Results
2016-15-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of operator inability to open the main passenger door following severe hot soak conditions. This AD requires the incorporation of a new configuration to the passenger door external handle detent to enhance the performance across the full range of the airplane operating temperatures. We are issuing this AD to prevent thermal expansion and permanent deformation at severe hot soak conditions, creating high friction between the spring pot housing and the slider that could result in inability to open the main passenger door and impede evacuation in the event of an emergency.
2001-10-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires removing certain foam filters from the cabin ducting installation located below the dado panels on the left- and right-hand sides of the airplane. The actions specified by this AD are intended to prevent an increased risk of spreading a fire or failure of the cabin to pressurize adequately if certain foam filters are installed. This action is intended to address the identified unsafe condition.
90-11-01: 90-11-01 BOEING OF CANADA, LTD., DEHAVILLAND: Amendment 39-6752. Final Rule of priority letter AD. Docket No. 90-CE-36-AD. Applicability: Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD unless previously accomplished within the last 25 hours TIS prior to the effective date of this AD. To prevent failure of the elevator pushrod assembly due to fatigue cracking, and the subsequent loss of control of the airplane, accomplish the following: (a) Remove the aft elevator control quadrant to elevator control horn pushrod from the airplane and remove the rod ends from both ends of the pushrod. (b) Visually inspect the pushrod and rod ends to ensure they are not bent, corroded, cracked, or damaged, and that the rod end bearings are free to rotate. (c) Thoroughly clean the rod ends and inspectfor cracks using a high sensitivity fluorescent dye penetrant. (d) Prior to further flight, using serviceable parts, replace any pushrods, rod ends or bearings which are bent, corroded, cracked or seized. Retain all defective parts for possible future examination by the FAA for 60 days after the date of the inspection. If the FAA has not requested this part before that time, properly dispose of the defective parts. (e) Within one week following the inspections specified in paragraphs (b) and (c) of this AD, submit a written report of the result of the inspections to include whether or not damage was found, part number(s) involved, extent, location, and description of any damage found. Submit the report to the FAA, Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581; Telephone (516) 791-6220; Facsimile (516) 791-9024. If the inspections were made previous to this AD, forward the requested data within one week of receiptof this AD. (Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and have been assigned OMB Control Number 2120-0056.) (f) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (g) An equivalent means of compliance or an adjustment of the compliance time of this AD may be approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581; Telephone (516) 791-6220; Facsimile (516) 791-9024. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. This amendment (39-6752, AD 90-11-01) becomes effective on November 16, 1990, to all persons except those to whom it has already been made effective by priorityletter from the FAA dated May 21, 1990.
2022-25-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report that a Model A319 airplane lost the right-hand front windshield in flight. Due to the design similarity, this condition can also exist or develop on Model A300, A300-600, and A310 series airplanes. This AD requires repetitive inspections and electrical test measurements (ETMs) of the affected parts, and applicable corrective actions, and prohibits the installation of affected parts under certain conditions, 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.
2016-14-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440), Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600- 2D15 (Regional Jet Series 705), Model CL-600-2D24 (Regional Jet Series 900), and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of undesirable changes in the Reference Airspeed (RAS) Bug, occurring during flight without pilot input. This AD requires replacing the flight control computer (FCC). We are issuing this AD to prevent uncommanded pitch changes, which could result in deviation from a safe flight path.
2001-10-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual to prohibit in-flight auxiliary power unit (APU) starts, and installing a placard on or near the APU start/stop switch panel to provide such instructions to the flight crew. This action is necessary to prevent flame backflow into the APU compartment through the eductor during in-flight APU starts, which could result in fire in the APU compartment. This action is intended to address the identified unsafe condition.
2001-09-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires a one-time inspection to detect cracking of the main landing gear (MLG) pistons, and repair or replacement of the pistons with new or serviceable parts, if necessary. This amendment requires, among other actions, repetitive dye penetrant and magnetic particle inspections to detect cracks of the MLG pistons; repair and replacement of discrepant parts; and installation of a preventative modification; as applicable. This amendment also provides for an optional terminating action for certain MLG pistons. This amendment is prompted by additional reports of failure of the MLG pistons during towing of the airplanes. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure of the pistons and subsequent damage to the airplane structure or injury to airplane occupants.
2016-14-09: We are superseding Airworthiness Directive (AD) 2014-14-06 for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, - 113, -114, and -115 airplanes; Model A320-111, -211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. AD 2014-14-06 required inspecting the aft engine mount retainers for surface finish, cracks, and failure, and replacement if necessary. This new AD requires repetitive inspections for damaged, cracked, broken, and missing aft engine mount retainers, and replacement if necessary. This AD was prompted by inspection results that have shown that the main cause of crack initiation in the aft engine mount retainers is the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. We are issuing this AD to detect and correct failure of retainer brackets of the aft engine mount and consequent loss of the locking feature of the nuts of the inner and outer pins; loss of thepins will result in the aft mount engine link no longer being secured to the aft engine mount.
2010-22-03: 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: Analysis performed in the frame of the Extended Service Goal has led Airbus to modify the inspection programme [modification of thresholds, intervals and associated configurations] which is currently required by DGAC (Direction G n rale de l'Aviation Civile) France AD F-2005-001. This modified inspection programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located in the centre wing box. This condition, if not corrected, could affect the structural integrity of the centre wing box. * * * * * The unsafe condition is reduced structural integrityof the wings. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-16-12: This amendment supersedes three existing airworthiness directives (AD); applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. One AD currently requires modification of the nacelle strut and wing structure for certain Boeing Model 767-200, -- 300, and --300F series airplanes powered by Pratt & Whitney engines. The second AD currently requires a similar modification for certain Boeing Model 767-200, -300, and -300F series airplanes powered by General Electric engines. The third AD currently requires repetitive inspections for cracking of the outboard pitch load fittings of the wing front spar, and corrective action if necessary, for certain Boeing Model 767-200 series airplanes. The third AD also provides a terminating action for the repetitive inspections, which is optional for uncracked pitch load fittings. This amendment requires, for airplanes subject to the first and second existing ADs on which certain modifications have been accomplished previously, reworking the aft pitch load fitting, and installing a new diagonal brace fuse pin. This amendment also requires, for airplanes subject to the third existing AD, replacing the outboard pitch load fitting of the wing front spar with a new, improved fitting, which terminates certain currently required repetitive inspections. The actions specified by this amendment are intended to prevent fatigue cracking in primary strut structure, which could result in separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition. \n\nDATES: Effective September 21, 2004. \n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 21, 2004. \n\n\tThe incorporation by reference of Boeing Service Bulletin 767- 57A0070, Revision 1, dated November 16, 2000, was approved previously by the Director of the Federal Register as of May 14, 2001 (66 FR 21069, April 27, 2001). \n\n\tThe incorporation by reference of Boeing Service Bulletin 767-54- 0081, dated July 29, 1999, was approved previously by the Director of the Federal Register as of May 7, 2001 (66 FR 17492, April 2, 2001). \n\n\tThe incorporation by reference of certain publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 5, 2001 (66 FR 8085, January 29, 2001). \n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 17, 2000 (65 FR 58641, October 2, 2000). \n\n\tThe incorporation by reference of Boeing Service Bulletin 767-57- 0053, Revision 2, dated September 23, 1999, was approved previously by the Director of the Federal Register as of July 24, 2000 (65 FR 37843, June 19, 2000).