Results
75-22-15: 75-22-15 MORANE SAULNIER (SOCATA) RALLYE: Amendment 39-2405. Applies to MS880B and MS885 airplanes, certificated in all categories, except serial numbers 1962 and subsequent; and MS892A150, MS893A, and MS894A airplanes, certificated in all categories, except serial numbers 11993 and subsequent. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible interference between the control stick and floor hat section, accomplish the following: Modify the floor adjacent to the control stick by increasing the clearance between the floor and control stick in accordance with the "Description" paragraph in Socata Service Bulletin No. 104 GR-27-09, dated September, 1972, or an FAA-approved equivalent. This amendment becomes effective November 4, 1975.
2017-08-10: We are superseding airworthiness directive (AD) 2017-01-01 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2017-01-01 required inspections of the low-pressure turbine (LPT) exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD corrects references to certain service bulletins in the compliance section of AD 2017-01-01. This AD was prompted by reports that references to service bulletins in AD 2017-01-01 are incorrect. We are issuing this AD to correct the unsafe condition on these products.
2017-06-11: We are superseding Emergency Airworthiness Directive (Emergency AD) 2015-24-51 for Airbus Helicopters Model EC120B. Emergency AD 2015-24-51 required inspections of the air conditioning system. This supersedure revises the applicability, some of the terminology, and the [[Page 18691]] inspection requirements. This AD was prompted by a report of an abnormal noise during flight of a Model EC120B helicopter that resulted in a precautionary landing. We are issuing this AD to prevent an unsafe condition on these products.
2024-15-13: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by occurrences of premature cracks in the outer layer of certain flight deck side windows caused by interference due to manufacturing tolerances. This AD requires initial and repetitive inspections of the flight deck side windows and applicable corrective actions, and prohibits the installation of affected flight deck side windows, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
75-03-05: 75-03-05 HAMILTON STANDARD: Amendment 39-2025. Applies to propeller Models 54H60-63, -81, -91, -111, -117, and -125. Compliance required as indicated, unless already accomplished. To prevent inflight separation of the extension sleeve, P/N 541850, Change B or earlier revision, from the pitch lock regulator assembly resulting in propeller pitchlocking, accomplish the following: A. Propellers with a total of 2500 or more hours in service as of the effective date of this AD or whose total time in service is unknown, accomplish the requirements of Paragraph (C) below within the next 100 hours time in service. B. Propellers with less than 2500 hours total time in service as of the effective date of this AD, accomplish the requirements of Paragraph (C) below prior to the accumulation of 2600 hours total time in service. C. 1. Replace the fluid transfer housing extension sleeve, P/N 541850B or earlier revision, with an extension sleeve, P/N 541850C or later revision,or with a modified extension sleeve in accordance with Hamilton Standard Service Bulletin HS Code 54H60, No. 59, Revision No. 1, dated August 1, 1972, or later FAA approved revision, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 2. Replace the surge valve housing, P/N 543734B or earlier revision, with housing P/N 543734C or later revision, or replace surge valve housing, P/N 535299E or earlier revision with housing P/N 535299F or later revision. 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 Hamilton Standard, Division of United Aircraft Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on February 5, 1975.
2017-08-07: We are adopting a new airworthiness directive (AD) for certain Learjet, Inc., Model 60 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper fuselage skin under the aft oxygen line fairing is subject to multi-site damage (MSD). This AD requires a one-time inspection of the fuselage skin for corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
76-01-09: 76-01-09 PILATUS AIRCRAFT LTD: Amendment 39-2490. Applies to Pilatus Model PC-6 airplanes (all variants) manufactured by Pilatus Aircraft Ltd. serial numbers 667 and subsequent and serial numbers 2001 through 2047 inclusive manufactured by Fairchild Hiller. Compliance is required as indicated. To prevent a possible fatigue failure of the elevator attachment brackets on the inboard ends of the right and left elevator surfaces, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 25 hours' time in service and thereafter at intervals not to exceed 50 hours time in service since the last inspection, visually inspect both the left and right brackets, P/N 6300.0011.00, of the welded attachment assembly for cracks in the flanges using a glass of at least 10 power in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (b) If cracks are found, before further flight, repair in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (c) Within the next 200 hours' time in service after the effective date of this AD, install reinforcement plates, P/Ns 6002.6993.51 and 6002.6993.52, unless already accomplished, in accordance with paragraph 2.2 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after all cracks have been repaired and reinforcement plates have been installed in accordance with paragraph (c) of the AD. (Fairchild Hiller Service Bulletin PC-6-55-3 pertains to this same subject.) This amendment becomes effective on February 6, 1976.
2024-16-04: The FAA is superseding Airworthiness Directive (AD) 2009-25- 13, which applied to certain Bombardier, Inc., Model BD-100-1A10 (Challenger 300) airplanes. AD 2009-25-13 required the deactivation of the left-hand (LH) baggage bay heater mat. Since the FAA issued AD 2009-25-13, Bombardier developed a new design solution for the potential uncontrolled heating of the baggage bay sidewall heater mat. This AD retains the requirements of AD 2009-25-13 and requires modifying the baggage bay sidewall interior panel, heater mat, and water tank heater installation, and doing functional testing. Upon the completion of the new actions, the retained requirements of AD 2009-25- 13 will terminate. This AD also revises the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2024-15-12: The FAA is superseding Airworthiness Directive (AD) 2021-26- 05, which applied to all Saab AB Model SAAB 2000 airplanes. AD 2021-26- 05 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2021-26-05 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-15-14: The FAA is superseding Airworthiness Directive (AD) 2021-17- 02, which applied to all ATR-GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2021-17-02 required a one-time inspection for discrepancies of the wire bundles between the left- and right-hand angle of attack (AOA) probes and the crew alerting computer, and, depending on findings, applicable corrective actions. AD 2021-17-02 also required, for certain airplanes, modifying the captain stick shaker wiring, and for all airplanes, revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to incorporate procedures for the stick pusher/shaker. Since the FAA issued AD 2021-17-02, additional modification of the affected wiring for certain airplanes was developed. This AD retains all of the requirements of AD 2021-17-02 and requires installing a new AOA power supply unit and removing the AFM amendment; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.