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2001-05-08: This amendment adopts a new airworthiness directive (AD) that applies to all VALENTIN GmbH (Valentin) Model 17E sailplanes. This AD requires you to inspect for, and correct, cracked or improperly installed central wing bolts; install a stronger central bolt if not already installed; and inspect for, and replace, problem telescopic rods. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to correct improperly installed or cracked central bolts and damaged, deformed, or loose telescopic rods. This condition, if not corrected, could cause the wing to separate from the sailplane, which could cause result in control of the sailplane.
79-12-09: 79-12-09 PIPER AIRCRAFT CORP: Amendment 39-3494. Applies to Model PA-36-285 serial numbers 36-7360001 through 36-7660135 airplanes certificated in all categories. To detect cracks in the engine mount attachment brackets, accomplish the following: (a) Within the next 50 hours in service from the effective date of this AD, unless accomplished within the previous 50 hours in service, and at intervals thereafter not to exceed 100 hours in service from the last inspection, inspect welds for cracks on the aft side of the gussets on the fuselage where the engine mount is attached using dye check or fluorescent penetrant inspection procedures or equivalent. (b) If cracks are found, install Piper Engine Mount Attachment Modification Kit No. 763877, or equivalent, prior to further flight. During the installation of the kit, inspect the welds for cracks on the forward side of the gussets on the fuselage where the engine mount is attached using dye check or fluorescent penetrantinspection procedures or equivalent. If cracks are found, remove weld from cracked area and reweld. (c) Upon incorporation of Piper Modification Kit No. 763877 or equivalent, compliance with this AD may be cancelled. (d) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. Piper S/B No. 615 dated 9/21/78, pertains to this subject. This amendment is effective June 19, 1979.
2007-17-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Deformations of cross sections of the rear exhaust pipes were stated on several serial numbers having logged varying operating hours. One strongly deformed exhaust pipe showed additional cracks near the welding. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
79-12-08: 79-12-08 PIPER: Amendment 39-3493. Applies to series PA-24-400 S/N 26-2 through 26-148; PA-30 S/N 30-2 through 30-2000; and PA-39 S/N 39-1 through 39-155 aircraft. PART A This part applies to all aircraft listed above. Compliance required within 50 hours of operation after the effective date of this AD and at each 50 hours of operation thereafter. To prevent fuel mismanagement from inter-port leakage with the fuel selector valve causing fuel to transfer from one tank to another, accomplish checks in accordance with the Instructions paragraph in Piper Service Letter No. 851, Part A or an approved equivalent. Item 3 is to be repeated only twice. If drainage still exceeds one half (1/2) fluid ounce of fuel then comply with Item 5. Item 5 is maintenance and must be performed by a certified mechanic. PART B This part applies to the cited Models PA-30 and PA-39 aircraft. If the airplane has been exposed to below freezing temperatures, compliance is required prior to the first flight of the day and after each refueling operation. To eliminate water contamination of the aircraft fuel supply, accomplish a check in accordance with the Instructions paragraph of Piper Service Letter 851, Part B, Item 2a and 2b or an approved equivalent check. PART C This part applies to the cited Model PA-24-400 aircraft. If the airplane has been exposed to below freezing temperatures, compliance is required prior to the first flight of the day and after each refueling operation. To eliminate water contamination of the aircraft fuel supply, accomplish a check in accordance with the Instructions paragraph in Piper Service Letter No. 851, Part C, Item 2a or an approved equivalent check. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive intervals. The checks required by this AD may be performed by the pilot. Equivalent checks, inspections, and maintenance must be approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 19, 1979.
2001-06-03: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330-301, -321, and -322 series airplanes, and all Model A340 series airplanes. This action requires replacing, with oversize fasteners, the interference fit fasteners between ribs 2 and 7 and between ribs 9 and 11; and reinforcing the cover plate of the torsion box of the aft passenger/crew doors. This action is necessary to prevent propagation of fatigue cracking of the top wing skin and the torsion box of the aft passenger/crew doors, which could lead to reduced structural capability of the airplane. This action is intended to address the identified unsafe condition.
2019-18-04: The FAA is superseding Airworthiness Directive (AD) 2005-17- 14, which applied to all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2005-17-14 required repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. AD 2005-17-14 also required repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. This AD retains some requirements of AD 2005-17-14 and revises the inspection procedures and compliance times, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of desynchronization of the rudder servo actuators. The FAA is issuing this AD to address the unsafe condition on these products.
79-08-02: 79-08-02 PIPER: Amendment 39-3446. Applies to Model PA-38-112, Serial Nos. as shown below, certificated in all categories. To avoid possible hazards in flight associated with a crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts, accomplish the following: (a) Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312. Compliance required within the next ten hours in service unless previously accomplished. 1. Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edges of the stabilizer pulley bracket mounting fitting P/N 77615-07 at the bend radius for cracks using a dye penetrant inspection method. 2. Report positive findings including crack length from paragraph (a) Inspection to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-RO174.) 3. If a cracked fitting is found, replace with an undamaged part of the same part number before further flight except a ferry flight under FAR 21.197 to a place of repair may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Serial Nos. 38-78A0001 through 38-79A0254. Compliance required within the next 100 hours in service unless previously accomplished. 1. Disconnect rudder cables from rudder, remove lower rudder hinge bolt and displace rudder to gain access to rear spar attachment bolts. 2. Remove lower vertical fin fairing, upper vertical fin fairing, upper vertical fin inspection panel and lower aft vertical fin inspection panel. 3. Using a calibrated torque wrench, check the torque of each of eighteen (18) stabilizer to fin and fin to fuselage attach bolts and tighten as required to 90-110 in-lbs. Torque value given takes into account friction drag torque. (Piper Service Bulletin No. 637 refers to the subject.) This amendment is effective April 12, 1979.
2007-17-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Instead of the hub normally used which carries the starter ring gear and the hub for the tooth belt a slip-clutch can be mounted. The unit contains the hub for the tooth belt and the starter ring gear. Occurrences during service have shown that under bad conditions excessive wear on several parts of the clutch can occur. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
56-25-04: 56-25-04 LOCKHEED: Applies to All Models 49, 149, 649, 649A, 749, 749A Aircraft; Model 1049 Serial Numbers 4001 Through 4024; Model 1049C Serial Numbers 4501 Through 4520 and 4523 Through 4538. Compliance required at first block overhaul following receipt of parts or by March 1, 1958, whichever occurs first. In view of the continuing series of incidents wherein flaps extend on one side of the aircraft out of symmetry with the other side, a means shall be installed which will automatically shut off the hydraulic power to the flap actuating motors whenever an asymmetrical condition exists. One method of accomplishing this means is described in Lockheed Service Bulletin No. 49/SB-794 for the 49/749 Series and No. 1049/SB-2270 for the 1049 Series.
2018-07-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80A, -80A1, -80A2, and -80A3 turbofan engines. This AD was prompted by high cycle fatigue (HCF) cracking of the low-pressure turbine (LPT) stage 3 nozzles. This AD requires replacement of the LPT stage 3 nozzles, part numbers (P/Ns) 9290M52P05 and 9290M52P06, installed. We are issuing this AD to address the unsafe condition on these products.