanges, and threads in hub bolt holes, and replacement of attach bolts and hubs, if necessary. This AD results from four reports in the last 12 months of eleven crackedor failed propeller attach bolts on Short Brothers Model SD3-30 airplanes. We are issuing this AD to prevent propeller separation from the airplane.
2013-17-06: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 050 airplanes, and Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of loose nuts on contactors in the electrical power center (EPC), and in some cases, burned contactors. This AD requires inspecting and, if necessary, adjusting, the torque values of nuts on circuit breakers, contactors, and terminal blocks of the EPC and battery relay panel. This AD also requires inspecting to determine if certain parts are installed, and installing the parts if necessary. We are issuing this AD to detect and correct loose nuts, which could result in arcing and potentially an onboard fire, possibly resulting in damage to the airplane and injury to occupants or maintenance personnel.
90-11-51 R1: 90-11-51 R1 AIRBUS INDUSTRIE: Amendment 39-6635. Final copy of, and revision to, telegraphic AD Docket No. 90-NM-103-AD. Applicability: Model A320 Series Airplanes, equipped with Garrett Auxiliary Power Unit (APU) GTCP36-300[A], Part No. 3800278-2, all serial numbers, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontained turbine rotor separation and subsequent reduced controllability of the airplane, accomplish the following: A. Within 72 hours (clock hours, not flight hours) after the effective date of this amendment, accomplish the following: 1. Revise the Limitations Section in the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM Limitations Section. Operation of the APU on the ground is prohibited, and operation of the APU during flight is prohibited, except during an emergency. 2. Install a placard next to the APU start switch in the cockpit to state: Operation of the APU on the ground is prohibited, and operation of the APU during flight is prohibited, except during an emergency. B. Within 30 days after the effective date of this amendment, install an external secondary turbine containment shield, Part Number 3615644-1, in accordance with Garrett Auxiliary Power Division Alert Service Bulletin GTCP36-49-A5973, dated May 17, 1990, or Revision 1, dated May 22, 1990. Installation of this containment shield constitutes terminating action for the requirements of paragraph A., above. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, 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 Garrett Auxiliary Power Division, 2739 East Washington Square, P.O. Box 5227, Phoenix, Arizona 85010. 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. Portions of this amendment were effective earlier to all recipients of telegraphic AD T90- 11-51, dated May 18, 1990. This AD revises telegraphic AD T90-11-51, issued on May 18, 1990. This amendment (39-6635, AD 90-11-51 R1) becomes effective on July 16, 1990.
2004-21-06: The FAA adopts a new airworthiness directive (AD) for all deHavilland Inc. Models DHC-2 Mk. I and DHC-2 Mk. II airplanes and for all Bombardier Inc. Model (Otter) DHC-3 airplanes powered by radial engines. This AD requires you to visually inspect the firewall connector plugs for proper lockwire security and replace or modify as appropriate. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. We are issuing this AD to prevent loss of ignition systems during flight caused by improper lockwire security, which could result in engine failure. This failure could lead to a forced landing of the airplane.
92-04-08: 92-04-08 GENERAL ELECTRIC COMPANY: Amendment No. 39-8179, Docket No. 91-ANE-58. Applicability: General Electric Company (GE) CF6-80A series turbofan engines installed on, but not limited to, Airbus A310 and Boeing 767 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure, an inflight engine shutdown, and damage to the aircraft, accomplish the following: (a) Prior to further flight, after the effective date of this AD, remove from service CF6-80A high pressure turbine rotor (HPTR) stage 1 disk/shafts identified by the following part number (P/N) and serial number (S/N): PART NUMBER SERIAL NUMBER 9362M58 MPOP8483 9362M58 MPOS1676 Prior to returning affected engines to service replace with a serviceable part. (b) Eddy current and fluorescent penetrant inspect, CF6-80A HPTR stage 1 disk/shafts identified by the following P/N and S/N, in accordance with the Accomplishment Instructions of GE CF6-80A Service Bulletin (SB) 72-605, dated December 20, 1991, within the next 400 cycles in service (CIS) after the effective date of this AD, not to exceed 3,400 total CIS since last chrome plating repair procedure: PART NUMBER SERIAL NUMBER 9234M67 MPOP2707 9234M67 MPON6442 9234M67 MPOP7075 9362M58 MPOS4048 (c) Remove from service CF6-80A HPTR stage 1 disk/shafts which exceed the serviceable limits defined in Paragraphs 2.C.(6) and 2.D. of the Accomplishment Instructions of GE CF6-80A SB 72-605, dated December 20, 1991. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine & Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (f) The inspections shall be done in accordance with the following General Electric document: Document No. Page No. Issue Date GE CF6-80A 1-29 Original Dec. 20, 1991 SB 72-605 Total Pages: 29 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 General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. (g) This amendment (39-8179, AD 92-04-08) becomes effective on March 27, 1992.
2022-20-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report that some rudder power control unit (PCU) load limiters were found in service with the crimping missing from the end cap; therefore, the pilot command from the load limiter might not transmit correctly. This AD requires a one-time inspection of the rudder PCU load limiters for correct crimping of the end cap, and replacing any defective rudder PCU load limiter. For certain airplanes, this AD would also require repetitive testing of the rudder PCU load limiter for correct functioning, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-02: 76-17-02 BEECH: Amendment 39-2697 as amended by amendment 39-3324. Applies to Models 58P and 58PA (Serial Numbers TJ-2 through TJ-19, TJ-21 through TJ-45, TJ-47 through TJ-54, and TJ-56 through TJ-58) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To prevent cracking of the cabin window located just forward of the cabin entrance door on the left side of the airplane, with resultant loss of cabin pressurization, accomplish the following: A. On airplanes that do not have the window frame reinforcement installed, as defined in Beechcraft Service Instructions 0828-110, Revision I or later approved revisions, accomplish the following in accordance with said service instructions: 1. Within 25 hours' time in service after the effective date of this AD and at the two next 50 hour time in service intervals thereafter, visually inspect the cabin window just forward of the cabin door on the left side of the airplane for cracks and if cracks are found during any inspection required herein, prior to any flight during which the cabin is pressurized, replace the window and install the window frame reinforcement. 2. If no cracks have been found during any inspection required in Paragraph A.1., within 100 hours' time in service after the initial inspection required by Paragraph A.1. install the window frame reinforcement. B. On airplanes that are flown unpressurized following discovery of a cracked window during any inspection required by Paragraph A of this Airworthiness Directive: 1. Fabricate a placard worded as follows: "DO NOT PRESSURIZE IN FLIGHT" and 2. Install said placard near the cabin pressurization control switch, and 3. Operate the aircraft in accordance with the placard until the cracked window is replaced. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.Amendment 39-2697 became effective August 24, 1976. This amendment 39-3324 becomes effective October 31, 1978.
2022-20-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports of insufficient clearance between the surrounding structure/skin of the aircraft and select bleed air ducts that supply the wing ice protection system (WIPS) in the rear fuselage. This AD requires inspecting the bleed air duct and surrounding structure for minimum clearance and damage, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-03-10: 90-03-10 BELL HELICOPTER TEXTRON, INC. (BHTI); CALIFORNIA DEPARTMENT OF FORESTRY; GARLICK HELICOPTERS; HAWKINS AND POWERS AVIATION; HERCULES; INTERNATIONAL HELICOPTERS, INC.; LENAIR CORPORATION; OFFSHORE CONSTRUCTION; OREGON HELICOPTERS; PILOT PERSONNEL INTERNATIONAL; SMITH HELICOPTERS; SOUTHERN AERO CORPORATION; SOUTHWEST FLORIDA AVIATION; and WEST COAST FABRICATIONS: Amendment 39-8029. Docket No. 90-ASW-09. Final Rule of Priority Letter AD 90-03-10. Applicability: All Model 204B, 205A, 205A-1, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and TH-1L helicopters, certificated in any category, with aluminum tail rotor grips, P/N 204-011-728-19, installed. Compliance: Required before further flight, unless already accomplished. To prevent failure of a tail rotor grip, which could result in loss of tail rotor control, accomplish the following: (a) Determine the part numbers and serial numbers of the tail rotor grips installed on the helicopter. (b) If the tail rotor grip installed is P/N 204-011-728-19 and is identified with any serial number listed below, remove and replace the grip with an airworthy part before further flight: Serial Numbers: A3-66287 A3-66333 A3-66356 A3-66361 A3-66365 A3-66370 A3-66377 A3-67149 A3-67171 A3-67184 A3-67207 (c) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the inspection and grip replacement may be accomplished. (d) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This Amendment (39-8029, AD 90-03-10) becomes effective on October 18, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-03-10 issued January 29, 1990, which contained this amendment.
2022-18-15: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600- 2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of corrosion on fuel clamshell couplings installed in the fuel tank, and a determination that new or more restrictive airworthiness limitations are necessary. This AD requires removing and replacing the fuel clamshell couplings on certain airplanes, and revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2004-21-03: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Model G-1159, G-1159A, G-1159B, and G-IV series airplanes. This AD requires a one-time inspection of the left and right aileron and elevator actuators to determine the part and serial numbers of each actuator, repetitive inspections of suspect actuators to detect broken damper shafts, and replacement of any actuator having a broken damper shaft. This AD also requires that operators report any broken damper shaft they find to the FAA. This AD also provides an optional terminating action for the repetitive inspection requirements of this AD. This AD is prompted by reports of broken or cracked damper shafts within the aileron and elevator actuator assemblies. We are issuing this AD to detect and correct broken damper shafts, which could result in locking of an aileron or elevator actuator (hard-over condition), subsequent loss of aileron or elevator control, and consequent reduced controllability of the airplane.
2022-20-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B2K-3C, B2-203, B4-2C, and B4-203 airplanes. This AD was prompted by reports of cracking of the flight compartment aft window frame and adjacent fuselage skin. This AD requires require a one-time check for previously accomplished repairs of the window pane and adjacent fuselage panel, and applicable corrective actions, 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.