Results
2000-14-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires an inspection of the powered drive unit power wires within three feet of each affected powered drive unit termination for mechanical damage; and repair, if necessary. This action also requires revising the wire harnesses; splicing any additional length wire; routing and installing parts; and replacing the floor panels with new and retained floor panels. This action is necessary to ensure that the powered roller pans are positioned properly. Improperly positioned powered roller pans could pierce a powered roller wire harness and cause sparking that could ignite adjacent insulation material, which could result in smoke and fire in the center cargo compartment of the airplane. This action is intended to address the identified unsafe condition.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 11, 2000.Comments for inclusion in the Rules Docket must be received on or before September 25, 2000.
67-22-02: 67-22-02 BELL: Amdt. No. 39-452. Part 39, Federal Register July 29, 1967. Applies to Model 206A Helicopters, Serial Numbers 4 through 20, 22 through 48, 50 through 56, 59, 61, and 63. Compliance required as indicated below after the effective date of this airworthiness directive, unless already accomplished. To assure proper grounding of both fuel boost pumps and prevent a potentially explosive condition in the fuel tank due to improperly wired electric fuel boost pumps, accomplish the following inspection and modification: (a) Before further flight, determine by either of the following methods that the white wire from each fuel boost pump is connected to the aircraft system ground wire: (1) If the wire identification is legible, by reference to the Master Electrical Wiring Diagram in the Model 206A Maintenance and Overhaul Manual, confirm that helicopter system wires numbered Q2A18N (to the Forward Boost Pump), and Q4A18N (to the Aft Boost Pump) are connectedto the white wire from the corresponding boost pump. (2) If the wire identification is not legible, turn all switches off and disconnect each fuel boost pump white wire from the aircraft system wire. Check each aircraft system wire thus exposed for proper grounding using an ohmmeter or continuity checking device. If the grounding is confirmed by either of the above methods, disconnected wires may be reconnected and the helicopter returned to service for not more than 25 hours before the modification required by subparagraph 2 below is accomplished. If grounding is not confirmed by either of the above methods, the fuel pump leads may have been reversed. Use the Master Electrical Diagram in the Maintenance and Overhaul Manual to determine correct connections, and connect the pumps to the aircraft system accordingly. The helicopter may then be returned to service for not more than 25 hours' operation before the modification required by subparagraph 2 below is accomplished. (b) Within the next 25 hours' time in service, modify the fuel boost pump wiring in accordance with Part B, Bell Helicopter Company Service Letter, Model 206A-No. 21, Revision A, dated July 18, 1967, or an equivalent method approved by the Director, Southwest Region, Federal Aviation Administration. This amendment effective on July 29, 1967.
64-20-01: 64-20-01 HARTZELL: Amdt. 803 Part 507 Federal Register August 28, 1964. Applies to Models HC-C2YK-1/7666-2 Serial Numbers AW-1 to AW-603 and HC-E2YL-2B/7663-4 Propellers Serial Numbers BG-1 to BG-777. Compliance required as indicated. There have been incidents of failure of the plastic pitch change blocks in Hartzell HC- E2YL-2B and HC-C2YK-1 propellers which resulted in severe roughness or vibration in flight. To correct this condition, accomplish the following: (a) Inspect propeller blades for pitch change movement and replace plastic pitch change blocks as necessary in accordance with Hartzell Service Bulletin No. 86 revised June 17, 1964, within 10 hours' time in service after the effective date of this AD unless already accomplished within the last 10 hours' time in service, and thereafter within every 10 hours' time in service from the last inspection. (b) When the modification specified in Hartzell Service Bulletin No. 86, revised June 17, 1964, has beenaccomplished, the repetitive inspections specified in paragraph (a) may be discontinued. (Hartzell Service Bulletin No. 86, revised June 17, 1964, covers this same subject.) This directive effective August 28, 1964.
2018-20-09: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This AD requires altering and re- identifying the overhead panel shock mount assembly (shock mount). This AD was prompted by the manufacturer's stress recalculations. The actions of this AD are intended to correct an unsafe condition on these products.
75-18-04: 75-18-04 LOCKHEED: Amendment 39-2343 as amended by Amendment 39-2514 is further amended by Amendment 39-3156. Applies to all Model 382 series airplanes, serial numbers 3946 and 4101 through 4541. On airplane serial numbers 3946 and 4101 through 4298 with 6300 hours or more total time in service, and on airplane serial numbers 4299 through 4541 with 9450 hours or more total time in service on the effective date of Amendment 39-3156, within the next 100 hours in service, unless already accomplished, ultrasonically inspect the outer wing lower panels at OWS 35 in accordance with Hercules Airfreighter Inspection Procedures SMP 515-A Card No. SP-61, revised August 5, 1975. Reinspect at the following intervals: (A) Airplane serial numbers 3946 and 4101 through 4298, at intervals not to exceed 3400 hours time in service from the last inspection until 20,000 hours, (without ECP 954) or 24,000 hours, (with ECP 954), at which time the interval is not to exceed 1700 hours from the lastinspection, and (B) Airplane serial numbers 4299 through 4541 at intervals not to exceed 6300 hours time in service from the last inspection. If a crack or cracks are found, before further flight, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Before the accumulation of more than 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-57-43, or later FAA-Approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspections required by this AD may be discontinued for those airplanes modified in accordance with the above paragraph. Amendment 39-2343 was effective August 22, 1975, and was effective August 6, 1975, for all recipients of the telegrams dated August 6, 1975, and August 8, 1975, which contained this amendment. Amendment 39-2514 became effective February 13, 1976. This Amendment 39-3156 becomes effective March 20, 1978.
2018-20-08: We are superseding Airworthiness Directive (AD) 2018-02-18, which applied to certain Airbus SAS Model A318, A319, and A320 series airplanes and Model A321-111, -112, -131, -211, -212, -213, -231, and - 232 airplanes. AD 2018-02-18 required revising the airplane flight manual (AFM) to provide guidance to the flightcrew for certain emergency procedures. This new AD requires revising the AFM, and for certain airplanes, removing a certain AFM revision. This AD also adds airplanes to the applicability. This AD was prompted by a determination that, when two angle of attack (AoA) sensors are adversely affected by icing conditions at the same time, data displayed on the back up speed scale (BUSS) could be erroneous. This AD was also prompted by a determination that the AFM needs to be revised for certain additional airplanes, and that the AFM may have been erroneously revised on certain airplanes not equipped with a BUSS function. We are issuing this AD to address the unsafe conditionon these products.
2005-24-05: This amendment adopts a new airworthiness directive (AD) for Boeing Vertol (Boeing) Model 107-II helicopters. This action requires a visual and magnetic particle inspection of the quill shaft. This amendment is prompted by the discovery of cracks in a quill shaft during a routine inspection. The actions specified in this AD are intended to detect a fatigue crack in a quill shaft and prevent separation of the quill shaft between the aft transmission and the mix box assembly, loss of rotor synchronization, and subsequent loss of control of the helicopter.
2005-22-02: The FAA is adopting a new airworthiness directive (AD) for all Gippsland Aeronautics Pty. Ltd. (Gippsland) Model GA8 airplanes. This AD requires you to repetitively inspect the upper and lower grooves of the forward cargo door slide for cracks, excessive wear, and excessive width. This AD also requires you to replace the forward cargo door slide if any of the above conditions are found during any inspection. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to prevent failure of the forward cargo door slide caused by cracks, excessive wear, or excessive width. This failure could result in the cargo door detaching from the airplane in flight, potentially causing damage by hitting the back end of the airplane.
2005-18-02: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part opportunity. This AD requires modifying the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2018-18-01: The FAA is superseding Airworthiness Directive (AD) 2018-10-11 for all CFM International S.A. (CFM) Model CFM56-7B engines. AD 2018- 10-11 required initial and repetitive inspections of certain fan blades and, if they fail the inspection, their replacement with parts eligible for installation. This superseding AD requires the same initial and repetitive inspections but revises the compliance time for the repetitive inspections. This AD was prompted by further analysis by the manufacturer that indicated a need to reduce the repetitive fan blade inspection interval based on ongoing root cause investigation of an April 2018 engine failure. The agency is issuing this AD to address the unsafe condition on these products.