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2020-09-16: The FAA is superseding Airworthiness Directive (AD) 2000-17- 09, AD 2008-04-19 R1, and AD 2015-26-09; and terminating all requirements of AD 2018-18-05; which applied to ATR-GIE Avions de Transport Regional Model ATR42-200, -300, and -320 airplanes. AD 2018-18-05 required updating the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations, and terminated the relevant requirements of AD 2000-17-09, AD 2008-04-19 R1, and AD 2015-26-09. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
93-07-01: 93-07-01 FOKKER: Amendment 39-8533. Docket 92-NM-42-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11339, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaudible communications between the forward and aft passenger compartments, which could potentially hamper emergency evacuation procedures, accomplish the following: (a) Within 12 months after the effective date of this AD, modify the passenger address system in accordance with Fokker Service Bulletin SBF100-23-017, Revision 1, dated April 3, 1992. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments andthen send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The modification shall be done in accordance with Fokker Service Bulletin SBF100-23- 017, Revision 1, dated April 3, 1992. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on May 10, 1993.
2020-10-02: The FAA is superseding Airworthiness Directive (AD) 2011-12-07 for Eurocopter France (now Airbus Helicopters) Model SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. AD 2011-12-07 required repetitively inspecting the adhesive bead between the bushings and the Starflex star (Starflex) arms and the Starflex arm ends. This new AD retains the requirements of AD 2011-12-07 while omitting helicopters with an improved Starflex installed from the applicability. This AD was prompted by the development of the improved Starflex by Airbus Helicopters. The actions of this AD are intended to address an unsafe condition on these products.
82-04-08: 82-04-08 PIPER AIRCRAFT CORPORATION: Amendment 39-4323. Applies to Piper Model PA-34-220T (Serial Numbers 34-8133001 through 34-8233020) airplanes certificated in any category. Compliance: Required as indicated unless already accomplished. To prevent a potentially hazardous condition during landing and ground operation due to the inadvertent retraction of the landing gear, accomplish the following: A) Within the next 50 hours time-in-service after the effective date of this AD, inspect and modify the landing gear selector and squat switches in accordance with the Instructions Section contained in Piper Service Bulletin No. 732, dated November 11, 1981. B) Any equivalent method of compliance may be approved by the Chief, Atlanta Aircraft Certification Office, FAA, Southern Region, Room 275, 3400 Norman Berry Drive, East Point, Georgia 30344. This amendment becomes effective February 25, 1982.
2000-14-51: 2000-14-51 AIR TRACTOR INCORPORATED: Amendment 39-11837; Docket No. 2000-CE-40-AD. (a) What airplanes are affected by this AD? This AD applies to the following Air Tractor airplane models and serial numbers: Model Serial Numbers AT-501 501-002 through 501-0060 that have been converted to turboprop power. AT-502 502-003 through 502-0061, except those that have been upgraded to the 8,000-pound gross weight configuration through the incorporation of Snow Engineering Co. Service Letter #80J. AT-502A All serial numbers. (b) Who must comply with this AD? Anyone who wishes to operate any of the above airplanes on the U.S. Register must comply with this AD. (c) What problem does this AD address? This AD is intended to detect and correct fatigue cracks in the wing lower spar cap, which could result in an in-flight separation of the wing from the airplane. (d) What actions must I accomplish to address this problem? To address this problem, you mustaccomplish the following: Action When Procedures (1) Initial Inspection: Visually inspect the wing lower spar cap at the wing center splice connection for cracks. At whichever of the following that is applicable: (i) For the Models AT-501 and AT-502 airplanes: Upon accumulating 4,000 hours time-in-service (TIS) on each wing or within the next 10 hours TIS after the effective date of this AD, whichever occurs later; or (ii) For the Model AT-502A airplanes: Upon accumulating 3,000 hours TIS on each wing or within the next 10 hours TIS after the effective date of this AD, whichever occurs later. Accomplish this inspection in accordance with the INSPECTION REQUIREMENTS section of Snow Engineering Co. Service Letter #197, dated June 13, 2000. Action When Procedures (2) Repetitive Inspections: Inspect using visual or ultrasonic methods the wing lower spar cap at the center splice connection for cracks. For all affected airplanes, accomplish the repetitive inspections as follows: (i) Visually: Within 50 hours TIS after the initial inspection and thereafter at intervals not to exceed 50 hours TIS; or (ii) Using ultrasonic methods: Within 400 hours TIS after the initial inspection and thereafter at intervals not to exceed 400 hours TIS. Accomplish these inspections in accordance with the INSPECTION REQUIREMENTS section of Snow Engineering Co. Service Letter #197, dated June 13, 2000. (3) Replace or modify any cracked wing lower spar cap, as specified in the service information. Prior to further flight after the inspection where the crack is found. Accomplish the replacement and modification as follows: (i) Replacement: Remove the wing with the cracked lower spar cap and return to Air Tractor for spar cap replacement. Immediately notify Air Tractor that you are sending the wing if the cracked spar cap can not be modified. (ii) Modification: In accordance with the TERMINATING ACTION section of Snow Engineering Co. Service Letter #197, dated June 13, 2000. (4) Modifying each lower spar cap is considered terminating action for the repetitive inspection requirement. This modification can only be accomplished if the lower spar caps are inspected before the modification is incorporated and: (i) no cracks are found; or (ii) any crack found can be removed by drilling the hole to the next larger size. This terminating action may be accomplished at any time provided the lower spar caps are not cracked. Accomplish in accordance with the TERMINATING ACTION section of Snow Engineering Co. Service Letter #197, dated June 13, 2000. (e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Your alternative method of compliance provides an equivalent level of safety; and (2) The Manager, Fort Worth Airplane Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector. The inspector may add comments before sending it to the Manager, Fort Worth ACO. Note: This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific actions you propose to address it. (f) Where can I get information about any already-approved alternative methods of compliance? Contact Rob Romero, Aerospace Engineer, FAA, Fort Worth ACO, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; telephone: (817) 222-5102; facsimile: (817) 222-5960. (g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD provided you comply with the following: (1) The hopper is empty; (2) Vne is reduced to 138 miles per hour (mph) (120 knots) indicated airspeed (IAS); and (3) Flight into known turbulence is prohibited. (h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Snow Engineering Co. Service Letter #197, dated June 13, 2000. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies of this document from Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374. You may look at copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (i) When does this AD become effective? This AD becomes effective August 4, 2000, to all affected persons who did not receive emergency AD 2000-14-51, issued July 3, 2000. Emergency AD 2000-14-51 contained the requirements of this amendment and became effective immediately upon receipt.
2020-08-11: The FAA is adopting a new airworthiness directive (AD) for all Yabora Industria Aeronautica S.A. Model ERJ 190- 300 and ERJ 190-400 airplanes. This AD was prompted by a failure propagation test, which revealed that when complete loss of the electrical digital current (DC) essential bus 2 was induced, the smoke detection system of the forward and aft electrical bays erroneously indicated the presence of smoke via the respective engine indication and crew alerting system (EICAS) messages. This AD requires revising the existing airplane flight manual (AFM) procedures associated with messages of smoke in the electronic bays presented on the EICAS, as specified in an Ag(ecirc)ncia Nacional de Avia(ccedil)(atilde)o Civil (ANAC) Brazilian AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
82-02-01: 82-02-01 PIPER: Amendment 39-4298. Applies to Model PA-38-112, Serial Nos. 38-78A0001 thru 38-81A0051 and 38-81A0105 certificated in all categories except aircraft incorporating Aileron Balance Weight Rib Reinforcement Kit, Piper Part No. 764140. To prevent possible hazards in flight associated with cracks in the Aileron Balance Weight Rib P/N's 77342-16 and -17 accomplish the following within the next 100 hours in service unless already accomplished, and thereafter at intervals not to exceed 100 hours in service from the last inspection. a. Remove the aircraft wing tips and aileron balance weights. b. Using a minimum 10 power magnifier, inspect the aileron balance weight rib flange area for cracks. c. If no cracks are found, reinstall the balance weights and wing tips. d. If cracks are found, replace the cracked ribs with undamaged ribs of the same part numbers and incorporate Aileron Balance Weight Rib Reinforcement Kit Piper Part No. 764140. e. Upon the incorporation of Aileron Balance Weight Rib Reinforcement Kit, Piper Part No. 764140, the repetitive inspection required by this AD may be discontinued. f. Alternate inspections, repairs or alterations which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. g. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. (Piper Service Bulletin No. 723 dated August 19, 1981, refers to this subject.) This amendment is effective January 11, 1982.
81-07-10 R1: This amendment amends an existing Airworthiness Directive (AD) applicable to Hughes Helicopters Model 369 series helicopters equipped with any cargo hook by clarifying cargo hook operating time recordation. This amendment is needed to relieve an undue burden on operations.
76-09-02: 76-09-02 BEECH: Amendment 39-2592. Applies to Models 200 and Military A100-1 (Serial Numbers BB-3 thru BB-19, BB-21 thru BB-38, BB-40, BB-41, BB-43 thru BB-75 and BB-78) and Model C-12A (Serial Numbers BC-1, BC-2, BC-3, BD-2 and BD-3) airplanes. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo detect inadequate edge distance on the bolt holes in the wing center section lower forward spar cap for attachment of the outer wing panel lower forward spar cap, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: \n\n\tA)\tInspect for proper fit between the wings and center section at the lower forward spar attachment as follows: \n\n\t\t1.\tUsing a vernier caliper or a suitable depth gage, graduated in increments of .01-inch, measure the protrusion of the wing spar cap below the center section spar cap at the lower forward wing spar cap below the center section spar cap at the lower forward wing attachment on both the LH and RH sides. \n\n\t\t2.\tIf the protrusion does not exceed .10-inch, no further action is necessary. \n\n\t\t3.\tIf the protrusion exceeds .10-inch, remove the wing and measure the edge distance of the wing attachment hole in the center section lower spar in accordance with Figure 1. Provide this information to the manufacturer and thereafter operate or modify the airplane in accordance with FAA-approved limitations or instructions provided by the manufacturer. \n\n\tB)\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tNOTE: The manufacturer's address is Beech Aircraft Corporation, Commercial Service Operations, Wichita, Kansas 67201. \n\n\tBeechcraft Service Instruction No. 0775-062 or later approved revisions cover the subject matter of this AD. \n\n\tThis amendment becomes effective May 3, 1976. \n\nFIGURE 1 \nAD 76-09-02
93-17-13: 93-17-13 SCHWEIZER AIRCRAFT CORPORATION and HUGHES HELICOPTERS, INC.: Amendment 39-8684. Docket Number 93-SW-11-AD. Applicability: Model 269A, 269A-1, 269B, 269C, and TH55A helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the lower coupling drive shaft (shaft), loss of power to the rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 30 days or 100 hours' time-in-service after the effective date of this AD, whichever occurs first-- (1) Install engine and rotor tachometer markings in accordance with Part II of Schweizer Aircraft Corporation Service Bulletin B-257.1, dated May 21, 1993 (SB). NOTE: Figure B-257.1-2 indicates the position of the white slippage mark on the lens and lens frame. (2) Visually inspect the shaft for cracks, machining steps, manufacturing tool marks, surface defects, and lack of cleanup during the production grinding operation in accordance with Part I of the SB. NOTE: Failure to accomplish proper cleanup of the shaft surface is evidenced by a non-uniform surface smoothness. The actual surface finish value may vary from shaft to shaft. (b) Repeat the visual inspection for cracks as described in paragraph (a)(2) of this AD at intervals not to exceed 300 hours' time-in-service from the last inspection. (c) Replace any shaft found to be unairworthy during the inspection required by this AD with an airworthy shaft, before further flight. (d) An alternative method 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, 181 South Franklin Avenue, Valley Stream, New York 11581. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) The modification and inspections shall be done in accordance with Part I and II of Schweizer Aircraft Corporation Service Bulletin B-257.1, dated May 21, 1993. 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas 76106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 20, 1993.