1、MIL-D-23222A 15 m 9797706 0428727 2 m l- i- “ z 13 ir MIL-D-23222A(AS) 18 March lq71 MILITARY SPECIFICATION Superseding MIL-D-23222 (Wep) 27 May 1963 DEMON,SIRATION REQUIREMENTS FOR HELICOEERS This specification has been approved by the Naval Systems Comd, Department of theNavy TABLE OF C0“S SCOPE S
2、cope Correlative Provisions Government Responsibilities Use of Demonstration Data by Board of Policy for Coordination of Test and Evaluation Policy on Release of Naval Aircraft for Trials inspection and Survey and Fleet Use Purpose of Demonstration Eurat ion of Demonst ration APPLICABLE DOCUMENTS Ef
3、fective Date of Documents Specifications and Standards Publications Other Documents RFIQUIRFMENTS General Location of Tests Test Authority Helicopter Configuration for Demonstration Tests Approval, Qualifications, and Instructions for Contractors Demonstration Pilots Flight Equipment for Contractors
4、 Test Pilots Release for Flight and Operating Limits Operating Mts for Contractors Pilots Operating Liimits for Navy Pilots Flight Monitoring Moving Picture Telemetering Coverage Chase Aircraft Pasagrap h 1 1.1 1-1.1 1.1.1.1 1*1.1*2 1.1.1.3 1.1.1.4 1.2 1.3 2 2.1 2.1.1 2.1.2 2.2 3 3.1 3.1.1 3.1.2 3.1
5、.3 3.1.4 3.1.4.1 3.1.5.1 3.1.5.2 3.1.6 3.1.6.1 391.5 3.1.6.2 3.1.6.3 i Licensed by Information Handling ServicesProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-23222A 15 m 9999906 0428930 9 m TABLE OF cON?“TS (Cont ) Eelicopter Changes and Adju
6、stments Flight Plan Release Test Instrument at ion General Installation, Calibration and Maintenance Check-Calibrat ions Re-Caiibrat ions Acceptance and Witnessing Procedures Instmentation Package Recovery Removal of Test Instmentation Requirements Prior to First Flight Planning Conference irs tmnta
7、t ion Conference Cruise Cor%rcl Tests Planning Conference Pre-Navy Preliminmy Evaluation Conference Post-Navy Preliminary Evaluation Conference Pre-Structural ikmonstration Conference Performance Tests Conference General Purpose CL- Rotor Brakes -heliiig and kfueling - kgine Fuel Feed Shaft ) settin
8、gs Anmnent Demonstration General Irmament installation : ;uns Rockets Attack, Patrol and Trainer Helicopters Air-to-air Rockets Air-to-ground Rockets uided Missiles Droppable Stois Convent iona L St ores NucLear Weapons Accuracy Armament Control V F- -.i- . .IKves and pull-outs with and without stor
9、es; flying qualities and performance; taxi, take-off, and landing; and hydroynamic tests shall be performed at the NAV-EN. Shipboard suitability tests shall be performed by NAVAIRmTCEN. 6 i I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-2322
10、2A 15 = 999790b 0428942 5 = L MIL-D-23222A (AS) 3.1.1 - (Cent ) (2) Tests involving tk carrying and release of guided missiles shall be performed at the NAYMISCEN (Naval Missile Center), Pt. bugp,Caifornia, (3) Aniament tests shall be performed at a location specified by COM NAVAIRTESTCEN. 3.1.2 the
11、 applicable NAWRO (Naval Plant Representative), or the conrmander of an activity or facility which is assipged by NAVAIR or by CCX4NAV- AIRTESTCEN under the policy set forth in this specification, to conduct and witness demonstrations and tests required to be performed under the terms of this specif
12、ication or other applicable documents. Test Authorities shall witness or designate witnesses for the demonstra- tions and tests, and shall approve demonstration plans, instrumentation, data-reduction procedures, and ail test methods and procedures for which detailed methods and procedures are not sp
13、ecified herein or in other applicable documents, For test authorities other than CCM NAVAI?IESCEN, the COM NAVmTm shall furnish instructions concerning the duties and responsibilities of test witnesses so that the actual performance of the tests, the collection of data during the tests, the decision
14、s made during and subsequent to the tests, and the reporting and documentation of test results will be consistent, comprehensive, serve the best interests of the Govement. Tests that are ;?ecif:.ad to be performed at one facility and that must, o? ii,x:.-.l.ty, be performed at some other facifiky, r
15、egardless of location, shall reICOpTER CONFIGURATTON FOR DEMONS“ION TESTS. - Except for the necessary addition of ballast to attain specified center-of-gravity locations, except for the necessary installation of special test instrumentation, and except as otherwise approved in writing by the test au
16、thority, or by the NAVAIR, helicopters employed in the perfomce of formal demonstration tests shall be identical, within production tolerances, to helfkopters of the same contract which are to be delivered or have been delivered for trials and to the Fleet. No special installation or deletion of any
17、 kind shall be undertaken without the aforementioned specific written approval, The word llfomlf in the first sentence of this paragraph refers to all demonstration tests, the results of which are intended to show that a design rquirement has been met in the test or that Provided by IHSNot for Resal
18、eNo reproduction or networking permitted without license from IHS-,-,- MIL-D-23222A 15 a 7799706 0428943 7 I MIL-D-23222A (AS) (Cont ) the design is suitable for fleet use, such as a test to demonstrate satisfactory operation of an item of equipment as part of the heli- copter weapon system; a struc
19、tural demonstration test to specified values of limit load factor, speed, altitude, and other pertinent parameters even though these salues may differ fmm the desim values; or a performance, or a flying-qualities demonstration test to demonstrate compliance with performance of flying-qualities desig
20、n requirements. Distribution of variable and useful loading, ani of ballast shall be satisfactory to test authorities during all demonstra- r tion tests including the contractors development flight tests. 3.1.4 unnecessary delay in the performance of the demonstration, and to safeguard the interests
21、 of the Government, skilled pilots who are experienced In flight testing and in the performance of all demonstra- tion tests, and who are properly and adequately equipped to perform the required demonstrations, shall be employed in the performance of all demonstration tests. These pilots shall be sa
22、tisfactory to NAVAIR and to test authorities concerned. Contractors shall instruct demonstration pilots thoroughly concerning the design, aerodynamic, structural (both static and dynamic), functional and reliibility llnitations, and special or unusual characteristics r: demWx?ation helicopters. Thes
23、e instructions shall be sufficiently tl?c;?ough and timely as to minimize ailab: 3 information, the operating limits authorized- by NAVAIR viG2 be either the full limits for which the contract requires the helicopter to be (aerodynamically, structurally, and functionally) designed, or the limits to
24、which the helicopter must be operated in order that the contractor may coniply with contract demonstration requirements. tractor my possess additional information which my justfry oper- ating limits pursuant to 3.1.5.1 and/or 3.1.5.2 that will be more restrictive than those authorized by NAVAIR. aut
25、horization by NAVAIR will be to the limits of %ormal flying“ which, for helicopter demonstration purposes, shall mean that: in NAVAIR It is recognized that the NAVPRO and/or the con- Normally, the initial (1) Normal takeoffs, hovering, and landings are authorized. (2) Autorotation with power recover
26、y only. (3 ) For multi-engine helicopters, fiighis with one engine out, are authorized, 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-23222A 15 W 797770b OY2B745 O U i I MIL-D-23222A (AS) 3.1.5 (Cont ) (4) Flying in normal attitude is autho
27、rized with the following limitations : (a) Normal load factors greater than 1.5 and less than 0.5 shall not be exceeded. The take-off gross weight shall not exceed 105% of the Basic Cesign Gross Weight. (b) An angle of bank of 30 shall not be exceeded. (c) Flight controls, power-plant controls, and
28、other systems, Innovations , and/or appur- tenances shall not be moved or operated so as to result in rapid or abrupt helicopter responses. (d) The speed in any direction at any altitude shall not exceed 0.8 times the mxmum speed attainable at the Basic Design Gross Weight in sustained level flight
29、at that altitude with norml-rated power or thrust, or the guaranteed cruise speed, whichever is greater. 8 “f - : Lbid authorization for release for flight has been gwhed, the NAVPR shall release helicopters for operation to more critical limits at the contractors plant* only after the NAVPR has det
30、ermined that all contractual prerequisites to such releases have been either complied with or waived by NAVAIR, and after NAVALR has authorized such releases. Requests by contractors for release for first flight, for release for operation to more critical limits at the contractors plant, and Fcr rel
31、ease for tests at locations other than at the con- tractors plant, shall sumnarize the status of ail contractual pre- requisites to the requested release unless the required status-of- completion infomtion is contained in the Demonstration, Planning, and Progress Report submitted to NAVAIR; in which
32、 case the contractors requests shall refer to somes of the necessary information. 3.1.5.1 OPEFMTING LJMlTS FOR CONTRACTORS PILOTS. - The operating limits for contractors flights shall not be more critical than any of the following: (1) ?hose authorized by NAVAIR. (2) Those authorized by the NAVPR. *
33、and for tests at locations other than at the contractors plant, 10 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. MIL-D-23222A 15 777770b 092879b 2 I - 3.1.5.1 MIL-D-23222A (AS) (C0nl-J 1 (3) ?hose which the contractor has determined or deduced to
34、 be safe based on realistic con- sideration of all pertinent factors including but not limited to the following; results of analyses of the whole helicopter and its ccpnponent pmts from the aercdynamic, structural, and functional viewpoints; status of completion of tests which may by this specificat
35、ion or by any of the docu- mnts listed in paragraph 2 herein, be required to be completed as a prerequisite to certain flights; and review of observations made and data recorded during prior flights, reduced and extra- polated to the maxirmn extent practicable, except that test authorities are autho
36、rized to waive reduction and extrapolation of the recorded data for tests performed pursuant to this paragraph 3.1.5.1(3) under their authority, when n their opinion, reduction and extrapolation of the data are not necessary for safety prior to further flight testing. Such waivers to expedite flight
37、 testing shall not be construed to negate other provisions of this document relating to submittal of data. Operating limits prmitt,eCi by (2- and (3), above, shall be not moICOpTER CHANGES AND ADJXJSIT4XP.S. - Subse- tion tests at NAVmm, no replacements, alterations, changes, or adjustments other th
38、an those required by normal maintenance pro- cedures shall be made wess approved by the CDMNAVsTcEN and/or NAVAIR subject to the requirements specified below, When a replacement, alteration, change, or adjustment, which would not be required by normal maintenance procedures, becomes necessary, or ap
39、pears to the contractor or the COMNAVAIRTESTCEN to be necessary, because of a dangerous or damaging occurrence (such as a violent response of the helicopter or control surface, or yielding, excessive wear, or failure of a region .of the structure or excessive or un- usual vibration), or because of a
40、ny malfunction (such as the failure of an engine, or of the transmission, or some other item of equipment necessary to continue to operate normaily), or for any other reason during the tests at NAVAiRTESCEN, the contractor shall submit concurrently to NAVAIR and to the COMNAVAEQESTCEN: quent to rele
41、ase of helicopters for demonstra- (1) A realistic technical evaluation of the signi- ficance of the disclosed design and construction deficiency, or other reason for the occurrence. (2) A record of tests at the contractors plant which disclosed the deficiency or, if applicable, an explanation as to
42、why the deficiency was not disclosed and19r reported during tests at the contractw E plant (3) Description of proposed corrective action in- cluding recomnendation of interim operating restrictions for helicopters of the same design, (4) Technical justification of proposed corrective action. (5) Sch
43、edules for changes to contract design data and changes to helicopters consistent with the proposed corrective action, (6) R-gineering change proposai including tests to be repeated to satisfactorily demonstrate the changed helicopter. 3.1.8 FLIGHT PLAN FELEASE. - The contractor shall procedures to b
44、e followed by the flight crew during the demonstration, for approval by NAVPRO. prepare flight plans covering tests and The flight plans shall include operating Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-D-23222A 15 W 9999906 0428949 W MILD
45、-23222A (AS) 3.1.8 (Cant) restrictions approved by NAVAIR or NAVPRO. more than one flight or extend beyond one day, provided the plan is not changed after release by the NAVPRO. The flight plan may cover 3.1.9 TEST INSTRUMENTATION 3.1.9.1 instmntation necessary to comply with the demonstration reqad
46、w used Li performing the demonstrations. All instruments and Instrument systems shall be installed in accor- dance with the highest stardards of mechar!ical and electrical installa- tion practices. shall be properly damped, shall have flat frequency response character- istics comensurate with the fr
47、eqr?cies of excitation of the variable to be measured, and shall be proper:.y mounted to assure valid measurement and freedom fmm extraneous excitations. me maximum time lag between any two or more channels requiring time correlation shall not exceed the time constant corresponding to the channel ha
48、ving the lowest flat frequency response requirement. The flat frequency response shall not be less than 60 CPS for all strain gages, accelerometers, pressure tranducers, and titsplacement and velocity measuring instruments, Magnetic tape recorders, if installed and used on demonstration aircraft at
49、NAVAI?ESW, musk be compatible with the existing wund station equipment at NAVAEQIBVXN. Telemetry equipment, if installed, shall be in accordance with 3.1.6.2. Calibration of each transducer or gage installation shall be made through the All tranducers and gages shall be properly located, 14 L .- i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,
