Results
2003-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 series airplanes, that requires installing new anti-swivel plates and weights on the engine fan cowl door latches and a new hold-open device. This action is necessary to prevent separation of the engine fan cowl door from the airplane in flight, which could result in damage to the airplane and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
2008-22-15: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Investigations after a CAS (crew alerting system) message "ENG 1 FIRE DETECT FAIL'' that occurred on an in-service aircraft revealed that the detector threshold tolerances could not permit to identify the failure of one single engine fire detector loop out of the two present on each engine. The fire detection system integrity is therefore not correctly monitored. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 11, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in thisAD as of December 11, 2008. The Director of the Federal Register approved the incorporation by reference of Dassault Service Bulletin F2000EX-137, Revision 1, dated December 7, 2006, listed in this AD as of February 2, 2007 (72 FR 2177, January 18, 2007).
2008-23-03: We are adopting a new airworthiness directive (AD) for the products listed above. 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: This Airworthiness Directive (AD) is prompted by a potential problem with the freedom of the brake pedals of some PC-6 series aircraft. The freedom of the brake pedals could be prevented because of an insufficient clearance between the rudder bar lugs on a few aircraft. In such conditions, it is possible that the master brake cylinder is not re-filled with the fluid from the reservoir, which can lead to a degradation of brake effectiveness. Mostly during landing, this can lead to difficulties with the directional control of the aircraft on ground and could cause a runway excursion. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-15-12: The FAA is superseding Airworthiness Directive (AD) 2018-08-02 for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. AD 2018-08-02 required initial and repetitive ultrasonic or visual inspections of the intermediate- pressure compressor (IPC) stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts, and removal of any cracked parts from service. This AD requires new inspections based on updated inspection thresholds and intervals for these IPC parts. This AD also adds an optional terminating action, amends the asymmetric power condition for engine inspection, and requires an inspection after a cabin depressurization event. This AD was prompted by IPC blade separations resulting in engine failures. Subsequently, the manufacturer identified the need to add new inspections and an optional terminating action, amend the asymmetric power condition for engine inspection, and require an inspection after a cabin depressurization event. The FAA is issuing this AD to address the unsafe condition on these products.
2007-19-18: We are adopting a new airworthiness directive (AD) for the products listed above. 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: The digital engine indicating system (DEI-NT) and associated control unit must get their latest software update. It has been found out in operation, that some combinations of system states while pressing switches can cause electrical damages to the system. A new software update is mandated to correct this deficiency and to incorporate additional safety functions to the system. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-08-05: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-45/-50 series turbofan engines, that requires installation of a fan stator case stiffening ring assembly, and a new stage one fan shroud. This amendment is prompted by a report of an uncontained stage one fan blade failure, which resulted in an inflight engine shutdown, and damage to the aircraft. The actions specified by this AD are intended to prevent an uncontained stage one fan blade failure, which can result in an inflight engine shutdown, and damage to the aircraft.
83-17-03: 83-17-03 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4709. Applies to all Model H.S. 748 series 2A airplanes certificated in all categories. To prevent wing structural failure accomplish the following, unless already accomplished: A. For airplanes with wing fuel tanks extending outboard beyond rib 350.366, within the next 1,500 hours or six months time in service, whichever occurs first after the effective date of this AD, inspect the rib/stringer bracket fasteners of the wing bottom surface at rib 224.366 and at stringers 4 and 6 at all ribs on each side of wing access panels W3 to W12 except W10, and perform the actions described in paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group H.S. 748 Service Bulletin 57/62 dated June 1980. B. Within the next 500 hours or 60 days time in service, whichever occurs first after the effective date of this AD, inspect the rib/stringer bracket fasteners of wing bottom surface rib 16.071 and stringers 9, 10, 11, and 12 and perform the actions described in paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group H.S. 748 Service Bulletin 57/63 dated June 1980. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 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 September 19, 1983.
84-09-05: 84-09-05 BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE: Amendment 39-4849. Applies to Model G102 ASTIR CS sailplanes, serial numbers 1001 through 1536 inclusive, certificated in any category. Compliance is required within the next 100 hours time in service, or within 120 days, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent bolt and pin failure, install modified spheric locking bolt, P/N 102-3500.21, and special nut, P/N 102-3510.21, in the forward horizontal stabilizer connection to the vertical stabilizer, and install new locking pins, P/N 102-2142.46, in the aft connecting plate for the horizontal stabilizer in accordance with instruction 1 and 2 of Grob Technical Information TM 306-17, dated June 10, 1981, or an FAA approved equivalent. Equivalent means of compliance may be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. The Burkhart Grob Flugzeugbau Industriestrabe Technical Information TM 306-17, dated June 10, 1981, identified and described in this directive 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 already received this document from the manufacturer may obtain copies upon request to Burkhart Grob Flugzeugbau Industriestrabe, D-8948 Mindelheim-Mattsies, West Germany or upon request to Burkhart Grob of America, Inc., 1070 Navajo Drive, Bluffton, Ohio. These documents also may be examined at the Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on May 3, 1984.
82-13-06: 82-13-06 SCHWEIZER (GULFSTREAM AMERICAN-GRUMMAN): Amendment 39-4410. Applies to Models G-164B (S/N 1B thru 656B), G-164C (S/N 1C thru 44C), and G164D (S/N 1D thru 16D) airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To detect elongation of the aileron cable attach holes and to eliminate the possibility of P/N A1450-281 bushings becoming dislodged from the aileron bellcrank, accomplish the following: a) Within 25 hours time-in-service after the effective date of this AD and every 12 months thereafter, on airplanes not modified in accordance with Gulfstream American Service Bulletin No. 75 (either original issuance or Revision "A" dated January 25, 1980), visually inspect the aileron bellcrank for elongation of the aileron cable attach holes per Part A of the revised service bulletin. If excessive elongation is found, prior to further flight, modify or replace the aileron bellcrank in accordance with Parts B and C of the revised service bulletin. b) Within 25 hours time-in-service after the effective date of this AD, on airplanes that have been modified in accordance with the original issue of Gulfstream American AG-CAT Service Bulletin No. 75, visually inspect the aileron bellcranks and if the bushings are loose or have less than .230 inch edge distance, replace the aileron bellcrank in accordance with Part D of Revision "A" of the Service Bulletin dated January 25, 1980. c) The repetitive inspections required by paragraph a) of this AD may be discontinued upon accomplishing the modifications described in Parts B and C of Gulfstream American AG-CAT Service Bulletin No. 75, Revision "A", dated January 25, 1980. d) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, New York Aircraft Certification Office, FAA, JFK International Airport, Jamaica, New York 11430. e) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. f) An equivalent method of compliance with this AD may be used if approved by the Chief, New York Aircraft Certification Office, FAA, JFK International Airport, Jamaica, New York 11430. This amendment supersedes Amendment 39-3882 (44 FR 11034) AD 80-17-08, effective August 15, 1980. This Amendment becomes effective on July 5, 1982.
2007-19-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Further to cases of parking brake loss at the gate, a pressure switch system had been introduced on some A300-600 aircraft. The aim of this modification was to recover pedals braking authority if parking brake is not efficient, without having to set the parking brake handle to OFF. However, it appears that in case of failure of the pressure switch system, there is the risk of double (normal and alternate) pressurization of the brakes potentially leading to undetected residual braking, which may lead to a loss of performances of the aircraft at Take-Off. The loss of performance could result in runway overrun or impact with obstacles or terrain during takeoff. We are issuing this AD to require actions to correct the unsafe condition on these products.