Results
2002-03-03: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to install a new strainer draining system in the cabin fuselage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent water from accumulating in the fuselage, then freezing and interfering with or causing the elevator controls to seize. This could result in loss of elevator control with consequent loss of airplane control.
2017-01-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321- 213, and A321-231 airplanes. This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. This AD requires inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the MLG. We are issuing this AD to address the unsafe condition on these products.
2017-01-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report that some inboard and outboard trailing edge flap rotary actuators may have been assembled with an incorrect no-back brake rotor-stator stack sequence during manufacturing. This AD requires inspecting the trailing edge flap rotary actuator, and replacing the rotary actuator or doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
98-02-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for discrepancies of the forward engine mount bulkhead of the nacelle strut, and corrective action, if necessary. That AD also provides for optional terminating action for the repetitive inspections. For certain airplanes, this amendment adds repetitive inspections for discrepancies in the forward engine mount bulkhead and in the forward lower spar web, and corrective actions, if necessary. For other airplanes, this amendment adds a one-time inspection to detect stop drilled cracks of the exterior of the forward engine mount chord, and replacement of the chord with a new chord, if necessary. This amendment also adds an additional optional terminating action for the repetitive inspections. This amendment is prompted by reports that fatigue cracking was found in an area adjacent to the inspection area specified in the existing AD. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could lead to the failure of the forward engine mount bulkhead and consequent separation of the engine from the airplane.
51-18-01: 51-18-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required at each periodic inspection. Two reports of loss of rudder control in flight as a result of fatigue failure of rudder torque tube have been received. Failures occur in the lower rib and pylon area. For complete inspection of the affected area, a section of the fabric should be opened by cutting along the leading edge upward to permit removal of a 10-inch section of the leading edge wood block then aft along the lower rib flange. This method will facilitate closing. (Replacement of removed wood leading edge section with lacing cord similar to original fastening is satisfactory.) Since the rudder torque tube is not heat-treated, cracks up to approximately 3/4 inch in length may be stop-drilled and welded. Where cracks have progressed further, it is recommended that the lower section of the torque tube be replaced by splicing between the No. 1 and No.2 ribs in accordance with Manual 18 practice.This supersedes AD 47-05-02.
75-27-02: 75-27-02 BRITISH AIRCRAFT CORPORATION: Amendment 39-2474. Applies to British Aircraft Corporation (BAC) Viscount Models 744, 745D and 810 airplanes, certificated in all categories. Compliance is required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of propeller feathering, install an electrical back-up to the primary manual feathering system in accordance with the instructions contained in BAC Bulletin-For- Modification No. FG.2122, dated February 11, 1972, (for Viscount Model 810 airplanes), or BAC Bulletin-For-Modification No. D.3245, dated February 11, 1972 (for Viscount Models 744 and 745D airplanes), as appropriate, or an equivalent of either approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, FAA-American Embassy, APO New York 09667. This amendment becomes effective on January 19, 1976.
2005-18-23: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires either determining exposure to runway deicing fluids containing potassium formate, or performing repetitive inspections of certain electrical connectors in the wheel well of the main landing gear (MLG) for corrosion, and follow-on actions. This new AD adds a new inspection requirement and related corrective actions. This AD is prompted by additional reports indicating that significant corrosion of the electrical connectors in the wheel well of the MLG has also been found on airplanes that land on runways treated with deicing fluids containing potassium acetate. We are issuing this AD to prevent corrosion and subsequent moisture ingress into the electrical connectors, which could result in an electrical short and consequent incorrect functioning of critical airplane systems essential to safe flight and landing of the airplane, including fire warning systems. \n\n\nDATES: This AD becomes effective October 19, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-24A1148, Revision 1, dated July 10, 2003; as listed in the AD; is approved by the Director of the Federal Register as of October 19, 2005.
2016-26-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This AD requires inspections of certain stringer fittings, replacement if necessary, and replacement of certain fasteners. We are issuing this AD to address the unsafe condition on these products.
2016-20-04: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA341G and SA342J. This AD prohibits autorotation training flights until the hardness of the landing gear rear crosstube (crosstube) is inspected. This AD is prompted by two reports of crosstubes failing during ground handling. These actions are intended to prevent failure of a crosstube, which could result in dropping or tipping of the helicopter.
83-15-09: 83-15-09 FAIRCHILD (SWEARINGEN): Amendment 39-4702. Applies to the following models and serial numbers of airplanes certificated in any category: Model SA226-T (S/N T-249 through T-275, and T-277 through T-291), Model SA226-TB (S/N T-276 and T-292 through T-417), Model SA226-AT (S/N AT-025 through AT-069, AT-071 through AT-074), Model SA226-TC (S/N TC-212 through TC-419), Any SA226 model and serial number airplane modified in accordance with Service Bulletin SB 32-016, Model SA227-AC (S/N AC-398 through AC-599) and all models with hydraulic nose wheel steering, Model SA227-AT (S/N AT-070, S/N AT-423 through AT-596), Model SA227-TT (S/N TT-421 through TT-597). Compliance: Required as indicated unless already accomplished. To assure reliable operation of the steering system: a) On or before November 1, 1983: 1) Modify the nose wheel steering systems of the affected Serial No. Model SA226-T, SA226-TB, SA226-AT, and SA226-TC airplanes in accordance with Fairchild (Swearingen) Service Bulletin SB 32-037 revised July 15, 1982, or if optional tiller wheel steering is installed, in accordance with SB 32-039 dated September 9, 1982. 2) Modify the nose wheel steering systems of the affected Serial Number Model SA227-AC, SA227-AT, and SA227-TT airplanes in accordance with Fairchild Service Bulletin SB 32-006 revised July 27, 1982. 3) When the modifications required by paragraphs a)1) and a)2) of this AD are accomplished, remove the nose wheel steering operational restrictions in the Limitations Section of the Airplane Flight Manual and placards in the airplane that were incorporated in accordance with Fairchild Swearingen Service Bulletins SBA 32-001 or SBA 32-032 both dated June 3, 1981. b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration, Southwest Regional Office, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on September 8, 1983.