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77-02-02: 77-02-02\tBOEING: Amendment 39-2811. Applies to Boeing Model 727-100 and -200 series airplanes certificated in all categories with .047" dia. static sensing holes. Compliance required within 3000 hours time in service after the effective date of this AD unless already accomplished. \n\tTo prevent fluctuations in airspeed and altitude information due to water being ingested and retained in the static port fittings, enlarge the static port sensing holes from .047" dia. to .125" dia. in accordance with Boeing Service Bulletin 727-34-94 (to be released) or later FAA approved service bulletins, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tBoeing 727-100 airplanes already incorporating Boeing S.B. 727-25-42, Revision 1, dated March 4, 1968, with elbow fitting MS21908D6, and Boeing S.B. 727-34-57, dated April 7, 1968, enlarging the static sensing holes, are in compliance with this AD. \n\tThe manufacturer's specifications and proceduresidentified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\tThis amendment becomes effective February 22, 1977.
2020-08-04: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G- JM, PW1124G1-JM, and PW1122G-JM model turbofan engines. This AD was prompted by reports of failures of certain low-pressure turbine (LPT) 3rd-stage blades. This AD requires replacement of the affected LPT 3rd- stage blades. The FAA is issuing this AD to address the unsafe condition on these products.
98-06-09: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires a visual inspection to detect fatigue cracking or loose fitting stress pads of the aileron operating arm brackets; and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking in the flanges of the aileron operating arm brackets, which could result in failure of the aileron operating arm brackets, failure of the aileron control system, and consequent reduced controllability of the airplane.
2008-09-12: 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that it is necessary to introduce Critical Design Configuration Control Limitations (CDCCL), in order to preserve critical fuel tank system ignition source prevention features during configuration changes such as modifications and repairs, or duringmaintenance actions. Failure to preserve critical fuel tank system ignition source prevention features could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-09-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: The Type Certificate Holder (TCH) has received several reports of failed Rudder torque tube assemblies. The torque tube assemblies are subject to repetitive inspection in accordance with Airworthiness Directive 2060 PRE 80. The recent failures occurred in service after the inspections required by AD 2060 PRE 80 had been performed. In the event of such failures, loss of directional control through both the Rudder and Nosewheel Steering may occur. The TCH has also received reports of loose rivets attaching the inboard Anchor Assembly to the Starboard Torque Tube. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-08-02: The FAA is adopting a new airworthiness directive (AD) for certain Thales AVS France SAS (Thales) Global Positioning System/ Satellite Based Augmentation System (GPS/SBAS) receivers installed on airplanes and helicopters. This AD was prompted by reports that Thales GPS/SBAS receivers provided, under certain conditions, erroneous outputs on aircraft positions. This AD requires the installation of a software update to the aircraft navigation database and insertion of a change to the applicable airplane flight manual (AFM). The FAA is issuing this AD to address the unsafe condition on these products.
80-13-12 R1: 80-13-12 R1 DEHAVILLAND: Amendment 39-3815 as amended by Amendment 39-4135. Applies to all DHC-6 model airplanes, Serial Numbers 1 thru 631, equipped with intermediate or high flotation tires, skis, or floats, certificated in all categories. To prevent possible failure of the engine nacelle lower longerons due to cracking or buckling, accomplish the following: (a) For aircraft equipped with high flotation tires (37 inch diameter or larger) and operating to or from unprepared surfaces, visually inspect inner edge of each engine nacelle lower longeron daily, six to eight inches aft of forward end of longeron, for cracks or buckling. Use at least a ten power glass for crack detection. (b) For aircraft equipped with intermediate flotation tires and operating to or from unprepared surfaces, skis, or floats, visually inspect longerons in accordance with procedure and method in paragraph (a), within 24 hours in service, unless already accomplished within the last 26 hours in service. This inspection must be repeated thereafter term at intervals not to exceed 50 hours in service from the last inspection. (c) For aircraft which have been equipped with any of the above landings or flotation gear and are now equipped with standard wheels and tires, visually inspect longerons in accordance with procedure and method in paragraph (a), within 24 hours in service after the effective date of this AD, unless already accomplished. (d) If cracks or buckles are found, replace the longeron with a serviceable one of the same part number, or with an approved equivalent, before further flight. (e) All above inspections may be discontinued when Modification No. 6/1655, or approved equivalent, is accomplished. (f) Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector. Amendment 39-3815 was effective July 1, 1980. This amendment 39-4135 is effective June 19, 1981.
91-08-51: 91-08-51 HONEYWELL: Amendment 39-7031. Docket No. 91-NM-94-AD. Applicability: Honeywell Flight Management System (FMS) one million word (1M or 700K) data bases (9104 cycle or earlier), as installed in, but not limited to, McDonnell Douglas Model MD-11 airplanes, and Boeing Model 747-400, 757, and 767 series airplanes, certificated in any category. Compliance: Required within 72 hours after the effective date of this AD, unless previously accomplished. To prevent improper navigation guidance during landing, accomplish the following: (a) Revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM. "Do not use NDB approaches in the FMS NAV data base. Nondirectional Beacons may be used as waypoints to build a manual NDB approach." (b) Install a placard, visible to both pilots, adjacent to the Control Display Unit, stating: "Do not use NDB approaches in the FMS NAV data base." (c) An 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate (for McDonnell Douglas airplanes); or the Manager, Seattle ACO, FAA, Transport Airplane Directorate (for Boeing airplanes). NOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO or Seattle ACO, as appropriate. (d) 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. This amendment (39-7031, AD 91-08-51) becomes effective on June 24, 1991, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T91-08-51, issued on April5, 1991, which contained this amendment.
88-18-01: 88-18-01 AIRBUS INDUSTRIE: Amendment 39-5998. Applies to Model A300 series airplanes, excluding the Model A300-600, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent the possibility that the emergency lighting will not be provided to the airplanes occupants for evacuation when the airplanes normal AC power is interrupted, accomplish the following. A. Within 10 days after the effective date of this AD, the following procedures must be applied and a copy of this AD or the changes indicated below must be inserted in the appropriate Section of the Airplane Flight Manual (AFM), as indicated below: 1. This sentence is to be inserted facing 3-02-00 page 11: "EMERGENCY PROCEDURES-DITCHING When ditching, the MIN CABIN LT selector (if installed) must be switched ON". 2. This sentence is to be inserted facing 3-02-00 page 12: "EMERGENCY PROCEDURES-EMERGENCY EVACUATION When the procedure EMERGENCY EVACUATION is applied, the EMER EXIT LT selector must be selected "ON" after parking brake is ON". 3. This sentence is to be inserted facing 4-03-00 page 1: "NORMAL PROCEDURES-TAXI Prior to push back, the MIN CABIN LT selector (if installed) must be switched "ON" and remain ON until gear retraction." 4. This sentence is to be inserted facing 4-03-00 page 4: "NORMAL PROCEDURES-LANDING Before landing, the MIN CABIN LT selector (if installed) must be switched "ON" and should remain ON until engine shutdown or until parked." 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 Operations Inspector (POI), who may add any comments 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 for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5998, becomes effective September 2, 1988.
98-17-07: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires inspection of the wing leading edge sections for the correct amount of bleed air exhaust holes, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent malfunction of the wing leading edge thermal anti-ice system, which could result in reduced controllability of the airplane and/or reduced structural integrity of the wing due to overheating.