Results
2002-14-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection of the wiring in the fuel control panel of the wings for chafing damage and for proper routing of the wiring; and corrective action(s), if necessary. This action is necessary to prevent chafing of the wiring in a cutout area in the wing fuel control panel due to improperly routed wiring, which could result in electrical arcing in an abnormal fuel vapor zone and consequent possible ignition of the fuel vapor. This action is intended to address the identified unsafe condition.
2008-22-16: The FAA is adopting a new airworthiness directive (AD) for certain GE CT58 series turboshaft engines. This AD requires recalculating the lives of certain part numbered compressor spools using a new repetitive heavy lift (RHL) multiplying factor. This AD results from reports of cracks originating from the inner faces of the locking screw holes in the compressor spool. We are issuing this AD to prevent cracks due to RHL missions. Cracks could result in an uncontained rotor burst and damage to, or loss of, the helicopter and serious injuries to any person onboard.
2008-22-11: The FAA is adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (HBC) Model 390 airplanes. This AD requires you to inspect hydraulic pump pressure output hose assemblies to determine if they are from the affected lots, inspect for hydraulic fluid leaks if the hose assemblies are from the affected lots, and replace all affected hose assemblies. This AD results from reports of hydraulic leaks from the hydraulic pump pressure output hose assemblies. We are issuing this AD to prevent leakage of hydraulic fluid from the pump output hose within the engine compartment, which could result in an in-flight fire.
95-10-09: This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft Model S-58 and S-58T series helicopters, that requires the removal and replacement of the transmission main gear box ring gear (ring gear) within certain time intervals, and establishes a retirement life for the ring gear. This amendment is prompted by reports of failures of the ring gear due to slow-growth fatigue cracks. The actions specified by this AD are intended to prevent failure of the ring gear, failure of the main transmission, and subsequent loss of control of the helicopter.
48-41-01: 48-41-01 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. I. Inspect wing bulkhead flanges and stringers at their intersections in the fuel tank area for cracks and repair as necessary at each No. 2 inspection (or equivalent periodic inspection approximating 100 hours) until permanent repairs and rework are accomplished. II. Complete rework in accordance with CVAC Service Bulletin No. 240-166A dated September 27, 1948, or equivalent should be accomplished not later than the next engine change.
47-21-14: 47-21-14 REPUBLIC: (Was Mandatory Note 4 of AD-769-2.) Applies only to Model RC-3 Aircraft Serial Numbers 5 to 500, Inclusive. Compliance required at the next 25-hour inspection or by August 1, 1947, whichever occurs first. To prevent fouling of the lower elevator cable on the elevator balance weight in the tail boom, incorporate Republic SK-17-14052-2 in the lower elevator control cable system. This elevator control cable guide is installed on the cross channel, in the tail boom, with the existing bolts holding the two inboard rudder pulley brackets. (Republic Service Bulletin No. 14 dated March 31, 1947, covers the same subject.)
63-27-02: 63-27-02 GRUMMAN: Amdt. 655 Part 507 Federal Register December 19, 1963. Applies to All Model G-21 Series Aircraft. Compliance required as indicated. As a result of cracks found on the rod end fitting, P/N 12727-7 located at the aft end of the rudder control push rod assembly, P/N 12727-1, accomplish the following within 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (a) Remove the rudder control push rod assembly, P/N 12727-1. This assembly consists of a tube with a fitting, P/N 12727-7, attached at each end. The length of the assembly is 20 1/2 inches from fitting center to fitting center. The rod assembly, used in conjunction with the left rudder pedals, is located below the pilot's compartment floor, the forward end approximately 2 1/2 inches below, and the aft end approximately 12 inches below . Laterally, the rod assembly is located approximately9 1/2 inches to the right of the aircraft's centerline. (b) Clean both rod end fittings, removing all grease and dirt. (c) Inspect both rod end fittings for cracks using a dye penetrant in conjunction with at least a 10-power magnifying glass, or an FAA approved equivalent inspection. (d) If a crack is found, that part shall be replaced in accordance with Grumman Drawing No. 12727 with a new part having the same part number, or an FAA approved equivalent before further flight. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern 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. NOTE: It should be ascertained that the proper rudder control stop bolt, Grumman P/N G19-4-11, or anFAA approved equivalent bolt (having a smooth head) is presently installed in the pedal stop block (P/N 12779) which is part of the rudder and elevator torque shaft support assembly (P/N 12722) at Hull Station 11. This directive effective January 20, 1964.
2008-22-01: We are adopting a new airworthiness directive (AD) for various transport category airplanes. This AD requires deactivation of PATS Aircraft, LLC, auxiliary fuel tanks. This AD results from fuel system reviews conducted by the manufacturer, which identified unsafe conditions for which the manufacturer has not provided corrective actions. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
91-24-06: 91-24-06 SAAB-SCANIA: Amendment 39-8092. Docket No. 91-NM-132-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 004 through 159; and Model SAAB 340B series airplanes, Serial Numbers 160 through 200; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the cowling doors from opening during flight, accomplish the following: (a) Within 90 days after the effective date of this AD, inspect and measure the Avibank latches on the nacelle forward cowling doors 7271110- 501/601, in accordance with SAAB Service Bulletin 340-71-035, Revision 1, dated December 18, 1990. (1) If the measurement is within the limits specified in Figure 2 of the service bulletin, no further action is required. (2) If the measurement is outside the limits specified in Figure 2 of the service bulletin, prior to further flight, install new latch triggers in accordance with paragraph 2.C. of the service bulletin.(b) 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may 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. (d) The inspection and replacement requirements shall be done in accordance with SAAB Service Bulletin 340-71-035, Revision 1, dated December 18, 1990. 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 SAAB-Scania AB, Product Support, S-581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8092, AD 91-24-06) becomes effective on January 7, 1992.
47-43-08: 47-43-08 CESSNA: (Was Service Note 6 of AD-768-5.) Applies to All 120 and 140 Aircraft Equipped With Beech R003 Propeller Having R003-201 Blades and Continental C-85 Series Engine. Compliance required prior to January 1, 1948, and thereafter upon completion of each 25 hours of operation. Remove the R003-201 propeller blades and visually inspect the propeller blade retainer ferrule for cracks at the fillet joining the cylindrical outer surface of the ferrule with the retaining face of the flange. Particular caution should be exercised not to injure or contaminate the thrust bearing which must be pressed away from the flange for the inspection. The propeller manufacturer's assembly and service instructions are to be followed during disassembly and reassembly of the propeller. If any indication of a crack is found, both blades should be replaced with the R003-225 blades. The 25-hour inspection may be discontinued if R003-225 blades are installed. The R003-225 blades are sufficiently similar to the R003-201 blades to be considered aerodynamically interchangeable in the same diameter without a flight test. (Beech Aircraft Co. propeller Service Letter No. 1 covers this same subject.)