Results
2018-11-03: We are adopting a new airworthiness directive (AD) Airbus Helicopters Model SA-365C, SA-365C1, and SA-365C2 helicopters. This AD requires establishing a life limit of 2,000 hours time-in-service (TIS) for the Starflex star/mast connecting bolt (bolt) and removing from service each bolt that exceeds its life limit. This AD is prompted by the discovery that the bolt's life limit was not included in helicopter maintenance records. The actions of this AD are intended to prevent an unsafe condition on these products.
2006-11-14: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This action requires inspecting each main transmission assembly mounting bolt (bolt) for wear or corrosion, and if wear or corrosion is found, replacing the bolt, bolt barrel nut, and cage. This amendment is prompted by a report of a failure of a bolt that was discovered during a routine maintenance inspection. The actions specified in this AD are intended to prevent failure of a bolt, which could result in loss of support of the main transmission and subsequent loss of control of the helicopter.
2006-11-15: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model ERJ 170 and Model ERJ 190 airplanes. This AD requires revising the Limitations section of the airplane flight manual to prohibit the flightcrew from moving the throttle into the forward thrust range immediately after applying the thrust reverser. This AD results from a report that, during landing, the thrust reverser may not re-stow completely if the throttle lever is moved into the forward thrust range immediately after the thrust reverser is applied. We are issuing this AD to prevent the flightcrew from performing a takeoff with a partially deployed thrust reverser, which could result in reduced controllability of the airplane.
47-06-06: 47-06-06 GLOBE: (Was Mandatory Note 9 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 408 Inclusive; 1001 to 1460 Inclusive; and 2001 to 2329 Inclusive. Compliance required prior to April 1, 1947. Cut off the egress end of the engine breather line to terminate the line 1-inch above the grill opening. This will prevent clogging of the line due to formation of ice during cold weather operation or the entry of foreign matter caused by the propeller blast. (Globe Customer Service Maintenance Bulletin No. 11 covers this same subject.)
2020-21-23: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as improperly manufactured horizontal stabilizer rear attachment bolts. If not corrected, this could lead to fatigue failure of the bolts and loss of airplane control. The FAA is issuing this AD to address the unsafe condition on these products.
68-19-01: 68-19-01 SIAI-MARCHETTI: Amendment 39-653. Applies to Model S.205-22/R airplanes, Serial Nos. 213, 370, 371, 372, 373, 374, 378, 379, 380, 381, 382, 384, 385, 387, 388, 389, 390, 392, 393, 394, 395, 396, 398, 4-124, 4-125. Compliance required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. Modify the limitation markings on the suction gage instrument, Siai P/N NS5F017, located on the right side of the instrument panel, by marking a green arc in the range from 4 inches Hg. to 5 inches Hg. and a red radial line at 5 inches Hg. and adjust the instrument's suction relief valve so that the suction gage reading is 4.5 + 0.1 inches Hg. at 2200 r.p.m., in accordance with Siai-Marchetti Service Bulletin No. 205B21 dated May 6, 1968, or later RAI-approved issue, or an FAA-approved equivalent. Check to insure that the suction gage reading does not exceed 5 inches Hg. at maximum engine r.p.m. This amendment becomes effectiveOctober 11, 1968.
2006-11-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 757 series airplanes. That AD currently requires revising the Airworthiness Limitations section of the maintenance manual (757 Airworthiness Limitations Instructions (ALI)) to incorporate certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSEs). This new AD requires incorporating a new revision to the Airworthiness Limitations section of the Instructions of Continued Airworthiness to mandate certain repetitive inspections for fatigue cracking of PSEs, and adds airplanes to the applicability in the existing AD. This AD results from a new revision to the ALI. We are issuing this AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
97-02-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, A310, and A320 series airplanes, that currently requires an inspection of the landing gear brakes for wear, and replacement if the specified wear limits are not met. That AD also requires incorporation of the specified wear limits into the FAA-approved maintenance inspection program. This amendment requires that certain wear limits that are dependent on brake stack weight be used in conjunction with specified brake stack weights, and that maximum allowable brake wear limits for additional brake units be incorporated into the FAA-approved maintenance program. This amendment is prompted by a report that some brakes that are subject to the requirements of the existing AD have not been removed from service and by the determination of the maximum allowable brake wear limits for additional brake unit part numbers. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy rejected takeoff.
2018-11-07: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD requires a one-time inspection of the aileron bellcrank support brackets and a thickness measurement of the affected lug attaching the support bracket; repetitive inspections of the affected aileron bellcrank support brackets; and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD was prompted by the identification of a manufacturing defect on certain aileron bellcrank support brackets that resulted in the material thickness of the affected lug attaching the support bracket to the rear spar of the wing to be insufficient. We are issuing this AD to address the unsafe condition on these products.
2018-11-05: We are superseding Airworthiness Directive (AD) 2018-06-10 for certain Honda Aircraft Company LLC Model HA-420 airplanes. AD 2018-06- 10 required incorporating a temporary revision into the airplane flight manual and replacing faulty power brake valves upon condition. This AD retains the actions required in AD 2018-06-10 and adds airplanes to the Applicability section. This AD was prompted by an inadvertent mistake in the serial number applicability (both in the service bulletin and in the AD). We are issuing this AD to address the unsafe condition on these products by correcting the inadvertent serial number error.