Results
2000-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the flight control computers (FCC) with new, improved FCC's having updated software installed. This amendment also requires, for some airplanes, modification of the wiring of the FCC's. The actions specified by this AD are intended to prevent autopilot reversions in certain flight conditions, which could result in misunderstanding by the flight crew and consequent reduced ability to take appropriate action. This action is intended to address the identified unsafe condition.
2016-07-15: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. This AD requires opening the fuel boxes and restoring the sealing. We are issuing this AD to prevent failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight of the airplane.
2011-01-02: 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: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 04/00/02/07/03-L024 of February 3rd, 2003 the JAA [Joint Aviation Authorities] recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require * * * a definition review against explosion hazards. * * * * * Failure of the auxiliary power unit (APU) bleed leak detection system could result in overheat of the fuel tank located in the horizontal stabilizer and ignition of the fuel vapors in that tank, which could result in a fuel tank explosion and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
68-26-02: 68-26-02 DE HAVILLAND: Amdt. 39-694. Applies to DHC-6 Type Airplanes. To detect loose or missing jo-bolts in wing struts which have accumulated 150 or more hours time in service as of the effective date of this A.D., accomplish the following: (a) Within the next 50 hours time in service, unless already accomplished, visually inspect the top and bottom of the right and left wing struts, P/N C6W1005-3, -4, for loose or missing jo-bolts in accordance with the procedure described in deHavilland Service Bulletin No. 6/166, or an FAA approved equivalent procedure. (b) Identical inspections must be conducted at subsequent times in service of 450 to 550 hours, 2450 to 2550 hours and 7450 to 7550 hours after the inspection required by (a) and thereafter at intervals not to exceed 5000 hours time in service. (c) Prior to further flight, missing jo-bolts must be replaced with jo-bolts of the same part number or an FAA approved equivalent part; but a maximum of four (4)missing in any strut may be replaced within the next 250 hours time in service provided: (1) they are not all next to each other in the same row of twelve (12); or (2) they do not include more than two (2) which are next to each other in the same row of twelve (12) within six (6) inches of the strut end. (d) Equivalent parts and inspection procedures must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector. This amendment is effective December 20, 1968.
2016-06-14: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80E1 turbofan engines with rotating compressor discharge pressure (CDP) seal, part number (P/N) 1669M73P02, installed. This AD was prompted by reports from the manufacturer of cracks in the teeth of two rotating CDP seals found during engine shop visits. This AD requires stripping of the coating, inspecting, and recoating the teeth of the affected rotating CDP seals. We are issuing this AD to prevent cracking of the CDP seal teeth, uncontained part release, damage to the engine, and damage to the airplane.
2011-01-01: 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 earlier MCAI, Brazilian Airworthiness Directive 2007-08-01, effective September 27, 2007, describes the unsafe condition as: Fuel system reassessment, performed according to RBHA-E88/SFAR- 88 (Regulamento Brasileiro de Homologacao Aeronautica 88/Special Federal Aviation Regulation No. 88), requires the inclusion of new maintenance tasks in the Critical Design Configuration Control Limitations (CDCCL) and in the Fuel System Limitations (FSL), necessary to preclude ignition sources in the fuel system. * * * The new MCAI, Brazilian Airworthiness Directive 2009-08-03, effective August 20, 2009, describes the unsafe condition as: An airplane fuel tank systems review required by Special Federal Aviation Regulation Number 88 (SFAR 88) and "RBHA Especial N mero 88'' (RBHA E 88) has shown that additional maintenance and inspection instructions are necessary to maintain the design features required to preclude the existence or development of an ignition source within the fuel tanks of the airplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
63-16-05: 63-16-05 UNIVERSAL: Amdt. 589 Part 507 Federal Register July 24, 1963. Applies to All Models Temco D-16 and D-16A Aircraft. Compliance required within 25 hours' time in service following the effective date of this AD and at each periodic inspection thereafter. (a) Inspect the flap and landing gear actuating cylinders for cracks. If any cracks appear, the cylinder must be replaced. (b) Determine, by means of a hydraulic gage, that the hydraulic system pressure relief valve is adjusted to 1125 + 25, -0 p.s.i. Excessive pressures could cause damage to the components of the system. (c) Unless already installed, install hydraulic fluid restrictors in the nose gear lines, Serial Numbers 1271 and subsequent, main gear lines, Serial Numbers 1790 and subsequent, and flap lines, all serial numbers. (d) Inspect the linkage adjustments of the landing gear bungee springs and the flap stops and determine that they have been properly adjusted in accordance with appropriate service manuals. (Tusco Corporation Service Letter No. 79 dated December 23, 1958, covers this same subject.) This directive effective August 23, 1963.
2016-07-01: We are superseding Airworthiness Directive (AD) 2014-07-04R1 for certain Model S-92A helicopters. AD 2014-07-04R1 required repetitive inspections in the upper deck area for incorrectly installed clamps and chafing between the electrical wires and the hydraulic lines and replacing any unairworthy wires or hydraulic lines. This new AD requires altering the wiring system in the upper deck area to correct the unsafe condition described in AD 2014-07-04R1. We are issuing this AD to prevent a fire in an area of the helicopter without extinguishing capability and subsequent loss of control of the helicopter.
84-21-03: 84-21-03 McDONNELL DOUGLAS: Amendment 39-4939. Applies to McDonnell Douglas Model DC-9, and C-9 (Military) series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent jamming of the elevator controls by a detached forward rod end, accomplish the following: \n\n\tA.\tWithin the next 650 hours time in service or 90 calendar days, whichever occurs first after the effective date of this AD, visually inspect the fitting assembly (rod end) part number (P/N) 3938704-1 and pushrod P/N 3938705-501, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-266, dated March 12, 1984, hereinafter referred to as ASB27-266, or later FAA approved revisions. \n\n\tB.\tIf results of visual inspection are satisfactory, accomplish paragraph 4 of Part 2, Accomplishment Instructions, of ASB27-266. \n\n\tC.\tIf results of visual inspection are unsatisfactory, proceed in accordance with paragraph 5, Accomplishment Instructions of ASB27-266. \n\n\tNOTE: If rod end P/N SM4-6T3 (exclude DC-9-80 series) is required and not available, P/N SM4-6T may be substituted. The latter has only one grease fitting which must be oriented to allow access for scheduled lubrication. \n\n\tD.\tAlternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective November 26, 1984.
83-23-06: 83-23-06 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4767. Applies to Model HS 748 series 2A and 2B airplanes certificated in all categories. To prevent structural failure of the engine subframe, accomplish the following, unless already accomplished: A. Prior to 7 years from date of manufacture, or within the next 12 months after the effective date of this AD, whichever occurs later, inspect engine subframe struts and perform the appropriate actions in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group HS 748 Service Bulletin 54/25, Revision 4, dated May 1979. B. Repeat the inspections of the subframe struts at seven year intervals from the last inspection. 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. D. 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 December 15, 1983.