Results
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.
74-25-06: 74-25-06 SIKORSKY: Amendment 39-2035. Applies to S-61L, S-61N, and S-61NM helicopters certified in all categories equipped with engine air inlet deflector installation (P/N S6107-21115 Series). Compliance with this airworthiness directive is required prior to next flight. Prior to each flight, reduce each takeoff gross weight limitation prescribed by the FAA approved Sikorsky Helicopter Flight Manual and applicable supplements 800 pounds until: (a) receipt and incorporation of Revision No. 6, dated June 13, 1974, or Revision No. 7, dated July 24, 1974, for the FAA approved S-61N helicopter Flight Manual (SA 4045-82), (b) receipt and incorporation of correcting revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, to Supplement No. 22, dated December 6, 1973, for the FAA approved S-61L helicopter flight manual (SA 4045-30) or, (c) receipt and incorporation of correcting revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, to Supplement No. 4, dated December 6, 1973, for the FAA approved S-61L (serial no. 61425 and subsequent) helicopter flight manual (SA 4045-100). This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated October 16, 1974.
76-01-02: 76-01-02 GRUMMAN AMERICAN: Amendment 39-2485 as amended by Amendment 39-2521. Applies to Grumman American Model AA-5, AA-5A and AA-5B airplanes, serial numbers AA5-0641 through AA5-0834, AA5A-0001 through AA5A-0050, AA5A-0054 through AA5A-0056, AA5B-0001 through AA5B-0169, AA5B-0171, and AA5B-0180 through AA5B- 0183, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent failure of the upper engine cowl, accomplish the following: (a) Visually check the upper engine cowl hinge assembly adjacent to the forward and aft attach brackets for cracks, (1) Within the next 15 hours' time in service after January 12, 1976 for Model AA-5B airplanes, and within the next 15 hours' time in service after the effective date of this amendment for Model AA-5 and AA-5A airplanes, or within 50 hours' total time in service, whichever occurs last. (2) Thereafter at intervals not to exceed 15 hours' time in service from the last inspection until modified in accordance with paragraph (b) below. (b) Replace the upper engine cowl hinge assembly with Grumman American Part Number 5101030-901 hinge assembly in accordance with Grumman American Service Bulletin No. 152 dated December 24, 1975 or later FAA approved revision thereto, (1) before further flight if cracks are found, but (2) No later than 100 hours' time in service after: (i) January 12, 1976 for Model AA-5B airplanes and (ii) the effective date of this amendment for Model AA-5 and AA- 5A airplanes. Equivalent modification may be approved by the Chief, Engineering and Manufacturing Inspection Branch, FAA Great Lakes Region. The checks for cracks required by this AD constitute preventive maintenance and may be performed by persons authorized to perform preventive maintenance under Federal Aviation Regulations, Part 43. The manufacturer's specifications and procedures identified and described in this directive areincorporated 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 Grumman American Aviation Corporation, 318 Bishop Road, Cleveland, Ohio 44143. These documents may also be examined at FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 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 Great Lakes Region. Amendment 39-2485 became effective January 12, 1976. This amendment 39-2521 becomes effective February 25, 1976.