SWEETWATER COUNTY — The search for a missing pilot and aircraft that began on Tuesday culminated Wednesday, Jan. 15, with the discovery of the crash site in a remote area
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Altera’s DO-254/ED-80 Certifiable Nios II Processor Leveraged in Thales Safety-Critical Avionics System Certified by EASA
Industry’s First DO-254/ED-80 Certifiable Soft Core Processor Saves Thales Nearly Two Years in Development Time
SAN JOSE, Calif., Dec. 20, 2010 — Altera Corporation today announced the European Aviation Safety Agency (EASA) certified a safety-critical avionics system that includes a DO-254/ED-80-certifiable version of Altera’s Nios® II embedded processor. Thales Avionics implemented a safety-critical version of the Nios II embedded processor in an Altera® HardCopy® ASIC for use in its family of integrated electronic standby instruments rather than developing a custom ASIC solution. Leveraging Altera’s DO-254/ED-80-certifiable processor allowed Thales to significantly reduce overall system development time when developing their family of integrated electronic standby instruments.
“When we began defining our integrated electronic standby instrument family, we determined it would be too costly and time consuming to develop a custom ASIC that meets the RTCA DO-254/Eurocae ED-80 objectives,” said Jerome Papineau, product manager at Thales Avionics. “The integration of a safety-critical Nios II embedded processor with a HardCopy ASIC saved nearly two years off our development while also saving considerable costs. The processor provides us with a compelling solution that meets our performance and system requirements while allowing us to manage system obsolescence. With its RTCA DO-254/Eurocae ED-80 level-B compliance determination, the Nios II embedded processor can be integrated into our system with confidence.”
Altera’s HardCopy ASICs offer customers a low-cost, low-risk and low-power migration path to take their FPGA prototype designs to volume production. The use of HardCopy ASICs provides Thales with improved single-event upset (SEU) immunity while also giving Thales pin-to-pin, functional and timing compatibility with the FPGA prototype design.
The development of a safety-critical version of Altera’s Nios II soft-core processor is the result of the close partnership and cooperation between Thales, HCELL Engineering and Altera, which dates back to 2006. The RTCA DO-254/Eurocae ED-80 compliance package of the Nios II embedded processor provides avionics equipment manufacturers a commercial off-the-shelf (COTS) microprocessor that can be quickly and easily implemented in safety-critical avionics applications. Leveraging the Nios II embedded processor in these systems helps manufacturers comply with safety standards while dramatically lowering development time and costs and eliminating the threat of processor obsolescence.
“Today’s announcement significantly reduces the risk barrier for customers wanting to implement a soft-core processor into their safety-critical avionics system,” said Amr El-Ashmawi, senior marketing manager in Altera’s military business unit. “Having the EASA certify Thales’s integrated electronic standby instruments allow us to clearly demonstrate the significant reduction in cost, development time and risk that Altera’s DO-254-certifiable Nios II processor provides.”
About the Safety-Critical Version of Nios II Processor
Altera’s Nios II embedded processor is a configurable, 32-bit FPGA-based soft microprocessor used in a wide variety of applications and end markets, including military, aerospace and avionics. The safety-critical version of the processor core includes complete RTCA DO-254/Eurocae ED-80 compliance, with source code and documentation such as a plan for hardware aspects of certification (PHAC), a hardware design document (HDD) and a hardware accomplishment summary (HAS). Airborne electronic hardware designers complying with the DO-254 standard can leverage the Nios II soft processor core while minimizing obsolescence in systems that typically have long life cycles. Nios II embedded processors can be implemented within Altera’s portfolio of Cyclone® series and Stratix® series FPGAs and HardCopy series ASICs. For more information about Altera’s DO-254 strategy, visit www.altera.com/end-markets/military-aerospace/do-254/mil-do-254.
About Altera
Altera® programmable solutions enable system and semiconductor companies to rapidly and cost-effectively innovate, differentiate and win in their markets. Find out more about Altera’s FPGA, CPLD and ASIC devices at www.altera.com. Follow Altera via Facebook, RSS and Twitter.
ALTERA, ARRIA, CYCLONE, HARDCOPY, MAX, MEGACORE, NIOS, QUARTUS and STRATIX words and logos are trademarks of Altera Corporation and registered in the U.S. Patent and Trademark Office and in other countries. All other words and logos identified as trademarks or service marks are the property of their respective holders as described at www.altera.com/legal.
Airbus Major Airshow Humiliation
Damaged A380 Wing
Update
The gearbox problem is not the only recent technical glitch that occurred. The aircraft’s huge propellors built by French company Ratier-Figeac, (indirectly owned by U.S. group United Technologies _UTX.N_,) developed cracks prematurely.
What: A380 superjumbo,
Where: Le Bourget airport, Paris
When: June 17, 2011
Who: no reported injuries
Why: Before an audience including 2,100 exhibitors from 45 countries—a jury of its peers—during the Paris Airshow, Airbus had to pull its A380 display.
The A 380 was withdrawn from the flying display when the jet had an on-the-ground collision with a building, clipping a wing on a taxiway structure.
Also, although it made a fly-over, the Airbus A400 M military transport demo was cancelled due to a “a minor gearbox problem”
Then on Saturday Airbus announced that two of three versions of the A350, would be delayed for about two years. We commend the decision to delay, because while Rolls Royce will be granted more time to develop a more powerful motor, hopefully Airbus will take the time to work on whatever bugs are in its system. A delay in release is clearly an opportunity to perfect the product, from a safety perspective.
See how a budget, no-frills Airbus jet that flyers will ‘suffer’ through compares to the same plane flown by a major airline
Where Iberia has all the traditional comforts of a long-haul airliner on the smaller plane, Wizz has crammed in 239 economy seats.
FAA: Helicopter Air Worthiness Directive
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
AD 2010-02-51
Agusta Model A109A, A109A II, A109C, and A109K2 helicopters
Regulatory Information
This Emergency Airworthiness Directive (AD) is prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI states that 2 of the 3 installed main rotor scissor fitting assembly fixing bolts (fixing bolts) on a Model A109K2 helicopter had cracked in flight. Investigation by the manufacturer revealed that the crack was caused by inadequate instructions for installing the bolts. Improper installation of the main rotor scissor fitting assembly, if not detected and corrected, could result in a crack in a fixing bolt, failure of the fixing bolt, and subsequent loss of control of the helicopter.
We have reviewed Agusta Alert Bollettino Tecnico (ABT) No. 109K-53 for Model A109K2 helicopters and ABT No. 109-131 for Model A109A, A109A II, and A109C helicopters, both dated December 18, 2009. The ABTs specify a one-time inspection to verify the correct installation of the main rotor scissor fitting assembly, part number (P/N) 109-0110-67 or P/N 109-0101-58, to determine if 2 washers are installed under the head of each fixing bolt. If 2 washers are not installed under the head of each fixing bolt, the ABTs specify replacing each fixing bolt with an airworthy fixing bolt, P/N 109-0101-78-5, and installing 2 washers under the head of each fixing bolt.
EASA has issued AD No. 2009-0274-E, dated December 18, 2009, to correct an unsafe condition for the specified Agusta model helicopters. EASA advises that failure of a fixing bolt could lead to loss of control of the helicopter.
These helicopter models have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, their technical agent, has notified us of the unsafe condition described in the MCAI AD.
We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Therefore, this AD requires, within 5 hours time-in-service (TIS), inspecting the main rotor scissor fitting assembly to determine if there are 2 washers installed under the head of each fixing bolt. If there are 2 washers installed under the head of each fixing bolt, no further action is required. If there are not 2 washers installed under the head of each fixing bolt, this AD requires, within 25 hours TIS after complying with paragraph (a) of this AD, replacing each fixing bolt and installing 2 washers under the head of each fixing bolt.
This AD differs from the MCAI AD in that we refer to “flight hours” as “hours TIS”. Also, we do not allow an optional date for replacing the fixing bolts.
This rule is issued under 49 U.S.C. Section 44701 pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this emergency AD.
2010-02-51 AGUSTA S.p.A: Directorate Identifier 2010-SW-05-AD.
Applicability: Model A109A, A109A II, A109C, and A109K2 helicopters, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent a crack in a main rotor scissor fitting assembly fixing bolt (fixing bolt), failure of a fixing bolt, and subsequent loss of control of the helicopter, do the following:
(a) Within 5 hours time-in-service (TIS), inspect the main rotor scissor fitting assembly, part number (P/N) 109-0110-67 and P/N 109-0110-58, to determine if there are 2 washers installed under the head of each fixing bolt, P/N 109-0101-78-5, as depicted in Figure 1 of Agusta Alert Bollettino Tecnico (ABT) No. 109K-53 for Model A109K2 helicopters, and ABT No. 109-131 for Model A109A, A109A II, and A109C helicopters, both dated December 18, 2009, as applicable.
(1) If there are 2 washers installed under the head of each fixing bolt, no further action is required.
(2) If there are not 2 washers installed under the head of each fixing bolt, within 25 hours TIS after complying with paragraph (a) of this AD, replace each fixing bolt, P/N 109-0101-78-5, and install 2 washers under the head of each fixing bolt as depicted in Figures 1 and 2 of the applicable ABT, by following the Compliance Instructions, Part II, paragraphs 1. through 3.5., of the applicable ABT.
(b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222-5961, for information about previously approved alternative methods of compliance.
(c) Joint Aircraft System/Component (JASC) Code 6220: Main Rotor Head.
(d) Copies of the applicable service information may be obtained from Agusta, Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA), Italy, telephone 39 0331-229111, fax 39 0331-229605/222595, or at http://customersupport.agusta.com/technical_advice.php.
(e) Emergency AD 2010-02-51, issued January 13, 2010, becomes effective upon receipt.
Note: The subject of this AD is addressed in European Aviation Safety Agency AD No. 2009-0274-E, dated December 18, 2009.
FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222-5961.