Results
95-23-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes and Model Avro 146-RJ70A, -RJ85A, and RJ-100A airplanes. This action requires inspections to detect cracking and evidence of exhaust leaks in the forward face of the central panel of the forward firewall of the auxiliary power unit (APU) bay, and replacement of the central panel with a new panel, if necessary. This amendment is prompted by a report indicating that cracking due to leakage of hot exhaust gases was found in the forward face of the forward firewall of the APU bay. The actions specified in this AD are intended to prevent such gas leakage and subsequent cracking, which could damage the wiring to the APU fire bottle; this condition could result in failure of the APU fire bottle to discharge in the event of an APU fire.
2005-05-11: The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328-300 series airplanes. This AD requires performing repetitive inspections for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the main landing gear (MLG), and replacing the assembly if any discrepancy is found. This AD is prompted by reports of cracking and breakage of the heat pack rotor assemblies. We are issuing this AD to find and fix discrepancies of the heat pack rotor assembly of the brake unit of the MLG and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing.
2023-23-08: The FAA is superseding Airworthiness Directive (AD) 2019-07- 05, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-07-05 required repetitive inspections for cracking of the 10VU rack fitting lugs and repair of any cracking. This AD continues to require the requirements of AD 2019-07-05, with reduced compliance times and removes airplanes having a certain modification from the applicability. This AD was prompted by a determination that certain repetitive inspection intervals need to be revised. The FAA is issuing this AD to address the unsafe condition on these products.
95-18-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, CL-600-2B16, and CL-600-2B19 series airplanes, that currently requires an inspection to detect cracking in the rudder control quadrant; replacement of any cracked quadrant with a new assembly; and retorquing of the castellated nut, as necessary. This amendment requires a follow-on inspection of certain rudder control quadrants to detect cracks that start at the inside root radius of the spigot; modification of any cracked quadrant; and eventual modification of certain quadrants. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by the development of a modification, which, when installed, will positively address the identified unsafe condition. The actions specified by this AD are intended to prevent loss of rudder control due to stress corrosion of the rudder control quadrant.
2000-24-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the electrical wires routed above the door actuation cables for minimum .50-inch clearance with the door in the open and closed position, damage due to chafing or electrical arcing, or damaged door actuation cables; and corrective actions, if necessary. This action is necessary to prevent damaged electrical wires or damaged door actuation cables due to chafing by the cables during operation of the forward passenger door, which could result in electrical arcing and consequent smoke in the area above the forward passenger door. This action is intended to address the identified unsafe condition.
2005-03-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires initial and repetitive inspections of certain frame stiffeners to detect cracking. If any cracking is found, this AD requires replacement of the stiffener with a new, reinforced stiffener. Replacement of the stiffener constitutes terminating action for certain inspections. This AD also requires a one-time inspection of any new, reinforced stiffener; and repair or replacement of the new, reinforced stiffener if any cracking is found during the one-time inspection. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to prevent fatigue failure of certain frame stiffener fittings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
92-18-07: 92-18-07 FAIRCHILD AIRCRAFT (formerly Swearingen Aircraft Corporation): Amendment 39-8351. Docket No. 92-CE-06-AD. Supersedes AD 91-23-04, Amendment 39-8073. Applicability: The following model and serial numbered airplanes, certificated in any category: Model Serial Numbers SA226-T T201 through T275, and T277 through T291 SA226-T(B) T(B)276, and T(B)292 through T(B)417 SA226-AT AT001 through AT074 SA226-TC TC201 through TC419 SA227-TT TT421 through TT541 SA227-AT AT423 through AT695 SA227-AC AC406, AC415, AC416, and AC420 through AC777 SA227-BC BC762, BC764, BC766, and BC777 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of control of the airplane because of improper operation of the power lever flight idle detent arms, accomplish the following: (a) Modify the power lever detent arms and cover assembly in accordance with the instructions in Fairchild Service Bulletin (SB) No. 226-76-008, issued January 15, 1991, revised December 17, 1991; or Fairchild SB No. 227-76-002, issued January 15, 1991, revised May 9, 1991, whichever is applicable. (b) If the modification required by paragraph (a) of this AD has been accomplished in accordance with either Fairchild SB No. 226-76-008 or Fairchild SB No. 227-76-002, both issued January 15, 1991, revised May 9, 1991, whichever is applicable (superseded AD 91-23-04), then no further action is required by this AD. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Fort Worth Airplane Certification Office, FAA, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Aircraft Certification Office. (e) The modification required by this AD shall be done in accordance with Fairchild Service Bulletin No. 226-76-008, issued January 15, 1991, revised December 17, 1991; or Fairchild Service Bulletin No. 227-76-002, issued January 15, 1991, revised May 9, 1991. The incorporation by reference of Fairchild Service Bulletin No. 226-76-008, issued January 15, 1991, revised December 17, 1991, was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of Fairchild Service Bulletin No. 227-76-002, issued January 15, 1991, revised May 9, 1991, was previously approved by the Director of the Federal Registeron December 10, 1991, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. 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, suite 700, Washington, DC. (f) This amendment (39-8351) supersedes AD 91-23-04, Amendment 39-8073. (g) This amendment becomes effective on October 2, 1992.
2023-23-13: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model RB211-Trent 800 engines. This AD is prompted by reports of cracks on certain intermediate-pressure compressor (IPC) rotor shaft balance lands. This AD requires initial and repetitive on-wing or in-shop borescope inspections (BSIs) of certain IPC rotor shaft balance lands for cracks, dents, and nicks, and replacement of the IPC rotor shaft if necessary, and would prohibit the installation of a certain IPC rotor shaft on any engine, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
90-11-10: 90-11-10 BOEING: Amendment 39-6608. Docket No. 89-NM-144-AD. \n\n\tApplicability: Model 757 and 767 series airplanes, equipped with Collins flight control computers (FCC), certified in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent intermittent altitude hold, altitude capture, and/or flight director mistracking anomalies, accomplish the following: \n\n\tA.\tWithin the next 24 months after the effective date of this AD, remove Collins manufactured FCC's which have Boeing P/N S241T100-103, and replace with units reworked to P/N S241T100-108, in accordance with Collins Service Bulletins FCC-701-22-10, Revision 2, dated March 24, 1988, and FCC-701-22-16, dated October 14, 1988. \n\n\tB.\tWithin the next 12 months after the effective date of this AD, remove Collins manufactured FCC's which have Boeing P/N S241T100-105 or -106, and replace with units reworked to P/N S241T100-108, in accordance with Collins Service Bulletin FCC-701-22-16, dated October 14, 1988. \n\n\tC.\tAlternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle,Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6608, AD 90-11-10) becomes effective on July 2, 1990.
2000-23-26: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR72 series airplanes, that requires a revision to the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate inspections to detect fatigue cracking in certain structure, inspection intervals, and life limits for certain components. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.