Results
99-10-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires repetitive inspections and functional tests of a trailing edge flap limit switch to verify proper operation, and replacement of the existing limit switch with a new limit switch, if necessary. This AD also requires modification of the stabilizer control system, which constitutes terminating action for the repetitive inspections and tests. This amendment is prompted by reports of uncommanded stabilizer trim motion due to failure of the trailing edge flap limit switch. The actions specified in this AD are intended to prevent such failure, which could result in uncommanded (nose down) stabilizer trim motion and consequent reduced controllability of the airplane.
2012-24-05: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 900 series turbofan engines. This AD requires inspection of the low pressure turbine (LPT) bearing housing end cover assembly in certain engines and, if necessary, its replacement. This AD was prompted by a Trent 900 engine experiencing a high intermediate pressure vibration fault, along with other fluctuating engine parameters, while in flight. We are issuing this AD to prevent fracture of the oil transfer tube, which could result in uncontained failure of the engine and damage to the airplane.
2012-22-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of an in-service incident where the propeller de- icing system became unavailable due to burnt/chafed wires within the alternating current contactor box (ACCB). This AD requires inspection for chafing, damage, and loose wiring within an ACCB and repair if necessary; and requires rework and re-identification of the wiring installation within each ACCB. We are issuing this AD to detect and correct damaged, chafed, or loose wiring within an ACCB, which could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pilot probe heater, engine intake heater, or propeller de-icing system, and subsequently adversely affect the airplane's flight characteristics in icing conditions.
2022-06-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-3 helicopters. This AD was prompted by reports of a main rotor (M/R) blade lead-lag damper in a tilted position. This AD requires inspecting the Flex Control Unit (FCU), and corrective actions if necessary, as well as rework and re-identification of the bearing pin, 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.
48-09-03: 48-09-03 LUSCOMBE: Applies to Model 8 Series Airplanes Below Serial Number 5682 Equipped With Kollsman Airspeed Instruments. Compliance required by April 1, 1948. To obtain more accurate airspeed readings remove small baffle LAC P/N 181112, which is attached to the fuselage at the airspeed static tube opening. Installation of this baffle provides inaccurate airspeed readings ranging from approximately +6 m.p.h. at stall to approximately +15 m.p.h. at minimum trim speed.
96-17-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Beech (Raytheon) Model Hawker 1000 and BAe 125-1000A series airplanes, that currently requires inspections to detect various discrepancies of the fuel hose assemblies on the auxiliary power unit (APU), and correction of any discrepancy found. That AD was prompted by several reports of heat damage to the fuel hose assembly on the APU. This amendment adds a requirement to replace the existing conduit of the fuel feed hose with new improved conduit, which will terminate the repetitive inspections. The actions specified by this AD are intended to prevent failure of a fuel hose due to heat damage caused by incorrect routing or bleed air leakage; such failure could result in a malfunction of the APU, a fuel fire in the fuselage rear equipment bay, and reduced structural integrity of the surrounding structure. The incorporation by reference of Raytheon Service Bulletin SB 49-44, dated January 20, 1995, listed in the regulations was approved previously by the Director of the Federal Register as of May 23, 1995 (60 FR 22501, May 8, 1995)
2004-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing airplane models, that currently requires either inspections for discrepancies of the fueling float switch wiring in the center fuel tank and follow-on actions, or deactivation of the float switch. This amendment requires replacing the float switches in the center and wing fuel tanks with new, improved parts; installing a conduit liner system in the center fuel tank; and replacing conduit assemblies in the wing fuel tanks with new parts, which terminates the existing requirements. For certain airplanes, this amendment also requires replacing certain existing sections of the electrical conduit in the center fuel tank with new conduit. This amendment also adds one additional airplane model to the applicability and removes another. The actions specified by this AD are intended to prevent contamination of the fueling float switch by moisture or fuel, and chafing of the float switch wiring against the fuel tank conduit, which could present an ignition source inside the fuel tank that could cause a fire or explosion. This action is intended to address the identified unsafe condition.
72-11-04: 72-11-04 ENSTROM: Amdt. 39-1452. Applies to Model F-28A (Serial Numbers 1 through 83) helicopters. Compliance: Required as indicated, unless already accomplished. To prevent failure of tail rotor drive taper pins with subsequent loss of directional control, accomplish the following: A) Unless Paragraph B has been accomplished, within 10 hours' time in service after the effective date of this AD visually inspect the 2 forward and 3 aft AN386 taper pins installed in the tail rotor drive shaft assembly for looseness. Prior to further flight replace all loose taper pins with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. NOTE: Loose pins can be detected by: 1. Wiggling the pin with the fingers. 2. Grasping the tail rotor drive shaft with the hand and rotating the shaft back and forth while observing the movement of the pin in the mating hole. 3. Examining for loss of paint on the pin at the edge of the mating hole. 4. Examining for formation of a burr at the edge of the hole. B) Within 25 hours' time in service after the effective date of this AD, replace all AN386 taper pins installed in the tail rotor drive shaft assembly with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. This amendment becomes effective June 1, 1972.
2022-06-03: The FAA is superseding Airworthiness Directive (AD) 2022-02-02 which applied to certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 204B, 205A, 205A-1, 205B, 210, and 212 helicopters with a certain main rotor hub strap pin (pin) installed. AD 2022-02-02 required removing certain outboard pins from service and prohibited installing them on any helicopter. This AD expands the applicability to all affected pins, regardless if they are outboard or inboard. This AD also requires inspecting the removed pin for any deformation and if it is deformed, removing the mating strap fitting (fitting) from service. This AD was prompted by the discovery that AD 2022-02-02 inadvertently limited its applicability to only outboard pins when, in fact, all pins are subject to the unsafe condition and the determination that a deformed pin may have damaged the fitting. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection to detect cracking of the swivel bogie beam lugs, and repair, if necessary. For airplanes on which no cracking is found, this amendment also requires an inspection to detect corrosion of the swivel pin lug surfaces and bores, and modification of the forward bogie beams. This amendment is prompted by reports indicating that swivel pin lugs of the main landing gear (MLG) have failed due to cracks resulting from stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in failure of the swivel-type bogie beam of the MLG; this condition could result in collapse of the MLG during landing.