Results
2014-13-09: We are adopting a new airworthiness directive (AD) for AHD Model EC135P1, P2, P2+, T1, T2, and T2+ helicopters. This AD requires repetitive visual inspections of the ring frame X9227 for a crack and, if there is a crack, replacing the ring frame before further flight. This AD is prompted by a fatigue crack in the ring frame. These actions are intended to detect a crack in the ring frame and prevent loss of the tail rotor and subsequent loss of control of the helicopter.
2014-13-15: We are adopting a new airworthiness directive (AD) for certain EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.) Model CN-235-300 airplanes. This AD was prompted by reports of reduced thickness of the center fuselage lower skin panel. This AD requires a detailed inspection to determine the presence of panel thickness reduction; and repetitive nondestructive testing (NDT) inspections and repair if necessary. We are issuing this AD to detect and correct reduced thickness of lower panel joints, which could result in reduced fatigue and damage tolerant characteristics of the lower panel joint to the adjacent side panels and failure of the center fuselage lower skin panel, resulting in loss of control of the airplane.
67-01-01: 67-01-01 BRITISH AIRCRAFT: Amdt. 39-321 Part 39 Federal Register December 16, 1966. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as directed. To prevent fatigue failures of the flap carriage links, accomplish the following until links, P/N AB09 A943, are replaced with modification PM 2245 links, P/N AB09 A3657: (a) For 200 Series airplanes having No. 1 flap links with less than 2,500 landings on the effective date of this AD, remove links from service before the accumulation of 3,000 landings. (b) For 200 Series airplanes having No. 1 flap links with 2,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (c) For 200 Series airplanes having No. 2 flap links with less than 11,500 landings on the effective date of this AD, remove links from service before the accumulation of 12,000 landings. (d) For 200 Series airplanes having No. 2 flaplinks with 11,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (e) For 200 Series airplanes having No. 3 flap links with less than 23,500 landings on the effective date of this AD, remove links from service before the accumulation of 24,000 landings. (f) For 200 Series airplanes having No. 3 flap links with 23,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (g) For 400 Series airplanes having No. 1 flap links with less than 1,500 landings on the effective date of this AD, remove links from service before the accumulation of 2,000 landings. (h) For 400 Series airplanes having No. 1 flap links with 1,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (i) For 400 Series airplaneshaving No. 2 flap links with less than 7,500 landings on the effective date of this AD, remove links from service before the accumulation of 8,000 landings. (j) For 400 Series airplanes having No. 2 flap links with 7,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (k) For 400 Series airplanes having No. 3 flap links with less than 15,500 landings on the effective date of this AD, remove links from service before the accumulation of 16,000 landings. (l) For 400 Series airplanes having No. 3 flap links with 15,500 or more landings on the effective date of this AD, remove links from service within the next 500 landings after the effective date of this AD. (m) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (British Aircraft Corporation (Operating) Ltd. (Weybridge Division), Alert Service Bulletin No. 27-A-PM2245 pertains to this subject.) This directive effective January 15, 1967.
2007-04-11: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2, B4-100, and B4-200 series airplanes. That AD currently requires supplemental structural inspections to detect fatigue cracking, and repair of cracked structure. This new AD requires revising the maintenance program by incorporating new and revised supplemental structural inspections, inspection intervals, and repairs; and repair of any damaged, cracked, or corroded structure; which would end the existing supplement structural inspections. This AD results from a review of service history and reports received from the current supplemental structural inspection document program. We are issuing this AD to prevent reduced structural integrity of these airplanes due to fatigue cracking.
2014-13-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, -500, -600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a review of the tail strobe light installation, which revealed that the tail strobe light is not electrically bonded to primary structure of the airplane. This AD requires installing a new tail strobe light housing and a new disconnect bracket, and changing the wire bundles. This AD also requires, for certain airplanes, an inspection to determine if sealant is applied, and corrective actions if necessary. We are issuing this AD to prevent, in case of a direct lightning strike to the tail strobe light, damage to the operation of other critical airplane systems due to electromagnetic coupling and large transient voltages, and damage to the control mechanisms or surfaces due to a fire, which could result in loss of control of the airplane.
2007-02-22: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This AD requires doing repetitive inspections for any missing, damaged, or incorrectly installed wiper rings in the splined couplings of the flap transmission shafts; inspections for any missing, damaged, or incorrectly installed rubber gaiters and straps on the sliding bearing/plunging joints of the flap transmission; and corrective action if necessary. This AD results from reviews in which the manufacturer determined that the splined couplings and sliding bearings of the flap transmission system could be affected by corrosion and wear. We are issuing this AD to detect and correct damaged, missing, or incorrectly installed components of the flap transmission system, which could result in reduced functional integrity of the flap transmission system and consequent reduced control of the airplane.
2014-06-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B- 1, and MBB-BK 117 C-2 helicopters with a certain Metro Aviation, Inc. (Metro), vapor-cycle air conditioning kit pulley (pulley) installed, which was sent previously to all known U.S. owners and operators of these helicopters. This AD supersedes AD 2013-12-06, which required inspecting the pulley for looseness and properly installed lockwire and re-installing the pulley. Since we issued AD 2013-12-06, we received a report of a possible design and manufacturing deficiency in some pulleys wherein they did not have sufficient thread depth, allowing the pulley to detach from the rotor brake disc. This AD requires inspecting each pulley attaching bolt hole to determine if there is sufficient depth of the threads and either removing the pulley if the depth is insufficient or installing dual locking tabs under each pulley attaching bolt if the depth is sufficient. These actions are intended to prevent the pulley from detaching, resulting in damage to the tail rotor (T/R) driveshaft, and subsequent loss of control of the helicopter.
70-07-05: 70-07-05 BRITTEN-NORMAN, LTD: Amdt. 39-965. Applies to Models BN-2 and BN-2A airplanes. To prevent possible engine fires due to accumulation of fuel in the rear of the carburetor air box and hot air ducting, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install drain holes in each carburetor air box and in each engine cowling in accordance with Britten-Norman Service Bulletin No. BN-2/SB.28, dated February 12, 1970, or later ARB-approved issue, or an FAA-approved equivalent. This amendment becomes effective March 31, 1970.
2006-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD requires certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD results from a report that, during structural testing of the cockpit door, the lower hinge block rotated and caused the mating hinge pin to disengage, and caused excessive door deflection. We are issuing this AD to prevent failure of a door attachment, which could result in uncontrolled release of the cockpit door under certain fuselage decompression conditions, and possible damage to the airplane structure.
2018-07-20: We are superseding Airworthiness Directive (AD) 2014-03-07, which applied to certain The Boeing Company Model MD-11 and MD-11F airplanes. AD 2014-03-07 required inspecting certain locations of the wire bundles of the center upper auxiliary fuel tank for damage, and corrective action if necessary. AD 2014-03-07 also required installing nonmetallic barrier/shield sleeving, new clamps, new attaching hardware, and a new extruded channel. This AD adds certain inspections and expands the applicability. This AD was prompted by the determination that it is necessary to require an inspection of the wire bundles for damage at certain center upper auxiliary fuel tank locations on certain airplanes. We are issuing this AD to address the unsafe condition on these products.