Results
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.
95-25-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection and other specified actions to ensure that the ground stud assemblies at three locations of the airplane are installed properly and torqued to certain specifications, to verify the integrity of the components of the ground stud assemblies, and to detect heat damage in adjacent areas; and correction of any discrepancy. That AD was prompted by reports indicating that arcing occurred across the pins in the galley external power receptacle due to loose attach hardware on the ground stud. The actions specified in that AD are intended to ensure that the ground stud assemblies are attached correctly so that arcing will not occur. Such arcing, if not corrected, could result in heat damage to adjacent structure and a fire in the forward cargo compartment, the center accessory compartment, or the aft fuselagecompartment. This action would expand the applicability of the existing AD to include additional airplanes.
2004-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Becker Flugfunkwerk GmbH AR 4201 VHF AM transceivers. This AD requires adding an aircraft flight manual (AFM) limitation to the Limitations Section of the AFM, and cockpit placard due to the intermittent malfunctioning of the transceiver, or removing the affected transceiver from service. This AD results from reports of crewmembers having difficulty communicating with Air Traffic Control and other aircraft due to the AR 4201 VHF AM transceiver's inability to block interference from transmitters operating on frequencies other than those set in the transceiver. We are issuing this AD to prevent difficulty in communicating with Air Traffic Control and other aircraft due to intermittent malfunctioning of the transceiver.
99-26-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection to verify the tension values of the aileron control cables of the left- and right-hand wings, and corrective actions, if necessary. This action also requires either replacement of the aileron control cables with new, improved aileron control cables, or replacement of the aileron control cables with new, improved aileron control cables and modification of the pulley bracket on the rear face of the bulkhead at frame station 3100. The FAA is issuing this AD in response to mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interference between the turnbuckles of the aileron control cables and the lightening holes, which could result in binding of the aileron control cables and consequent reduced controllability of the airplane.
2013-17-04: We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A Series Engine. This AD results 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. The MCAI describes the unsafe condition as oil leaks in the intake channel in the area of the valve guide on some cylinder heads could increase the oil consumption and result in engine stoppage. We are issuing this AD to require actions to address the unsafe condition on these products.
2022-21-11: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 204B, 205A, and 205A-1 helicopters and various restricted category helicopters. This AD was prompted by a report of cracked main rotor blades (MRBs). This AD requires repetitive inspections of each MRB and removing any cracked MRB from service. The FAA is issuing this AD to address the unsafe condition on these products.
78-19-01: 78-19-01 ROLLS-ROYCE LIMITED (Formerly Rolls-Royce (1971) Limited): Amendment 39-3297. Applies to Model RB-211-22B engines which have high pressure turbine discs, part number and serial number as indicated, installed. Compliance is required as indicated, unless already accomplished. To ensure adequate life limit margin for, and to prevent failure of the high pressure turbine discs listed herein, accomplish the following: (a) Permanently remove from service the following high pressure turbine discs before or upon reaching the flight cycle life limit shown. Part No. Serial No. Revised Life Limit Flight cycles LK48423 CQDY 107 2900 LK48423 CQDY 140 2900 LK48423 CQDY 130 2900 LK48423 CQDY 133 2900 LK48423 CQDY 134 2900 LK48423 CQDY 233 2900 LK53204 CQDY 334 4350 LK53204 CQDY 345 4350 LK53204 CQDY 389 4350 LK53204 CQDY 417 3500 LK53204 CQDY 419 4350 LK53204 CQDY 426 4350 LK53204 CQDY 427 3500 LK53204 CQDY 436 2500 LK53204 CQDY 449 4350 LK53204 CQDY 540 4350 LK53204 CQDY 578 3000 LK53204 CQDY 579 3000 LK53204 CQDY 581 4350 LK53204 CQDY 583 3500 LK69209 A2 CQDY 592 4350 LK53204 CQDY 624 2900 LK53204 CQDY 625 4350 LK53204 CQDY 627 3500 LK53204 CQDY 630 3600 LK53204 CQDY 631 4350 LK53204 CQDY 655 3500 LK53204 CQDY 702 4350 LK53204 CQDY 703 3500 LK53204 CQDY 712 4350 LK53204 CQDY 730 3500 LK69209 CQDY 740 4350 LK62143 CQDY 757 2250 LK53204 CQDY 770 4350 LK53204 CQDY 771 4350 LK53204 CQDY 805 2400 LK58998 CQDY 958 2250 LK58998 CQDY 964 2250 LK53204 CQDY 965 2250 LK58998 CQDY 976 2250 LK58998 CQDY 989 2250 LK69213 CQDY 996 4360 LK58998 CQDY 998 2250 LK58998 CQDY 1002 1200 LK58998 CQDY 1037 2250 LK58998 CQDY 1076 2250 LK58998 CQDY 1140 2250 NOTE: Rolls-Royce Limited Service Bulletin RB.211-72-4300, Revision 3, dated May 12, 1978, pertains to this same subject. (b) Permanently remove from service the following high pressure turbine discs before or upon reaching 2900 flight cycles: Part No. Serial No. LK53203 CQDY 241 LK48424 CQDY 242 LK53203 CQDY 257 LK53195 CQDY 309 LK53204 CQDY 428 LK53204 CQDY 657 LK53204 CQDY 678 LK53204 CQDY 697 LK53204 CQDY 773 LK53204 CQDY 951 LK69210 CQDY 1227 LK69210 CQDY 1419 NOTE: Rolls-Royce Limited Service Bulletin RB.211-72-4304, Revision 2, dated June 3, 1977, pertains to this same subject. (c) In accordance with the provisions of FAR 21.197 and FAR 21.199 the aircraft may be flown to a base where the disc removals required by this AD may be performed. NOTE: For the purpose of this AD a flight cycle is considered to be an operating sequence consisting of engine starting, takeoff operation, landing and engine shutdown. This amendment becomes effectiveSeptember 25, 1978.
2022-18-11: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by a report of a crack found in a front spar lower chord undergoing an underwing longeron replacement. This AD requires repetitive inspections for cracking of the left and right side ring chords, repair angles, front spar lower chords, and front spar webs (depending on configuration) common to the underwing longeron located at station (STA) 1035; modification of the front spar lower chord for some airplanes; repetitive post-modification inspections; and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2004-20-10: The FAA adopts a new airworthiness directive (AD) for all Valentin GmbH & Co. Taifun 17E sailplanes. This AD requires you to do an operational check of the front wing-locking mechanism left and right, inspect stop key movement, inspect wing and fuselage side root ribs, inspect the wing side shear force fittings, and take any corrective actions that may be required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct malfunction of wing-locking mechanism, which could result in failure of the wing-locking mechanism disengagement. This failure could lead to unlocking of wing in flight and consequent loss of control of the sailplane.
2022-19-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-2C series airplanes. This AD was prompted by a report that insufficient clearance was found between the right stabilizer trim shut-off control wire (bundle W0589) and an elevator control cable. This AD requires a one-time inspection for insufficient clearance between the elevator control cable and wire bundle W0589 on the airplane's left crown, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2013-17-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; Model A340-200 and - 300 series airplanes; and Model A340-541 and -642 airplanes. This final rule was prompted by reports of wing tip brakes (WTBs) losing their braking function in service due to heavy wear on the brake discs. WTBs are designed to stop and hold the mechanical transmission of slats and flaps in certain failure cases. This final rule requires repetitive operational tests of certain WTB pressure-off-brakes (POBs) for performance on the flap and slat systems, and replacement of any affected WTB with a new or serviceable part if the test fails. This final rule also requires eventual replacement of all affected WTBs with a new part, which terminates the repetitive tests. We are issuing this final rule to prevent loss of the WTB braking function, and consequent inability of the flap or slat system to be stopped and held in [[Page 53636]] position during operation, which could result in loss of control of the airplane.