1、UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 UNIFIED FACILITIES CRITERIA (UFC) NAVY ENGINE TEST CELLS APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Includ
2、ing Ch 4, September 2008 UNIFIED FACILITIES CRITERIA (UFC) NAVY ENGINE TEST CELLS Any copyrighted material included in this UFC is identified at its point of use. Use of the copyrighted material apart from this UFC must have the permission of the copyright holder. U.S. ARMY CORPS OF ENGINEERS NAVAL
3、FACILITIES ENGINEERING COMMAND (Preparing Activity) AIR FORCE CIVIL ENGINEER SUPPORT AGENCY Record of Changes (changes are indicated by 1 . /1/) Change No. Date Location 1 January 2007 Table 5-1; Paragraph 5-5.2.1.4 and 6-5.7. 2 April 2007 Figure 6-2; Paragraph 6-5.5 and 6-5.7.2. 3 November 2007Adde
4、d paragraph 1-6. 4 September 2008Paragraph 1-6; Table 5-1; Table 6-1; Paragraph 6-4.2; 6-4.3; 6-5; 6-5.7.2; Appendix B.FOREWORD Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 The Unified Fac
5、ilities Criteria (UFC) system is prescribed by MIL-STD 3007 and provides planning, design, construction, sustainment, restoration, and modernization criteria, and applies to the Military Departments, the Defense Agencies, and the DoD Field Activities in accordance with USD(AT however, the inspection
6、s and proof tests are the only primary means to ensure the integrity of the foundation concrete and associated embedment hardware. 4 The following three NAVFAC systems are critical from a safety and asset risk perspective: (Refer to NAVFAC BMS B 10 15.2.1 on the NAVFAC portal.) Fire suppression syst
7、em; The T-10 sprinkler protection to consist of overhead deluge system having a density Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 3of .35 gpm/ft2 and a water spray system for the engine
8、 and the floor area underneath the trailer having a density of .50 gpm/ft2. NOTE: The T-10 fire suppression discharge density shall be verified every 3 years with actual flow tests timed and measured in coordination with the base fire department. /4/ Engine air start compressor; and Engine tie down
9、restraints (inspection and testing certification procedure, contained herein /3/ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 CHAPTER 2 T-10 STANDARD JET ENGINE TEST CELL 2-1 GENERAL. When
10、 siting the T-10, emphasize operation, function, noise abatement and safety. Other factors to consider include topography, vegetative cover, existing construction, weather elements, wind direction, soil conditions, flood hazards, natural and man-made obstructions, adjacent land use, availability of
11、usable airspace, accessibility of utilities and future expansion capability. Give careful consideration to vehicular parking, pedestrian access and traffic flow. 2-2 ANTI-TERRORISM/FORCE PROTECTION. Use standoff criteria in UFC 4-010-01, Design: DOD Minimum Antiterrorism Standards for Buildings. 2-3
12、 T-10 SAFETY CLEARANCE. Orient the T-10 such that it is compliant with all runway safety zone and imaginary surface criteria of NAVFAC P-80.3, Facility Planning Factor Criteria for Navy/Marine Corps Shore Installations Safety Clearance and UFC 3-260-01, Airfield and Heliport Planning and Design. 2-4
13、 LIST OF NAVFAC STANDARD DRAWINGS. NAVFAC DWG. NO. DISCIPLINE DWG. NO. TITLE COVER 1405131 T-1 INDEX DRAWING 1405132 A-1 GENERAL NOTES, LEGEND however, does not offer the same margin of safety that the type XIII fitting, and, thus, the original test frequency of an annual poof test is still valid. 5
14、-3 DISCUSSION. The Navys current shore facilities maintenance program encourages prudent expenditure of facility maintenance dollars. The NAVFAC aviation facilities engineering program is dedicated to providing criteria that reflect user functional requirements as well as optimizing return on invest
15、ment. Safety is always the highest priority. 5-4 CRITERIA. Use the following guidance for inspection and testing to determine that all component parts of a land-based aircraft and engine restraint system are in a safe and properly maintained operating condition. Naval Air Station activities regularl
16、y engaged in aircraft engine overhaul shall inspect and proof test their aircraft engine restraints to the frequency shown in Table 5-1 and 6-1. 17Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2
17、008 Table 5-1 Inspection and Test Frequency Note: The system consists of a restraint fitting (Type XIII, XI-A, etc.) fastened to a steel embedment anchored in the concrete foundation. Load test the system at the following intervals: Requirement Type XIII Type XI-A Initial Installation Load test new
18、installations prior to operational use Load test new installations prior to operational use Certification renewal Inspect and load test every 5 years Inspect and load test 1 every three (3) years. /1/ After repair and/or replacement of any of the components (i.e., restraint fittings, bolts, etc.) Lo
19、ad test repaired assembly prior to operational use Load test repaired assembly prior to operational use Visual Signs of deterioration Prior to each operational use Prior to each operational use NOTE: Due to ongoing problems with alkali-silica deterioration, the recommended minimum test frequency for
20、 engine restraints is three years at the following airfields: NAS Point Mugu, CA; NAS Fallon, NV; NOLF San Nicolas Island, CA; MCAS Iwakuni, Japan; MCAS Cherry Point, NC; NAS Whidbey Island, WA; and MCAF Quantico, VA. The frequency can be reset to the standard frequency once inspection determines th
21、ere is no alkali-silica reaction present at the test cells. NOTE: In lieu of the three-year load test for airfields with a history of poor quality concrete, concrete cores can be taken to ensure that alkali-silica is not present. Core tests will extend the frequency of testing for type XIII to once
22、every five years. 5-5 DESCRIPTION OF SYSTEM. The proof load system (encl (1) generally consists of a hydraulic system for applying the load, which includes a hand pump and a single acting pull cylinder; special structural fixtures which interface with the proof load test fitting; and a chain assembl
23、y, turnbuckle and hardware to interface with the restraint fitting to be tested. 5-5.1 Special Safety Precautions for Outdoor Unabated Check Pad Proof Test. (Unless the chain fall and the dynamometer in Figure A-5 are used to feather in the applied load) 5-5.1.1 Barricade or rope off the area around
24、 tie down fittings. Secure area size of 50 feet by 100 feet minimum. 5-5.1.2 Provide secondary restraints to proof load system using a 1-inch (25-mm) diameter nylon rope secured to adjacent tie downs. Nylon rope to be a minimum length of 50 feet and is to be secured to proof test load system in a 18
25、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 slack condition; absorbing load only in the event of an unanticipated release of the primary tie down fittings. NOTE: For T-10 and Hush House a
26、pplications, the run room is to be secured as if an actual engine test were being conducted. 5-5.2 Proof Loads. Restraint fitting proofloads with the corresponding pull angles are indicated in the following Table 5-1. 5-5.2.1 Ensure the proof load tests for Jet Engine Test Cells and Unabated Power C
27、heck Facility restraint systems are in accordance with Table 5-1. Use test procedures that gradually increase the load in increments as follows: 5-5.2.1.1 Single XI-A (“+” configuration-Proof-test load= 30,000 lbs. 10,000 lbs. Hold for one minute 20,000 lbs. Hold for one minute 25,000 lbs. Hold for
28、one minute 30,000 lbs. Hold for ten minutes 5-5.2.1.2 Single XI-A (“x” configuration-Proof-test load= 45,000 lbs. 10,000 lbs. Hold for one minute 30,000 lbs. Hold for one minute 40,000 lbs. Hold for one minute 45,000 lbs. Hold for ten minutes 5-5.2.1.3 Dual XI-A (“x” or “+” configuration- and Dual T
29、ype XIII Proof-test load= 60,000 lbs. 10,000 lbs. Hold for one minute 30,000 lbs. Hold for one minute 40,000 lbs. Hold for one minute 50,000 lbs. Hold for one minute 60,000 lbs. Hold for ten minutes 5-5.2.1.4 Single XIII Proof-test load= 90,000 lbs. 19Provided by IHSNot for ResaleNo reproduction or
30、networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 20,000 lbs. Hold for one minute 45,000 lbs. Hold for one minute 70,000 lbs. Hold for one minute 90,000 lbs. Hold for ten minutes 1 (Deleted incorrect step.) /1/ 5-5.2.2 Ensure the proof test
31、load for Aircraft Acoustical Enclosure (Hush House) restraint systems is in accordance with Chapter 6. Use test procedures that gradually increase the load in increments as follows: 5-5.2.2.1 Dual XIII Proof-test load= 60,000 lbs. 10,000 lbs. Hold for one minute 30,000 lbs. Hold for one minute 40,00
32、0 lbs. Hold for one minute 50,000 lbs. Hold for one minute 60,000 lbs. Hold for ten minutes 5-5.3 Inspection and Test Procedures. 5-5.3.1 Induce tension in the chain assembly by slowly pumping the hydraulic hand pump until the assembly is taut. When the load is applied, keep personnel clear of the i
33、mmediate test area. 5-5.3.2 Increase the load gradually in increments. After each load increment and when the final proof load is reached, close and hold the hydraulic safety valve. Remotely observe the restraint system during the loading phases. If any indication of cracking or deformation is appar
34、ent, gradually release the load and terminate the test. 5-5.3.3 After the loading phase is completed and the load released, inspect the restraint system components (fittings, bolts, anchor base and concrete in the immediate area) for signs of distress. Replace fittings and anchors showing such distr
35、ess. 5-5.4 Scheduling and Performance Responsibility. 20Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 Scheduling of inspections and tests is the responsibility of the AIMD Power plants offi
36、cer or his designated representative tasked with overseeing the daily operation of the test facility. Inspection and tests must be made by qualified personnel familiar with inspection and certification of load handling devices. Qualified personnel shall be regularly engaged with weight testing, heav
37、y industrial rigging applications, or be approved by the NAVFAC Criteria Program. 5-5.5 Inspection and Test Results. 5-5.5.1 Promptly initiate necessary action to correct discrepancies found during inspections and tests. 5-5.5.2 Furnish a copy of the deficiencies found and the required corrective ac
38、tion to NAVAIR Lakehurst, code 4.8.6.8 and to NAVFAC Atlantic, Special Assistant for Aviation Facilities. If deficiencies are found by the inspection, report to the AIMD (Aircraft Intermediate Maintenance Department) power plants officer or a representative of the NAVAIR AETS (Aircraft Engine Test S
39、ystem) team for resolution. 5-6 ACTION. 5-6.1 Design. Design all new jet engine test facility, unabated power check pads, and aircraft acoustical enclosures using the guidance for the above-mentioned Aircraft and Engine System proof Load Test Requirements. In the future, inspect and certify the jet
40、engine test facility, unabated power check pads, and aircraft acoustical Aircraft and Engine System fittings in accordance with the requirements of this UFC. 21Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4
41、, September 2008 Figure 5-1 Proof Load Test System for Type XIII & XI-A Test FittingProof LoadTest FittingTest FittingTest StandTie Down FittingAnchor Tee(GFE)Proof LoadTest FittingAnchor BaseHand Pump AssemblyTie Down Anchor BaseXIII Tie Down Deck Fitting (GFE)Test StandTest Stand Anchorage Plate22
42、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UFC 4-212-01N July 27, 2006 Including Ch 4, September 2008 Table 5-2 Jet Engine Test Cell and Unabated Power Check Facility Restraint System Proof Loads/Pull Angles Restraint Fitting(s) Type Maximum Saf
43、e Working Load (Pounds) In-Service Usage Proof Test Load (Pounds) Proof-Test Angle (Degrees) NotesSingle XI-A (“+”) Configuration 15,000 In-airframe Run-up and/or Out of Airframe Engine Run-up 30,000 15 (1) Single XI-A (“x”) Configuration 22,500 In-airframe Run-up and/or Out of Airframe Engine Run-u
44、p 45,000 15 (2) Dual XI-A (“x” or “+”) Configuration 30,000 Out of Airframe Engine Run-up 60,000 30 (3) Single F2 22,500 In-airframe Run-up and/or Out of Airframe Engine Run-up 45,000 15 (2) Dual F2 30,000 Out of Airframe Engine Run-up 60,000 30 (3) Single XIII 45,000 In-airframe Run-up and/or Out o
45、f Airframe Engine Run-up 90,000 15 (4) Dual XIII 30,000 Out of Airframe Engine Run-up 60,000 30 (3) Single F1 45,000 In-airframe Run-up 90,000 15 (4) NOTES: (1) A 30,000 pound proof-load-test of a single, “+” configured Type XI-A fitting certifies a site for a maximum safe working load of 15,000 pou
46、nds. Simultaneous, dual-engine, maximum testing (military and/or afterburner) is prohibited for all aircraft. All aircraft and engine testing exceeding 15,000 pounds of thrust is also prohibited. (2) A 45,000 proof-load-test of a single fitting certifies a site to test all aircraft (except F-14A+/D)
47、 and all engines (except F110-GE-400). This does not include simultaneous, dual engine afterburner testing of F-4, F-14A and F/A-18 aircraft. (3) A 60,000 pound proof-load-test on a dual set of fittings certifies a site to test all engines. (4) A 90,000 pound proof-load-test on a single fitting certified a site to test all aircraft (excluding simultaneous, dual-engine afterburner testing of F-14A+/D aircraft) and all engines. 23Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
