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86-26-01: 86-26-01 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5496. Applies to all Model DHC-8-101 and - 102 series airplanes, certificated in any category, equipped with upper and lower fore rudder mounting brackets, P/N's 85530097-105 and -107. Compliance required as indicated, unless previously accomplished. To prevent the failure of the fore rudder upper and lower mounting brackets and fin rear spar web accomplish the following: A. Within the next 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service, conduct a visual inspection of the upper and lower fore rudder mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 1. If cracks are found in the mounting brackets, prior to further flight: a. Conduct a visual inspection of the upper spar web for cracks in the vicinity of the mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. b. Reinforce the fore rudder mounting brackets by installing de Havilland Modifications 8/0647 in accordance with the Accomplishment Instruction of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 2. If, after accomplishing the visual inspection required by paragraph A.1.a., above, cracks are found in the spar web, prior to further flight, replace the cracked spar web with a new web in accordance with de Havilland Dash 8 Maintenance Manual (PSM 1-8-2), or accomplish an FAA-approved repair. B. Within 500 hours time-in-service after the effective date of this AD, install de Havilland Modification 8/0647 in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. Prior to installation of Modification 8/0647, conduct the visual inspections required by paragraph A., above, and perform the repair required by paragraph A.2., above, if necessary. C. Incorporation of de Havilland Modification 8/0647 constitutes terminating action for the repetitive inspection of paragraph A.., above. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division ofBoeing of Canada Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective January 5, 1987.
47-25-10: 47-25-10 CONVAIR: (Was Service Note 4 of AD-2-571-2.) Applies to All BT-13 Series Airplanes Equipped With Wood Elevator Tabs. Compliance required not later than September 1, 1947, and each 20 hours of operation thereafter. The elevator tabs should be closely inspected to determine if any sign of glue failure, dry rot, or cracking of plywood exists adjacent to glue joints. Attachment of aluminum alloy extension to tab may have weakened the trailing edges of wood tabs or weathering of wood may have caused deterioration. If any failure or deterioration is found, the tab should be immediately replaced or repaired in an adequate manner.
94-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires modification of the power transfer unit (PTU). This amendment is prompted by reports of fatigue cracks found in the drain port housings of the PTU's on several airplanes. The actions specified by this AD are intended to prevent failure of the PTU housing due to fatigue cracking, which could result in the loss of both hydraulic systems (until the PTU is shut off).\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 28, 1994.
2004-12-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires, among other actions, replacement of the existing air driven generator (ADG) wire assembly in the right air conditioning compartment with a certain new wire assembly. This amendment requires replacement of the ADG wiring and two associated clamps; inspection of the ADG wiring for correct wire identification, riding, and damage, and inspection of the associated routing/clamps for correct installation; and corrective actions if necessary. The actions specified by this AD are intended to prevent loss of the charging capability of the airplane battery due to chafing. Loss of the charging capability of the airplane battery, coupled with a loss of all normal electrical power, could prevent continued safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2021-25-12: The FAA is superseding Airworthiness Directive (AD) 2017-19- 09, which applied to certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series airplanes. AD 2017-19-09 required modifying the nose landing gear (NLG) shock strut assembly. This new AD requires repetitive lubrications of the trailing arm of the NLG. This new AD also requires revising the existing maintenance or inspection program to include new and revised airworthiness limitations (life limits for certain bolts). This AD was prompted by reports of a certain bolt being found missing or having stress corrosion cracking. The FAA is issuing this AD to address the unsafe condition on these products.
93-06-07: 93-06-07 DE HAVILLAND, INC.: Amendment 39-8532. Docket 92-NM-81-AD. Applicability: Model DHC-7 series airplanes, serial numbers 003 through 113, inclusive; Model DHC-8-102 and -103 series airplanes, serial numbers 003 through 321, inclusive; and Model DHC-8-301 and -311 series airplanes, serial numbers 100 through 320, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of both hydraulic systems due to depletion of hydraulic fluid, accomplish the following: (a) For Model DHC-7 series airplanes: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing Quantity Limiting Valves (QLV), from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 7/2610; in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992. (b) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated 6,700 total hours time-in-service or more as of the effective date of this AD, or if 50 months or more have passed since the airplane was manufactured as of the effective date of this AD: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (c) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated less than 6,700 total hours time-in-service as of the effective date of this AD and if less than 50 months have passed since the airplane was manufactured as of the effective date of this AD:Prior to the accumulation of 7,700 hours time-in-service since the airplane was manufactured, or within 12 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The removal, modification, and replacement shall be done in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992 (for Model DHC-7 series airplanes); or de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992 (for Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes); as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 12, 1993.
94-04-18: This amendment supersedes Airworthiness Directive (AD) 92-24-01, which currently requires inspecting the elevator balance arm assemblies of certain Beech Aircraft Corporation Models 34C and T34C-1 airplanes to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and also requires replacing the assembly if insufficient welds are found. The Federal Aviation Administration (FAA) has determined that the existing AD should also apply to certain Beech Model T34C airplanes. This action retains the requirements of AD 92-24-01 and incorporates these Beech Model T34C airplanes. The actions specified by this AD are intended to prevent separation of an elevator balance arm assembly from the elevator because of an insufficient weld, which could result in loss of control of the airplane.
2004-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes. This action requires repetitive inspections for cracks or evidence of damage/distortion of the anti-skid drive coupling clips for the hubcaps of the main landing gear (MLG) wheels; repetitive measurement of the gap and height dimensions of the coupling clips; corrective actions, if necessary; and eventual replacement of all coupling clips with new, improved coupling clips. This action is necessary to prevent excessive gaps in the anti-skid drive coupling clips for the hubcaps of the MLG, which could result in momentary loss of the normal braking system at low speeds, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2012-12-01: We are superseding an existing airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R and A300 F4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A310 series airplanes. That AD currently requires modifying the wiring in the right-hand electronics rack. This new AD requires replacing the cockpit multi-tank indicators (MTI), and for certain airplanes, replacing high-level, low-level, and overflow sensors and their harness connectors, and re-instating the low-level warning indication to the cockpit MTI. This AD was prompted by reports of failures of four fuel level sensor-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing this AD to prevent degradation of the electrical insulation sleeves of the low- level indication lamps on the MTI, which could cause a short circuit that might result in high voltage being conveyed to the high- and low- level sensors in the wing tanks. This condition could cause the level sensor to heat above acceptable limits, possibly resulting in a fuel tank explosion, and consequent loss of the airplane.
2021-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by the determination that certain part-numbered fairings were never introduced into the main rotor (MR) tip lights kit design definition and were not certified for icing conditions. This AD requires replacing affected parts. This AD also prohibits, after modification of the helicopter as required, installing any affected part on any helicopter 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.