Results
2006-01-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2006-01-51 that was sent previously by individual notices to all known U.S. owners and operators of Frakes Aviation (Gulfstream American) Model G-73 (Mallard) series airplanes and Model G-73 airplanes that have been converted to have turbine engines. This AD requires an inspection to detect repairs, cracking, or corrosion of the wings from wing station (WS) 77L to WS 77R, front spar to rear (main) spar; removal of repairs, if found; removal of sealant from the interior of the wet bays; and repair of any crack or corrosion. This AD results from a report indicating that the right wing of a Frakes Aviation (Gulfstream American) Model G-73 (Mallard) airplane separated from the fuselage on takeoff, which resulted in the airplane impacting the water near Miami Beach, Florida. We are issuing this AD to prevent structural failure of the wing and loss of control of the airplane.
2019-18-05: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series airplanes. This AD was prompted by reports of the nose landing gear (NLG) locking in a partially extended position due to loose bushings on the lock link of the NLG locking mechanism. This AD requires repetitive inspections of the bushings and the lower lock link of the NLG for discrepancies, and corrective actions if necessary. This AD also requires replacement of the lower lock link of the NLG, which terminates the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-15: This action confirms the effective date of Airworthiness Directive (AD) 99-02-15, which applies to certain Avions Pierre Robin Model R2160 airplanes. AD 99-02-15 requires repetitively inspecting the engine bearer for cracks, and replacing the engine bearer with a reinforced part either immediately or at a certain time period depending on whether cracks are found during the inspections. Replacing the engine bearer with a reinforced part terminates the repetitive inspection requirement. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to detect and correct cracks in the engine bearer, which could result in the engine separating from the airplane.
79-18-09: 79-18-09 LOCKHEED CALIFORNIA: Amendment 39-3536. Applies to Lockheed L- 1011-385 series airplanes certificated in all categories. Compliance required within the next 400 hours' time in service from the effective date of this AD, unless already accomplished. To prevent local structural damage and insure security of the No. 2 engine generator feeder cables, accomplish the following: (a) Inspect the No. 2 engine generator feeder cables in the aft body area between Fuselage Station 2011 and Fuselage Station 2053 above Waterline 350 for looseness and slack, surface abrasions, discoloration of outer surface and close proximity to structure without clamps or other protective supports. Inspect feeder cable support clamps for lack of clamp cushions and bent or dislodged mount brackets or clamps. These inspections are to be made in accordance with Part 2 of Lockheed Service Bulletin 093-24-086, dated August 2, 1979. (b) If any of the above discrepant conditions is found toexist, prior to further flight perform corrective action in accordance with Part 2 of Lockheed Service Bulletin 093-24-086, dated August 2, 1979. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. This amendment becomes effective August 29, 1979.
2006-01-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplanes, listed above. This AD requires installing two-stage relays in the electronics rack (90VU), and performing related corrective and investigative actions. This AD results from reports of inadvertent rudder trim activation when the autopilot is on. We are issuing this AD to prevent inadvertent trim activation when the autopilot is on and the slats are extended, which could result in rudder activation when the autopilot is turned off.
2019-18-07: The FAA is superseding Airworthiness Directive (AD) 2015-17- 14, which applied to all Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015- 17-14 required repetitive rototest inspections of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. This AD continues to require the actions of AD 2015-17-14, adds actions for certain airplanes, and reduces the compliance times for certain airplanes, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also reduces the applicability. This AD was prompted by further analysis and widespread fatigue damage (WFD) evaluations which identified the need to reduce the initial compliance times and repetitive intervals for the inspections for certain airplanes, and to add work for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires inspection(s) to detect fatigue cracking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable part. That AD also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if accomplished, terminates the repetitive inspections. This amendment requires that the subject inspection be accomplished repetitively following installation of brake line hydraulic restrictors. This amendment is prompted by an additional report of fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG. The actions specified by this AD are intended to prevent collapse of the MLG due to fracturing of the shock strut cylinder.
83-11-03: 83-11-03 PACIFIC SCIENTIFIC COMPANY, KIN-TECH DIVISION: Amendment 39-4662. Applies to Pacific Scientific flight attendant restraint system rotary buckle assemblies, Part Numbers 1107261-01, -05 and -09, manufactured prior to 1982. Compliance required within 180 days from the effective date of this AD, unless previously accomplished. To prevent the entrapment of occupants caused by the inability to release the restraint system assembly, accomplish the following: a. Inspect flight attendant restraint systems to determine if Pacific Scientific rotary buckle as identified in Figure 1 of Pacific Scientific Service Bulletin 1107261-25-01 is installed. b. If installed, determine if the old lower cover 1107270-01 or the new cover assembly 1107525-01 is installed. The cover is not identified with a part number; however, with the old cover only the two (2) attachment screw heads will be seen. The new cover assembly also has two (2) rivet upsets on the outside of the cover assembly and, in addition, the lap belt and/or inertia reel nameplate should be identified with the letter "M" after the assembly part number. c. If the new cover assembly 1107525-01 is installed, no further action is required per this AD. d. If the old cover 1107270-01 is installed, replace the old cover with the new 1107525-01 cover assembly and stamp or mark a suffix letter "M" next to part number on each lap belt and on inertia reel nameplate. NOTE: Pacific Scientific Service Bulletin 1107261-25-01, Revision 1, dated June 1, 1982, pertains to this subject. e. Alternate inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region. This amendment becomes effective July 18, 1983.
2006-01-08: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model Avro 146-RJ airplanes. This AD requires reviewing the airplane's maintenance records to determine if certain tasks of the BAE Systems (Operations) Limited BAe146/Avro RJ Maintenance Planning Document issued May 15, 2004, have been accomplished. This AD also requires doing repetitive detailed inspections of the external fuselage skin adjacent to the longeron at rib 0 from frame 29 to frame 31, and repairing any damage. This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracking of the fuselage skin, which could result in structural failure of the fuselage.
62-21-04: 62-21-04 LOCKHEED: Amdt. 489 Part 507 Federal Register October 3, 1962. Applies to All Model 1649A Aircraft. Compliance required as indicated. As a result of chordwise cracks on the wing lower milled skin at wing Station 590, the following shall be accomplished: (a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the past 600 hours' time in service, and at periods thereafter not exceeding 1,000 hours' time in service following that initial inspection, inspect from wing Station 580 through wing Station 600, the external lower surface of the aft skin panels, P/N 472066, for any evidence of cracks emanating from the aft edge of the panel through the rear beam attachment holes. Inspection shall be by close visual or dye penetrant means. (b) Any cracks shall be repaired prior to further flight in accordance with Lockheed 1649 Service Bulletin No. 73, Section 1, "Modification Data," and Lockheed Drawing SED61- 9004, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (c) The periodic inspections may be discontinued following repair per (b) or when an uncracked skin panel has been reinforced in accordance with Lockheed 1649 Service Bulletin No. 73. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Field Service Letter FS/240893L, dated April 14, 1960, and Lockheed 1649 Service Bulletin No. 73 cover this same subject.) This directive effective November 2, 1962.