Results
99-12-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires replacing the passenger oxygen container and mask assembly with an improved design passenger oxygen container and mask assembly. This AD is the result of an incident where a passenger had put on the oxygen mask and the lanyard pin did not automatically pull and initiate oxygen flow during a loss of airplane pressurization while in-flight. The actions specified by this AD are intended to prevent the above situation from occurring on other airplanes, which could result in passenger injury if the lanyard pin is not manually pulled in a timely manner.
2012-18-03: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division PW4000-94'' and PW4000-100'' turbofan engines having a 1st stage high-pressure turbine (HPT) seal support, part number (P/N) 55K601 (contained within assembly P/N 55K602-01) or P/N 50K532 (contained within assembly P/N 50K530-01), installed. This AD was prompted by 58 reports of cracked 1st stage HPT air seal rings, including 15 in-flight engine shutdowns. This AD requires removal and replacement of the 1st stage HPT seal support and inspection of the 1st stage HPT air seal ring. We are issuing this AD to prevent failure of the 1st stage HPT air seal ring, which could lead to an internal oil fire, uncontained engine failure, and damage to the airplane.
58-13-02: 58-13-02 BEECH: Applies to Models B50, C50, D50, E50 and F50. Compliance required as soon as possible but not later than November 15, 1958. The AN 3158 tail light assembly does not meet the requirements of the Civil Air Regulations for intensity and light pattern. It must be replaced by an assembly meeting those requirements. Beech Kit 50-169 provides an acceptable assembly. (Beech Service Bulletin 33, 24, 17, 9 and 2 for B50, C50, D50, E50 and F50, issued April 1958, covers this same subject.)
2009-04-16: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747- 200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That AD currently requires an inspection to determine if acceptable external skin doublers are installed at the stringer 6 (S-6) lap splices, between station (STA) 340 and STA 400. For airplanes without the acceptable external skin doublers, the existing AD also requires repetitive related investigative actions and corrective actions if necessary. The existing AD also provides an optional terminating modification for the repetitive related investigative actions. This new AD mandates the optional terminating modification. This AD results from a report of cracked fastener holes at the right S-6 lap splice between STA 340 and STA 380. We are issuing this AD to prevent cracking in the fuselage skin, which could result in rapid decompression and loss of structural integrity of the airplane.
2012-17-11: We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. This AD was prompted by reports that the fire extinguisher in the toilet vanity unit needs to be mounted vertically rather than horizontally. This AD requires inspecting to determine if a certain fire extinguisher bottle is installed, and repositioning the affected fire extinguisher bottle to the vertical position. We are issuing this AD to detect and correct the orientation of the fire extinguisher bottle in the toilet vanity unit to the vertical position, which if not corrected, could result in a toilet waste bin fire spreading, and consequent damage to the airplane and injury to its occupants.
74-04-04: 74-04-04 CANADAIR: Amendment 39-1787. Applies to all CL-44D4 and CL-44J airplanes which have experienced more than 7,000 landings. To detect cracks in the lugs of the rear spar attachment lower fitting, P/N 44-10149, of the main landing gear actuator, accomplish the following: 1. Within the next 100 landings after the effective date of this AD, unless accomplished within the last 900 landings, and at intervals thereafter not to exceed 1,000 landings, inspect the lower lugs of the main landing gear actuator rear spar attachment fitting, P/N 44-10149, for cracks using a dye penetrant method with a glass of at least 10-power or an approved equivalent inspection. 2. If cracks are found, reduce the inspection intervals as noted in the instructions of paragraphs i, ii, iii of the Inspection Data of Canadair Service Information Circular No. 371-CL- 44. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data, submitted through an FAA maintenance inspector. 4. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Canadair Limited, Attention: Mr. C. Bloom, P.O. Box 6078, Montreal, Canada. These documents may also be examined at the Engineering and Manufacturing Branch, FAA, Eastern Region, J.F.K. International Airport, Jamaica, New York 11430, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Eastern Region. This amendment is effective February 18, 1974.
99-11-08: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines, that requires installation of a main fuel control (MFC) that incorporates a flange vent groove and installation of an MFC with improved overspeed protection. This amendment is prompted by reports of rapid uncommanded engine acceleration events. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane.
2012-17-07: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 excessive voids in the adhesive joint between the center wing spars and the [[Page 54801]] upper center wing skins. This condition could cause the wing to fail, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
98-09-24: This amendment adopts a new airworthiness directive (AD) that applies to certain Diamond Aircraft Industries (Diamond) Models H-36 "Dimona" ; and HK 36 R "Super Dimona" sailplanes. This AD requires: inspecting the elevator rib area for damage on certain Models H-36 " Dimona" and HK 36 R "Super Dimona" sailplanes, and either immediately or eventually replacing the elevator ribs depending on the results of the inspection; replacing the M6 screws that attach the wheel axle to steel support with M8 screws on certain Models HK 36 R "Super Dimona" sailplanes; and inspecting the shoulder harness fittings for improper bonding on certain Diamond Model H-36 "Dimona" sailplanes, and repairing any harness with an improper bond. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Austria. The actions specified by this AD are intended to prevent failure of either the shoulder harness fittings, elevator rib, or the wheel axle to steel support attachment, which could result in passenger injury caused by an inadequate restraint system; reduced sailplane controllability caused by structural damage to the elevator; and/or reduced sailplane controllability during takeoff, landing, and ground operations caused by the installation of incorrect wheel axle screws.
96-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of a certain galley; repetitive inspections to detect damage and to determine the clearance of generator wires in the auxiliary power unit (APU); and repair or replacement of the damaged wires. This amendment is prompted by reports indicating that, during an unscheduled removal of a galley from the production line, the insulation of one of the generator wires of the APU was found damaged due to inadequate clearance with the adjacent structure. The actions specified by this AD are intended to prevent such damage, which could result in a short in the electrical wiring of the APU and, thus, pose a potential fire hazard.