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2007-12-21: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-26-08, which applies to all Hawker Beechcraft Corporation (HBC) Model 390 airplanes. AD 2006-26-08 currently requires you to repetitively inspect the hydraulic pump outlet tube on both engines and immediately replace the tube if damage is found. AD 2006- 26-08 also requires you to incorporate an airplane flight manual (AFM) change that limits operation of an engine with its associated firewall hydraulic shutoff valve closed. If an engine is operated with its firewall hydraulic shutoff valve closed, you must replace the hydraulic pump outlet tube. We issued AD 2006-26-08 as an interim action while we worked with the type certificate holder to develop a design change. HBC has now developed kits that incorporate design changes for the hydraulic pump outlet tubes and dampener supports so this AD retains the actions of AD 2006-26-08 until the new modification kits required by this AD are installed. We continued to receive additional reports of failures of the hydraulic pump outlet tube. We are issuing this AD to prevent failure of the hydraulic pump outlet tube and consequent leaking of hydraulic fluid. Such leakage could result in a fire. There is also a risk of loss of hydraulic system functions including normal gear extensions, speed brakes, roll spoilers, lift dump, and normal brakes. DATES: This AD becomes effective on June 20, 2007. On June 20, 2007, the Director of the Federal Register approved the incorporation by reference of Raytheon Aircraft Company Kit--Dampener Support Improvement, Drawing No. 390-5804 (Kit 390-5804-0001 Field Service Kit) and Raytheon Aircraft Company Kit--Hydraulic Pump Pressure Hose Installation No. 390-5805 (Kit 390-5805-0001 Field Service Kit), as referenced in Hawker Beechcraft Mandatory Service Bulletin 29-3800, Issued May 2007, as listed in this AD. As of February 2, 2006 (71 FR 5581, February 2, 2006), the Director of the Federal Register approved the incorporation by reference of Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January 2006; and Raytheon Safety Communique No. 267, dated January 2006, as listed in this AD. We must receive any comments on this AD by August 20, 2007.
2007-12-17: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires replacing the metallic tubes enclosing the vent and pilot valve wires in the left- and right-hand wing fuel tanks with non-conductive hoses. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source inside the fuel tank that could ignite fuel vapor and cause a fuel tank explosion and loss of the airplane.
96-18-15: This amendment supersedes an existing airworthiness directive (AD) 96-01-08, which superseded Priority Letter AD 95-23-02, both of which were applicable to certain serial-numbered Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHT) Model 222, 222B, 222U, and 230 helicopters, that currently requires an initial check of both surfaces of each tail rotor blade (blade) for cracks; an inspection of the blade skin if a crack of a specified size or location is found in the paint; and replacement of the blade if a crack is found in the blade skin. This AD requires the same actions as required by the existing AD, but expands the applicability to include additional blade part numbers (P/N). This amendment is prompted by three incidents in which a crack developed in the stainless steel blade skins due to sanding marks on the blades that occurred during the manufacturing process on BHT Model 230 helicopters, which are similar in design to the Model 222, 222B and 222U helicopters. The actions specified by this AD are intended to prevent failure of a blade due to a fatigue crack, loss of the tail rotor and tail rotor gear box, and subsequent loss of control of the helicopter.
2007-12-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Two A330 operators have reported uncontained APU (auxiliary power unit) generator failures on ground. In both events, a loud noise was heard, followed by an APU automatic shutdown. Preliminary investigations confirmed an uncontained APU Generator failure with subsequent aircraft structural damages to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU fire wall which might reduce its fire extinguishing capability, possibly leading to a temporary uncontrolled fire which constitutes an unsafe condition. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2007-12-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires repetitive inspections to detect cracks and/or corrosion of the girt bar support fitting at certain main entry doors (MED), and repair or replacement of the support fitting. The existing AD also provides for various terminating actions for the repetitive inspections. This new AD requires the following additional actions: An inspection, for certain airplanes, for correct installation of square and conical washers in the girt bar support fitting; an inspection, for certain other airplanes, to determine if the washers are installed; and related investigative and corrective action if necessary. This AD results from a report that the square and conical washers may be installed incorrectly in the girt bar support fitting on airplanes on which the support fitting was repaired or replaced in accordance with the requirements of the existing AD. We are issuing this AD to detect and correct corrosion of the girt bar support fitting, which could result in separation of the escape slide from the lower door sill during deployment, and subsequently prevent proper operation of the escape slides at the main entry doors during an emergency. We are also issuing this AD to detect and correct incorrect installation of the square and conical washers in the girt bar support fitting, which could result in failure of the escape slide when deployed. \n\nDATES: This AD becomes effective July 16, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 16, 2007. \n\n\tOn December 16, 1996 (61 FR 58318, November 14, 1996), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747-53A2378, Revision 1, dated March 10, 1994.
92-01-08: 92-01-08 PRATT & WHITNEY CANADA: Amendment 39-8132. Docket No. 90-ANE-29. Applicability: Pratt & Whitney Canada (PWC) PW115, PW118, PW118A, PW120, PW120A, PW121, PW123, PW124B, and PW125B model turboprop engines, with specific engine serial numbers noted in the applicable service bulletins (SB). Affected engines are installed in, but not limited to, the Aerospatiale ATR-42, and ATR-72, British Aerospace ATP, DeHavilland of Canada DHC-8, Embraer EMB-120, Canadair CL-215T, and Fokker 50 aircraft. Compliance: Required at the next engine module overhaul, hot section inspection (HSI), or within 36 months from the effective date of this airworthiness directive (AD), whichever occurs first, unless accomplished previously. To prevent seizure of the high pressure rotor, and subsequent inability to restart the engine inflight, accomplish the following: (a) Rework or replace with a serviceable part, the high pressure turbine front cover in accordance with the requirements of anyof the following PWC SBs, as applicable: SB 20417, Revision 2, dated August 20, 1990, SB 20412, dated November 27, 1989; SB 20604, Revision 1, dated February 25, 1991; or SB 20979, dated April 29, 1991. (b) Rework the low pressure turbine stator vane assembly in accordance with the requirements of PWC SB 20456, Revision 3, dated August 20, 1990. (c) For engines incorporating the "triple segmented" high pressure vane ring segment assembly, Part Number (P/N) 3037761, rework or replace the high pressure vane segments as follows: (1) For PW115, PW118, PW120, PW120A, and PW121 model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of either of the following PWC SBs, as applicable: SB 20419, Revision 3, dated November 26, 1990; or SB 20886, Revision 2, dated February 11, 1991. (2) For PW118A, PW123, PW124B, and PW125B model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SBs, as applicable: SB 20419, Revision 3, dated November 26, 1990; SB 20726, dated February 19, 1990; SB 20742, Revision 4, dated June 12, 1991; SB 20886, Revision 2, dated February 11, 1991; or SB 20869, Revision 1, dated April 26, 1991. (d) For engines incorporating the "triple segmented" high pressure vane ring segment assembly, P/N 3037761, rework or replace with a serviceable part, the cooling air nozzle housing assembly as follows: (1) For PW115, PW118, PW120, PW120A, and PW121 model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SB's, as applicable: SB 20341, Revision 2, dated September 3, 1991, SB 20436, dated March 6, 1989, or SB 20873, Revision 3, dated April 8, 1991. (2) For PW118A, PW123, PW124B, and PW125B model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SB's, as applicable: SB 20341, Revision 2, dated September 3, 1991, SB 20436, dated March 6, 1989, SB 20873, Revision 3, dated April 8, 1991, SB 20896, Revision 3, dated August 26, 1991, or SB 20872, Revision 2, dated July 8, 1991. (e) An alternative method of compliance or adjustment of the compliance time, that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (f) 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. (g) The engine modifications shallbe done in accordance with the following Pratt & Whitney Canada SB's: DOCUMENT NO. PAGE ISSUE/REVISION DATE SB 20341R2 1-4 Rev. 2 Sept. 3, 1991 Total Pages: 4 SB 20412 1-8 Original Nov. 27, 1989 Total Pages: 8 SB 20417R2 1-7 Rev. 2 Aug. 20, 1990 Total Pages: 7 SB 20419R3 1-6 Rev. 3 Nov. 26, 1990 Total Pages: 6 SB 20436 1-3 Original Mar. 6, 1989 Total Pages: 3 SB 20456R3 1-3 Rev. 3 Aug. 20, 1990 4 Rev. 1 Oct. 12, 1989 5 Rev. 2 Apr. 30, 1990 6-8 Original Jun. 21, 1989 Total Pages: 8 SB 20604R1 1-7 Rev. 1 Feb. 25, 1991 Total Pages: 7 SB 20726 1-3 Original Feb. 19, 1990 Total Pages: 3 SB 20742R4 1-4 Rev. 4 June 17, 1991 Total Pages: 4 SB 20869R1 1-6 Rev. 1 Apr. 26, 1991 Total Pages: 6 SB 20872R2 1-30 Rev. 2 July 8, 1991 Total Pages: 30 SB 20873R3 1-7 Rev. 3 Apr. 8, 1991 Total Pages: 7 SB 20886R21-6 Rev. 2 Feb. 11, 1991 Total Pages: 6 SB 20896R3 1-9 Rev. 3 Aug. 26, 1991 Total Pages: 9 SB 20979 1-7 Original Apr. 29, 1991 Total Pages: 7 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 Pratt & Whitney Canada, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec J4G 1A1. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (h) This amendment becomes effective on July 27, 1992.
2007-12-03: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires revising the Limitations section of the airplane flight manual to include procedures for pulling the "HYD PWR XFER'' circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. This AD results from reports of fluid loss in the No. 2 hydraulic system, causing the power transfer unit to overspeed, increasing the fluid flow within the No. 1 hydraulic system. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane.
2007-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD requires, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. This AD also requires, for certain airplanes, revising the de Havilland DHC-8 Maintenance Program Manual to include the MLG shock strut servicing task. This AD results from reports of over-extension of the MLG shock strut piston, which allows the torque links to go over-center and rest on the piston. We are issuing this AD to prevent loss in shock absorption during touchdown and failure of the shock strut housing, which could result in a subsequent loss of directional control.
2007-02-23: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200, -300, and -300ER series airplanes. This AD requires replacement of the gimbal plates of the left and right outboard trailing edge flaps with improved gimbal plates and other specified actions. This AD results from a broken pivot link found on the inboard support for the outboard trailing edge flap. We are issuing this AD to prevent disconnection of the drive arm from its drive gimbal, due to a broken pivot link on an outboard flap support, which could result in unexpected roll of the airplane and loss of control of the airplane.
92-06-16: 92-06-16 BOEING: Amendment 39-8196. Docket No. 91-NM-191-AD. \n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757- 53A0060, dated August 8, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent side-of-body floor panels from breaking away from the floor beams during a 9g forward load event, accomplish the following: \n\n\t(a)\tWithin the next 24 months after the effective date of this AD, examine the identification placards of each side-of-body floor panel to determine the manufacturer and date of manufacture of the panel, as specified in Figure 1 of Boeing Alert Service Bulletin 757-53A0060, dated August 8, 1991. \n\n\t\t(1)\tIf the panel was manufactured by Hexcel before January 7, 1991: Prior to further flight, repair all one-piece inserts in the panel or replace the panel, in accordance with Boeing Alert Service Bulletin 757-53A0060, dated August 8, 1991. \n\n\t\t(2)\tIf thepanel was manufactured by Hexcel panel on or after January 7, 1991, or if the panel was not manufactured by Hexcel: No further action is required. \n\n\t(b)\tAn alternative method 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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base where the requirements of this AD can be accomplished. \n\n\t(d)\tThe inspection shall be done in accordance with Boeing Alert Service Bulletin 757-53A0060, dated August 8, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. 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. \n\n\t(e)\tThis amendment becomes effective on April 28, 1992.