Results
2001-26-22: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model Avro 146-RJ series airplanes, that requires a one-time inspection of the S4 and S5 static pipes of the pitot static system for discrepancies, and follow-on corrective actions, if necessary. This action is necessary to prevent failure of the S4 and S5 static pipes and consequent failure of the maximum differential pressure protection for the airplane, which could lead to the fuselage of the airplane being overstressed and result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2001-26-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Hamilton Sundstrand model 247F propellers. This action requires a one-time rework of certain model 247F propellers by removing all four propeller blades from service, replacing those blades with serviceable propeller blades, and marking the propeller with a new part number. This amendment is prompted by nine reports of the blades partially slipping at the bond joint between the blade tulip and the composite blade airfoil interface. The actions specified in this AD are intended to prevent the loss of a propeller blade, which may result in loss of airplane control.
2001-26-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 series airplanes, that requires a one-time inspection of the water line heater tape where it passes close to the duct assemblies of the air distribution system for the flight compartment to detect damage, and follow-on actions. This amendment also requires eventual replacement of certain duct assemblies or foam insulation on those duct assemblies with new duct assemblies or improved foam insulation. This action is necessary to prevent ignition of foam insulation on the air distribution ducts, which could result in a fire in the airplane. This action is intended to address the identified unsafe condition.
97-03-02: This amendment adopts a new airworthiness directive (AD) that applies to Glasflugel Models H301 "Libelle", H301B "Libelle", Standard "Libelle", Standard Libelle 201B, Club Libelle 205, and Kestrel sailplanes. This AD requires measuring and adjusting the control surface weight and static moment, and inserting amendments into the Glasflugel Flight and Service Manual. This AD results from reports of considerable variation of the weight and static moment of the control surface on the affected sailplanes found during repair or repainting of the control surface. The actions specified by this AD are intended to prevent sailplane flutter because the weight and static moment of the control surface are not within certain limits, which could result in flutter and subsequent loss of control of the sailplane.
2001-25-04: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) Models LTS101-600A-2 and LTS101-600A-3 turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop engines. This amendment requires replacing certain fuel controls that have beryllium-copper bellows with improved fuel controls that incorporate Inconel 718 stainless steel welded bellows. This amendment is prompted by a report of an uncommanded power loss on a Textron Lycoming LTS101 engine due to a corrosion damaged fuel control bellows. The actions specified by this AD are intended to prevent the engine from reducing the fuel flow to minimum flow resulting in an uncommanded power loss.
2001-24-32: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200B, 747-200C, 747-200F, 747SP, and 747SR series airplanes. This AD requires a one-time inspection for chafing of certain wire bundles behind the flight engineer's panel; repairs, if necessary; and a modification to reroute a certain electrical wire bundle to ensure sufficient clearance between that wire bundle and an adjacent flood light support bracket. This action is necessary to prevent chafing of certain electrical wire bundles, which could result in smoke in the cockpit, and uncommanded discharge of fire extinguishing bottles for the No. 4 engine and consequent reduction of the ability to fight a fire in the No. 4 engine. This action is intended to address the identified unsafe condition.
51-16-01: 51-16-01\tBELLANCA: Applies to All Models 14-13 and 14-13-2 Airplanes. \n\n\tCompliance required within the next 25 hours of operation, but not later than August 1, 1951. \n\n\tAs a result of a recent failure of the elevator trim tab in flight, the modification of the trim tab attachment to the elevator as shown in Figure 1 should be made. \n\n\n\n\nFIGURE 1 \n\n\t(Bellanca Service Bulletin No. 14, Models 14-13 and 14-13-2, covers this same subject.)
66-01-03: 66-01-03 PILATUS: Amdt. 39-173, Part 39, Federal Register December 24, 1965. Applies to Model PC-6 Series Airplanes, Serial Numbers 515, 522, and 524 through 580. Compliance required as indicated, unless already accomplished. To prevent further instances of fuel flow restriction, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, inspect fuel shutoff valve P/N 321-ITX 6D for correct installation of the valve plug in accordance with Pilatus Service Bulletin No. 36, dated September 1965, or later Swiss Federal Air Office- approved revision. If the valve plug protrudes more than 2mm. (0.078 inch), before further flight, replace the valve with a new valve P/N 6238.124. (b) Within the next 60 hours' time in service after the effective date of this AD, replace fuel shutoff valve P/N 321-ITX 6D with a new valve P/N 6238.124, in accordance with Pilatus Service Bulletin No. 36, dated September 1965, or later Swiss Federal Air Office- approved revision.
69-19-06: 69-19-06 GENERAL DYNAMICS: Amdt. 39-842. Applies to all Model 22 Aircraft equipped with axle beam P/N 9729-68-1 and Model 22M Aircraft equipped with axle beam P/N 1057-68-1. Compliance required within the next 2000 hours' time in service after the effective date of this AD or before the accumulation of 9000 hours' total time in service, whichever occurs later, unless already accomplished. Several failures of the main landing gear axle beam have been attributed to cracks originating near the center jack pad on the beam lower surface. The crack then progresses upward until complete failure of the beam occurs at a point above the axle beam pivot pin. The initial crack in the beam develops due to stress corrosion or hydrogen embrittlement. To prevent further failures of this nature, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (a) Inspect and rework each Model 22 Aircraft axle beam assembly P/N 9729-68-1 in accordance with General Dynamics/Convair 880 Service Bulletin Number 32-87, dated February 7, 1966, (or later FAA approved revision), and each Model 22M Aircraft axle beam assembly P/N 1057-68-1 in accordance with General Dynamics/Convair 880M Service Bulletin Number 32-56, dated February 7, 1966, (or later FAA approved revision). (b) Removal of beam material extending below .006 inch depth from the original beam surface will require individual evaluation by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 18, 1969.
70-05-06: 70-05-06 HARTZELL PROPELLERS: Amdt. 39-954. Applies to Hartzell T10176( ) and T10176H( ) type blades installed on Hartzell HC-B3TN-5C series propellers used on AiResearch TPE331-( ) type engines. Compliance required as indicated, unless already accomplished. a. Propellers with 700 or more total hours in service, inspect in accordance with paragraphs (c) and (d) within the next 50 hours after the effective date of this AD, and reinspect in accordance with paragraph (c) every 1500 hours in service from the last inspection. b. Propellers with less than 700 total hours in service inspect in accordance with paragraphs (c) and (d) prior to the accumulation of 750 hours in service and reinspect in accordance with paragraph (c) every 1500 hours in service from the last inspection. c. Remove the blades from the propeller and the smaller needle bearing from the bottom of the blade pilot tube hole. In accordance with Hartzell Bulletin No. 95 dated 7 January 1970, or FAA approved equivalent procedure, clean and inspect the inner surface of the pilot tube hole for cracks by dye penetrant method and visually inspect for scratches, gouges or tool marks in the area of minimum wall thickness. Replace before further flight any cracked blade or blade having scratches, gouges, or tool marks in the critical radius with a blade which has been inspected in accordance with this AD and found satisfactory. d. Inspect the blade for minimum wall thickness in the shank area in accordance with Hartzell Bulletin No. 95 dated 7 January 1970. Replace before further flight any blade having a wall thickness less than that noted in Bulletin No. 95 with a blade inspected in accordance with this AD and found satisfactory. e. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust repetitive inspection intervals specified in this AD. (Hartzell Bulletin No. 95 dated7 January 1970 and Manual 118A cover this subject.) This amendment is effective March 11, 1970.