Results
72-19-05: 72-19-05 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1520. Applies to Pitts Model S-2A series Airplanes, S/N 2001 through 2030. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, to prevent failure of the horizontal stabilizer leading edge support tube, accomplish the following: (1) Remove the left and right horizontal stabilizers as follows: NOTE: Keep track of all hardware and replace the same parts in their original locations, unless other options are indicated. (i) Disconnect the elevator trim tab push rods from the horns beneath the stabilizers (leave the rods connected to the tab horns). NOTE: Some airplanes may have AN310-1032 nuts and AN380 cotter pins installed on the AN3 bolts, instead of AN365-1032 nuts. If so, you may either reinstall the AN310-1032 nuts with new AN380 cotter pins, or use AN365-1032 self-locking nuts and undrilled AN3 bolts.(ii) Remove the two AN4 bolts through the flying wire lugs and elevator hinges, left and right. NOTE: It is not necessary to loosen the flying wires. (iii) Remove the 4 AN3 bolts through the stabilizer leading edge and trailing edge tubes, left and right. NOTE: It is not necessary to remove the stabilizer root fairings. (iv) Remove the access plates adjacent to the stabilizer trailing edge, reach inside the aft fuselage and remove the two AN3 bolts through the elevator trim control shaft. NOTE: It is not necessary to disconnect the elevator horn. (v) Remove the left and right horizontal stabilizers by pulling them straight outboard. (2) Thoroughly clean with solvent the exposed portions of the 2-2123 stabilizer leading edge support tube which protrudes from the fuselage. Dye-check this tube in the vicinity of the AN3 bolt holes, and visually inspect for cracks. (i) If cracks are found, order a replacement P/N 2-2123 assembly fromthe manufacturer. (ii) If cracks are not found, accomplish the following. (3) Cut off the outer ends of the stabilizer leading edge support tube, P/N 2- 2123, so that the dimension from the center of the AN3 bolt hole to the outer end of the tube is 1/2 inch, left and right sides. Remove all burrs and rough edges. (4) Redrill the AN3 bolt holes in the stabilizer leading edge support tube, P/N 2-2123, and through the mating holes in the stabilizer leading edge tubes with a number 10 drill (.193 to .199 diameter), left and right. (5) Apply zinc chromate to bare metal surfaces. (6) Reassemble in the reverse order of Step 1. (7) Stencil on upper surfaces of both the left and right horizontal stabilizers, near the leading edge, the words "No lift", in letters one-half inch high or higher, and in a color which contrasts sharply with the paint finish on the stabilizer. Pitts Service Bulletin Number 6 pertains to this same subject. This amendmentbecomes effective September 20, 1972.
71-04-03: 71-04-03 AMERICAN AVIATION: Amdt. 39-1155. Applies to American Aviation Corp., Model AA-1, certificated in all categories S/N AA1-0001 through AA1-0432. (a) Within the next 10 hours in service after the effective date of this AD unless already accomplished, inspect and test the nose gear strut in accordance with the procedures of American Aviation Service Bulletin No. 121A dated 1/8/71 or with an equivalent method. (b) Replace defective parts prior to further flight with a part received from the manufacturer after 1 June 1970 or inspected and tested in accordance with this directive. (c) Equivalent methods and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This airworthiness directive is effective February 25, 1971 and was effective as to all recipients of the letter dated January 12, 1971 which contained this airworthiness directive.
2004-15-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-202, -203, -223, and -243 airplanes, and A330-300 series airplanes, that requires modification of the control box of the auxiliary power unit (APU). This action is necessary to prevent uncommanded in-flight shutdown of the APU, which could result in loss of critical electrical systems when the airplane is operated in emergency electrical configuration, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
96-18-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Piaggio Model P-180 airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
2021-03-16R1: The FAA is removing Airworthiness Directive (AD) 2021-03-16, which applied to all Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2021-03-16 required inspecting each sliding door and replacing the upper rail or front roller or removing the front roller from service if necessary. Since the FAA issued AD 2021-03-16, inspection results and further investigation have confirmed that the in-flight loss of a sliding door, which prompted AD 2021-03-16, was an isolated case resulting from incorrect operation and maintenance error. Therefore, the FAA has determined that no unsafe condition is likely to exist or develop on the sliding doors on other helicopters in the fleet. Accordingly, AD 2021-03-16 is removed.
72-08-01: 72-08-01 BOEING: Amdt. 39-1428. Applies to Boeing Model 747 airplanes, listed in Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions except the Model 747-131. \n\tCompliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 400 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, until modified per Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions. \n\tTo detect failed landing gear alternate extension actuators, accomplish the following: \n\tInspect landing gear alternate extension actuators in accordance with Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revisions, until modified in accordance with Boeing Service Bulletin 747-32-2118, dated December 20, 1971, or later FAA-approved revision, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective April 7, 1972.
96-18-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 and -15 series airplanes, that requires repetitive inspections to detect cracks in the bulkhead tee caps, and repair and follow-on actions, if necessary. It also provides for an optional terminating modification for the repetitive inspections. This amendment is prompted by reports of cracking in the bulkhead tee caps at a fuselage station in the area of certain longerons due to fatigue. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in loss of pressurization and damage to adjacent structure.
2004-15-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate updated Airworthiness Limitation Items, Safe Life Items, and Certification Maintenance Requirements. The actions specified by this AD are intended to ensure the structural integrity of the airplane by ensuring that fatigue cracking of certain structural elements is detected and corrected in a timely manner. This action is intended to address the identified unsafe condition.
2022-07-05: The FAA is superseding Airworthiness Directive (AD) 2022-05- 09, which applied to certain MARS A.S. emergency parachutes. AD 2022- 05-09 required removing emergency parachutes with certain manufacture dates or serial numbers from service. Since the FAA issued AD 2022-05- 09, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on this aviation product. The MCAI identifies the unsafe condition as the length of the ripcord between the pins being too long, which could cause a malfunction of the emergency parachute. This AD retains the actions required by AD 2022-05-09 and expands the applicability.
68-06-02: 68-06-02 GENERAL DYNAMICS (CONVAIR): Amendment 39-564. Applies to General Dynamics (Convair) Type 30A incorporating Supplemental Type Certificate SA414EA- D. Compliance required as indicated: (a) Upon arrival at the next stop, install a placard on each of the three right hand row seats at fuselage station 1344 (row 28 on American Airlines' Drawing No. FCA-2047 Rev. D) stating, "Do Not Occupy". (b) The placard required by part (a) may be removed by incorporating an approved modification strengthening the seat support structure approved by the Chief, Engineering & Manufacturing Branch, Eastern Region. This amendment is effective March 22, 1968.