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99-23-22: This amendment adopts a new airworthiness directive (AD) that is applicable to various transport category airplanes equipped with certain Mode "C" transponder(s) with single Gillham code altitude input. This action requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. This amendment is prompted by reports that, during level flight, the Traffic Alert Collision Avoidance System (TCAS II) issued false advisories that directed the flightcrew to change course and either climb or descend. The actions specified in this AD are intended to prevent such false advisories due to inaccurate airplane altitude reporting, which could result in the flightcrew deviating the airplane from its assigned flight path and a possible mid-air collision.
87-02-01: 87-02-01 SCHWEIZER AIRCRAFT CORP.: Amendment 39-5512. Applies to all Schweizer gliders (including kit built), all serial numbers certificated in any category, and all models listed below: SGU 1-7 SGS 2-8 (TG-2) SGS 2-12 (TG-3) SGU 1-19 SGU 1-20 SGU 1-21 SGU 2-22, 2-22A, 2-22C, 2-22CK, 2-22E, 2-22EK SGS 1-23, 1-23B, 1-23C, 1-23D, 1-23E, 1-23F, 1-23G, 1-23H, 1-23H15 SGS 1-24 SGS 1-26, 1-26A, 1-26B, 1-26C, 1-26D, 1-26E SGS 2-32 SGS 2-33, 2-33A, 2-33AK SGS 1-34, 1-34R SGS 1-35C SGS 1-36 (Sprite) Compliance is required as indicated unless already accomplished. To prevent the possibility of the tow-hook inadvertently slipping out of the release-arm and releasing the tow-line, which could result in a forced landing, accomplish the following: (a) Within the next 5 tow release actuations after the effective date of this AD, perform the following: (1) Inspect the tow-release installation for proper part numbers, excessive wear, and possible rework or replacement of parts in accordance with Part 3A, 3B, and 3C in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. (2) Perform the operational check in accordance with Figure 4 in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. (b) Thereafter, at intervals not to exceed 100 hours time-in-service, accomplish the steps in Part 3B, and 3C, and Figure 4 in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, Telephone (516) 791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Schweizer Service Bulletin No. SA-001, dated October 3, 1986, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not received this document from the manufacturer may obtain copies upon request to Schweizer Aircraft Corp, P.O. Box 147, Elmira, New York 14902, Telephone (607) 739-3821. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 86-ANE-46, Room 311, between the hours of 8:00 a.m. and 4:30 p.m. Monday through Friday, except Federal holidays. This amendment becomes effective on January 21, 1987.
89-07-12: 89-07-12 SIKORSKY AIRCRAFT: Amendment 39-6171. Applicability: Model S-76 series helicopters, certificated in any category, that are equipped with tail rotor horn, P/N 76101-05006. Compliance: Required as indicated, unless already accomplished. To prevent possible fatigue failure of the tail rotor component, which could result in a reduction of directional control and hazardous tail rotor vibration in the helicopter, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD or before the accumulation of 12,000 hours time in service, whichever occurs later, replace the tail rotor horn, P/N 76101-05006, with a serviceable tail rotor horn that has not exceeded 12,000 hours' time in service. Thereafter, replace the tail rotor horn P/N 76101-05006, with a serviceable tail rotor horn before the accumulation of 12,000 hours' time in service. (b) Operators who have not kept records of hours' time in service on individual tail rotor horn component parts must substitute the hours' time in service of the tail rotor blade bonded assembly, P/N 76101-05020 or P/N 76088-20077. (c) For purposes of complying with this AD, the hours' time in service for the individual tail rotor horn and blade components that were not installed at the time of issuance of the initial rotorcraft airworthiness certificate must be determined from rotorcraft records. (d) Upon request, an alternate means of compliance which provides a level of safety equivalent to the requirements of this AD may be used when approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. (e) Upon submission of substantiating data by an owner or operator through an FAA Aviation Safety Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118, may adjust the compliance time specified in this AD. This amendment (39-6171, AD 89-07-12) becomes effective on April 27, 1989.
2018-22-07: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. This AD requires inspection of the stage 6 seal ring for correct installation and inspection of the high-pressure compressor (HPC) stages 2-5 spool for cracks. This AD also requires replacement of the HPC stages 2-5 spool if the stage 6 seal ring is incorrectly installed or if the HPC stages 2-5 spool is found cracked. This AD was prompted by a shop finding of axial cracks in the interstage 5-6 seal teeth of the HPC stages 2-5 spool spacer arm, due to an incorrectly installed stage 6 seal ring. We are issuing this AD to address the unsafe condition on these products.
98-20-17: This amendment adopts a new airworthiness directive (AD) that applies to certain SAFT America Inc. P/N 021929-000 (McDonnell Douglas P/N 43BO34LB02) and P/N 021904-000 (McDonnell Douglas P/N 43BO34LB03) nickel cadmium batteries that are installed on aircraft. This AD requires replacing all battery terminal screws, verifying that the battery contains design specification cells, and replacing the cells if the battery contains non-design specification cells. This AD is the result of an incident where the cell screws on one of the affected batteries were exposed to chloride, which caused the heads of some fasteners to shear off and eventually resulted in the battery exploding. The actions specified by this AD are intended to prevent such an occurrence, which could result in loss of emergency power to electrical flight components or other emergency power systems required in the event of loss of the aircraft primary power source.
98-20-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires inspections to detect corrosion on areas of the airplane structure where black film thermal insulation is used; repair, if necessary; and replacement of black insulation blankets with certain aluminized (silver) insulation. This amendment is prompted by reports of corrosion forming on areas of the airplane structure where the black film covers the thermal insulation blankets. The actions specified by this AD are intended to prevent degradation of the structural capability of the airplane fuselage and sudden loss of cabin pressure due to corrosion of the airplane fuselage structure.
66-09-02: 66-09-02 DOWTY ROTOL: Amdt. 39-215 Part 39 Federal Register March 23, 1966. Applies to Dowty Rotol Propellers, (c) R.193/4-30-4/50, installed on Fairchild F-27; (c) R.184/4- 30-4/50, installed on Grumman G-159; and (c) R.179/4-20-4/33, installed on Viscount 810. Compliance required within the next 200 hours' time in service after the effective date of this AD unless already accomplished. To prevent further improper operation of the propeller pitch lock under high oil temperature conditions, rework the existing Lock Support Sleeve, Dowty Rotol P/N RA.61236, in accordance with Dowty Rotol Service Bulletin No. 61-185 (Modification No. (c) VP.2032) or later ARB-approved revision. This directive effective April 22, 1966. Revised June 16, 1966.
83-10-03: 83-10-03 CESSNA: Amendment 39-4655. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Numbers \n172M\n17266940 thru 17267584\n172N\n17267585 thru 17274009\n172P\n17274010 thru 17275762, 17275764, 17275765, 17275769, 17275770, 17275788, 17275792, 17275793, 17275796, 17275798, 17275800 thru 17275803, 17275806, and 17275818\nR172K\nR1722000 thru R1723454\nF172\nF17201445 thru F17202194\nFR172\nFR17200591 thru FR17200675\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent possible jamming of the elevator control, accomplish the following: \n\n\ta)\tWithin the next 100 hours time-in-service, modify the right-hand control wheel yoke guide in accordance with the instructions in Cessna Single-Engine Customer Care Service Information Letter SE82-38, dated August 13, 1982, and SE82-38 Revision # 1 dated October 29, 1982. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished.c)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendment becomes effective on June 30, 1983.
2005-24-01: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders. This AD requires you to make pen and ink changes to the Limitations Section of the glider maintenance manual to eliminate contradictory information concerning the structural life limit. This AD results from a review by FAA of the Limitations Section of the CENTRAIR Model 101AP glider maintenance manual that revealed conflicting information concerning the structural life limit. We are issuing this AD to assure that the published life limit is adhered to and to prevent structural failure of the glider once this life limit is reached.
2018-23-12: We are adopting a new airworthiness directive (AD) for Zodiac Aero Evacuation Systems (also known as Air Cruisers Company) fusible plugs installed on emergency evacuation equipment for various transport category airplanes. This AD was prompted by reports indicating that affected fusible plugs activated (vented gas) below the rated temperature. This AD requires an inspection of the fusible plugs to determine the part number and lot number, and replacement of all affected fusible plugs. We are issuing this AD to address the unsafe condition on these products.