Results
2000-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Allison Engine Company AE 3007 series turbofan engines. This AD would require removal of certain cone shafts from service before exceeding new cyclic life limits and replacement with serviceable parts. This amendment is prompted by additional testing and low cycle fatigue (LCF) life analysis that substantiate lower cyclic lives than originally determined. The actions specified by this AD are intended to prevent LCF failure of cone shafts, which could result in an uncontained engine failure and damage to the aircraft.
81-24-04: 81-24-04 SWEARINGEN: Amendment 39-4261. Applies to the following airplane models approved for flight into known icing: Model SA226-T (Serial Numbers T-205E; T-215E, T-201 through T-275 and T-277 through T-291); Model SA226-T(B) (Serial Numbers T-276; T-303E; and T-292 through T-419); Model SA226-AT (Serial Numbers AT-003E, AT-038E, AT-062E, AT-064E, and AT-001 through AT-419); and Model SA-226-TC (Serial Numbers TC-211E, TC-211EE, TC-211EEE, TC-211EEEE, TC-202E, TC-208E, TC-215E, TC-222E, TC-222EE, TC-227E, TC-228E, TC-229E, TC-234E, TC-237E, TC-238E, TC-239E, TC-255E, TC-246E, and TC-201 through TC-419) airplanes. (Airworthiness Directive Docket No. 81-ASW-37.) Compliance is required within the next 10 hours' time in service after the effective date of this AD unless already accomplished. To prevent operation in icing conditions wherein ice shed from the propeller spinner could be ingested into the engine inlet, resulting in flameout and subsequent total loss of engine power, accomplish the following: (a) Strike from the Type of Operations paragraph in the Operation Limitations Section of the FAA approved Airplane Flight Manual the words, "and icing conditions." (b) Install a placard, minimum 1/4 inch lettering, on the instrument panel in plain view of the pilot stating, "Flight into known icing conditions prohibited." NOTE: Installation of an auto ignition system in accordance with Fairchild Swearingen Corporation Service Bulletin SB 74-002 dated October 22, 1981, removes the limitations in (a) and (b) above. (c) Any alternate equivalent method of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. 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 personsaffected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Director of Product Support, Fairchild Swearingen Corporation, P.O. Box 32486, San Antonio, Texas 78284. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, and at the FAA Headquarters, 800 Independence Avenue, SW., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at their headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective November 19, 1981.
2015-06-04: We are superseding Airworthiness Directive (AD) 2011-13-07 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-13-07 requires revising the airplane flight manual (AFM) to include a procedure to power off a radio-altimeter or revert to the correct radio-altimeter output. This new AD requires revising the AFM to include a simpler procedure to revert to the correct radio-altimeter output. This AD was prompted by an analysis which showed that AFM procedures could be simplified. We are issuing this AD to ensure that the flightcrew has procedures in the event of a radio-altimeter lock-up, which inhibits the display of warnings along with certain abnormal conditions, during the switch into landing mode during altitude cruise. If not corrected, this could result in the flightcrew being unaware of possible system failures that require immediate action by the flightcrew, leading to possible loss of control of the airplane.
2000-07-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-07-51 that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model 717-200 series airplanes by individual notices. This AD requires coiling and stowing of electrical wires between the glareshield control panel and the Integrated Standby Instrument System; and revising the abnormal procedures of the Procedures section of the Airplane Flight Manual to include procedures for identifying and pulling certain circuit breakers if the altimeter Captain's Primary Flight Display (PFD) data become unreliable. This action is prompted by a report of two incidents in which an intermittent loss of altitude data occurred simultaneously on the Captain's PFD, First Officer's PFD, and the Integrated Standby Instrument System (ISIS) altitude display due to a voltage drop in the power distribution control unit. The actions specified by this AD are intended to prevent loss of all altitude information and subsequent essential navigation data for continued safe flight and landing.
2000-09-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires various inspections and functional tests to detect discrepancies of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment adds an appendix and revises certain actions in the existing AD. This amendment is prompted by a report indicating that completion of the cone brake test of the center drive unit is ineffective for certain airplanes. The actions specified in this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
2022-16-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by the discovery that overwing emergency exit door (OWEED) handle covers were difficult to open on some airplanes. This AD requires replacing the existing OWEED handle cover brackets with newly designed OWEED handle cover brackets and installing placards regarding this replacement, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
97-11-04: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 412 and 412EP helicopters, that requires creation of a component history card or equivalent record using a Retirement Index Number (RIN) system; establishes a system for tracking increases to the accumulated RIN; and establishes a maximum accumulated RIN for certain main rotor masts (masts) and main rotor spline plates (spline plates). This amendment is prompted by fatigue analyses and tests that show certain masts and spline plates fail earlier than originally anticipated because of an unanticipated high number of takeoffs and external load lifts utilizing high power settings, in addition to the time-in-service (TIS) accrued under normal operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the mast or spline plate, which could result in failure of the main rotor system and subsequent loss of control of the helicopter.
2000-09-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires tests, inspections, and adjustments of the thrust reverser system. That AD also requires installation of a terminating modification, and repetitive follow-on actions. This amendment revises certain actions in the existing AD. This amendment is prompted by a report indicating that certain instructions referenced in the existing AD for accomplishment of the cone brake test of the center drive unit are not accurate for certain airplanes. The actions specified in this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
82-16-02: 82-16-02 FOKKER B.V.: Amendment 39-4424. Applies to Model F28 Series 1000 and 4000 airplanes certificated in all categories, serial numbers as indicated below. Note: Some serial numbers listed may actually be 2000, 3000, 5000, or 6000 airplanes that are not presently eligible for U.S. certification. Those serial numbers may be disregarded insofar as this AD is concerned. 1. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to airplanes with serial numbers (S/N's) 11004 through 11016. Compliance required within the next 750 hours time in service. To prevent inadvertent cross connection of the engine fire extinguishing bottle electrical wiring, install placards and inspect and rework the wiring in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/26-2, Revision 1, dated March 19, 1970. B. Applies to airplanes with S/N's 11003, 11004, 11006, and 11009 through 11012. Compliance required within the next 900 hours time in service. To preclude inadvertent fuel transfer, install a 1.0 p.s.i. check valve and rework the defueling control valve wiring in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28-3 dated January 6, 1970. C. Applies to airplanes with S/N's 11004 through 11016, 11021 through 11052, 11054 through 11061, 11063 through 11066, and 11991 through 11993. Compliance required within the next 100 hours time in service. To preclude fuel leakage, inspect fuel supply tubes for chafing damage, repair or replace such tubes as necessary, and provide adequate chafing protection in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28- 8 dated December 24, 1969 (S/N's 11004 through 11016), or Service Bulletin F28/28-22, Revision 1, dated December 18, 1972 (S/N's 11021 through 11052, 11054 through 11061, 11063 through 11066, and 11991 through 11993). D. Applies to airplanes with S/N's 11053, 11062, 11077, 11080, 11081, 11090 through 11093, 11108 through 11112, 11114 through 11116, 11118, 11120 through 11124, 11126 through 11128, 11130, 11133, 11135, 11138 through 11142, and 11144. Compliance required within the next 100 hours time in service. To preclude a fuselage fire, perform both of the following: (1) Inspect the APU fuel supply line for interference with electrical wiring and replace as necessary; and (2) Modify the fuel supply line installation and electrical wiring to provide adequate clearance in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28-32, Revision 1, dated September 3, 1979. E. Applies to all airplanes having check valve Part No. 123312-2-1 installed in the Auxiliary Power Unit (APU) bleed air duct. Compliance required within the next 100 hours time in service and at no greater than 3000 hour intervals time in service thereafter. To preclude damage to the APU, inspect the check valve for wear and replace, as necessary, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/36-9, Revision 1, dated February 16, 1973. F. Applies to airplanes with S/N's 11003 through 11056 and 11991 through 11993. Compliance required within the next 100 hours time in service. To ensure proper functioning of the fire seal, inspect the seventh stage bleed air duct fire seal and modify, as necessary, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/36- 10 dated February 12, 1973. G. Applies to airplanes with S/N's 11003 through 11101, and 11991 through 11993. Initial compliance required within the next 100 hours time in service and on a daily basis thereafter. To detect failure of the APU extension silencer and thereby preclude failure of APU exhaust jet pipe, inspect the extension silencer in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/49-24 dated February 23, 1976. These inspections may be discontinued upon installation of an improved APU extension silencer in accordance with Fokker Service Bulletin F28/49-21, Revision 1, dated May 10, 1976. H. Applies to airplanes with S/N's 11003 through 11131, and 11991 through 11993. Compliance required within the next 1500 hours time in service. To ensure adequate drainage of fuel leakage from the APU compartment, modify the APU enclosure drain system in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/49-25 dated July 18, 1977. I. Applies to airplanes with S/N's 11003 through 11013. Compliance required within the next 750 hours time in service. To maintain the integrity of the firewall, close the unused holes in the left hand and right hand engine nacelle firewalls in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/54-2, Revision 1, dated June 15, 1970. J. Applies to airplanes with S/N's 11003 through 11073, 11075, and 11991 through 11993. Compliance required within the next 150 hours time in service. To prevent control cable failure due to corrosion, inspect, replace as necessary, and treat HPC and RPM control cables in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/76-16, Revision 1, dated October 6, 1975. K. Applies to airplanes with S/N's 11003 through 11124, 11126 through 11132, 11134, 11991, and 11992. Compliance required within the next 100 hours time in service. To preclude inadvertent closure of the fire shutoff valves, inspect and correct microswitch adjustment, as necessary, and install seal wire (safety wire) on fire switch guards in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/76-20 dated January 1, 1979. 2. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. Special 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. 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). This amendment becomes effective August 30, 1982.
2015-05-08: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower rainbow fittings on the outer wing are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the upper and lower rainbow fittings on the outer wing to detect cracks propagating from fasteners attaching the fittings to skin panels, and related investigative and corrective actions if necessary; and replacement of the upper and lower rainbow fittings on the outer wing. We are issuing this AD to prevent fatigue cracking of the upper and lower rainbow fittings on the outer wing and skin-panel- to-fitting fastener holes, which could result in reduced structural integrity of the airplane and possible separation of the wing from the airplane.