Results
2014-16-23: We are superseding Airworthiness Directive (AD) 2011-16-01 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-16-01 required adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and installing placards in the cockpit; replacing the frame of the emergency switch box; replacing certain horizontal stabilizer electronic control units (HSECU); revising the Limitations section of the airplane flight manual (AFM); and revising the maintenance program to incorporate a certain task. This new AD requires modifying the fly-by-wire (FBW) standard; and operational testing of the electric motors reversion relays and trim emergency command of the horizontal stabilizer trim system (HSTS), and repairs if necessary. This AD was prompted by an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane.
2014-17-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes; Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of rupture of the uplock springs of the nose landing gear (NLG) and main landing gear (MLG) doors and legs. This AD requires repetitive inspections of the uplock springs of the NLG and MLG doors and legs for broken and damaged springs, and corrective actions if necessary. We are issuing this AD to detect and correct improper free fall extension of the MLG or NLG, which could lead to possible loss of control of the airplane on the ground, and consequent damage to the airplane and injury to occupants.
74-23-08: 74-23-08 GRUMMAN AMERICAN CORPORATION: Amendment 39-2007. Applies to Grumman G-159 airplanes certificated in all categories. Compliance required within the next 200 hours time in service after the effective date of this airworthiness directive unless already accomplished. To provide dual electrical power for the fire extinguisher squib circuits accomplish the following or an equivalent rework approved by the Chief, Engineering and Manufacturing Branch, Southern Region. Remove the existing left and right engine fire extinguisher switches and left hand eyebrow circuit breaker panel nameplate. Install MS24524-21 switches, electrical wiring, 159SB10112-1 nameplate and check out system in accordance with Grumman Gulfstream I Aircraft Service Change 210. This amendment becomes effective November 15, 1974.
66-22-02: 66-22-02\tBOEING: Amdt. 39-285 Part 39 Federal Register September 7, 1966. Applies to Model 727 Series Airplanes Listed in Boeing Service Bulletin No. 29-22, Dated February 21, 1966.\n \n\tCompliance required within the next 700 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failure of the pneumatic brake system due to leaks between the control valve and the brake housing, modify the pneumatic brake system line installation in accordance with Boeing Service Bulletin No. 29-22, dated February 21, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective October 7, 1966.
2016-18-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300ER series airplanes. This AD requires replacing the low-pressure oxygen flex hoses with new non- conductive low-pressure oxygen flex hoses in the gaseous passenger oxygen system in airplanes equipped with therapeutic oxygen. This AD was prompted by a determination that the low-pressure oxygen flex hoses in the gaseous passenger oxygen system can potentially be conductive. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen flex hoses in the gaseous passenger oxygen system, which can cause the flex hoses to melt or burn, and a consequent oxygen-fed fire in the passenger cabin.
2014-16-26: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX airplanes. This AD was prompted by our determination to introduce a corrosion prevention control program, among other changes, to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to include the maintenance tasks and airworthiness limitations specified in the Airworthiness Limitations section of the airplane maintenance manual. We are issuing this AD to prevent reduced structural integrity and reduced controllability of the airplane.
2014-16-25: We are superseding Airworthiness Directive (AD) 2007-06-12 for certain Airbus Model A330-200 and A330-300 airplanes. This new AD reduces the compliance times for reinforcing the structure of the center fuselage. This AD was prompted by a new fatigue and damage tolerance evaluation that revealed the compliance time for an existing reinforcement of the fuselage has to be reduced. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
2014-16-05: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by reports of ``BLEED 1(2) LEAK'' messages displayed on the engine indication and crew alert system (EICAS), and indirect damage to components of the electrical wiring interconnection system (EWIS) in the engine pylon area. This AD requires inspecting the EWIS components for damage, and repair if necessary. This AD also requires installing pre-cooler deflectors on the left- and right-hand pylons, and applying silicone sealant. We are issuing this AD to prevent indirect damage to EWIS components near the engine bleed air pre-coolers, which could result in a dual engine roll back to idle and consequent dual engine power loss and reduced controllability of the airplane.
75-01-04: 75-01-04 BEECH: Amendment 39-2062. Applies to Models A23-19, 19A, M19A and B19 (Serial Numbers MB-1 through MB-520); Model B19 Sport 150 (Serial Numbers MB-521 through MB-616); Models 23, A23, A23A, B23 and C23 (Serial Numbers M-1 through M-1361); Model C23 Sundowner 180 (Serial Numbers M-1362 through M-1485); Models A23-24 and A24 (Serial Numbers MA-1 through MA-368); Model A24R (Serial Numbers MC-2 through MC-95); and Models A24R and B24R Sierra 200 (Serial Numbers MC-96 through MC-180) airplanes. Compliance: Required as indicated, unless already accomplished. A) To reduce the possibility of improper or unintentional movement of the fuel selector valve, within 50 hours' time in service after the effective date of this AD, replace the existing fuel selector valve guard with a P/N 169-920001-43 or P/N 169-920000-165 as applicable to the airplane. B) To prevent binding and assure complete shutoff of the P/N 169-920000-61-127 or -131 selector valve in the "Off" position, within 50 hours' time in service after the effective date of this AD, and thereafter at each annual, progressive or 100-hour inspection interval as required by Federal Aviation Regulation 91.169, check this valve for binding and shutoff characteristics in accordance with Beechcraft Service Instruction No. 0364-289, Rev. III, or later FAA-approved revision. If the valve does not meet the criteria contained in this Service Instruction, prior to further flight, replace it with an improved selector valve, P/N 169-380086-1, in accordance with Beechcraft Service Instruction No. 0622-289 or later FAA-approved revision. The above inspections are not applicable to the P/N 169-380086-1 selector valve and may be discontinued when it is installed. C) Equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. This amendment becomes effective January 7, 1975.
2014-16-18: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG). This AD requires revising the maintenance program by incorporating a new safe- life limitation for the NLG main fitting. We are issuing this AD to prevent collapse of the NLG, which could lead to degradation of direction control on the ground or an un-commanded turn to the left, and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants.