Results
96-18-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 60 airplanes, that requires modification of the aft core cowl nozzle of the engine nacelles. This amendment is prompted by a report that the sealant material in the aft core cowl nozzle of the engine nacelle was found to extend higher than the nozzle's forward flange, which can allow it to interfere with the proper operation of the emergency fuel shutoff actuating mechanism. The actions specified by this AD are intended to prevent physical interference of the emergency fuel shutoff actuating mechanism and resultant engine shutdown.
2002-22-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires a one-time inspection for missing bolts on the inboard and outboard support of the inboard main flap, and follow-on inspections and corrective actions, if necessary. This amendment adds an inspection that was inadvertently omitted from the existing AD. The actions specified in this AD are intended to detect missing, loose, or cracked bolts on the supports of the inboard main flap and prevent loss of the inboard main flap, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition. \n\nDATES: Effective November 14, 2002.\n\n\tThe incorporation by reference, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 27, 2002 (67 FR 52401, August 12, 2002).\n\n\tComments for inclusion in the Rules Docket must be received on orbefore December 30, 2002.
2024-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Austro Engine GmbH Model E4 and E4P engines. This AD was prompted by reports of engine failures and the determination that certain batches of cap screws, installed on the inner main bearing positions of the engine, were manufactured at the lower end of the material strength tolerance. This AD requires replacing certain cap screws with a part eligible for installation and prohibits installing certain cap screws on any inner main bearing position of any engine. This AD also prohibits installing certain engine cores on any engine unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
2011-04-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a general visual inspection for damage of wiring (including chafing, pinched wires, and exposed wires) and correct routing of wires in the left and right circuit breaker panels, and related investigative and corrective actions if necessary. This AD results from reports of wire damage on the pilot and copilot circuit breaker panels caused by a short circuit between chafed wiring and the circuit breaker panel forward mounting bracket. We are issuing this AD to detect and correct damaged or misrouted wires, which could result in a short circuit and the loss of systems associated with the wiring (including fire suppression function for one engine and essential avionics systems).
95-17-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 series airplanes. This action requires removing the main landing gear (MLG) stop bolts from the bracket assembly on the upper scissors for those airplanes with a MLG door stop installation, and servicing the MLG oleos for all affected airplanes. Incidents where two of the affected airplanes made an emergency gear-up landing prompted this action. The actions specified by this AD are intended to prevent the MLG doors from jamming, which could prevent the gear from extending and could result in an emergency gear-up landing.
2002-21-10: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Pratt and Whitney (PW) model 4000 series turbofan engines. That action required PW4000 engines with potentially reduced stability margin to be limited to no more than one engine on each airplane, and required removing engines that exceed high pressure compressor (HPC) cycles-since-overhaul (CSO) or cycles-since-new (CSN) from service based on the engine's configuration and category. That action also required establishing a minimum build standard for engines that are returned to service, and performing cool-engine fuel spike testing (Testing-21) on engines to be returned to service after having exceeded HPC cyclic limits or after shop maintenance. This amendment establishes requirements similar to those in the existing AD being superseded, and introduces a rules-based criterion to determine the engine category classification for engines installed on Airbus A300 airplanes. This amendment also adds requirements to manage the engine configurations installed on Boeing 747 airplanes, and requires that repetitive Testing-21 be performed on certain configuration engines. This amendment also establishes criteria that requires Testing-21 on certain engines with Phase 0 or Phase 1, FB2T, or FB2B fan blade configurations. In addition, this amendment re- establishes high pressure compressor (HPC)-to-high pressure-turbine (HPT) cycles-since-overhaul (CSO) cyclic mismatch criteria, and adds criteria to address engine installation changes, engine transfers, and thrust rating changes. Also, this amendment establishes criteria to allow engine stagger without performing Testing-21 for engines which are over their respective limits. This amendment also introduces new requirements on the Phase 3, first run subpopulation engines which were identified after the issuance of NPRM Docket No. 2000-NE-47-AD. The Phase 3, first run subpopulation engines have a significant increase in surge rate and Testing-21 failure rate than the rest of the PW4000 fleet. In order to manage the subpopulation engines to preclude a dual-engine surge, immediate action is required. This immediately adopted rule includes the requirements proposed in the NPRM as well as the required actions for the Phase 3, first run subpopulation engines. This amendment is prompted by investigation and evaluation of PW4000 series turbofan engines surge data, and continuing reports of surges in the PW4000 fleet. The actions specified in this AD are intended to prevent engine takeoff power losses due to HPC surge. DATES: Effective November 12, 2002. The incorporation by reference of certain publications listed in the rule is approved by the Director of the Federal Register as of November 12, 2002. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 17, 2002 (67 FR 1, January2, 2002). Comments for inclusion in the Rules Docket must be received on or before December 24, 2002.
2024-02-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that a certain nondestructive test (NDT) procedure associated with a certain airworthiness limitation for inspecting the inboard, mid, and outboard flap metallic end ribs does not contain all of the necessary instructions. This AD requires a revision to the existing maintenance or inspection program to require using a revised NDT procedure when performing an airworthiness limitation task. This AD also prohibits the use of earlier revisions of that NDT procedure. The FAA is issuing this AD to address the unsafe condition on these products.
95-18-11: This amendment supersedes Airworthiness Directive (AD) 73-05-03, which currently requires repetitively inspecting the rear spar cap for cracks on certain de Havilland DHC-6 series airplanes, and replacing any cracked rear spar cap. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires modifying the wing rear spar support (Modification No. 6/1301) as terminating action for the currently required repetitive inspections. The actions specified by this AD are intended to prevent cracking of the top flange of the wing spar attachment caps, which, if not detected and corrected, could result in loss of control of the airplane.
2024-02-55: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited Model 505 helicopters. This AD was prompted by reports of cracked vertical stabilizer top end cap assemblies. This AD requires an initial and recurring inspections of the vertical stabilizer top end cap assembly and corrective action if a crack is found, as specified in a Transport Canada AD, which is incorporated by reference. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
2002-21-11: This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. This AD requires you (for all affected airplanes) to inspect the upper longeron at the horizontal stabilizer attachment for cracks using a fluorescent dye check penetrant method, repair any cracks found, and modify the horizontal stabilizer. This AD also requires a limit on operation to the Normal category until accomplishment of the initial inspection and modification on airplanes with less than 200 hours time-in-service (TIS). This AD is the result of reports of fatigue cracks at the horizontal stabilizer attachment on the affected airplanes. The actions specified by this AD are intended to detect and correct cracks in the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage with consequent loss of control of the airplane.