Navy Landing Gear Perspective Tribaloy-Treated F/A-18C/D

Slides:



Advertisements
Similar presentations
Pneumatic Cylinders Chapter 3.
Advertisements

“The Strength of Experience”
Issues Related to Qualification of HVOF Coatings on Landing Gear For fatigue and hydrogen embrittlement, the issue is the impact of the coating deposition.
Lesson 31 Main Engine Repair (II).  1. Crankpin bearing overhaul  2. Fuel pump removal & re-installation  3. Cylinder head removal/replacement  4.
Today’s Solution QMI 3-Step Fuel System Cleaning.
Cylinders and Actuators
Aerospace Use Of Hexavalent Chromium And Soluble Nickel In Relation To REACh 7th October 2009 From a combined Goodrich and Rolls-Royce review of the implications.
Tomislav Skračić, MA Undergraduate English Course for MARINE ENGINEERS 4th Semester Essential reading: SPINČIĆ, A., PRITCHARD, B, An English Textbook For.
How to Pull a Truck & Trailer Safely Ethan Williams.
Refuge Alternative Examinations, Approvals, and Refits Stakeholder Meeting-MSHA HQ June 27, 2012.
File Name & Location 12/05/2015, Page 1 STATUS OF F/A - 18 E/F NLG RIG TESTING.
Hydraulic Safety Colorado Mine Safety Training Program John Barton CMSP.
A Hard Chrome Alternatives for Hydraulic Components Program established to assist United States Air Force Airborne Accessories Directorate Avionics and.
HCAT PROGRESS REPORT FEBRUARY 2002 GOODRICH LANDING GEAR HCAT STATUS CONDUCTING THREE FULL SCALE TESTS: 1. Fatigue of entire MLG - Dash-8 Series
Cost/Benefit Analysis Conducted at Landing Gear Repair Facility Analysis conducted by Concurrent Technologies Corporation using Environmental Cost Accounting.
The gasses, fumes and dust produced by welding and cutting processes can be hazardous. There are 3 basic methods to protect personnel against hazardous.
SAE AERO DESIGN 2004 HEAVY-LIFT CARGO PLANE Stephen McNulty Richard-Marc Hernandez Jessica Pisano Yoosuk Kee Chi Yan Project Advisor: Siva Thangam Control.
Environmentally Conscious Design & Manufacturing (ME592) Date: April 24, 2000 Slide:1 Environmentally Conscious Design & Manufacturing Class 20: Remanufacturing.
Exhaust valve Exhaust valves open inwards into the cylinder, so that the gas pressure in the cylinder will ensure positive closure and help in dislodging.
Lindy Hughes Fleet Fire Protection Program Engineer Southern Nuclear Operating Company June 4, 2013 Fire Protection.
Introduction to Hydraulics ClassAct SRS enabled. In this presentation you will: identify the fundamental parts of a hydraulic system and safety issues.
Soft Field Takeoff and Landing. Soft Field Takeoff w Before landing, will you be able to take off? w Complex and high performance aircraft often have.
Welding Fumes and Gasses
Automotive Bearings and Sealants
Passive, Semi-Active and Active Suspension System
Project Status as of 1 April 2003
Engine Tune-Up.
1 CHROMIUM PLATING REPLACEMENT AT SIKORSKY AIRCRAFT ROBERT GUILLEMETTE JOHN BARTALOTTA MATERIALS AND PROCESSES ENGINEERING APRIL 26, 2001.
7A1 Friction & Galling Test
This presentation is for illustrative and general educational purposes only and is not intended to substitute for the official MSHA Investigation Report.
POLLUTION PREVENTION SUB-IPT HCAT MEETING April 01 Long Beach, CA HARD CHROME PLATING ALTERNATIVES Mary Gilman Boeing C-17 Pollution Prevention Project.
Gas Turbine Engine Project Materials Joint Test Protocol Document Principally Prepared By Jerry Schell GE Aircraft Engines Additional Input From GTE OEMs.
Engine Installation, Break-In, and In-Chassis Repairs
Airbus A330, Picture from wikipedia website Aircraft Landing Gear
Receiving Inspection This is the inspection of the engine as it is removed from the aircraft and received at the overhaul site The purpose of the.
Jeff Moorman Hydraulic Systems and Flight Control Actuators (301) Navy Rod Seal Testing Project Status as of 1 Sept 2002 Results from Rod Seal.
A Hard Chrome Alternatives for Hydraulic Components Program established to assist Oklahoma City Air Logistics Center Airborne Accessories Directorate Avionics.
Upgrades and Activities of 13kA EE systems during LS1 Bozhidar Panev TE-MPE-EE
Building Dependable Distributed Systems Chapter 1 Wenbing Zhao Department of Electrical and Computer Engineering Cleveland State University
OEM Experienced REMANUFACTURING Company Different Names – Same Company Same World Class Standards &
ILLINOIS COMMERCE COMMISSION Darin Burk Manager – Pipeline Safety 1.
Keith Legg Overview of fatigue/spalling tests HCAT Program Review Long Beach April 2001.
A Hard Chrome Alternatives for Hydraulic Components Program established to assist Oklahoma City Air Logistics Center Airborne Accessories Directorate Avionics.
Hard Chrome Replacement NADEP Jacksonville February, 2002 Michael Linn Materials Engineering.
ENGINES How They Work & Why They Fail Classifications Operational design (four-stroke, two-stroke, rotary, etc.) Number of cylinders (four, five, six,
Note location of different length bolts
ON CONDITION TASK Module 3 UNIT III HOW TO PERFORM RCM " Copyright 2002, Information Spectrum, Inc. All Rights Reserved."
Chapter 4 Compression System
Why Choose Xtek? Xtek Crane Wheels. Crane Maintenance Spending Survey Results From AIST Crane Symposium Wheel Assemblies 43%
Stracener_EMIS 7305/5305_Spr08_ Systems Availability Modeling & Analysis Dr. Jerrell T. Stracener, SAE Fellow Leadership in Engineering EMIS 7305/5305.
Auto Mechanics Tools Piston Ring Compressor.
Internship final presentation Paula Skrobucha September- October 2015 Cracow University of Technology Paula Skrobucha PH-DT26/10/2015.
Compression Is an adiabatic process. This means heat is derived from the process. As we squeeze the air fuel mixture it gets hot. Normal compression ratio.
Engine Technology Engine Diagnostic its requires an understanding of the fundamentals & a systematic approach to determine what the problem is. If the.
AVTC Model Based Design Curriculum Development Project.
Components Valves.
Parking brake selector valve
TOPIC TOPIC Failure in Landing Gear of Mirage 5.
TABLE OF CONTENT INTRODUCTION OVERHAUL PROCESS DOCUMENT REQUIRED
LANDING GEAR SYSTEMS THIS TRAINING MANUAL HAS BEEN PREPARED FOR MAINTENANCE TECHNICIANS AND DOES NOT SUPERSEEDED INFORMATION CONTAINED IN APPLICABLE AIRCRAFT.
AIRCRAFT MAINTENANCE TOWING OF AIRCRAFT.
Automatic Transmissions and Transaxles
Engine Compression Testing
Compressor Safety Practices
Spring Gas.
Landing gear systems.
PRESENTATION ON SUMMER TRAINING PROGRAM
What are the Basic Causes of Leaks in Car Spark Plug Tubes
Welding Fumes and Gasses
Automotive Engines Theory and Servicing
Presentation transcript:

Navy Landing Gear Perspective Tribaloy-Treated F/A-18C/D Main Gear Shock Absorber By Salvatore Piu August 2001 HCAT mtg

F/A-18A-D Main Landing Gear Tribaloy T-400 - Treated Shock Absorber Issue Proposed modifications Tests and flight evaluation Status

Issue Severe wear/scoring found on cylinder and piston at overhauls: Currently replace 100% Piston Rings (P/N 74A410855-2001/-7001) and Snubber Rings (P/N 74A410611-2001/-7001 Currently replace @ 90 % Piston Heads (P/N 74A410853-2003/-7001)

Shock Absorber Configuration P/N 74A410850-1009 Two stages Low pressure chamber, 150 psig, 8.87 inch stroke (shown in blue) High pressure chamber, 1265 psig, 4.25 inch stroke (shown in green) Total Stroke: 13.12 inches F/A-18C/D- shock absorber is not chrome-finished: Electrolysis-Nickel plating is used in stead of chrome.

Proposed Modifications Purpose: Reduce wear and internal damage of parts that typically get scrapped when worn -> increase time between overhauls Changes: Piston ring & snubber ring material change: from hard anodized aluminum to beryllium copper Piston head treated with Tribaloy SWA UHP-180 T-400 HVOF-deposited coating Tribaloy 400 Treated Area: Not the main piston area typically treated with Hard Chrome On an area where no previous coating applied

Piston head Piston Head Material: PH-13Mo Triballoy surface rides on bare 300M material (piston head is constantly in an “oil bath”)

Potential Benefits Increased MTBF Improved fleet readiness Longer component life Reduced overhaul costs Increased safety

Tests and Fight Evaluation Two shocks modified, S/N EMC 0632 & EMC 0635 Lab Tests Shock absorber ATP (service pressure) Load-stroke tests (verify consistency of static, load-stroke performance)

Tests and Flight Evaluation Flights Both shocks installed on product support plane (at Boeing, St. Louis, October, 1997): 23 flights (31 touchdowns) Performed post-flight load/stroke test (replaced leaking schroeder valve) Both shocks installed on one in-service aircraft (May 5, 1998) Request @ 30 CV arrested landings to provide meaningful data Flight clearance limited to 40 CV arrested landings Extended flight clearance to avoid interfering with fleet operations Right main landing gear experienced planing mechanism failure with EMC 0635 ( 60 field landings, 13 FCLP, & 80 CV arrested landings Removed both shocks immediately after planing mechanism failure

Tests and Flight Evaluation F/A-18A-D Planing Mechanism Function: plane the main wheel axle and compress the gear (shock absorber) to fit in the wheel well System has historical failures 8 primary components in system Improperly functioning shock is a suspect contributor to failures 8 Primary Components of F/A-18A-D Planing Mechanism are: Planing Link Knee Joint Bell Crank Assembly Connecting Link Shrink Link Upper Lock Link Lower Lock Link Crank (to axle) Over-Center Spring (to lock links)

Tests and Flight Evaluation Teardown inspection: shocks in excellent condition Goal reset by Navy: 200 CV landings Inspected, serviced, and placed shocks back on a fleet aircraft Shocks on various aircraft from May 99 to June 00 Modified shocks both participated in planing mechanism failures For each planing mechanism occurrence, shock removed from the failed gear, inspected, re-serviced, and placed on a fleet aircraft 5 on MLG’s with EMC 0635 (3 different MLG’s) 1 on a MLG with EMC 0632 (one of the MLG’s previously failed with EMC 0635)

Status Flight Evaluation Achieved 200 CV arrestments with one shock Personnel associate modified shocks with planing mechanism failures due to repeated participation In-service fleet evaluation halted by US Navy Teardown inspection: Wear observed was considerably less than would be expected (based on usage & compare to previous overhauled shocks)

Participated Planing System Failure Status Shock S/N Normal Field Landing Touch & Goes FCLP CV Bolter Field Arrestment Participated Planing System Failure EMC 0635 133 8 13 146 1 5 *1, *2 EMC 0632 137 12 54 200 *2, *3 Notes: EMC 0635 participated in 2 planing system failures, not included in qty (5), prior to Triballoy-associated modifications. Aircraft with modified shocks squawked for a pause in the stroking of the landing gear during landing (EMC 0635 lab tested for cause: nothing found) EMC 0632 exhibited slow to extend characteristics prior to modifications

S/N EMD 0635: Piston Head & Ring

S/N EMD 0635: Cylinder

Current Plan One Additional Flight Evaluation One aircraft with one new shock and and new-modified shock 200+ CV & FCLP landing Tear-down and compare both shocks If no issues found, implement change to spares and normal overhaul of existing shocks