Results
2009-06-12: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: * * * * * The Bombardier CL-600-2B19 airplanes have had a history of flap failures at various positions for several years. Flap failure may result in a significant increase in required landing distances and higher fuel consumption than planned during a diversion. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-18-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that when the number 2 engine thrust reverser (T/R) was opened, the right-hand T/R hinge nut located at position 4 was found detached; investigation revealed that certain nuts could have been installed with noncompliant locking features, or with locking features that could degrade quicker than anticipated. This AD requires replacing any existing nut on the T/R hinge with a new nut, installing a new nut and washer if necessary, and applying a torque stripe at each T/R hinge location, 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.
2020-18-14: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines with a certain high-pressure turbine (HPT) rotor stage 2 disk installed. This AD was prompted by a report from the manufacturer that a subsurface anomaly was found on a HPT rotor stage 2 disk. This AD requires an ultrasonic inspection (USI) of the HPT rotor stage 2 disk and, depending on the result of the inspection, replacement of the HPT rotor stage 2 disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
62-08-07: 62-08-07 GRUMMAN: Amdt. 420 Part 507 Federal Register April 14, 1962. Applies to Model G-164 Aircraft Serial Numbers 1 Through 100 Inclusive. For aircraft with 200 or more hours' time in service, compliance is required within 10 hours' time in service after the effective date of this AD. For aircraft with less than 200 hours' time in service, compliance is required within 25 hours' time in service after the effective date of this AD, or before 210 hours' total time in service is exceeded whichever occurs first. To preclude loss of aileron control, accomplish the following: (a) Replace the aileron cable control sector support brackets, upper and lower, in lower wing panels with new support brackets, P/N 1854-13 (Kit of replacement parts, A1854, furnished by Grumman), or FAA approved equivalent. Install the parts and the aileron cables in accordance with Grumman Aircraft Engineering Corp. Mandatory Service Bulletin No. 20 dated January 24, 1962, or FAA approved equivalent.(b) Visually inspect aileron control system pushrod assemblies, Grumman P/N's A1866-1 and A1866-3, in both lower wing panels, for loose rod end fittings due to elongation of rivet holes. Repair or replace loose fittings prior to further flight. After initial compliance, visually inspect the aileron control system pushrod assemblies at each periodic inspection thereafter until one of the following, or FAA approved equivalent is accomplished: (1) Insert aluminum alloy bar, 2024-T3, 7/16 O.D. x 7/8-inch plugs in each end of A1866-11 and A1866-13 tubes and reinstall the rod ends with two AN 470-AD5 rivets per rod end. (2) Install Grumman P/N A1866-25 in lieu of A1866-1 and P/N A1866-27 in lieu of A1866-3. (Grumman Service Bulletin No. 20 dated January 24, 1962, and the Addendum thereto dated February 3, 1962, cover this subject.) This directive effective April 25, 1962.
2003-20-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes. This action requires, among other actions, various inspections to detect cracks of the cockpit enclosure window sill, and follow-on and corrective actions, as applicable. This action is necessary to prevent fatigue cracking of the internal doublers and frame structure of the fuselage skin of the cockpit enclosure window sill, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
94-16-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires inspections, adjustments, and functional tests of the thrust reverser system. This amendment adds a requirement for installation of an additional thrust reverser system locking feature, periodic functional tests of that locking feature following its installation, and repair of any discrepancy found. This amendment is prompted by the identification of a modification that ensures that the level of safety inherent in the original type design of the thrust reverser system is further enhanced. The actions specified by this AD are intended to prevent possible discrepancies in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
2003-20-05: The FAA adopts a new airworthiness directive (AD) for certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to inspect the forward and aft dihedral fittings for cracks and replace any cracked fitting. This AD also requires you to modify the aft dihedral fitting and spar-cap bolt holes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent cracks from developing in the forward and aft dihedral fittings, which could result in failure of the wing in certain maneuvers. Such failure could lead to loss of control of the airplane.
2020-18-51: The FAA is adopting a new airworthiness directive (AD) for certain Sandia attitude indicators (attitude indicators). This AD was sent previously to all known U.S. owners and operators of aircraft with these attitude indicators installed. This AD requires revising the existing Airplane Flight Manual (AFM) for your airplane to prohibit operation under instrument flight rules (IFR) or night visual flight rules (VFR) and prohibit coupling the autopilot with an affected attitude indicator. This AD was prompted by reports of 54 failed attitude indicators. The FAA is issuing this AD to address the unsafe condition on these products.
80-22-11: 80-22-11 BELL: Amendment 39-3950. Applies to Model 206 L-1 helicopters, certificated in all categories (Airworthiness Docket No. 80-ASW-44). Compliance required as indicated. To prevent possible fatigue failure of the main rotor grip, P/N 206-011-132-009, remove and replace as specified below, the main rotor grips having serial numbers: A1-00001, A1-00004 through A1-00007, A1-00009, A1-00010, A1-00014, A1-00016, A1-00017, A1-00019, A1-00021 through A1-00024, A1-00027 through A1-00029, A1-00031 through A1-00036, A1-00038 through A1-00040, A1-00042 through A1-00044, A1-00046 through A1-00050, A1-00053 through A1-00057, A1-00059, A1-00061, A1-00062, A1-00064, A1-00066 through A1-00068, A1-00071, A1-00073 through A1-00075, A1-00077, A1-00078, A1-00080, A1-00083 through A1-00093, A1-00095, A1-00096, A1-00098 through A1-00101, A1-00103 through A1-00106, A1-00111, A1-00113, A1-00115, A1-00116, A1-00118 through A1-00120, A1-00124, A1-00130 through A1-00136, A1-00192, A1-00222,A1-00248, A1- 00287, A1-00300, A1-00305, and A1-00308. a. Replace those grips with less than 1,150 hours' total time in service on the effective date of this AD, prior to accumulating 1,200 hours' total time in service. b. Replace those grips with 1,150 or more hours' total time in service on the effective date of this AD, within 50 hours' time in service. c. Compliance with Bell Helicopter Textron Alert Service Bulletin 206L-80-15, dated July 29, 1980, fulfills compliance with this AD. d. The retirement time of those main rotor grips specified above is reduced from 4,800 hours to 1,200 hours by this AD. e. The helicopter may be flown in accordance with FAR 21.197 to a base where repairs can be performed. This amendment becomes effective October 27, 1980.
77-04-02: 77-04-02 PIPER: Amendment 39-2834. Applies to Model PA-36-285, Serial Nos. 36- 7360001 through 36-7660135 certificated in all categories. To prevent possible hazards associated with loss of directional control due to tail wheel shimmy, accomplish the following within the next 100 hours in service from the effective date of this AD unless previously accomplished.: (a) On aircraft Serial Nos. 36-7560001 through 36-766080 incorporate Piper Kit Number 761 034 tail wheel modification or equivalent. (b) On aircraft Serial Nos. 36-7360001 through 36-7660135 incorporate Piper Kit Number 761 067, Fuselage Frame Reinforcement or equivalent. (c) Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Upon request with substantiating data, submitted through an FAA Maintenance Inspector, the compliance time for incorporating the alterations may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin Number 506 pertains to this subject.) This amendment is effective February 21, 1977.