Results
57-05-01: 57-05-01 CURTISS-WRIGHT: Applies to all C-46 Series aircraft. Compliance required by August 1, 1957. During emergency extension of the landing gear, hydraulic dump valves are actuated in the landing gear hydraulic system to vent fluid directly overboard in order to prevent trapped fluid from preventing the lowering of the landing gear. On early model aircraft this fluid was vented overboard on the inboard side of the nacelles directly aft of the exhaust stack. This has resulted in fires in areas where no fire detection or protection is provided. In order to prevent this occurrence, item (1), (2), or (3) should be accomplished. (1) The vent line should be rerouted to vent from nacelle tail cone in accordance with Curtiss-Wright Service Bulletin C-46 1226 or Curtiss-Wright Drawing No. 20-575-3206. (2) The vent line should be rerouted to return to the main system as outlined in change A of T.O. 01-25LA-209. (3) The vent line should be rerouted to anapproved equivalent of item (1) or (2). Either item (1) or (2) may have been accomplished on later model aircraft at the factory or by the military; however, the aircraft may have been further modified and should be inspected for compliance.
67-17-01: 67-17-01 AERO PRODUCTS: Amdt. 39-417 Part 39 Federal Register May 11, 1967. Applies to Models A6441FN-606 and A6441FN-606A Propellers. Compliance required as indicated. (a) On or before July 1, 1967, unless already accomplished, on each propeller in which is installed a fixed spline P/N 6522974, Serial No. 1367 and up, or P/N's 6523110 and 6509978, accomplish the following: (1) Remove from service all fixed splines P/N's 6523110 and 6509978. (2) Remove from service any P/N 6522974, Serial No. 1367 and up, fixed spline which does not meet the specification requirements for core hardness. (Reference: Allison Commercial Service Letter 189, Page 7, titled "Fixed Spline," Paragraph B.4.c.) (b) Within the next 10 hours' time in service, unless already accomplished, each propeller in which is installed a fixed spline P/N 6523110, or 6509978, or P/N 6522974, with Serial No. 1367 and up, must be inspected and marked as required by Allison telegram THO- 641W-LOD, dated April 7, 1967, as modified by Allison telegram THO-662W-LOD, dated April 10, 1967. Thereafter, repetitive daily inspections are required as specified in those telegrams. (c) If, during the daily inspection, it is determined that a propeller blade is beyond tolerance as set forth in those telegrams, the propeller shall be removed from service and be - (1) Retained by the operator, with immediate notification to the Chief, Engineering and Manufacturing Branch, FAA Central Region, pending further instructions by him; or (2) Returned to an approved overhaul base and the Chief, Engineering and Manufacturing Branch, FAA Central Region, notified immediately. (d) The daily inspection required by this AD may be discontinued when the fixed splines identified in (a)(1) have been removed from service and replaced by airworthy fixed splines, or when the fixed splines identified in (a)(2) have been inspected for core hardness and determined to meet specifications or have been replaced by airworthy fixed splines. (e) Within the next 10 hours' time in service from the effective date of this amendment, unless already accomplished, each propeller which has not been modified to comply with the restrictor installation of paragraph (a) of AD 67-20-01 and in which is installed a fixed spline Part Number 6508538, accomplish the markings and inspections outlined in paragraphs (b) and (c). This amendment effective September 20, 1967, for all persons except those to whom it was made effective by telegram dated September 8, 1967. This supersedes AD 67-12-01. This directive effective May 11, 1967. Revised September 20, 1967.
2020-24-06: The FAA is superseding Airworthiness Directive (AD) AD 2019- 08-13 for Textron Aviation, Inc., (type certificate previously held by Cessna Aircraft Company) Models 525, 525A, and 525B airplanes with Tamarack Aerospace Group (Tamarack) active load alleviation system (ATLAS) winglets installed in accordance with Supplemental Type Certificate (STC) SA03842NY. AD 2019-08-13 was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as malfunction of the ATLAS. This AD results from the identification of corrective actions that, if implemented, allow operators to reactivate the ATLAS and restore operations to normal procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2003-23-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires modification of the number 3 left and right emergency exit doors. This amendment requires a new, improved modification of the number 3 left and right emergency exit doors, which terminates the requirements in the existing AD. The actions specified by this AD are intended to prevent the number 3 emergency exit doors from jamming, which could impede the safe evacuation of passengers and crew during an emergency. This action is intended to address the identified unsafe condition.
2009-20-06: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: DGAC [Direction Generale de l'Aviation Civile] France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, amendment 39-5871] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). Following the life extension activities linked to the A310 program, the interval of inspection for A310-200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC * * *. Some stress analysis conducted in the frame of the life extension activities of the A300-600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4- 620 and A300C4-620 aircraft models. * * * * * The unsafe condition is cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. We are issuing this AD to require actions to correct the unsafe condition on these products.
67-03-05: 67-03-05 LOCKHEED: Amdt. 39-326 Part 39 Federal Register December 22, 1966. Applies to Models 649, 749, and 1049 Airplanes Powered by Wright 749C18BD-1 and 975C18CB-1 Engines Equipped With Hamilton Standard 43E60/6869-0, 43E60/6901-0, and 43E60/6903-0 Propellers. Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To minimize propeller vibratory stresses, amend the FAA-approved Airplane Flight Manual to include the following operating limitations: Continuous ground running between 2,300 and 2,650 r.p.m. with the propeller governing is prohibited. Continuous static ground running in a crosswind above 2,650 r.p.m. is prohibited. This directive effective January 23, 1967.
2020-24-05: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA- 28-160, PA-28-180, PA-28-235, PA-32-260, and PA-32-300 airplanes. This AD was prompted by reports of corrosion found in an area of the main wing spar not easily accessible for inspection. This AD requires inspecting the left and right main wing spars for corrosion, and, if corrosion is found, taking all necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-03-15 R1: This amendment revises an existing airworthiness directive (AD), applicable to various Boeing and McDonnell Douglas transport category airplanes, that currently requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. The actions specified by that AD are intended to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This amendment removes certain requirements for certain airplanes and revises the direction to the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning occurs, rather than "when the cabin altitude warning horn sounds." This action is intended to address the identified unsafe condition.
94-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8, DC-9, and DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) airplanes; that requires inspection of the center and side windshields, and replacement of discrepant windshields. This amendment is prompted by reports that the core ply of certain windshields was incorrectly tempered during the manufacturing process. The actions specified by this AD are intended to prevent failure of the windshield.
2020-23-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. This AD was prompted by a report of a manufacturing and control issue regarding the ceramic balls in the bearing installed in the swashplate assembly of the main rotor mast assembly. This AD requires repetitive inspections of the bearing in the swashplate assembly of the main rotor mast assembly for discrepancies (ceramic balls that have a hard point or sensitive axial play or both) and, depending on the findings, replacement of an affected main rotor mast assembly with a serviceable main rotor mast assembly, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.