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90-23-13: 90-23-13 FOKKER: Amendment 39-6803. Docket No. 90-NM-219-AD. Applicability: Model F-28 Mark 0100 series airplanes, Serial Numbers 11244 through 11286, 11289, 11291 through 11293, 11295, 11297, 11300, 11303, 11306, 11308, 11310, 11312, and 11314, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of flight path control during automatic flight, accomplish the following: A. Within 5 days after the effective date of this AD, incorporate the following changes into the Limitation Section of the FAA approved Airplane Flight Manual. This may be accomplished by inserting a copy of this AD in the AFM. 1. Section 2.01.01 - Delete the following statements if incorporated in the "Kinds of Operation" paragraph in this section. - CAT II approach. Compliance with FAA AC 120-29 has been demonstrated. - CAT IIIA approach. Compliance with FAA AC 120-28C has been demonstrated. - Autoland. Compliance with FAA AC 20-57A has been demonstrated. 2. Section 2.08.01 - a. Delete the following paragraphs: - Autopilot. - CAT II Approach (AP Coupled Only). - ILS Approach. b. If a "GA MODE" paragraph is incorporated, delete the following text: "During approach, after land 2/3 is annunciated until 500 feet above ground level (AGL), certain autopilot (AP) monitors are not available. It is the pilot's responsibility to monitor the AP performance during this phase. In case of a go-around (GA) during this phase, the AP shall be disconnected before triggering the TOGA lever." c. If an "Aircraft Equipment" paragraph is incorporated, this paragraph must be deleted. d. The following limitations must be added to Section 2.08.01: "AUTOPILOT - The autopilot must not be used in the take-off mode. The autopilot must not be used below 1,500 feet AGL." B. Within 5 days after the effective date of this AD fabricate a placard which states:"The autopilot must not be used in the take-off mode. The autopilot must not be used below 1,500 feet AGL." Install this placard in full view of the pilot in the cockpit. C. Within 14 days after the effective date of this AD, perform an inspection of the autopilot primary servomotors in accordance with Fokker Service Bulletin F100-22-021, dated August 22, 1990. If the jumper wires are missing, prior to further flight, replace the affected servomotor with a modified unit, in accordance with the Fokker service bulletin. NOTE: The Fokker service bulletin references Collins Alert Service Bulletin SVO-1000-22-A05, Revision 1, dated August 22, 1990, for additional instructions. D. Following the inspection required by paragraph C. of this AD, and modification, if necessary, the changes to the flight manual and the placard required by paragraphs A. and B. of this AD may be removed. E. 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6803, AD 90-23-13) becomes effective on November 26, 1990.
2016-16-03: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes. This AD results from 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 cracked elevator torque tubes. We are issuing this AD to require actions to address the unsafe condition on these products.
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.