Results
76-18-05: 76-18-05 PIPER: Amendment 39-2715. Applies to Models PA-30, Serial Nos. 30-1 through 30-2000, and PA-39, Serial Nos. 39-1 through 39-155 certificated in all categories. To prevent possible hazards in flight associated with cracks in the radius of the bend relief holes of the forward fin attachment channel assembly accomplish the following within the next 50 hours in service from the effective date of this AD unless previously accomplished. a. Visually inspect the forward fin attachment channel P/N 22903-00 around the radius of the bend relief cutouts for cracks using a magnifying glass of at least five power or an approved equivalent inspection. b. Cracked parts must be replaced with a part of the same number or equivalent that has been inspected in accordance with this AD and found acceptable prior to further flight, except that the Airplane may be flown in accordance with FAR 21.197 to a base where a repair can be made. c. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Letter No. 777 refers to this subject.) This amendment is effective September 10, 1976.
76-11-06: 76-11-06 PIPER: Amendment 39-2629. Applies to Model PA-31P, S/Ns 31P-1 to 31P-7630001 inclusive, and 31P-7630003. Compliance required within the next 100 hours in service after the effective date of this AD unless already accomplished. To prevent the hazards associated with the possibility of the alternator switch bus bar link shorting to the adjacent fuselage bulkhead, accomplish the following: (a) Alter the existing switch bus bar link insulation in accordance with the "Instructions" paragraph in Service Bulletin No. 473, dated March 24, 1976, or with an approved alternate method. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region who must also approve any alternate alteration. This amendment is effective June 4, 1976.
2007-13-10: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas DC-10-30 and DC-10-30F airplanes. This AD requires installing Teflon sleeving around the fuel pump wire harness inside the conduit in the aft supplemental fuel tank. This AD results from fuel system reviews conducted by the manufacturer. 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.
2001-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires identifying the part and serial numbers of the pressure reducing valve on each air pressurization unit, testing pressure reducing valves and air pressurization units having affected serial numbers, and replacing faulty valves or units with new parts. The actions specified by this AD are intended to prevent the simultaneous failure of two air pressurization units, which could result in loss of three hydraulic circuits and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-05-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires inspecting the sliding cabin plug door (sliding door). This AD was prompted by the failure of the sliding door's jettison mechanism due to corrosion. The actions of this AD are intended to address an unsafe condition in these products.
76-11-01: 76-11-01 PIPER: Amendment 39-2623. Applies to PA-31P airplanes certificated in all categories. To prevent possible adverse airplane vibration effects at higher altitudes, accomplish the following within the next 25 hours in service after the effective date of this Airworthiness Directive, unless already accomplished: (a) Attach the following operating limitation placard on the pilot's side window molding in full view of the pilot: OPERATING SPEEDS ALT Vno Vne 1000 mph mph 13 230 278 15 230 268 17 230 258 19 221 248 21 212 238 23 203 228 25 194 218 27 185 208 29 176 198 (NOTE: Speeds shown are CAS) (b) Incorporate Piper PA-31P Airplane Flight Manual revision dated January 22, 1976 in Piper PA-31P Airplane Flight Manual 1615. (Piper Service Bulletin No. 478 refers to this same subject.) This amendment is effective May 31, 1976.
2001-03-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires revising the airplane flight manual (AFM) to prohibit flight into known icing conditions; inspecting the anti-ice manifold assembly for missing material, and performing corrective actions if necessary; replacing the anti-ice manifold assembly with a new assembly, which terminates the AFM revision requirement; and revising the Learjet 45 maintenance program to incorporate additional inspections and maintenance practices for the anti-ice manifold assembly. This action is necessary to prevent metal fragments from breaking off the anti-ice manifold assembly due to fatigue, which could block a duct in the anti-ice system and result in an unannunciated loss of ice protection. This action is intended to address the identified unsafe condition.
2017-23-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the lower chord of the left wing rear spar. This AD requires repetitive inspections for cracking of the lower chord of the rear spar and lower aft skin and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2001-02-11: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters that requires replacing any main rotor mast assembly (mast), part number (P/N) 204-011-450-001, within 25 hours time-in-service (TIS). This amendment is prompted by the crash of a restricted category Model UH-1B helicopter due to failure of a mast, P/N 204-011-450-001. The same mast P/N is used on the Model 204B helicopters. The actions specified by this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
2018-04-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-112, A319-115, A320-214, A320-232, and A321-211 airplanes. This AD was prompted by in-service experience and further analysis, which showed that the galley 5 without kick-load retainers, was unable to withstand the expected loading during several flight phases or in case of emergency landing. This AD requires modification of galley 5 trolley compartments by adding kick-load retainers. We are issuing this AD to address the unsafe condition on these products.