Results
91-15-05: 91-15-05 ROLLS-ROYCE plc: Amendment 39-7068. Docket No. 91-ANE-19. Applicability: Rolls-Royce plc (RR) GEM Mk 530 series engines, installed on, but not limited to, Westland 30 aircraft. [[Dart]] Compliance: Required as indicated, unless previously accomplished. To prevent external fuel leakage from the hydromechanical fuel control unit (HMU) which could result in a fire hazard in the engine nacelle, accomplish the following: (a) For engines equipped with Hamilton-Standard Model JFC118-22 HMU, part numbers 779218-3, 779218-6, 779218-9, 779218-12, excluding HMU's marked "MS090-001" adjacent to the identification plate, perform the following: (1) Perform an HMU leak check inspection in accordance with RR Service Bulletin (SB) GEM- 73-24, dated October 29, 1990, within the next 15 hours time in service after the effective date of this AD. (2) Thereafter, reinspect the HMU daily for fuel leakage within 30 minutes of the last shut-down of the day, in accordance with RR SB GEM-73-24. (3) Remove from service, prior to further flight, HMU's exhibiting any fuel leakage when inspected in accordance with paragraphs (a)(1) or (a)(2) of this AD. (4) X-ray or disassemble inspect the HMU for correct assembly in accordance with the Accomplishment Instructions of Hamilton-Standard (HS) SB JFC118-22-73-10, dated November 21, 1990, at the next engine shop visit or HMU removal, or by December 31, 1991, whichever occurs first. (5) Remove from service, prior to further flight, HMU's confirmed incorrectly assembled when inspected in accordance with paragraph (a)(4) of this AD. (6) For HMU's determined to be correctly assembled when inspected in accordance with paragraph (a)(4) of this AD, the repetitive inspections of paragraphs (a)(1) or (a)(2) of this AD are no longer required. (b) For the purpose of this AD, shop visit is defined as the induction of an engine into a shop for the conduct of maintenance. (c) 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. (d) 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, Aircraft Certification Service, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (e) The leak check inspection and the x-ray and disassembly inspection shall be done in accordance with the following documents: Document Page Revision Date RR SB GEM-73-24 1-4 Original October 29, 1990 Total Pages: 4 HS SB JFC118-22-73-10 1-12 Original November 21, 1990 Total Pages: 12 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 the United Technologies Corporation, Hamilton- Standard Division, Technical Publications Department, One Hamilton Road, Windsor Locks, Connecticut 06096- 1010, and Rolls-Royce plc, Leavesden, WD27BZ, England. 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. Airworthiness Directive 91-15-05 published in Federal Register on July 23 was not distributed to the public by FAA due to a clerical error in the AD. This corrected version of Airworthiness Directive 91-15-05, Amendment 39-7068, published in the Federal Register on August 8, 1991, becomes effective on August 19, 1991. This amendment (39-7068, AD 91-15-05) becomes effective on August 19, 1991.
96-19-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of certain flexible oxygen hoses, located in the flight compartment gangway and in the consoles, with insulated hose assemblies. This amendment is prompted by reports of either insufficient or no clearance between these hoses and adjacent structure or electrical wiring. The actions specified by this AD are intended to prevent chafing of the flexible oxygen hoses, which could result in an uncontrollable loss of oxygen from the flightcrew oxygen system, and could allow the presence of oxygen in areas where ignition is possible.
2007-16-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600, A310-200, and A310-300 series airplanes. That AD currently requires inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and doing corrective actions if necessary. This new AD also requires inspecting for damage of the identified elevators in accordance with a new repetitive inspection program, at new repetitive intervals; and would provide an optional terminating action for the repetitive inspections. This AD results from reports of damage caused by moisture/water inside the elevator. We are issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and reduced controllability of the airplane. DATES: This AD becomes effective September 18, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 18, 2007. On February 3, 2006 (70 FR 77301, December 30, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300-600-55A6032, dated June 23, 2004; and Airbus All Operators Telex A310-55A2033, dated June 23, 2004.
76-03-05: 76-03-05 BEECH: Amendment 39-2510. Applies to Models 35-B33, 35-C33, E-33, F-33 and G-33 (Serial Numbers CD-388 thru CD-981 and CD-983 thru CD-1304); and Model P-35 (Serial Numbers D-6842 thru D-7139 and D-7141 thru D-7309) airplanes. Compliance: Required as indicated unless already accomplished. To preclude contact of the tachometer cable housing with the battery relay, within the next 50 hours' time in service after the effective date of this AD, install a tachometer cable housing stand-off bracket on the battery box and secure the tachometer cable housing to this bracket in accordance with Beechcraft Service Instruction No. 0784-241 or later FAA-approved revisions or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 17, 1976.
95-17-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, and CL-600-2B16 series airplanes. This action requires functional testing of the brake of the horizontal stabilizer trim actuator (HSTA); and exercising the pitch trim system, revising the FAA-approved Airplane Flight Manual (AFM), operational testing of the HSTA, and replacing the HSTA or horizontal stabilizer trim control unit, if necessary. This amendment is prompted by reports of overspeed annunciation of the pitch trim due to slippage of the no-back device on the HSTA. The actions specified in this AD are intended to prevent uncommanded movement of the HSTA due to failure of the no-back device on the HSTA to operate properly; this condition could adversely affect the controllability of the airplane.
2007-16-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. That AD currently requires repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD revises certain applicabilities and compliance times in the existing AD. This AD results from several reports of cracks of the station 800 frame assembly on airplanes that had accumulated fewer total flight cycles than the initial inspection threshold in the original AD. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. \n\n\nDATES: This AD becomes effective September 13, 2007. \n\n\tOn July 17, 2006 (71 FR 33595, June 12, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2451, Revision 1, dated November 10, 2005. \n\n\tOn August 30, 2001 (66 FR 38891, July 26, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2451, including Appendix A, dated October 5, 2000.
90-05-07: 90-05-07 BRITISH AEROSPACE: Amendment 39-6526. Docket No. 89-NM-232-AD. Applicability: Model BAe 146-200A and -300A series airplanes, equipped with Modification HCM30107C and HCM30300A, as listed in British Aerospace Inspection Service Bulletin 25-A157, dated August 14, 1989, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To ensure unrestricted passage of air from above the cabin floor to below the floor in the event of rapid decompression, accomplish the following: A. Inspect the cabin insulation bags between frames 19 to 26, and frames 32 to 40, inclusive, both left and right sides of the cabin, to ensure the lower edge of the insulation bag is 4 inches above the level of the floor structure, in accordance with British Aerospace Service Bulletin 25-A157, dated August 14, 1989. 1. If sufficient clearance is found, reassemble parts and return the airplane to service.2. If insufficient clearance is found, prior to further flight, modify the insulation bags by folding under the lower edge and securing the insulation bags, in accordance with the service bulletin. B. 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. C. 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, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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. This amendment (39-6526, AD 90-05-07) becomes effective on April 9, 1990.
2007-15-05: The FAA is adopting a new airworthiness directive (AD) for all transport category airplanes identified above. This AD requires an inspection to determine if a certain fuel pump housing electrical connector is installed. This AD also requires a revision to the FAA- approved airplane flight manual (AFM) to advise the flightcrew of the appropriate procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump housing electrical connector if applicable. This AD also requires the deactivation of certain fuel tanks or fuel pumps and the installation of placards if applicable. This AD allows the optional replacement of the fuel pump housing electrical connectors with new, improved parts, which would terminate the AFM revisions, deactivation of certain fuel tanks and fuel pumps, and placard installation. This AD results from a report of two failures of the fuel pump housing electrical connector. We are issuing this AD to prevent continued arcing following a short circuit of the fuel pump housing electrical connector, which could damage the conduit that protects the power lead inside the fuel tank; this condition could create an ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
78-01-08: 78-01-08 BOEING: Amendment 39-3113. Applies to all Model 727 series airplanes certificated in all categories with autospeed brake system installed and airplanes with auto wheel brakes in conjunction with JT8D-17R engines and Boeing automatic throttle clutches, except airplanes with Engine Pressure Ratio (EPR) activated takeoff warning system. \n\tCompliance required as indicated. \n\tWithin 2000 hours time in service after the effective date of this AD, unless already accomplished, set the thrust lever operated switches S197, S784, S553, and S555 to provide actuation down to and including -65 degrees F per applicable part of Boeing Service Bulletin 727-31-30, or later FAA approved revisions, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \tFor airplanes which have automatic throttles not designed by Boeing, the modification kits available from Boeing may not be applicable. Operators of those airplanes must submit their proposed modifications to the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective January 16, 1978.
96-22-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive Tap Test inspections to detect debonding of the elevator skins, and corrective actions, if necessary. This amendment is prompted by a report of a debonded area of the upper skin of an elevator that was discovered during a visual inspection. The actions specified by this AD are intended to prevent the presence of water in the elevator, which could cause debonding of the elevator skins and, consequently, adversely affect the structural integrity of the elevator.
2007-13-09: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires modifying the fuel boost pump container of the center tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion.
96-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 and Model F28 Mark 0100 series airplanes, that requires an inspection to verify that adequate clearance exists between the insulation screen and the two adjacent terminal bolts, and replacement of the circuit breaker terminal bolts with new bolts, if necessary. This amendment is prompted by a report that circuit breaker terminal bolts that were too long were discovered installed in the circuit breaker panels. The actions specified by this AD are intended to prevent damage to the insulation screen between adjacent rows of circuit breakers, as the result of a circuit breaker terminal bolt being too long; this condition could lead to electrical arcing and loss of the associated electrical system, which could result in the potential for an electrical fire.
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.
2007-11-13: The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model 717-200 airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new removal limits for certain components of the flap system and to reduce the interval of inspections for fatigue cracking of certain principal structural elements (PSEs). This new AD requires revising the ALS of the Instructions for Continued Airworthiness to incorporate reduced initial inspection and repeat inspection intervals for certain PSEs. This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane.
2007-03-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines, with certain low pressure (LP) compressor modules installed. This AD requires an ultrasonic inspection (UI) of LP compressor fan blades for cracks, within 30 days after the effective date of the AD on certain serial number (SN) Tay 650-15 engines. This AD also requires initial and repetitive UIs of LP compressor fan blades on all engines. This AD also requires, for Tay 650-15 and Tay 651-54 engines, UIs of LP compressor fan blades whenever the blade set is removed from one engine and installed on a different engine. This AD results from a report that a set of LP compressor fan blades failed before reaching the LP compressor fan blade full published life limit. We are issuing this AD to prevent LP compressor fan blades from failing due to blade root cracks, leading to uncontained engine failure and damageto the airplane.
76-22-01: 76-22-01 BELLANCA AIRCRAFT CORPORATION: Amendment 39-2753. Applies to: MODEL SERIAL NUMBER 7 ECA 1126-76 thru 1173-76 7GCAA 324-76 thru 332-76 7GCBC 887-76 thru 942-76 7KCAB 551-76 thru 584-76 8KCAB 219-76 thru 265-76 8GCBC 188-76 thru 228-76 And all previous serial numbered airplanes in which the adjustable front seat has been installed per Bellanca Kit #252. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To detect permanent deformation and/or cracks in the lower frame side tubes on the adjustable front seat, accomplish the following: a. Inspect the left and right side lower seat frame side tubes for evidence of cracks and/or permanent deformation in an area just forward of the side brace and side tube junction. A permanent upward bow in the side tube at this junction is evidence of permanent deformation. The area can best be inspected after removal of theseat cushion. b. If cracks and/or permanent deformation are found, repair per AC 43.13-1 and install Bellanca Kit #253, or replace the seat frame with a new reinforced seat frame P/N 7-1513, before further flight. c. If cracks and/or permanent deformation are not found, install Bellanca Kit #253 within the next 20 hours' time in service after the effective date of this AD. Bellanca Service Letter #C-125 dated May 19, 1976 pertains to this subject. This amendment becomes effective November 2, 1976.