Results
98-04-06: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires repetitive visual inspections for signs of fuel leakage of the outer wing beginning with Rib 21 and continuing outward, 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 in this AD are intended to prevent fuel leakage on the outboard wing, which could result in a fuel explosion and fire.
2006-11-07: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting certain bus bars in the DA-A panel to ensure that the bus bars match the panel configuration and clearance is adequate between the bus bars and adjacent components, and performing corrective action if necessary. This AD results from two reports of inadequate clearance between the bus bars in the DA-A panel. We are issuing this AD to prevent insufficient electrical isolation for the electrical bus configuration and inability of the flightcrew to isolate the bus bars in an emergency situation involving a dual generator failure, which could result in extra loads on the main ship batteries and consequent loss of power to the main essential bus.
85-01-06: 85-01-06 BOEING: Amendment 39-4982. Applies to Model 737 series airplanes certificated in all categories listed in Boeing Service Bulletin 737-53A1064, Revision 3, dated November 23, 1983. To prevent sudden loss of cabin pressure resulting from undetected cracking of the frames adjacent to the forward airstair, accomplish the following prior to accumulation of 29,000 landings, or within 90 days from the effective date of this AD, whichever occurs later, unless previously accomplished: \n\n\tA.\tVisually inspect for cracks the body station 351.2 and 360 frames in accordance with the Flight Safety Addendum in Boeing Service Bulletin 737-53A1064, Revision 3, or later FAA approved revisions. Repeat the internal visual inspection at intervals not exceeding 3000 landings for Group 1 airplanes without external doublers installed in accordance with Boeing Service Bulletin 737-53-1058. For all other airplanes, repeat the inspection at intervals not exceeding 6000 landings. \n\n\tB.\tIf cracks are detected, repair before further flight in accordance with Service Bulletin 737-53A1064, Revision 3, or later FAA approved revisions, and continue the repetitive inspections of paragraph A., above. \n\n\tC.\tAs an alternative to the internal inspections of paragraph A., above, operators may visually inspect the external skin for cracks in the area of the forward airstair door cutout in accordance with Boeing Service Bulletin 737-53A1064, Revision 3, or later FAA approved revisions. Repeat external skin inspections at intervals not exceeding 300 landings until the internal frame inspection of paragraph A. is accomplished within 3000 flight cycles of the initial external visual inspection. Continue inspections in accordance with paragraph A. \n\n\tD.\tIf skin cracks are detected, unless previously accomplished during the same inspection period, inspect the frames in accordance with paragraph A., above. Repair cracks in accordance with the Structural Repair Manual or Boeing Service Bulletin 737-53-1058, as applicable, and continue the inspections of paragraph A. \n\n\tE.\tAirplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and 21.199 with prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tModification of airplanes in accordance with the Accomplishment Instructions, Part II of Boeing Service Bulletin 737-53A1064, Revision 3, or later FAA approved revisions, constitutes terminating action for this AD. \n\n\tG.\tFor purposes of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tH.\tUpon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD, if the request contains substantiating data to justify the increase for the operator.\n \n\tI.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, Northwest Mountain Region, Seattle, Washington. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 25, 1985.
87-20-05: 87-20-05 PACIFIC SCIENTIFIC COMPANY: Amendment 39-5693. Applies to TSO C22f lap belt assemblies, part number 1107177 (all dash numbers), manufactured between September 1, 1984, and January 1, 1986. Compliance required within 180 days after the effective date of this AD, unless previously accomplished. To eliminate lap belt assemblies with belt retractor shafts which do not provide adequate strength, accomplish the following: A. Inspect all Pacific Scientific TSO C22f lap belt assemblies, part number 1107177 (all dash numbers), in accordance with Pacific Scientific Company Safety Advisory Letter (on the Mark V Reel Lap Belt Assembly, which deals with this problem), to determine if they have part number 1106294-01 retractor shafts made of the correct material. This is determined by visual examination of the end of the shaft: If the color is gold anodize, the shaft is acceptable. If the color is a dull battleship grey anodize, the shaft must be replaced prior to further flight. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance 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 information from the manufacturer may obtain copies upon request to Pacific Scientific Company, 1346 S. State College Boulevard, Anaheim, California 92803. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective October 26, 1987.
2006-15-14: This amendment adopts a new airworthiness directive (AD) for Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A-3 helicopters that requires replacing certain fixed bolts and nuts, re-identifying certain main rotor nuts, and revising the Airworthiness Limitations-- Time Change Items (TCI) list to reflect the new life limits and new part numbers. This amendment is prompted by a re-evaluation of certain fatigue-critical parts, which resulted in establishing new life limits for certain like-numbered parts and re-identifying a certain existing part with a different part number, or in some cases, replacing them with new parts. The actions specified by this AD are intended to prevent fatigue failure of the fixed bolts and nuts, and subsequent loss of control of the helicopter.
98-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the main landing gear (MLG), and follow-on corrective actions, 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 detect and correct a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the bearing, and consequent collapse of the MLG during landing.
97-24-17: This document publishes in the Federal Register an amendment adopting priority letter airworthiness directive (AD) 97-24-17, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires inspections of components in the tail rotor drive system for scratches, cracks, fretting, corrosion, and proper torquing, lubrications of the oil cooler blower shaft hanger bearings and oil cooler hanger bearings (hanger bearings), and removal of corrosion inhibitive adhesive barrier tape (barrier tape) from the tail rotor gearbox and the tail rotor gearbox support assembly faying surfaces. This amendment is prompted by numerous reports of three problems, all of which are related to the tail rotor drive system. The actions specified by this AD are intended to: detect scratches, cracks, fretting, and corrosion in the disc pack couplings; prevent inadequate lubrication of the hanger bearingsand oil cooler blower shaft; and prevent loss of mounting torque on the tail rotor gearbox. Failure of any of these components could result in loss of power to the tail rotor and subsequent loss of control of the helicopter.
88-01-09: 88-01-09 BOEING: Amendment 39-5818. Applies to Model 737-300 series airplanes listed in Boeing Service Bulletin 737-34-1220 dated April 30, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent loss of the primary Electronic Flight Instrument System (EFIS) displays, accomplish the following: \n\n\tA.\tReplace the EFIS symbol generators in accordance with Boeing Service Bulletin 737-34-1220 dated April 30, 1987, or later FAA-approved revisions. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle 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 a base for accomplishmentof the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents 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. \n\n\tThis amendment becomes effective February 16, 1988.
2006-15-12: The FAA is adopting a new airworthiness directive (AD) for certain CASA Model C-212-CC airplanes. This AD restricts the operation of the airplane to carrying either passengers or cargo (but not both) in the same compartment, unless the airplane is modified to include an approved protective liner between the passengers and the cargo. This AD results from our determination that affected airplanes, when carrying both cargo and passengers in the same compartment, cannot achieve the required level of performance. We are issuing this AD to prevent a hazardous quantity of smoke, flames, and/or fire extinguishing agent from the cargo compartment from entering a compartment occupied by passengers or crew.
98-13-03: This amendment supersedes Airworthiness Directive (AD) 82-20-04 R1, which currently requires repetitively inspecting the main landing gear (MLG) hinge fitting, support angles, and attachment bolts on British Aerospace H.P. 137 Mk1 and Jetstream series 200 airplanes, and repairing or replacing any part that is cracked beyond certain limits. This AD requires installing improved design MLG fittings, as terminating action for the repetitive inspections that are currently required by AD 82-20-04 R1, and will incorporate the Jetstream Model 3101 airplanes into the Applicability of the AD. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. The actions specified by this AD are intended to prevent structural failure of the MLG caused by fatigue cracking, which could result in loss of control of the airplane during landing operations.
2000-22-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires modification of the canted pressure deck drain system in the wheel well of the main landing gear (MLG). This amendment is prompted by reports of ice accumulation on the aileron control cables and on the MLG door and door seal during flight, due to fluid entering the canted pressure deck area, leaking into the MLG wheel well, and freezing. The actions specified by this AD are intended to prevent such ice accumulation, which could render one of the aileron control systems and/or the MLG doors inoperative, resulting in reduced controllability of the airplane.
89-13-08: 89-13-08 BOEING: Amendment 39-6241. \n\tApplicability: Model 757 series airplanes, listed in Boeing Service Bulletin 757-32- 0083, dated December 15, 1988, certificated in any category. \n\n\tCompliance: Required within the next 750 landings after the effective date of this AD or prior to the accumulation of 10,000 landings, whichever occurs later, unless previously accomplished. \n\n\tTo prevent the partial loss of braking and, potentially, the complete loss of braking, accomplish the following: \n\n\tA.\tReplace aluminum brake metering valve actuation shafts with steel shafts, in accordance with Boeing Service Bulletin 757-32-0083, dated December 15, 1988. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: 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, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6241, AD 89-13-08) becomes effective on July 24, 1989.
2019-06-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 A-1, MBB-BK 117A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, MBB-BK 117 C-1, and MBB-BK 117 C-2 helicopters. This AD requires repetitive inspections of the tail rotor (T/R) gearbox housing. This AD was prompted by a report that a crack was found in a T/R gearbox housing. The actions of this AD are intended to correct an unsafe condition on these products.
99-15-04 R1: This amendment revises Airworthiness Directive (AD) 99-15-04, which currently requires you to calibrate, inspect, and repair or replace portions of the turbine inlet temperature system on all The New Piper Aircraft, Inc. (New Piper) Models PA-46-310P and PA-46-350P airplanes (different actions for different airplane models). Information reveals that the AD should not apply to airplanes where the factory installed turbine inlet temperature gauge and associated probe have been replaced through supplemental type certificate (STC). This AD retains the actions of AD 99-15-04, and restricts the applicability accordingly. The actions specified by this AD are intended to prevent improper engine operation caused by improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes, which could result in engine damage/failure with consequent loss of control of the airplane.
85-25-05: 85-25-05 BOEING: Amendment 39-5178. Applies to Model 757-200 series airplanes listed in Boeing Service Bulletin 757-27-0069, dated November 4, 1985. To detect nuts installed in the aileron, rudder and elevator power control actuators, and rudder ratio changer that have insufficient self-locking torque characteristics, accomplish the following, unless already accomplished: \n\n\tA.\tWithin 30 days after the effective date of this AD, check the self-locking nuts, P/N BACN10JC12CM or BACN10JC12CD, for proper self-locking torque in accordance with Paragraph III of Boeing Service Bulletin 757-27-0069, dated November 4, 1985, or later FAA- approved revision. If any self-locking nut is found not to meet the self-locking torque requirements of Boeing Service Bulletin 757-27-0069, dated November 4, 1985, or later FAA- approved revision, replace it prior to further flight with a nut found to meet the self-locking torque requirements of the above referenced service bulletin. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle 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 a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this document who have not already received copies of the service bulletin may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents 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. \n\n\tThis amendment becomes effective December 21, 1985.
85-02-06: 85-02-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4988. Applies to Model 47G-2A, G-2A-1, G-3, G-3B, G-3B-1, G-3B-2, G-3B-2A, G-4, G-4A, G-5, G-5A, J, J-2, J-2A, and K helicopters with 37-foot diameter main rotor systems and hydraulic boost in longitudinal and lateral cyclic flight control systems, certificated in all categories. (Airworthiness Docket No. 83-ASW-47.) Compliance is required within the next 100 hours time in service after the effective date of this AD. To prevent critical flight control failure in the main rotor system, accomplish the following: (a) Inspect for and remove any incorrect AN/NAS standard bolts installed between hydraulic servo and swashplate control plate, Part Number (P/N) 47-150-184-7, which are not listed in the applicable and current illustrated parts breakdown manual. For removal of incorrect AN/NAS standard bolts, utilize the applicable maintenance and overhaul instructions. (b) Install, torque, and safety, required BellHelicopter Textron, Inc., standard bolts, utilizing applicable and current maintenance and overhaul instructions and illustrated parts breakdown manual. (c) Inspect flight control system for safety and security. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (e) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to fly the aircraft to a base where the requirements of this AD may be accomplished. (Bell Helicopter Alert Service Bulletin No. 47-83-8 pertains to this subject.) This amendment becomes effective February 6, 1985.
2019-05-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) 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 a fractured main landing gear (MLG) orifice support tube (OST). This AD requires replacing the MLG OST, and revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
73-18-03: 73-18-03 ROCKWELL INTERNATIONAL: Amendment 39-1707 as amended by Amendment 39-3201. Applies to Model NA-265-40 Serial Numbers 282-1 and subsequent; Model NA-265-50 Serial Number 287-1; Model NA-265-60 Serial Numbers 306-1 through -139; Model NA-265-70 Serial Numbers 370-1 through -9; and Model NA-265-80 Serial Numbers 380-1 through -61. Compliance required as indicated after the effective date of this AD. To detect possible cracks, corrosion, or breaks in the surface finish in the wing spars and related areas, accomplish the following: (a) On or before June 18, 1974, unless previously accomplished within one year, and at intervals not to exceed two years thereafter, inspect the upper and lower flanges of the front and rear spars in the area of the wing center section, and the lugs on the rear spar and wing trailing edge panel rib, per the instructions of Rockwell International, Inc., Sabreliner Division Service Bulletin No. 73-11, dated June 18, 1973, or later FAA-approved revisions, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to further flight, if cracks, corrosion, or breaks in the surface finish are found in the front or rear spars in the area of the wing center section, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Prior to further flight, if cracks are found in the lugs on the rear spar and wing trailing edge rib, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Airplanes may be operated in accordance with FAR 21.197 to a base where maintenance is to be performed. Amendment 39-1707 became effective October 8, 1973. This Amendment 39-3201 becomes effective May 5, 1978.
2006-10-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-223, -321, -322, and -323 airplanes. This AD requires repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the LAPF firewall. We are issuing this AD to detect and correct this cracking, which could reduce the effectiveness of the firewall and result in an uncontrolled engine fire.
87-25-02: 87-25-02 SIKORSKY AIRCRAFT: Amendment 39-5778. Applies to all Model S-76A and S-76B series helicopters through and including serial number 760350, certified in any category. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of AC electrical power due to 26 VAC transformer single ground connection failure, provide separate ground connections for 26 VAC transformers 1 and 2. NOTE: Sikorsky Service Bulletin No. 76-24-5, AC Electrical Power System - AC Power Transformer Ground Wires Termination-Separation of, dated October 19, 1987, constitutes an acceptable means of compliance with this requirement. This amendment becomes effective December 31, 1987.
89-02-03: 89-02-03 BEECH: Amendment 39-6104. Applicability: Model 200 (Serial Numbers BB-2 through BB-161) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished per Beech Service Bulletin No. 2240, dated February 1988, or Beech Letter No. 52-83-0030, dated January 20, 1983, or Beech Letter No. 52-85-0049, dated April 17, 1985. To prevent possible failure of the wing main outboard spar, accomplish the following: (a) Within the next 200 hours time-in-service (TIS) after the effective date of this AD, or upon accumulating 10,000 hours TIS, whichever occurs later, replace both wing main outboard spars in accordance with Beech Service Bulletin No. 2240, dated February 1988. Only the left wing main spar need be replaced for Serial Nos. BB-149 through BB-161. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalentmeans of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6104, AD 89-02-03) becomes effective on February 8, 1989.
2019-05-13: We are removing AD 2007-22-05 and AD 2013-13-13 (referred to after this as ``the affected ADs''), which applied to Airbus SAS Model A300-600 and A310 series airplanes. The affected [[Page 10406]] ADs required certain actions to address various unsafe conditions. The affected ADs are no longer necessary because we have since issued other ADs to address these unsafe conditions. Accordingly, we are removing the affected ADs.
85-01-04: 85-01-04 PITTS: Amendment 39-4980. Applies to Model S-2A (S/N's 2001 through 2105) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of normal aileron and elevator control: (a) Visually inspect the cockpit control tube assembly using a 10 power glass for cracks in the area of the welds attaching the P/N 2-5100-12 stick housings to the P/N 2-5100-11 tube. (1) If cracks are detected weld shut the cracks and install a P/N 2-5100-20 gusset at both the fore and aft stick housing locations in accordance with Pitts Service Letter No. 5, Revision B. (2) If cracks are not present, install P/N 2-5100-20 gussets in accordance with Pitts Service Letter No. 5, Revision B. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) Installation of P/N 2-5100-19 gussets in accordance with Pitts Service Letter No. 5, Revision A, satisfies the requirements of this AD. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Denver Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 10455 East 25th Avenue, Suite 307, Aurora, Colorado 80010; Telephone (303) 340-5594. This amendment becomes effective on January 21, 1985.
99-03-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-03-10 which was sent previously to all known U.S. owners and operators of Agusta Model A109E helicopters by individual letters. This AD requires, before further flight, inspections of the exhaust ejector locking system, clamp, and dampers for each engine. This AD also requires, at specified time intervals, verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment is prompted by an inflight incident in which a metallic clamp which secured the left-hand engine exhaust ejector to the ejector saddle became detached and subsequently separated from the helicopter. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, which could result in damage to the main or tail rotor system and subsequent loss of control of the helicopter.
2006-10-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action if necessary. This new AD requires new inspections for cracking or severe wear of the bearings of the link assembly, inspections of any link assembly not previously inspected for damage, and corrective actions if necessary. This AD also ends the existing repetitive inspections for certain airplanes, and extends the repetitive interval for the existing repetitive inspections and the compliance time for the corrective action on certain other airplanes. This AD also provides an optional terminating action. This AD results from additional reports indicating fractured bearings of the link assembly joint in the inboard and outboard flaps of the trailing edge. We are issuing this AD to prevent failure of the bearings in the link assembly joint, which could result in separation of the inboard or outboard flap and consequent loss of control of the airplane. \n\nDATES: This AD becomes effective June 19, 2006. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 19, 2006. \n\n\tOn February 14, 2002 (67 FR 4328, January 30, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000.