Results
81-06-07: 81-06-07 GULFSTREAM AMERICAN CORPORATION (formerly Grumman American Corporation, Grumman Aerospace Corporation): Amendment 39-4054. Applies to Gulfstream American Model G-1159, serial numbers 1 through 258, and 775, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent improper functioning of the landing gear system, accomplish the following: Within the next 10 hours time in service after the effective date of this AD, inspect the landing gear selector valve to determine valve part number (Ref. Gulfstream II Illustrated Parts Catalog (IPC) Figure 32-23, Item 52). (a) If P/N 1159SCH216-1 or P/N 1159SCH216-5 is installed, no further action is required. (b) If P/N 1159SCH216-3 is installed, accomplish the following: (1) Before further flight, install placard adjacent to the landing gear selector handle. The wording of the placard shall be: "INTERRUPTION OF LANDING GEAR RETRACTION OR EXTENSION PROHIBITED",using letters of 1/8 inch minimum height. Concurrently, FAA Approved Flight Manual Supplement No. GII-81-01, dated February 6, 1981, must be added to the Airplane Flight Manual. The Flight Manual Supplement may be obtained from Gulfstream American Corporation, P.O. Box 2206, Savannah, Georgia 31402. (2) Within 60 landing gear operating cycles (one retraction and one extension) after effective date of this AD, replace P/N 1159SCH216-3 landing gear selector valves with either a P/N 1159SCH216-1 or a P/N 1159SCH216-5 valve. Remove the placard and the Airplane Flight Manual Supplement added in section (1) when either of the replacement valves is installed. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. NOTE: Information concerning replacement selector valves may be obtained from Gulfstream American Corporation Customer Bulletin No. 305, amendment No. 1, January 15, 1981. This amendment is effective March 27, 1981.
2019-03-08: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports of an overheat failure mode of the hydraulic engine-driven pump (EDP), and a determination that the affected EDP needs to be replaced with an improved EDP. This AD requires replacement of a certain EDP with an improved EDP. We are issuing this AD to address the unsafe condition on these products.
2019-03-21: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of corrosion and chromium layer chipping of the forward and aft pintle pins of the main landing gear (MLG) shock struts. This AD requires repetitive inspections for discrepancies of affected forward and aft pintle pins of the MLG shock struts, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
62-10-04: 62-10-04 PRATT & WHITNEY: Amdt. 432 Part 507 Federal Register April 26, 1962. Applies to All JT4A Series Turbojet Engines. Compliance required within the next 85 hours' time in service after the effective date of this directive and thereafter at periods not to exceed 85 hours' time in service from the last inspection. Inspect third stage turbine rotor blades, P/N 405903, 411803, or 411903, for looseness or rattling in accordance with Pratt & Whitney Aircraft telegraphic message of November 15, 1961. If any blade looseness or rattling is found, remove the engine for blade replacement prior to further flight, except that an operator conducting more frequent periodic inspections than at the 85-hour intervals may delay replacement of loose blades for one additional 15-hour period of time in service provided that time in service since a known no loose blade condition will not exceed 85 hours. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Pratt & Whitney Aircraft telegraphic messages of November 15, 1961, and January 29, 1962, cover the same subject.) This directive effective April 26, 1962. (Revised June 14, 1962, for all persons except those to whom it was made effective immediately by individual telegrams dated May 14, 1962.)
2005-24-09: The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller assemblies, models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X. This AD requires, within 10 flight hours or 10 days after the effective date of this AD, whichever occurs first, removing certain serial number propeller hubs from service. This AD results from a report by the manufacturer that they manufactured and released 40 propeller hubs with improperly machined socket retention threads. We are issuing this AD to prevent cracked propeller hubs, which could cause failure of the propeller hub, blade separation, and loss of control of the airplane.
2002-19-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier-Rotax GmbH 912 F series and 912 S series reciprocating engines with fuel pump assembly part number (P/N) 996.596 installed. This action requires initial and repetitive visual inspections and tests of the fuel pump assembly for fuel leakage. This amendment is prompted by two reports of fuel pump assembly fuel leaks. The actions specified in this AD are intended to prevent in-flight fuel leaks of the fuel pump assembly, which could result in an engine fire.
2005-06-01: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC 155B1 helicopters that requires inspecting the chamfer of the stop on the cabin sliding doors (doors) and installing an airworthy stop if the chamfer exceeds a certain length; and prior to each flight, visually checking the door to determine if it is correctly locked in the open position before flying with the doors open, and checking the locking indicator light and the position of the door handles before flying with the doors closed. This amendment also requires revising the Limitations Section of the Rotorcraft Flight Manual (RFM) to prohibit the opening or closing of a cabin sliding door at airspeeds of 40 or greater knots indicated airspeed (KIAS). This amendment is prompted by a report of a door separating from a helicopter during flight. The actions specified by this AD are intended to prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter.
2005-24-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-300 series airplanes. This AD requires replacing the frequency converters used to supply power for medical and galley utility outlets with modified frequency converters, and related actions. This AD results from a report indicating that a hard short circuit condition between the output of certain frequency converters and their downstream circuit breakers will produce a continuous output current that could cause the undersized output wiring to overheat when the frequency converters fail to shut off. We are issuing this AD to prevent overheating of the output wiring of the frequency converters, which could result in the failure of a wire bundle and consequent adverse effects on other systems sharing the affected wire bundle.
2019-03-05: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD revises the life limit for the nose landing gear (NLG) assembly. This AD was prompted by revised airworthiness limitations determined by Bell. The actions of this AD are intended to prevent an unsafe condition on these products.
2019-03-03: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series; Model A319 series; Model A320 series; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of multiple angle of attack (AoA) probe blockages. This AD requires all elevator [[Page 4687]] aileron computer (ELAC) units to be upgraded with new software, or replaced with upgraded units. We are issuing this AD to address the unsafe condition on these products.
56-24-01: 56-24-01 CONVAIR: Applies to All 240, 340 and 440 Series Aircraft. Compliance recommended at the next engine overhaul but required on all aircraft by September 1, 1957. Several cases of engine cylinder failures have occurred in which it was subsequently impossible to feather the propeller. The feathering line is presently routed over the top of the No. 8 cylinder and when this cylinder is dislodged, due to stud failures or flange failure, the feathering line is severed thus preventing feathering and causing an additional fire hazard from oil being pumped onto the engine. The record of cylinder failures from studs loosening or breaking indicates that the front row cylinders are mainly involved. To prevent loss of feathering control from such failures, either of the following actions is required: 1. The propeller feathering line is to be rerouted between cylinders. (Convair Service Bulletins Nos. 240-479, 340-205 and 440-23 cover an acceptable method of complying with this modification on Models 240, 340 and 440, respectively.) 2. The propeller feathering line is to be routed between cylinders on the front row of cylinders. It shall be acceptable for the line to pass over the top of a rear row cylinder provided there is adequate flexibility in the line assembly to allow for some displacement without breaking line or fittings in the event of a cylinder failure.
2005-24-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. That AD currently requires revising the airplane flight manual (AFM) to prohibit in-flight auxiliary power unit (APU) starts, and installing a placard on or near the APU start/stop switch panel to provide such instructions to the flightcrew. This new AD adds an optional revision to the AFM that allows limited APU starts and adds a terminating action. This AD results from the airplane manufacturer developing modifications that revise or eliminate the need for restrictions to in-flight APU starts. We are issuing this AD to prevent flame backflow into the APU compartment through the eductor during in- flight APU starts, which could result in fire in the APU compartment.
2019-02-05: We are superseding Airworthiness Directive (AD) 2013-11-03, which applied to certain Viking Air Limited Model CL-215-1A10 and CL- 215-6B11 (CL-215T Variant) airplanes. AD 2013-11-03 required repetitive detailed inspections for cracking of the left-hand (LH) and right-hand (RH) wing lower skin, and repair if necessary. This AD requires repetitive borescope inspections of the LH and RH wing lower skin and repetitive eddy current inspections of the LH and RH wing front and rear lower spar caps. This AD was prompted by reports of a fractured wing lower rear spar cap and reinforcing strap and a report of cracking of the wing lower skin and rear spar. We are issuing this AD to address the unsafe condition on these products.
2004-25-16: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2001-17-13, which applies to aircraft equipped with a Kelly Aerospace Power Systems (Kelly Aerospace) part number (P/N) 14D11, A14D11, B14D11, C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 fuel regulator shutoff valve used with Kelly Aerospace B1500, B2030, B2500, B3040, B3500, B4050, or B4500 B-Series combustion heaters. AD 2001-17-13 requires you to visually inspect or pressure test the fuel regulator shutoff valves for leaks and replace the fuel regulator shutoff valve if leaks are found. This AD is the result of continued reports of fuel regulator shutoff valve problems and the manufacturer revising the service information to modify the pressure test procedures and to specify installing improved design replacement parts. This AD retains the actions required in AD 2001-17-13, makes the inspection repetitive, and requires installing improved design replacement parts. We are issuing this AD to prevent failure of the fuel regulator shutoff valve, which could result in fuel leakage in aircraft with these combustion heaters. This failure could result in an aircraft fire.
81-19-06: 81-19-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-4218. Applies to Model Falcon 10 series airplanes, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loosening of seat belt screws, jamming of movement locking spigots, rupture of movement actuator coupling endfitting, and rupture of backrest housings in pilot and co-pilot seats, accomplish the following: (a) Within the next 300 hours time in service after the effective date of this AD, on Falcon 10 airplanes serial numbers 1 through 20, 22 through 31, 33 through 38, 41 and 42, modify the pilot and co-pilot seat belt attachments in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Avions Marcel Dassault - Breguet Aviation Service Bulletin No. F10 0085, Revision 1, dated November 30, 1979, or an FAA-approved equivalent. (b) Within the next 300 hours time in service after the effective date of this AD, on Falcon 10 airplanes serialnumbers 1 through 49, 51 through 90, 92, 94 through 97, 99, 100, 102 and 104, modify the pilot and co-pilot seat fore and aft movement locking control in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Avions Marcel Dassault - Breguet Aviation Service Bulletin No. F10 0143, Revision 1, dated November 30, 1979, and SICMA AERO-SEAT Service Bulletin No. 376/F10/BS02, Revision 1, dated November 30, 1979, or an FAA-approved equivalent. (c) Within the next 600 hours time in service after the effective date of this AD, or before the accumulation of 1600 hours time in service, whichever occurs later, modify and improve greasing of the actuator endfitting on the following pilot and co-pilot seats in accordance with the instructions in paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Avions Marcel Dassault - Breguet Aviation Service Bulletin No. F10 0148, Revision 2, dated February 1, 1980, and SICMA AERO-SEAT Service Bulletin No. 376/F10/BS03, Revision 1, dated November 30, 1979, or an FAA-approved equivalent: Part No. Seat Serial Numbers Pilot Seat 376-2R1 1 through 52 376-211 53 through 117 376-22 118 through 123 Co-Pilot Seat 376-3R1 1 through 52 376-311 53 through 83 and 85 through 117 376-32 118 through 122 (d) Within the next 600 hours time in service after the effective date of this AD or before the accumulation of 1600 hours time in service, whichever occurs later, on Falcon 10 airplanes serial numbers 1 through 102, 104 through 123, 125 through 128, and 133, modify the pilot and co-pilot seat backrest housings in accordance with the instructions in paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Avions Marcel Dassault - Breguet Aviation Service Bulletin No. F10 0193, Revision 1, dated November 30, 1979, and SICMA AERO-SEAT Service Bulletin No. 376-0017, Revision 2, dated November 30, 1979, or an FAA-approved equivalent. (e) If an equivalent means of compliance is used in complying with this AD, thatequivalent means must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Falcon Jet Corporation, 90 Moonachie Avenue, Moonachie, New Jersey 07074. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington DC 20591. This amendment becomes effective October 14, 1981.
60-01-05: 60-01-05 LOCKHEED: Amdt. 74 Part 507 Federal Register January 6, 1960. Applies to all 188A and 188C Aircraft. Compliance required as indicated. Continuing investigation of the propeller deicing power transfer relay has shown the design of the relay is such that properly tightened terminals cannot be assured for a practical interval of time due to cold flowing of plastic relay body. Upon arrival at the next station where maintenance personnel are available, deactivate the propeller deicing system by pulling the control circuit breaker on the main and essential direct current bus at the forward load center. Placard the propeller deicing system inoperative. On arrival at main base disconnect 8-gage power wires from the priority A and B bus to the propeller deicing power relay. Type and stow at priority bus end. With the propeller deicing system deactivated, aircraft may be dispatched into known icing conditions if Icex compound (B. F. Goodrich Company Adhesive Depressant No. 6) is applied to all propeller blade fairing heater boots and spinners under the following conditions: After initial application, Icex compound shall be reapplied after cumulative exposure to not more than six hours precipitation during flight or after 50 hours elapsed time, whichever occurs first. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27, 1959, covers this same subject.) The propeller electrical deicing system may be returned to operative status when the original propeller ice control relay (Lockheed P/N 613649-1, Leach P/N 9202-4516) has been removed and a new relay (Lockheed P/N 613422-17, Hartman B124-GL) has been installed in the circuit and physically located in the main transfer relay box in a manner approved by an authorized representative of the Administrator. When the propeller electrical deicing system has been reactivated in this manner, Icex compound will no longer be required for aircraft dispatching into known icing conditions. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27 covers the deactivation of the original Leach relay and the use of Icex compound. Lockheed 188 Service Bulletin No. 403, effective December 15, 1959, describes a satisfactory and approved means of installing the replacement Hartman relay.) This airworthiness directive sent by telegram to all operators of Lockheed 188A and 188C aircraft on December 8, 1959.
2005-23-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200 and -300 series airplanes. This AD requires replacing hinge assemblies with new hinge assemblies in the outboard overhead stowage bins and reworking hinge assemblies in the outboard overhead stowage bins that are adjacent to curtain tracks. This AD results from reports of hinge assemblies of outboard overhead stowage bins breaking or the stowage bin doors not latching properly. We are issuing this AD to prevent the outboard overhead stowage bins opening during flight and releasing baggage, and consequently injuring passengers and blocking the aisles during emergency egress.
2018-26-04: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that due to an issue with the flight warning system (FWS) logic, it is possible that the ``AIR Auxiliary Power Unit (APU) BLEED LEAK'' electronic centralized aircraft monitoring (ECAM) alert can trigger several times. This AD requires revising the airplane flight manual (AFM) to incorporate procedures related to an APU bleed leak. We are issuing this AD to address the unsafe condition on these products.
98-17-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-17-10 that was sent previously to all known U.S. owners and operators of Pratt & Whitney Canada (PWC) PW530A series turbofan engines by individual letters. This AD requires recording engine surge events in the aircraft maintenance records. If an engine surge event is experienced, this AD requires, prior to the next flight, inspecting that engine for evidence of second stage stator vanes rubbing on the compressor rotor. In addition, this AD requires reworking all affected engines to increase the clearance between the second stage stator vanes and the compressor rotor. This amendment is prompted by reports of 4 inflight engine shutdowns and 2 additional unscheduled engine removals for significant compressor rotor damage. The actions specified by this AD are intended to prevent an inflight engine shutdown due to rubbing of the second stage stator vanes on the compressor rotor.
80-08-06 R1: 80-08-06 R1 GENERAL ELECTRIC COMPANY: Amendment 39-3740 as amended by Amendment 39- 4005. Applies to CJ610-8A and -9 turbojet and CF700-2D and -2D-2 turbofan engines with turbine disks identified by serial numbers below. To prevent low cycle fatigue failure of turbine disks suspected to have foreign material segregation, accomplish the following within the next 50 cycles. Remove from service first stage turbine disks, P/N 5011T75P01, and second stage turbine disks P/N 5011T76P01, with serial numbers listed below and replace with serviceable disks: SERIAL NUMBERS: FIRST STAGE: GATWZA 00585 GATWZA 00637 GATWZA 00677 GATWZA 00587 GATWZA 00640 GATWZA 00679 GATWZA 00599 GATWZA 00641 GATWZA 00680 GATWZA 00601 GATWZA 00642 GATWZA 00681 GATWZA 00604 GATWZA 00644 GATWZA 00682 GATWZA 00607 GATWZA 00645 GATWZA 00683 GATWZA 00610 GATWZA 00646 GATWZA 00687 GATWZA 00611 GATWZA 00647 GATWZA 00690 GATWZA 00613 GATWZA 00649 GATWZA 00691 GATWZA 00615 GATWZA 00652 GATWZA 00692 GATWZA 00616 GATWZA 00658 GATWZA 00693 GATWZA 00617 GATWZA 00662 GATWZA 00704 GATWZA 00618 GATWZA 00663 GATWZA 00705 GATWZA 00624 GATWZA 00664 GATWZA 00706 GATWZA 00626 GATWZA 00665 GATWZA 00707 GATWZA 00627 GATWZA 00667 GATWZA 00708 GATWZA 00630 GATWZA 00671 GATWZA 00709 GATWZA 00632 GATWZA 00672 GATWZA 00710 GATWZA 00633 GATWZA 00673 GATWZA 00713 GATWZA 00634 GATWZA 00674 GATWZA 00714 GATWZA 00635 GATWZA 00676 GATWZA 00715 FIRST STAGE: OJAWZA 11J774-22 OJAWZA 11J796-20 OJAWZA 11J796-01 OJAWZA 11J796-21 OJAWZA 11J796-03 OJAWZA 11J796-23 OJAWZA 11J796-04 OJAWZA 11J796-24 OJAWZA 11J796-05 OJAWZA 11J796-31 OJAWZA 11J796-06 OJAWZA 11J796-32 OJAWZA 11J796-07 OJAWZA 11J796-35 OJAWZA 11J796-08 OJAWZA 11J796-41 OJAWZA 11J796-09 OJAWZA 11J796-42 OJAWZA 11J796-11 OJAWZA 11J796-43 OJAWZA 11J796-13 OJAWZA 11J796-44 OJAWZA 11J796-15 OJAWZA 11J796-45 OJAWZA 11J796-16 SECOND STAGE: GATWZA 00541 GATWZA 00583 GATWZA 00614 GATWZA 00542 GATWZA 00585 GATWZA 00616 GATWZA 00545 GATWZA 00587 GATWZA 00617 GATWZA 00547 GATWZA 00588 GATWZA 00618 GATWZA 00548 GATWZA 00589 GATWZA 00619 GATWZA 00549 GATWZA 00590 GATWZA 00621 GATWZA 00550 GATWZA 00592 GATWZA 00622 GATWZA 00551 GATWZA 00593 GATWZA 00623 GATWZA 00552 GATWZA 00594 GATWZA 00624 GATWZA 00553 GATWZA 00595 GATWZA 00630 GATWZA 00554 GATWZA 00596 GATWZA 00632 GATWZA 00557 GATWZA 00597 GATWZA 00634 GATWZA 00563 GATWZA 00598 GATWZA 00636 GATWZA 00564 GATWZA 00600 GATWZA 00637 GATWZA 00565 GATWZA 00601 GATWZA 00638 GATWZA 00566 GATWZA 00602 GATWZA 00640 GATWZA 00567 GATWZA 00604 GATWZA 00642 GATWZA 00570 GATWZA 00605 GATWZA 00643 GATWZA 00571 GATWZA 00607 GATWZA 00646 GATWZA 00574 GATWZA 00609 GATWZA 00648 GATWZA00575 GATWZA 00610 GATWZA 00649 GATWZA 00577 GATWZA 00611 GATWZA 00651 GATWZA 00580 GATWZA 00612 GATWZA 00581 GATWZA 00613 SECOND STAGE: OJAWZA 11J781-01 OJAWZA 11J781-19 OJAWZA 11J781-02 OJAWZA 11J781-20 OJAWZA 11J781-03 OJAWZA 11J781-21 OJAWZA 11J781-04 OJAWZA 11J781-22 OJAWZA 11J781-05 OJAWZA 11J781-23 OJAWZA 11J781-06 OJAWZA 11J781-24 OJAWZA 11J781-07 OJAWZA 11J781-25 OJAWZA 11J781-08 OJAWZA 11J781-26 OJAWZA 11J781-09 OJAWZA 11J781-27 OJAWZA 11J781-10 OJAWZA 11J781-28 OJAWZA 11J781-11 OJAWZA 11J781-29 OJAWZA 11J781-12 OJAWZA 11J781-31 OJAWZA 11J781-13 OJAWZA 11J781-32 OJAWZA 11J781-14 OJAWZA 11J781-33 OJAWZA 11J781-15 OJAWZA 11J781-34 OJAWZA 11J781-16 OJAWZA 11J781-35 OJAWZA 11J781-17 OJAWZA 11J781-37 OJAWZA 11J781-18 OJAWZA 11J781-38 General Electric Company Alert Service Bulletin Nos. (CJ610) A72-135, Addendum 1, dated May 19, 1980, and (CF700) A72-142, Addendum 1, dated May 19, 1980, refer to this subject. This amendment was effective upon receipt of the Emergency Airworthiness Directive dated May 30, 1980, and is effective to all others on February 2, 1981.
62-11-02: 62-11-02 GENERAL ELECTRIC: Amdt. 437 Part 507 Federal Register May 12, 1962. Applies to All Models CJ805-23, CJ805-23B, and CJ805-23C Turbofan Engines. Compliance required as indicated. To preclude low cycle fatigue failure of the fan bluckets, remove GE P/N's 109R164P1, 107R392P1, 107R362P5, 107R362P6, 109R200P1, or 109R197P1 from engines and retire from further service upon accumulation of operating cycle life limit as scheduled in GE Alert Service Bulletins Nos. A/23/72-58 and A/23B/72-18, unless the engine is operated in conjunction with an inspection program approved by FAA Eastern Region Engineering and Manufacturing Branch. Under an approved inspection program, the bluckets shall be removed from service and replaced with new units when inspection dictates. For the purposes of this AD, an operating cycle is considered to be an excursion of engine operation from engine start to takeoff to shutdown. Restart in the air is also a cycle. Ground operations encompassinga start and operation to takeoff power is a cycle. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated April 26, 1962. This supersedes AD 62-09-03. Revised September 7, 1962.
2005-23-21: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracking of the junction between the thrust reverser forward frame and the 12 o'clock and 6 o'clock beams; the thrust reverser common fittings; and the thrust reverser J-ring structure at the 12 o'clock and 6 o'clock positions; and related investigative and corrective actions. This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o'clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane.
98-21-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-700 and -800 series airplanes. This action requires a one-time inspection to determine the serial numbers of the fire detector assemblies and elements for the auxiliary power unit (APU) and engines, and replacement of the assemblies or elements with new or serviceable parts, if necessary. This amendment is prompted by a report indicating that certain fire detector elements were not checked for leaks during manufacturing and, therefore, may not have the correct set points for the fire warning system. The actions specified in this AD are intended to prevent failure of the APU or engine fire detection systems to detect a fire in a timely manner, which could result in egress of an APU or engine compartment fire to other parts of the airplane.
98-20-39: This amendment adopts a new airworthiness directive (AD) that applies to certain Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires inspecting each forward attachment fitting bolt of the wing tip tanks for the correct bolt and replacing any incorrect bolt. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Japan. The actions specified by this AD are intended to prevent the wing tip tank from separating from the airplane because of an incorrect bolt corroding, which could result in loss of control of the airplane.
56-21-04: 56-21-04 RUSSELL: Applies to Safety Belts Equipped With Russell Manufacturing Co.'s 2 Inch Rusco Tog-L-Lok Safety Belt Buckle. Compliance required as soon as possible but not later than December 30, 1956. Recurring instances have been reported wherein Russell Model RM-3 and RM-4 belt assemblies have slipped and unlocked under relatively low tension loads. Accordingly, it has been determined that safety belt assemblies RM-3 and RM-4 manufactured between July 1, 1954, and August 1, 1956, as meeting Technical Standard Order C22b standards and equipped with Rusco Tog-L-Lok buckles, are unairworthy and must be reworked or replaced with belt assemblies that conform to TSO-C22b standards. Due to the need for precise jigs to accomplish the rework of these assemblies, reworking in the field is not feasible. However, the Russell Manufacturing Co. has submitted satisfactory substantiating data for reworking the unsatisfactory safety belt assemblies at the factory. In addition to the above difficulty, some of the faulty Tog-L-Lok buckles may have been sold as, or on, military surplus equipment and, therefore, there is some likelihood that other companies or individuals may have renovated or manufactured and sold safety belt assemblies which incorporate these faulty buckles. The characteristics of these buckles are such that if the assembly does not slip or unlock under a maximum tensile load of 100 pounds, the belt assembly is satisfactory. Accordingly, a maximum tensile load of 100 pounds need be applied to these belt assemblies to check their airworthiness. If the assembly does not slip or unlock under this load, the assembly may be considered satisfactory and rework or replacement is not necessary.