Results
99-24-14: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1A2 series turbofan engines. This action requires removing from service stage 2 high pressure turbine (HPT) disks and impeller spacers prior to exceeding new, lower cyclic life limits and imposes a drawdown program for those parts that currently exceed, or will exceed, the new lower limits. This amendment is prompted by the results of a refined low cycle fatigue (LCF) analysis. The actions specified in this AD are intended to prevent LCF cracking and failure of stage 2 HPT disks and impeller spacers, which could result in an uncontained engine failure and damage to the aircraft.
91-16-03: 91-16-03 AIRBUS INDUSTRIE: Amendment 39-7093. Docket No. 91-NM-90-AD. Applicability: Model A300, A310, and A300-600 series airplanes equipped with escape slides, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent delayed passenger evacuation during an emergency, accomplish the following: A. Within 30 days after the effective date of this AD, or prior to the accumulation of 300 hours time-in-service after the effective date of this AD, whichever occurs first, perform a close visual inspection of the escape slide girt bars for correct installation, in accordance with paragraph 4 of Airbus Industrie All Operators Telex (AOT) 25-01, dated July 30, 1990. If the girt bars are incorrectly installed, prior to further flight, repair in accordance with the AOT. B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approvedby the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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. D. The inspection and repair requirements shall be done in accordance with Airbus Industrie All Operators Telex (AOT) 25-01, dated July 30, 1990. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W.,Room 8401, Washington, D.C. This amendment (39-7093, AD 91-16-03) becomes effective on September 11, 1991.
2014-09-11: We are adopting a new airworthiness directive (AD) for certain GROB-WERKE Models G115EG and G120A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks in the left hand elevator flange. We are issuing this AD to require actions to address the unsafe condition on these products.
99-19-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 1329-23 and 1329-25 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.
2014-09-12: We are adopting a new airworthiness directive (AD) for certain Alpha Aviation Concept Limited Model R2160 airplanes. This AD results from [[Page 26609]] mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the metal screen shield over the ignition switch may ground out the ignition terminals. We are issuing this AD to require actions to address the unsafe condition on these products.
99-19-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA 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.
88-07-08: 88-07-08 GENERAL ELECTRIC: Amendment 39-5869. Applies to General Electric (GE) CT7-5A, -5A1, and -5A2 turbopropeller engines as installed in Saab-Fairchild SF340A aircraft. Compliance is required as indicated, unless already accomplished. To prevent power turbine (PT) overspeed resulting in an uncontained failure or adverse aircraft yaw due to reaction of the fuel control to an erroneous PT speed signal during ground operation with the bottoming governor (BG) enabled, accomplish the following no later than May 16, 1988: (a) Remove propeller overspeed governor (OSG), Dowty Rotol (DR) Part Number (P/N) 661001001, and replace with OSG, DR P/N 661001002, in accordance with procedures contained in DR Service Bulletin (SB) SF340-61-11, dated October 8, 1986. (b) Install cable, GE P/N 6068T47P01, between the propeller OSG and the hydromechanical unit in accordance with GE CT7 Turboprop SB 74-09, dated October 10, 1986. (c) Install engine BG deactivation switches,Mod Kit Saab SF340-76-018-01, in the power lever quadrant in accordance with procedures contained in Saab SB SF340-76-018, dated October 24, 1986. (d) Upon accomplishment of paragraphs (a) through (c) above: (1) Remove from the SF340A Aircraft Flight Manual (AFM) the BG disabling procedures required by AD 86-10-51, paragraphs (a)(1) and (a)2. (2) Discontinue operating in accordance with the procedures listed in AD 86-10-51, paragraph (b). NOTE: Subsequent to compliance with this AD, aircraft operation shall be conducted in accordance with the latest AFM revision. (e) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. (f) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12New England Executive Park, Burlington, Massachusetts 01803. (g) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Dowty Rotol SB SF340-61-11, dated October 8, 1986; General Electric CT7 Turboprop SB 74-09, dated October 10, 1986; and Saab SB SF340-76-018, dated October 24, 1986, identified and described in this document are 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 already received these documents from the manufacturer, may obtain copies upon request to Dowty Rotol Limited, Cheltenham Road East, Gloucester, England GL2 9QH; General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910; and Saab-Scania AB, S-581 88, Linkoping, Sweden. This document may also 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-21, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment supersedes Amendment 39-5473 (51 FR 44439; December 9, 1986), AD 86-10-51. This amendment becomes effective on May 9, 1988.
86-20-04: 86-20-04 ARCTIC AIRCRAFT COMPANY: Amendment 39-5412. Applies to Arctic Model Interstate S-1B2 "Tern" (Serial Numbers 1001 through 1029) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service (TIS) or within 31 calendar days after the effective date of this AD, whichever comes first, unless already accomplished. To preclude the possibility of catastrophic flutter of the ailerons and/or the elevators during flight at high speeds, resulting in possible loss of the airplane, accomplish the following: (a) Re-mark the airspeed indicator by removing that portion of the yellow arc that presently extends from 142 miles per hour (123 knots) to 160 miles per hour (139 knots), and the red radial line presently located at 160 miles per hour (139 knots), and marking a red radial line located at 142 miles per hour (123 knots). (b) Replace the existing Airplane Flight Manual (AFM) with the FAA approved Airplane Flight Manual forthe Arctic Model Interstate S-1B2 airplane, Revision 7 dated April 15, 1986. If the airplane is currently operated as a seaplane, detach the FAA approved Seaplane Flight Manual Supplement from the existing Airplane Flight Manual and attach it to the new Manual. Also, detach any FAA approved Airplane Flight Manual Supplements, required with currently-installed major alterations, from the existing Airplane Flight Manual and attach them to the new Manual. (c) Check the airplane's instrument panel to determine if there is a placard reading "SEAPLANE MANEUVERING SPEED 105 MPH (CAS)" and "SEAPLANE MAXIMUM SPEED 142 MPH (CAS)". If so, remove the existing placard and replace it with the placard reading "SEAPLANE MANEUVERING SPEED 105 MPH (CAS)", supplied with Arctic Aircraft Company Service Bulletin No. 5. (d) Accomplish the actions required in paragraph (a) of this AD at a certificated repair station with a Class 1 instrument rating or an appropriate limited instrument rating. The checks and actions required in paragraphs (b) and (c) of this AD may be accomplished by the owner/operator. Make the entries in the airplane's maintenance records documenting the accomplishment of the inspections, checks, and actions required by this AD as prescribed by FAR 91.173. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Anchorage Aircraft Certification Office (ANM-100A); FAA; 701 C Street, Box 14; Anchorage, Alaska 99513. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Arctic Aircraft Company, Post Office Box 6-141, Anchorage, Alaska 99502; Telephone (907) 243-1580; or FAA, Office of the Regional Counsel; Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on October 12, 1986.
2014-09-06: We are adopting a new airworthiness directive (AD) for certain \n\n((Page 24549)) \n\nThe Boeing Company Model 777F series airplanes. This AD was prompted by a report of a fire that originated near the first officer's seat and caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the stowage box and supernumerary ceiling area. We are issuing this AD to prevent electrical current from passing through an internal, anti-collapse spring of the low-pressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn and lead to an oxygen-fed fire near the flight deck.
2006-04-06: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A319, A320, and A321 series airplanes. That AD currently requires repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or de-bonding of the protective half-shells; corrective actions, if necessary; and terminating action. This new AD removes the repetitive inspections to detect wear of the inboard flap trunnions and to detect wear or de- bonding of the protective half-shells; and corrective actions if necessary. This new AD adds repetitive detailed inspections of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane. DATES: This AD becomes effective March 24, 2006. The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-57-1133, excluding Appendix 01, dated July 28, 2005, as of March 24, 2006. On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000.