Results
2024-08-02: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a report of an electrical contactor that failed with contacts in the intermediate position, causing the airplane to lose power to multiple electrical systems. This AD requires repetitive operational tests of the affected part, and, depending on findings, accomplishment of applicable corrective action, 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.
87-11-06: 87-11-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5607. Applies to Bell Helicopter Textron, Inc., Model 214ST helicopters, S/N's 28101 through 28159, and Models 214B and 214B-1, S/N's 28001 through 28070, certificated in any category, equipped with upper and lower locking plates, P/N's 214-010-231-101 and 214-010-232-101. Compliance is required as indicated, unless already accomplished. (a) To prevent failure of the collective hub locking plate, on the Model 214ST, 214B, and 214B-1 helicopters, replace the P/N 214-010-232-101 lower locking plate and the P/N 214-010-231-101 upper locking plate with locking plate P/N 214-010-569-101 in accordance with Part I of BHTI ASB 214-86-36, dated October 8, 1986, or ASB 214ST-86-37, Rev. A, dated November 3, 1986, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (b) Within the next 25 hours' time in service after completing the requirements of paragraph(a) and thereafter at intervals not to exceed 25 hours' time in service from the last inspection, visually inspect the hub and lower hub nut assembly for slippage in accordance with Part II of BHTI ASB 214-86-36, dated October 8, 1986, or ASB 2145T-86-37, Rev. A, dated November 3, 1986. (c) Within the next 500 hours' time in service after completing the requirements of paragraph (a) and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, perform the following in accordance with Part III of BHTI ASB 214-86-36, dated October 8, 1986, or ASB 214ST-86-37, Rev. A, dated November 3, 1986: (1) Inspect the hub locking plate, P/N 214-010-569-101, for cracks. (2) If a crack is found during this inspection, replace the hub locking plate with a serviceable part. (3) Retorque the lower hub nut and install locking plate, P/N 21 4-010-569- 101, as detailed in paragraph (a). (d) Installation instructions for the scissors and sleeve may be found in the BHTI- 214ST Maintenance Manual, Chapter 62-21-00, and 214B Maintenance Manual, Chapter 65-20- 00. (e) Upon compliance with this airworthiness directive, the inspections and actions required by priority letter Airworthiness Directive No. 86-12-01, issued June 6, 1986, may be discontinued. (f) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. The procedure shall be done in accordance with BHT1 ASB 214-86-36, dated October 8, 1986,or ASB 214ST-86-37, Rev. A., dated November 3, 1986. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1). Copies may be obtained upon request to Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, Attention: Customer Support. Copies maybe inspected at the Office of Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment becomes effective May 26, 1987.
85-14-08: 85-14-08 BRITISH AEROSPACE VISCOUNT: Amendment 39-5095. Applies to Model 700 and 800 series airplanes, certificated in any category. To prevent failure of Alternators Part Number N0505 or 0505/1 which are or have been installed at the Number 2 position on Model 800 Series airplanes accomplish the following, unless already accomplished: A. Replace with a serviceable unit or overhaul in accordance with the Lucas overhaul manual reference 24-20-02 prior to the accumulation of 1250 flying hours or within the next 150 flying hours, whichever occurs later, and thereafter at intervals not to exceed 1250 flying hours. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, Aircraft Certification Division, FAA, Northwest Mountain Region. C. 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. This amendment becomes effective August 16, 1985.
87-07-06: 87-07-06 BOEING: Amendment 39-5588. Applies to all Model 747 and 757 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo ensure proper passenger door operation during emergency evacuation, accomplish the following: \n\n\tA.\tWithin 60 days after the effective date of this AD, in order to find defective passenger door emergency power reservoirs, inspect the serial numbers of those reservoirs installed on airplanes in accordance with Boeing Service Bulletin 747-52A2201 (for Model 747 airplanes) or 757-52A0022 (for Model 757 airplanes), both dated September 15, 1986, or later FAA-approved revisions or check the applicable airplane records for those passenger door emergency power reservoir serial numbers listed in H. R. Textron Service Bulletin 803300-52-05 dated September 15, 1986, or later FAA-approved revisions. \n\n\t\t1.\tIf the serial number is not one listed in H. R. Textron Service Bulletin referenced above, no further action is necessary. \n\n\t\t2.\tFor any reservoir on which the serial number matches one listed in the H. R. Textron Service Bulletin referenced above, determine if the reservoir is fully charged. If any discharged emergency power reservoir is found, replace or modify before further flight in accordance with the applicable Boeing Service Bulletin referenced above. \n\n\tNOTE: These units may have been installed on Boeing Models 747 and 757 series airplanes other than those listed in the Boeing Service Bulletins referenced above. \n\n\t\t3.\tFor each emergency power reservoir installed on an airplane with a serial number listed in H. R. Textron Service Bulletin 803300-52-05, dated September 15, 1986, determine on a daily basis that the reservoir is fully charged. This daily procedure may be discontinued once the reservoir is modified in accordance with the applicable Boeing Service Bulletin referenced above. If any discharged emergency power reservoir is found, replace or modify before further flight in accordance with the applicable Boeing Service Bulletin referenced above. \n\n\tB.\tWithin 15 months after the effective date of this AD, modify all emergency power reservoirs listed in H. R. Textron Service Bulletin 803300-52-05, dated September 15, 1986, in accordance with the applicable Boeing Service Bulletin referenced above. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective May 1, 1987.
2024-06-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports from the supplier that some overheat detection sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires maintenance records verification, and if an affected part is installed, prohibits the use of certain Master Minimum Equipment List (MMEL) items under certain conditions by requiring revising the operator's existing Minimum Equipment List (MEL). This AD also requires testing the overheat detection sensing elements, marking each serviceable sensing element with a witness mark, and replacing each nonserviceable part with a serviceable part. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2005-08-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, and -800 series airplanes. This AD requires doing a general visual inspection for sealant at the interface of the upper spar fittings, strut side skins, and the fittings of the thrust reverser strut fairing on the engine struts; and applying an injection seal or silicone sponge rubber with fillet seal if necessary. This AD is prompted by a report that an injection seal in the engine strut area may not have been properly completed or installed during production. We are issuing this AD to prevent flammable fluid (such as fuel or hydraulic fluid) from leaking onto a hot engine exhaust nozzle or into the engine core fire zone, and consequently causing an uncontrolled fire or explosion.
2024-07-07: The FAA is superseding Airworthiness Directive (AD) 2010-18- 06, which applied to all GA8 Airvan (Pty) Ltd Model GA8 and GA8-TC320 airplanes. AD 2010-18-06 required inspections and a minor design change to the forward slide of the cargo door with corrective action as necessary. Since the FAA issued AD 2010-18-06, the Civil Aviation Safety Authority (CASA), which is the aviation authority for Australia, superseded the previous CASA Australia AD to incorporate more detailed inspections and additional modifications as specified in updated service information published by the manufacturer. This AD was prompted by reports of in-flight cargo door separation. This AD requires inspections and rework (modifications) of the cargo door with corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2024-06-13: The FAA is superseding Airworthiness Directive (AD) 2022-21-15 for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. AD 2022-21-15 required replacing the rudder T-yoke axle with an improved rudder T-yoke axle. Since the FAA issued AD 2022-21-15, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD requires, for certain airplanes, inspecting the rudder steering bracket edge distance and depending on the inspection results, inspecting the T-yoke bolt hole for wear and play, and corrective action if necessary. For certain airplanes this AD requires replacing the rudder T-yoke bolt (axle) with a serviceable part, installing a new self-locking nut, and applying torque seal marks on the rudder T-yoke bolt head and self-locking nut. For all airplanes this AD requires repetitively inspecting the torque seal marks on the rudder T-yoke bolt head for proper alignment and the self-locking nut for proper installation and corrective action if necessary. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2005-08-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 series airplanes. This AD requires repetitive detailed inspections for cracks in the crease beam and adjacent structure of the fuselage, and related investigative and corrective actions if necessary. This AD is prompted by fatigue cracks found in the crease beam during a follow-on inspection of a previously installed modification. We are issuing this AD to find and fix fatigue cracking of the fuselage frame, which could result in reduced structural integrity of the frame and consequent rapid decompression of the airplane.