Results
2020-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Yabora Industria Aeronautica S.A. Model ERJ 170 airplanes and Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of installation of inverted poles of the horizontal stabilizer pitch trim switches on the control yokes, which causes opposite commands for the horizontal stabilizer. This AD requires installing supports for the horizontal stabilizer control yoke pitch trim switches and re-identifying the control yokes, as specified in two Agencia Nacional de Aviacao Civil (ANAC) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2003-11-15 R1: This amendment revises an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that currently requires replacing the lanyards on the pressure relief door for the thrust reverser with new, improved lanyards, and doing associated modifications. The actions specified by that AD are intended to ensure that the lanyards on the pressure relief door have adequate strength. Lanyards of inadequate strength could allow the pressure relief door to detach from the thrust reverser in the event that an engine bleed air duct bursts, which could result in the detached door striking and damaging the horizontal stabilizer, and consequent reduced controllability of the airplane. This amendment is prompted by the fact that a certain paragraph of the existing AD prohibits installation of certain part numbers of lanyards; the numbers listed in that paragraph correspond to new, improved lanyards that are acceptable for installation. This amendment willcorrect these part numbers to prohibit installation of suspect lanyards while allowing installation of the new, improved lanyards. This action is intended to address the identified unsafe condition.
94-23-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-30 and -30F series airplanes, that requires replacement of cargo door latch spool fitting attach bolts fabricated from H-11 steel with Inconel bolts. This amendment is prompted by a report of a broken latch spool fitting attach bolt found on a cargo door on a Model DC-9 series freighter airplane. The actions specified by this AD are intended to prevent inadvertent opening of a cargo door while the airplane is in flight, and subsequent loss of pressurization and reduced controllability of the airplane.
2009-24-18: We are adopting a new 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: * * * [I]ncidents of throttle jam and engine shutdowns, caused by premature wear of the rack and pinion mechanism of part number (P/N) 2100140-005 and -007 Engine Throttle Control Gearbox (ETCG), installed on Bombardier CL-601 and 604 aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
65-26-02: 65-26-02 LEARJET: Amdt. 39-159 Part 39 Federal Register November 25, 1965. Applies to Model 23 Airplanes. Compliance required before further flight, unless already accomplished. To prevent runaway aileron or stabilizer trim due to shorting of wires, accomplish the following: (a) Remove two side screws holding control column covers, P/N 2315153-015 (Figure 59-7 Lear Parts Cat.). If screw length exceeds 3/8-inch, rework before further flight in accordance with Lear Jet Corporation instructions. (b) Remove lens, P/N 2315155-025; bracket, P/N 2315155-024; and two attaching screws (Figure 59-33-34-35, Lear Parts Catalog). Remove map light. Cap and stow map light wires. Do not replace any parts. Leave cavity open. If wiring in cavity is damaged, rework before further flight in accordance with Lear Jet Corporation instructions. (c) It is requested that the inspection results be reported by telegraph or telephone to FAA, CE-200, 4820 Troost Avenue, Kansas City, Missouri. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated November 17, 1965.
95-11-07: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires inspections to detect cracking of H-11 attach bolts of the upper vertical stabilizer and replacement of these bolts and associated nuts with Inconel bolts and nuts. This amendment is prompted by failure of the attach bolts of the upper vertical stabilizer due to stress corrosion. The actions specified by this AD are intended to prevent undetected cracked or failed attach bolts that may lead to reduced structural integrity of the vertical stabilizer.
57-07-02: 57-07-02 BELL: Applies to Model 47 Helicopters Except the Following: Model 47G 1529, 1689 and Up; 47G2 1506, 1957 and Up; Model 47H1 1361, 1534 and Up; Model 47J 1420, 1421, 1423, 1424, 1428 and Up; Model 47K. Compliance required as indicated. 1. In order to insure that rotor hub equalizer link assembly, P/N 47-120-025-1, is assembled with sufficient threads engaged to meet safety requirements, the following inspection must be conducted and part reworked as necessary by April 15, 1957, unless item 2 has been accomplished. (a) Inspect rod end, P/N 47-120-025-7, for adequate distance between end of shank to safety inspection hole, 0.230 to 0.270 inch required. (b) Inspect for adequate distance between shank end of P/N 47-120-025-5 rod end shank end of P/N 47-120-025-7 rod end. Maximum of 15/32 (0.468) inch is allowed. NOTE: If dimension between rod ends exceeds 15/32 (0.468) inch, hub assembly must be rerigged and link assemblies must be adjusted until this dimension is below this valve. 2. Rework on, or before, next overhaul of main rotor hub assembly. Rework link assemblies, P/N 47-120-025-1, which do not meet conditions described in above inspection, item 1(a) as follows: (a) Remove link assembly, P/N 47-120-025-1 from main rotor hub assembly and remove rod end, P/N 47-120-025-7 from link assembly. (b) Drill a No. 50 (0.070) inch diameter hole through shank at a point 0.230- 0.270 inch from shank end and 90 degrees from existing inspection hole. (c) Reassemble link assembly, install on hub assembly, and rerig hub assembly. Use new safety inspection hole to determine that rod end has sufficient threads engaged. (Bell Service Bulletin No. 118SB dated February 1, 1957, covers this same subject.)
94-21-01: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 series airplanes, that requires modification of the potentiometer lever stops on the nose wheel steering. This amendment is prompted by a report that the potentiometer stops installed currently on these airplanes are too short to limit excessive uncontrolled potentiometer movement in the event of a mechanical link failure. The actions specified by this AD are intended to prevent the airplane from departing the runway during takeoff or landing in the event of the failure of the mechanical link between the rudder pedals and the potentiometer.
2020-25-11: The FAA is superseding Airworthiness Directive (AD) 2014-12- 12, which applied to certain Airbus Helicopters Model EC120B and EC130B4 helicopters. AD 2014-12-12 required inspecting and, if necessary, replacing parts of the sliding door star support attachment assembly. This AD requires modifying the sliding door star support stringer as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). This AD was prompted by several incidents involving helicopter left-hand side doors (both swinging and sliding) that revealed weaknesses in the locking mechanism. The FAA is issuing this AD to address the unsafe condition on these products.
96-25-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that requires repetitive inspections to detect cracks of the rear bracket attached to the outboard rib of the shroud boxes and the surfaces of the lugs adjacent to the bushes, and replacement, if necessary. This amendment also requires replacement of the outboard aft brackets of the shroud boxes with modified brackets that have floating boxes, which terminates the repetitive inspections. This amendment is prompted by a report that the lug of the rear outboard bracket failed due to fatigue. The actions specified by this AD are intended to prevent fatigue-related cracking in the subject lug, and the consequent failure of this lug; this condition could result in the loss of the shroud box and, consequently, lead to reduced controllability of the airplane.
2003-25-13: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires a one- time inspection for damage of the power feeder cables and surrounding structure, and repair if necessary. For certain airplanes, this amendment requires fabricating and installing a power feeder support bracket assembly and clamps at station Y=595.000, left side. For certain other airplanes, this amendment requires installing two power feeder support brackets and clamps at station Y=606.000, left side. This action is necessary to prevent chafing of the external ground power feeder cables against the adjacent structure, which could result in arcing and fire. This action is intended to address the identified unsafe condition.
95-10-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
2020-25-02: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Support and Services Model 340A (SAAB/SF340A) and SAAB 340B airplanes; and Model SAAB 2000 airplanes. This AD was prompted by reports that certain nose landing gear (NLG) door attachment bolts are susceptible to hydrogen embrittlement. This AD requires replacing certain NLG door attachment bolts with serviceable bolts, 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.
59-10-07: 59-10-07 LYCOMING: Applies to O-320, O-340, O-360, GO-480, GSO-480, IGSO-480 and O-540 Series Engines As Noted. Compliance required as soon as possible but not later than July 1, 1959. It has been found that due to normal expansion of the cylinders during engine operation, the cylinder baffle clamps can become wedged between the cylinders causing barrel distortion and possible extensive damage to the cylinder bore and piston assembly. To correct this condition, the cylinder baffle clamps must either be (1) removed and replaced with baffle retainers and retainer hooks, or (2) removed and reworked to provide more clearance between the lower portion of the clamp and the cylinder. Lycoming Service Bulletin No. 254A lists the parts required to comply with alternate method (1) above. An acceptable method of accomplishing the rework noted as alternate method (2) is also outlined in that bulletin, as well as the serial numbers of engines which comply with the requirements of this directive as delivered from the factory.
2003-26-01: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time general visual inspection to identify the material of the rudder assembly, and corrective actions, if necessary. For airplanes with a graphite assembly, this action requires repetitive general visual inspections of the flange bolts of the rudder front spar for any loose bolts, and corrective actions, if necessary. This action is necessary to detect and correct loose bolts common to the flange of the rudder front spar and main thrust hinge and actuator assembly, as well as the auxiliary actuator support fitting, which could cause the rudder actuator to separate from the rudder during certain flight conditions, resulting in loss of rudder control and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2009-24-19: We are adopting a new 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: An A320 operator experienced difficulties in extending the RAT [ram air turbine] during a deployment testing. During the trouble shooting, the Ejection Jack of the RAT was removed and investigated. The investigation identified excessive wear of the uplock segments against the inner cylinder of the Ejection Jack, due to an incorrect blend radius of the inner cylinder. * * * This Ejection Jack failure may prevent the effective deployment and use of the RAT in emergency conditions. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-26-06: The FAA is adopting a new airworthiness directive (AD) for certain Technify Motors GmbH TAE 125-02-99 and TAE 125-02-114 model reciprocating engines. This AD was prompted by a report of a defective turbocharger hose discovered on an airplane during a pre-flight inspection. This AD requires the removal and replacement of the affected turbocharger hose. The FAA is issuing this AD to address the unsafe condition on these products.
2003-25-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires modifying the fuel pipe couplings and installing bonding leads in specified locations within the fuel tank. This amendment continues to require the modification and installation, but adds new modifications of the bonding leads for certain airplanes. This amendment also changes the applicability of the existing AD. The actions specified by this AD are intended to prevent ignition sources and consequent fire/explosion in the fuel tank. This action is intended to address the identified unsafe condition.
2009-24-20: We are adopting a new 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: Frost, snow, slush or ice on the wing leading edges and upper wing surfaces may change the stall speeds, stall characteristics and the protection provided by the stall protection system, which could result in reduced controllability of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
94-18-03: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls- Royce plc (R-R) RB211 series turbofan engines. This action requires removing from service intermediate pressure (IP) compressor stage 6-7 rotor shafts that exceed new, reduced cyclic life limits. This amendment is prompted by a report of an uncontained failure of an IP compressor stage 6-7 rotor shaft. The actions specified in this AD are intended to prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 26, 1994. Comments for inclusion in the Rules Docket must be received on or before November 8, 1994.
95-24-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the check valves of the thrust reverser with modified valves on certain airplanes and the replacement of the manual control valves of the thrust reverser with modified valves on certain other airplanes. This amendment is prompted by recent engineering analysis, which revealed that, if the non-return valve installed on the hydraulic return line of the thrust reverser were to jam in the closed position, it could cause pressurization of the Hydraulic Control Unit (HCU). The actions specified by this AD are intended to prevent such pressurization of the HCU due to jamming of the non-return valve in the hydraulic return line, and consequent deployment of a thrust reverser during flight; this condition, if not corrected, could adversely affect the controllability of the airplane.
2020-24-04: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures for conducting an approach with a localizer- based navigation aid, monitoring localizer raw data, calling out any significant deviations, and performing an immediate go around if the airplane has not intercepted the final approach course as shown by the localizer deviation. This AD was prompted by reports that the autopilot flight director system (AFDS) failed to transition to the instrument landing system localizer (LOC) beam after the consistent localizer capture function in the flight control modules initiated a transition to capture LOC during approach. The FAA is issuing this AD to address the unsafe condition on these products.
94-17-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, -300, and -400 series airplanes, that requires various modifications of certain evacuation ramp/slides. This amendment is prompted by reports of several evacuation ramp/slide malfunctions. The actions specified by this AD are intended to prevent delayed inflation of evacuation ramp/slides, which could delay or impede the evacuation of passengers during an emergency.
2008-11-02 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Lockheed Model L-1011 series airplanes. That AD currently requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive fuel system limitations to phase in those inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.DATES: This AD is effective December 18, 2009. On June 25, 2008 (73 FR 29410, May 21, 2008), the Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD. We must receive any comments on this AD by January 19, 2010.
2021-01-04: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes, excluding Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracked or completely severed lugs in the upper aft corner stop fitting assembly of the forward entry door. This AD requires an inspection, a measurement, or a records check of that assembly to determine the part number, and replacement if a certain part is found. The FAA is issuing this AD to address the unsafe condition on these products.