Results
96-21-10: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
96-21-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that requires either replacement or modification of the hydraulic damper assembly. This amendment is prompted by reports indicating that insufficient damping of the hydraulic shimmy damper in the main landing gear (MLG) can allow high torsional vibration to occur. The actions specified by this AD are intended to prevent such vibration, which can damage the MLG assembly and lead to its collapse.
93-04-02: 93-04-02 ROCKWELL INTERNATIONAL/COLLINS AVIATION DIVISION: Amendment 39-8504. Docket No. 93-CE-18-AD. Applicability: TDR-94D Mode S transponders, P/N CPN 622-9210-002, installed on, but not limited to the following, certificated in any category: Aerospatiale ATR-42 and ATR-72 series airplanes Saab 340A and 340B airplanes Short Model SD3-60 airplanes de Havilland DHC-7 and DHC-8 series airplanes British Aerospace ATP airplanes Gulfstream G-II, G-III, and G-IV series airplanes Dassault Mystere-Falcon 50, Mystere-Falcon 200, and Mystere-Falcon 900 airplanes Canadair Challenger CL-601 airplanes British Aerospace HS 125-700A airplanes Beechcraft 300 series airplanes Compliance: Required as indicated, unless already accomplished. To prevent a mid-air collision or a near-miss situation caused by failure of these Mode S transponders, accomplish the following: (a) Within the next 10 calendar days after theeffective date of this AD, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot's clear view on the instrument panel: "OPERATION OF TCAS II IN ANY MODE OTHER THAN THE "TA ONLY" MODE IS PROHIBITED." (b) Within the next 6 calendar months after the effective date of this AD, modify the software of the Mode S transponders in accordance with the Accomplishment Instructions section of Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. The placard required by paragraph (a) of this AD is no longer required after this modification is incorporated. (c) If parts for the above modification are not available, the airplane operator may comply with the placard requirement of paragraph (a) of this AD until the modification is incorporated based upon a schedule established by the manufacturer through the Atlanta Aircraft Certification Office. (d) Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The modification required by this AD shall be done in accordance with Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 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 Rockwell International/Collins General Aviation Division, 1100 West Hibiscus Boulevard, Melbourne, Florida 32901. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC. (g) This amendment becomes effective on March 26, 1993.
2021-07-03: The FAA is superseding Airworthiness Directive (AD) 2015-05- 03, which applied to certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015-05-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). This AD continues to require the actions specified in AD 2015-05-03. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and incorporating additional structural repairs and modifications to preclude WFD. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary, as well as the corresponding structural repairs and modifications to preclude WFD. The FAA is issuing this AD to addressthe unsafe condition on these products.
2005-18-01: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 turbine aft cooling plate, part number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 installed. This AD requires a onetime eddy current inspection (ECI) of certain P/N stage 2 turbine aft cooling plate boltholes. This AD results from reports of six stage 2 turbine aft cooling plates found cracked during inspection. We are issuing this AD to prevent stage 2 aft cooling plate separation, resulting in uncontained engine failure and damage to the airplane.
78-17-04: 78-17-04 GENERAL DYNAMICS: Amendment 39-3283. Applies to all Model 340 and 440 series and C-131E airplanes in passenger configuration, including those modified for turbopropeller power, certificated in all categories. To insure that the passenger emergency escape window release handle access door can be opened, accomplish the following: (a) Within the next 10 hours time in service from the effective date of this AD unless already modified in accordance with paragraph (c) or (d), check each passenger emergency escape window release handle cover assembly to assure that the release handle access door swings open without restriction. If the release handle access door cannot be opened, modify the cover assembly per General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978 prior to the next flight. (b) Repeat the checks specified in (1) on all unreworked cover assemblies prior to first flight of each day pending accomplishment of the rework defined in General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978. (c) Within 30 days or 50 hours time in service, whichever occurs earlier from the effective date of this AD, accomplish the rework defined in the General Dynamics Service Bulletin noted in paragraph (b) at which time checks required by this AD may be discontinued. (d) Alternate methods of insuring that the release handle access door can be opened may be used if approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (e) The checks specified in this AD may be performed by flight crew personnel. (f) Record the accomplishment of check in a record maintained by the operator. This amendment becomes effective September 5, 1978.
92-06-12: 92-06-12 BELL HELICOPTER TEXTRON, INC.: Amendment 39-8192. Docket No. 90-ASW-48. Applicability: All Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, certificated in any category, with the main transmission sungear, part number (P/N) 206-040-662-101, installed. Compliance: Required as indicated, unless already accomplished. To prevent premature wear of the sungear and mating spur gears which could result in transmission failure, accomplish the following: (a) At the next inspection interval for the main transmission sungear, P/N 206-040-662-101, but no later than 1,500 hours' time in service after the effective date of this AD, remove and replace sungears which have the following serial numbers: SD-0005 SD-0010 SD-0020 SD-0022 SD-0023 SD-0024 SD-0025 SD-0026 SD-0027 SD-0031 SD-0033 SD-0034 SD-0035 SD-0036 SD-0037 SD-0039 SD-0040 SD-0043 SD-0044 SD-0046 SD-0054 SD-0055 SD-0057 SD-0060 SD-0062 SD-0065 SD-0066 SD-0067 SD-0068 SD-0069 SD-0071 (b) In conjunction with (a), inspect the pinion spur gears which mate with the above listed sungears for micro pitting or hardlines in the gear teeth due to the insufficient tip relief, or improper tooth profile of the sungear. Determine if wear or damage is within specified limits according to the applicable BHTI maintenance, repair and overhaul manuals. (c) If wear or damage exceeds the specified limits, remove and replace the affected spur gears with serviceable parts before further flight. (d) An alternative method of compliance or adjustment of the compliance times which provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, Aircraft Certification Service, FAA, Fort Worth, Texas, 76193-0170. (e) Bell Helicopter Textron, Inc., Alert Service Bulletins No. 206-90-56, Rev. A, dated 1/15/91 or 206L-90-69, Rev. A, dated 1/15/91, as applicable, provide an acceptable, alternate means of compliance with this AD. (f) This amendment becomes effective on April 13, 1992.
96-20-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive operational tests to verify proper deployment of the ram air turbine (RAT), and replacement of the rotary actuator motor with a new or serviceable rotary actuator motor, if necessary. This amendment is prompted by reports of corroded rotary actuator motors of the RAT found on in-service airplanes. The actions specified by this AD are intended to ensure that the RAT actuator motor is not corroded to the point where it may result in the failure of the RAT to deploy and subsequently result in loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
2021-07-04: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by in-service data, which revealed that the minimum operating airspeeds in severe icing conditions, computed to provide adequate stall margins, do not provide sufficient margins to stall speeds at high bank angle while exiting severe icing conditions. This AD requires revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to provide emergency procedures and limitations for operating in severe icing 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.
92-24-04: 92-24-04 BOEING: Amendment 39-8409. Docket No. 92-NM-103-AD. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes; as listed in Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent uncommanded deployment of the thrust reverser, accomplish the following: \n\t(a)\tWithin 12 months after the effective date of this AD, modify the engine thrust reverser control system, in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Seattle ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\t(e)\tThis amendment becomes effective on December 14, 1992.